431-ICD-000049 Revision – C Effective Date: May 27, 2009 Expiration Date: May 27, 2014

Lunar Reconnaissance Orbiter Project

External Systems Interface Control Document for the Lunar Reconnaissance Orbiter Ground System

LRO GSFC CMO

May 27, 2009

RELEASED

Goddard Space Flight Center Greenbelt, Maryland

National Aeronautics and Space Administration

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CM FOREWORD

This document is a Lunar Reconnaissance Orbiter (LRO) Project Configuration Management (CM)-controlled document. Changes to this document require prior approval of the applicable Configuration Control Board (CCB) Chairperson or designee. Proposed changes shall be submitted to the LRO CM Office (CMO), along with supportive material justifying the proposed change. Changes to this document will be made by complete revision.

Questions or comments concerning this document should be addressed to:

LRO Configuration Management Office Mail Stop 451 Goddard Space Flight Center Greenbelt, Maryland 20771

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Signature Page

Prepared by: Reviewed by:
Electronically Signed on NGIN __________ Electronically Signed on NGIN __________
Ralph Casasanta Date Jim Clapsadle. Date
LRO Ground System Engineer LRO Ground System Engineer
Code 444 GSFC, Code 444
Reviewed by:
Electronically Signed on NGIN __________ Electronically Signed on NGIN __________
Jack Murphy. Date Ron Zellar Date
LRO Mission Operations Lead LR System Engineer
GSFC, Code 444 GSFC/NASA, Code 556
Electronically Signed on NGIN __________ Electronically Signed on NGIN __________
Rivers Lamb. Date Sue Hoge. Date
LRO Flight Dynamics Lead Flight Dynamics Facility Operations Director
GSFC, Code 595 GSFC, Code 595
Electronically Signed on NGIN __________ Electronically Signed on NGIN ________
Stefan Waldherr. Date Leslie Ambrose Date
JPL, Telecommunications and Mission Network Integration Manager
Services Manager, Office 911 GSFC/NASA, Code 450.1
Approved by:
Electronically Signed on NGIN __________ Richard S Saylor, Jr. Date LRO Ground System and Operations Lead GSFC, Code 444

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

LUNAR RECONNAISSANCE ORBITER PROJECT DOCUMENT CHANGE RECORD Sheet: 1 of 1

REV LEVEL DESCRIPTION OF CHANGE APPROVED BY DATE APPROVED
Rev -Initial Release, Released per 431-CCR-000210 R. Saylor 19 Jan 2007
Rev – A Released per 451-CCR-000383 R. Saylor 08/20/2007
Rev – B Release per 451-CCR-001058 Rick Saylor 9/16/2008
Rev – C Release per 451-CCR-001373; see associated file Proposed RevC 431-ICD-000049 Mods for list of requested changes Rick Saylor 5/22/2009

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List of TBDs/TBRs

Item No. Location Type Summary Ind./Org. Due Date
1
2
3
4

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TABLE OF CONTENTS

Page

1.0 INTRODUCTION ..................................................................................................................................... 1-1

1.1 PURPOSE AND SCOPE ............................................................................................................................... 1-1

1.2 DOCUMENT ORGANIZATION .................................................................................................................... 1-1

1.3 REQUIREMENTS TRACEABILITY METHODOLOGY .................................................................................... 1-1

1.4 APPLICABLE DOCUMENTS ....................................................................................................................... 1-1

1.5 REFERENCED DOCUMENTS ...................................................................................................................... 1-2

1.6 OTHER DOCUMENTED REFERENCES ........................................................................................................ 1-2

2.0 GROUND SYSTEM OVERVIEW .......................................................................................................... 2-1

2.1 GROUND SYSTEM ARCHITECTURE .......................................................................................................... 2-2

2.1.1 The LRO Space Communications Network........................................................................................ 2-3

2.1.2 LRO Mission Operations Center ....................................................................................................... 2-4

2.1.3 The Science Operations Centers ........................................................................................................ 2-4

2.1.4 Flight Dynamics Facility ................................................................................................................... 2-5

2.1.5 Ground System Communications ....................................................................................................... 2-5

2.2 LRO MOC OPERATIONAL SYSTEMS ....................................................................................................... 2-7

2.2.1 ITOS-Supported Real-time Telemetry and Commanding ................................................................... 2-8

2.2.2 Data Processing System..................................................................................................................... 2-9

2.2.3 Data Management System ................................................................................................................. 2-9

2.2.4 Mission Planning System................................................................................................................. 2-10

2.2.5 Attitude Ground System ................................................................................................................... 2-10

2.2.6 Trending and Analysis System......................................................................................................... 2-10

2.2.7 Monitoring and Alert System........................................................................................................... 2-10

2.3 FLIGHT DYNAMICS FACILITY ................................................................................................................ 2-11

2.4 MISSION OPERATIONS TEAM ................................................................................................................. 2-11

2.5 FLIGHT SOFTWARE MAINTENANCE FACILITY ....................................................................................... 2-11

2.6 LRO SPACE COMMUNICATIONS NETWORK ........................................................................................... 2-11

3.0 LRO GS EXTERNAL INTERFACE PRODUCT SYNOPSIS ............................................................. 3-1

4.0 LRO GROUND SYSTEM EXTERNAL INTERFACES AND PRODUCT ...................................... 4-24

4.1 FLIGHT DYNAMICS FACILITY PRODUCTS .............................................................................................. 4-24

4.1.1 (FDF-6) INP Station Acquisition Data ............................................................................................ 4-26

4.1.1.1 Product Details .................................................................................................................................... 4-26

4.1.1.2 Format .................................................................................................................................................. 4-27

4.1.2 (FDF-10) OEM Station Acquisition Data ........................................................................................ 4-28

4.1.2.1 Product Details .................................................................................................................................... 4-29

4.1.2.2 Format .................................................................................................................................................. 4-29

4.1.3 (FDF-5) DSN Predict-Grade SPK Data.......................................................................................... 4-30

4.1.3.1 Product Details .................................................................................................................................... 4-30

4.1.3.2 Format .................................................................................................................................................. 4-30

4.1.4 (FDF-41) DSN Long-Term Scheduling Grade SPK Data ............................................................... 4-31

4.1.4.1 Product Details .................................................................................................................................... 4-32

4.1.4.2 Format .................................................................................................................................................. 4-32

4.1.5 (FDF-7) Laser Ranging Site Prediction Data ................................................................................. 4-33

4.1.5.1 Product Details .................................................................................................................................... 4-33

4.1.5.2 Format .................................................................................................................................................. 4-33

4.1.6 (FDF-8) Space Network Acquisition Data ....................................................................................... 4-35

4.1.6.1 Product Details .................................................................................................................................... 4-35

ii

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4.1.6.2 Format .................................................................................................................................................. 4-35

4.1.7 (FDF-9) Ground Station View Period Predicts File ........................................................................ 4-37

4.1.7.1 Product Details .................................................................................................................................... 4-38

4.1.7.2 Format .................................................................................................................................................. 4-38

4.1.8 (FDF-3) LRO Beta Angle Predict File ............................................................................................ 4-41

4.1.8.1 Product Details .................................................................................................................................... 4-41

4.1.8.2 Format .................................................................................................................................................. 4-41

4.1.9 (FDF-4) LRO Definitive Ephemeris File ......................................................................................... 4-42

4.1.9.1 Product Details .................................................................................................................................... 4-42

4.1.9.2 Format .................................................................................................................................................. 4-42

4.1.10 (FDF-29) LRO Definitive SPICE SPK File ................................................................................ 4-44

4.1.10.1 Product Details .................................................................................................................................... 4-44

4.1.10.2 Format .................................................................................................................................................. 4-44

4.1.11 (FDF-30) LRO Predictive SPICE SPK File ................................................................................ 4-44

4.1.11.1 Product Details .................................................................................................................................... 4-45

4.1.11.2 Format .................................................................................................................................................. 4-45

4.1.12 (FDF-13) Lunar Orbit Ascending and Descending Node Predicts ............................................. 4-45

4.1.12.1 Product Details .................................................................................................................................... 4-46

4.1.12.2 Format .................................................................................................................................................. 4-46

4.1.13 (FDF-14) Lunar Orbit Terminator Crossing Predicts ................................................................ 4-47

4.1.13.1 Product Details .................................................................................................................................... 4-47

4.1.13.2 Format .................................................................................................................................................. 4-47

4.1.14 (FDF-15) Mission Eclipse Predicts ............................................................................................ 4-48

4.1.14.1 Product Details .................................................................................................................................... 4-48

4.1.14.2 Format .................................................................................................................................................. 4-48

4.1.15 (FDF-16) Lunar Ephemeris ........................................................................................................ 4-49

4.1.15.1 Product Details .................................................................................................................................... 4-50

4.1.15.2 Format .................................................................................................................................................. 4-50

4.1.16 (FDF-23) Orbiter State Vector Table ......................................................................................... 4-51

4.1.16.1 Product Details .................................................................................................................................... 4-51

4.1.16.2 Format .................................................................................................................................................. 4-52

4.1.17 (FDF-17) Orbiter Thruster Maneuver Plans.............................................................................. 4-53

4.1.17.1 Product Details .................................................................................................................................... 4-53

4.1.17.2 Format .................................................................................................................................................. 4-53

4.1.18 (FDF-19) Orbiter Post Maneuver Report................................................................................... 4-56

4.1.18.1 Product Details .................................................................................................................................... 4-57

4.1.18.2 Format .................................................................................................................................................. 4-57

4.1.19 (FDF-18) Post Separation Report .............................................................................................. 4-58

4.1.19.1 Product Details .................................................................................................................................... 4-59

4.1.19.2 Format .................................................................................................................................................. 4-59

4.1.20 (FDF-20) Predicted LRO Ephemeris File .................................................................................. 4-60

4.1.20.1 Product Details .................................................................................................................................... 4-60

4.1.20.2 Format .................................................................................................................................................. 4-61

4.1.21 (FDF-21) Predicted Lunar Ground Track File ........................................................................... 4-62

4.1.21.1 Product Details .................................................................................................................................... 4-62

4.1.21.2 Format .................................................................................................................................................. 4-62

4.1.22 (FDF-22) Definitive Lunar Ground Track File .......................................................................... 4-63

4.1.22.1 Product Details .................................................................................................................................... 4-64

4.1.22.2 Format .................................................................................................................................................. 4-64

4.1.23 (FDF-25) Thruster Calibration Data.......................................................................................... 4-65

4.1.23.1 Product Details .................................................................................................................................... 4-65

4.1.23.2 Format .................................................................................................................................................. 4-66

4.1.24 (FDF-36) FDF Reprocessed SPICE Definitive Ephemeris Data SPK........................................ 4-67

4.1.24.1 Product Details .................................................................................................................................... 4-68

4.1.24.2 Format .................................................................................................................................................. 4-68

4.1.25 (FDF-37) FDF Solar Conjunction File ...................................................................................... 4-69

iii

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Revision – C

4.1.25.1 Product Details .................................................................................................................................... 4-70

4.1.25.2 Format .................................................................................................................................................. 4-70

4.1.26 (FDF-38) Target Thruster Vector File........................................................................................ 4-72

4.1.26.1 Product Details .................................................................................................................................... 4-72

4.1.26.2 Format .................................................................................................................................................. 4-72

4.1.27 (FDF-39) Laser Ranging Site View Period Predicts .................................................................. 4-74

4.1.27.1 Product Details .................................................................................................................................... 4-75

4.1.27.2 Format .................................................................................................................................................. 4-75

4.1.28 (FDF-40) Definitive Goddard Trajectory Determination System (GTDS) Ephemeris File ........ 4-77

4.1.28.1 Product Details .................................................................................................................................... 4-77

4.1.28.2 Format .................................................................................................................................................. 4-77

4.1.29 (FDF-42) FDF Time Coefficient File ......................................................................................... 4-78

4.1.29.1 Product Details .................................................................................................................................... 4-78

4.1.29.2 Format .................................................................................................................................................. 4-78

4.1.30 (FDF-44) Trajectory Insertion Data........................................................................................... 4-79

4.1.30.1 Product Details .................................................................................................................................... 4-79

4.1.30.2 Format .................................................................................................................................................. 4-79

4.1.31 (FDF-45) LRO Operations Activity Request ............................................................................... 4-80

4.1.31.1 Product Details .................................................................................................................................... 4-81

4.1.31.2 Format .................................................................................................................................................. 4-81

4.2 STATIONPRODUCTSANDDESCRIPTIONS ................................................................................. 4-84

4.2.1 (GNSO-1) SCN Support Schedules.................................................................................................. 4-86

4.2.1.1 Product Details .................................................................................................................................... 4-87

4.2.1.2 Format .................................................................................................................................................. 4-87

4.2.2 (WS1-5) (USN-3) Station Raw Tracking Data................................................................................. 4-89

4.2.2.1 Product Details .................................................................................................................................... 4-89

4.2.2.2 Format .................................................................................................................................................. 4-90

4.2.3 (WS1-10) (USN-6) Archived VC0 Telemetry Data .......................................................................... 4-94

4.2.3.1 Product Details .................................................................................................................................... 4-95

4.2.3.2 Format .................................................................................................................................................. 4-95

4.2.4 (WS1-11) (USN-7) Archived VC1 Telemetry Data .......................................................................... 4-96

4.2.4.1 Product Details .................................................................................................................................... 4-97

4.2.4.2 Format .................................................................................................................................................. 4-97

4.2.5 (WS1-12) (WS1-13) Archived Telemetry Data File......................................................................... 4-98

4.2.5.1 Product Details .................................................................................................................................... 4-99

4.2.5.2 Format .................................................................................................................................................. 4-99

4.2.6 (WS1-6) (WS1-7) (USN-4) (USN-5) (SN-1) Real-time Orbiter Telemetry Data ............................ 4-100

4.2.6.1 Product Details .................................................................................................................................. 4-100

4.2.6.2 Format ................................................................................................................................................ 4-101

4.2.7 (WS1-1) (USN-1) Station Status Packets....................................................................................... 4-101

4.2.7.1 Product Details .................................................................................................................................. 4-101

4.2.7.2 Format ................................................................................................................................................ 4-101

4.2.8 (WS1-2) (USN-2) Weather Data .................................................................................................... 4-102

4.2.8.1 Product Details .................................................................................................................................. 4-102

4.2.8.2 Format ................................................................................................................................................ 4-102

4.2.9 (WS1-3) (WS1-4) Ka-Band Telemetry............................................................................................ 4-104

4.2.9.1 Product Details .................................................................................................................................. 4-105

4.2.9.2 Format ................................................................................................................................................ 4-105

4.2.10 (WS1-8) Ka-Band RF Receiver Data ........................................................................................ 4-105

4.2.10.1 Product Details .................................................................................................................................. 4-105

4.2.10.2 Format ................................................................................................................................................ 4-106

4.2.11 (WS1-14) (WS1-16) Raw Telemetry File Data .......................................................................... 4-107

4.2.11.1 Product Details .................................................................................................................................. 4-108

4.2.11.2 Format ................................................................................................................................................ 4-108

4.2.12 (DSN-1) DSN Tracking Data .................................................................................................... 4-108

4.2.12.1 Product Details .................................................................................................................................. 4-108

iv

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4.2.12.2 Format ................................................................................................................................................ 4-109

4.2.13 (DSN-2) (DSN-3) Real-time Telemetry Data ............................................................................ 4-109

4.2.13.1 Product Details .................................................................................................................................. 4-111

4.2.13.2 Format ................................................................................................................................................ 4-111

4.2.14 (DSN-5) (DSN-6) Archived Telemetry Data ............................................................................. 4-111

4.2.14.1 Product Details .................................................................................................................................. 4-112

4.2.14.2 Format ................................................................................................................................................ 4-112

4.2.15 (DSN-4) DSN Station Monitor Packets ..................................................................................... 4-112

4.2.15.1 Product Details .................................................................................................................................. 4-112

4.2.15.2 Format ................................................................................................................................................ 4-113

4.3 SCIENCEOPERATIONCENTERPRODUCTSANDDESCRIPTIONS ........................................ 4-113

4.3.1 (CRaTER-1) (DLRE-1) (LAMP-1) (LEND-1) (LOLA-1) (LROC-1) (MIRF-1) LRO Operations Activity Request ............................................................................................................................................ 4-113

4.3.1.1 Product Details .................................................................................................................................. 4-114

4.3.1.2 Format ................................................................................................................................................ 4-114

4.3.2 (LOLA-5), (LROC-4), (MIRF-4) Target Request ........................................................................... 4-117

4.3.2.1 Product Details .................................................................................................................................. 4-118

4.3.2.2 Format ................................................................................................................................................ 4-118

4.3.3 (DLRE-2) (LAMP-2) (LOLA-3) (MIRF-2) Instrument FSW Load ................................................. 4-119

4.3.3.1 Product Details .................................................................................................................................. 4-120

4.3.3.2 Format ................................................................................................................................................ 4-120

4.3.4 (LOLA-2) LOLA Improved Lunar Gravity Model.......................................................................... 4-125

4.3.4.1 Product Details .................................................................................................................................. 4-125

4.3.4.2 Format ................................................................................................................................................ 4-125

4.3.5 (LOLA-4) LOLA Processed OD Information ................................................................................. 4-126

4.3.5.1 Product Details .................................................................................................................................. 4-126

4.3.5.2 Format ................................................................................................................................................ 4-127

4.3.6 (LOLA-6) LOLA Processed Laser Ranging Data.......................................................................... 4-127

4.3.6.1 Product Details .................................................................................................................................. 4-128

4.3.6.2 Format ................................................................................................................................................ 4-128

4.3.7 (LOLA-7) Lunar Laser Retro-Reflector Event Information ........................................................... 4-129

4.3.7.1 Product Details .................................................................................................................................. 4-129

4.3.7.2 Format ................................................................................................................................................ 4-129

4.3.8 (LR-1) Laser Ranging Schedule Information ................................................................................. 4-130

4.3.8.1 Product Details .................................................................................................................................. 4-131

4.3.8.2 Format ................................................................................................................................................ 4-131

4.3.9 (LROC-2) LROC Instrument Initialization Command Sequence ................................................... 4-133

4.3.9.1 Product Details .................................................................................................................................. 4-133

4.3.9.2 Format ................................................................................................................................................ 4-134

4.3.10 (LROC-3) LROC Daily Command Sequence ............................................................................ 4-135

4.3.10.1 Product Details .................................................................................................................................. 4-135

4.3.10.2 Format ................................................................................................................................................ 4-135

4.3.11 (MIRF-3) Mini-RF Command Timeline .................................................................................... 4-139

4.3.11.1 Product Details .................................................................................................................................. 4-139

4.3.11.2 Format ................................................................................................................................................ 4-140

4.4 LRO FSWM FACILITY TO LRO MISSION MOC INTERFACE PRODUCTS ................................... 4-144

4.4.1 (FSWM-1) Orbiter FSW Load Files .............................................................................................. 4-144

4.4.1.1 Product Details .................................................................................................................................. 4-144

4.4.1.2 Format ................................................................................................................................................ 4-144

4.5 LRO MISSION OPERATIONS CENTER PRODUCTS AND DESCRIPTIONS ............................. 4-145

4.5.1 (MOC-7) Daily Command Load Report ........................................................................................ 4-145

4.5.1.1 Product Details .................................................................................................................................. 4-145

4.5.1.2 Format ................................................................................................................................................ 4-145

4.5.2 (MOC-2) SPICE SCLK Clock Correlation File ............................................................................. 4-148

4.5.2.1 Product Details .................................................................................................................................. 4-148

4.5.2.2 Format ................................................................................................................................................ 4-148

v

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4.5.3 (MOC-33) SPICE Event Kernel ..................................................................................................... 4-149

4.5.3.1 Product Details .................................................................................................................................. 4-150

4.5.3.2 Format ................................................................................................................................................ 4-150

4.5.4 (MOC-40) SPICE FK – Frame Kernels......................................................................................... 4-151

4.5.4.1 Product Details .................................................................................................................................. 4-151

4.5.4.2 Format ................................................................................................................................................ 4-151

4.5.5 (MOC-41) SPICE Predicted CK (Predicted S/C Orientation) ....................................................... 4-152

4.5.5.1 Product Details .................................................................................................................................. 4-152

4.5.5.2 Format ................................................................................................................................................ 4-153

4.5.6 (MOC-42) SPICE Definitive CK (Definitive S/C Orientation) ...................................................... 4-153

4.5.6.1 Product Details .................................................................................................................................. 4-153

4.5.6.2 Format ................................................................................................................................................ 4-153

4.5.7 (MOC-43) SPICE Definitive HGA Orientation CK ....................................................................... 4-154

4.5.7.1 Product Details .................................................................................................................................. 4-154

4.5.7.2 Format ................................................................................................................................................ 4-154

4.5.8 (MOC-44) SPICE Definitive SA Orientation CK ........................................................................... 4-155

4.5.8.1 Product Details .................................................................................................................................. 4-155

4.5.8.2 Format ................................................................................................................................................ 4-155

4.5.9 Instrument – Spacecraft Housekeeping Data File ......................................................................... 4-156

4.5.9.1 Product Details .................................................................................................................................. 4-156

4.5.9.2 Format ................................................................................................................................................ 4-156

4.5.10 Instrument Housekeeping Data Files ........................................................................................ 4-158

4.5.10.1 Product Details .................................................................................................................................. 4-158

4.5.10.2 Format ................................................................................................................................................ 4-158

4.5.11 Instrument Raw Measurement Data Files................................................................................. 4-159

4.5.11.1 Product Details .................................................................................................................................. 4-159

4.5.11.2 Format ................................................................................................................................................ 4-159

4.5.12 (MOC46 – MOC60) Meta Summary Reports............................................................................ 4-161

4.5.12.1 Product Details .................................................................................................................................. 4-161

4.5.12.2 Format ................................................................................................................................................ 4-161

4.5.13 Real-time VC0 housekeeping data ............................................................................................ 4-166

4.5.13.1 Product Details .................................................................................................................................. 4-169

4.5.13.2 Format ................................................................................................................................................ 4-169

4.5.14 (MOC-73) Archived CRaTER VC0 Telemetry File ................................................................... 4-169

4.5.14.1 Product Details .................................................................................................................................. 4-169

4.5.14.2 Format ................................................................................................................................................ 4-170

4.5.15 (MOC-30) Mini-RF Operations Opportunity ............................................................................ 4-170

4.5.15.1 Product Details .................................................................................................................................. 4-171

4.5.15.2 Format ................................................................................................................................................ 4-171

4.5.16 (MOC-62) RTS Command Load Report.................................................................................... 4-172

4.5.16.1 Product Details .................................................................................................................................. 4-173

4.5.16.2 Format ................................................................................................................................................ 4-173

4.5.17 (MOC-71) Data Recorder Model Report.................................................................................. 4-175

4.5.17.1 Product Details .................................................................................................................................. 4-175

4.5.17.2 Format ................................................................................................................................................ 4-175

4.6 MOC PRODUCTS TO STATIONS ................................................................................................... 4-179

4.6.1 (MOC-34) (MOC-36) Real-time Orbiter Commands (WS1 and USN and SN).............................. 4-181

4.6.1.1 Product Details .................................................................................................................................. 4-181

4.6.1.2 Format ................................................................................................................................................ 4-181

4.6.2 (MOC-35) DSN Real-time Orbiter Commands .............................................................................. 4-181

4.6.2.1 Product Details .................................................................................................................................. 4-182

4.6.2.2 Format ................................................................................................................................................ 4-182

4.7 NAVIGATION AND ANCILLARY INFORMATION FACILITY (NAIF) INTERFACE AND PRODUCTS4182

4.7.1 (NAIF-1) SPICE Planetary SPK .................................................................................................... 4-183

4.7.1.1 Product Details .................................................................................................................................. 4-183

vi

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4.7.1.2 Format ................................................................................................................................................ 4-183

4.7.2 (NAIF-2) SPICE LSK – Leap Second ............................................................................................ 4-183

4.7.2.1 Product Details .................................................................................................................................. 4-184

4.7.2.2 Format ................................................................................................................................................ 4-184

4.7.3 (NAIF-3) SPICE Generic PCK (Planetary Constants).................................................................. 4-184

4.7.3.1 Product Details .................................................................................................................................. 4-185

4.7.3.2 Format ................................................................................................................................................ 4-185

4.7.4 (NAIF-4) SPICE Lunar Reference Frame ..................................................................................... 4-185

4.7.4.1 Product Details .................................................................................................................................. 4-186

4.7.4.2 Format ................................................................................................................................................ 4-186

4.8 LAUNCH SITE (KSC) PRODUCT AND DESCRIPTIONS ............................................................................... 4-186

4.8.1 (KSC-1) (KSC-2)Real-time Orbiter Telemetry .............................................................................. 4-186

4.8.1.1 Product Details .................................................................................................................................. 4-187

4.8.1.2 Format ................................................................................................................................................ 4-187

4.8.2 (KSC-3) Archived VC0 Orbiter Telemetry..................................................................................... 4-187

4.8.2.1 Product Details .................................................................................................................................. 4-187

4.8.2.2 Format ................................................................................................................................................ 4-188

4.8.3 (KSC-4) Archived VC1 Telemetry Data ......................................................................................... 4-188

4.8.3.1 Product Details .................................................................................................................................. 4-188

4.8.3.2 Format ................................................................................................................................................ 4-188

4.8.4 (KSC-5)Archived VC2 Telemetry Data .......................................................................................... 4-188

4.8.4.1 Product Details .................................................................................................................................. 4-189

4.8.4.2 Format ................................................................................................................................................ 4-189

4.8.5 (KSC-6) Archived VC3 telemetry Data .......................................................................................... 4-189

4.8.5.1 Product Details .................................................................................................................................. 4-189

4.8.5.2 Format ................................................................................................................................................ 4-190

4.8.6 (LV-1) Launch Vehicle Post Separation Vector ............................................................................. 4-190

4.8.6.1 Product Details .................................................................................................................................. 4-190

4.8.6.2 Format ................................................................................................................................................ 4-190

4.9 LROMOCPRODUCTINTERFACE WITH THE LAUNCH SITE ................................................................. 4-190

4.9.1 (MOC-38) Telemetry to KSC ......................................................................................................... 4-190

4.9.1.1 Product Details .................................................................................................................................. 4-191

4.9.1.2 Format ................................................................................................................................................ 4-191

4.9.2 (MOC-37) Commands to KSC ....................................................................................................... 4-191

4.9.2.1 Product Details .................................................................................................................................. 4-191

4.9.2.2 Format ................................................................................................................................................ 4-192

4.9.3 (MOC-69) LRO-Provided Separation Data File ........................................................................... 4-192

4.9.3.1 Product Details .................................................................................................................................. 4-192

4.9.3.2 Format ................................................................................................................................................ 4-192

4.10 LROMOCPRODUCTINTERFACE WITH THE FLIGHT DYNAMICS FACILITY ......................................... 4-194

4.10.1 (MOC-63) Propulsion System Data .......................................................................................... 4-194

4.10.1.1 Product Details .................................................................................................................................. 4-194

4.10.1.2 Format ................................................................................................................................................ 4-195

4.10.2 (MOC-65) Definitive Spacecraft Body Frame Attitude File ..................................................... 4-196

4.10.2.1 Product Details .................................................................................................................................. 4-196

4.10.2.2 Format ................................................................................................................................................ 4-197

4.10.3 (MOC-66) Spacecraft HGA Motion File ................................................................................... 4-198

4.10.3.1 Product Details .................................................................................................................................. 4-198

4.10.3.2 Format ................................................................................................................................................ 4-199

4.10.4 (MOC-67) Spacecraft Solar Array Motion File ........................................................................ 4-199

4.10.4.1 Product Details .................................................................................................................................. 4-200

4.10.4.2 Format ................................................................................................................................................ 4-200

4.10.5 (MOC-68) OBC Generated Attitude Data File ......................................................................... 4-200

4.10.5.1 Product Details .................................................................................................................................. 4-201

4.10.5.2 Format ................................................................................................................................................ 4-201

4.10.6 (MOC-72) LRO Thruster Data.................................................................................................. 4-203

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4.10.6.1 Product Details .................................................................................................................................. 4-204

4.10.6.2 Format ................................................................................................................................................ 4-204

4.10.7 (MOC-74) Predictive LRO Spacecraft Body Attitude File ........................................................ 4-206

4.10.7.1 Product Details .................................................................................................................................. 4-206

4.10.7.2 Format ................................................................................................................................................ 4-207

4.11 LRO MOC PRODUCT INTERFACES WITH CDDIS (VIA THE LOLA SOC) ............................................ 4-209

4.11.1 (MOC-64) Laser Ranging GO Flag .......................................................................................... 4-209

4.11.1.1 Product Details .................................................................................................................................. 4-209

4.11.1.2 Format ................................................................................................................................................ 4-209

APPENDIX A: – ABBREVIATIONS AND ACRONYMS ................................................................................. A-1

APPENDIX B – SAMPLE PRODUCT FORMATS............................................................................................ B-1

SAMPLE FDF PRODUCTS ...................................................................................................................................... B-1

B.1.1 (FDF-6) INP-2 Acquisition Data Sample ......................................................................................... B-1

B.1.2 (FDF-10) OEM Acquisition Data Sample ........................................................................................ B-2

B.1.3 (FDF-7) LR Prediction Data Sample................................................................................................ B-3

B.1.4 (FDF-8) Space Network Acquisition Data Sample ........................................................................... B-4

B.1.5 (FDF-9) Ground Station View Period Predicts Data Sample .......................................................... B-5

B.1.6 (FDF-3) LRO Beta Angle Predict File Sample ................................................................................. B-6

B.1.7 (FDF-4) LRO Definitive Ephemeris File Sample ............................................................................. B-7

B.1.8 (FDF-13) Lunar Orbit Ascending and Descending Node Predicts Sample...................................... B-8

B.1.9 (FDF-14) Lunar Orbit Terminator Crossing Predicts Sample ......................................................... B-9

B.1.10 (FDF-15) Mission Eclipse Predicts Data Sample...................................................................... B-10

B.1.11 (FDF-16) Lunar Ephemeris Data Sample ................................................................................. B-11

B.1.12 (FDF-17) Orbiter Thruster Maneuver Plans Data Sample ....................................................... B-12

B.1.13 (FDF-19) Orbiter Post Maneuver Report Data Sample ............................................................ B-13

B.1.14 (FDF-18) Post Separation Report Data Sample ........................................................................ B-14

B.1.15 (FDF-20) Predicted LRO Ephemeris File Sample ..................................................................... B-16

B.1.16 (FDF-21) Predicted Lunar Ground Track File Sample ............................................................. B-17

B.1.17 (FDF-22) Definitive Lunar Ground Track File Sample ............................................................. B-18

B.1.18 (FDF-23) Orbiter State Vector Table Sample ............................................................................ B-19

B.1.19 (FDF-25) Thruster Calibration Data File Sample ..................................................................... B-20

B.1.20 (FDF-37) Solar Conjunction File Sample ................................................................................. B-21

B.1.21 (FDF-38) Target Thruster Vector File Sample .......................................................................... B-22

B.1.22 (FDF-39) LR Ground Station View Period Sample ................................................................... B-23

B.1.23 (FDF-44) Trajectory Insertion Data Sample ............................................................................. B-24

SPACE COMMUNICATIONS DATA PRODUCTS ...................................................................................................... B-25

B.1.24 (GNSO-1) Station Support Schedules Sample............................................................................ B-25

B.1.25 (WS1-2) and (USN-2) Station Weather Data Sample ................................................................ B-26

B.1.26 (WS1- 8) Ka-Band RF Receiver Data File Sample .................................................................... B-27

SCIENCE OPERATIONS CENTER PRODUCTS ......................................................................................................... B-28

B.1.27 (CRaTER-1) (DLRE-1) (LAMP-1) (LEND-1) (LOLA-1) (LROC-1) (MIRF-1) LRO Operations Activity Request Sample ................................................................................................................................ B-28

B.1.28 (LOLA-4), (LROC-4), (MIRF-4) Target Requests ...................................................................... B-29

B.1.29 (DLRE-2) DLRE FSW Load Samples......................................................................................... B-30

B.1.30 (LAMP-3) LAMP Instrument FSW Load Sample....................................................................... B-32

B.1.31 (LOLA-2) LOLA Improved Lunar Gravity Model Sample ......................................................... B-33

B.1.32 (LOLA-3) LOLA Instrument FSW Load Sample ........................................................................ B-34

B.1.33 (LOLA-6) LOLA Processed Laser Ranging Data Sample .......................................................... B-35

B.1.34 (LOLA-7) Lunar Laser Retro-Reflector Avoidance Event File Sample...................................... B-36

B.1.35 (LR-1) Laser Ranging Schedule Data Sample ........................................................................... B-37

B.1.36 (LROC-3) LROC Daily Command Sequence Sample ................................................................ B-38

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B.1.37 (MIRF-2) Mini-RF Load Files ................................................................................................... B-39

B.1.38 (MIRF-3) Mini-RF Command Timeline Files ............................................................................ B-40

MISSION OPERATIONS CENTER PRODUCTS ......................................................................................................... B-41

B.1.39 (MOC-7) Daily Command Load Report Sample ........................................................................ B-41

B.1.40 (MOC-62) RTS Command Load Report Sample ........................................................................ B-42

B.1.41 (MOC-2) SCLK SPICE Clock Correlation File Sample ............................................................ B-43

B.1.42 (MOC-40) SPICE FK – Frame Kernel Sample .......................................................................... B-45

B.1.43 (MOC-41- MOC-44) SPICE CK File Comments Sample .......................................................... B-48

B.1.44 (MOC-30) Mini-RF Operations Opportunity Sample ................................................................ B-50

B.1.45 (MOC-46 thru MOC-60) Meta-Summary Report Sample .......................................................... B-51

B.1.46 (MOC-63) Propulsion System Data File Sample ....................................................................... B-54

B.1.47 (MOC-65) Definitive Spacecraft Body Frame Attitude File ...................................................... B-55

B.1.48 (MOC-66) Spacecraft HGA Motion File .................................................................................... B-56

B.1.49 (MOC-67) Spacecraft Solar Array Motion File ......................................................................... B-57

B.1.50 (MOC-68) OBC Generated Attitude Data File .......................................................................... B-58

B.1.51 (MOC-72) LRO Thruster Data File ........................................................................................... B-59

B.1.52 (MOC-74) Predictive LRO Spacecraft Body Attitude File ......................................................... B-60

B.1.53 (MOC-64) Laser Ranging Go-NOGO Flag Sample File ........................................................... B-61

B.1.54 (MOC-69) LRO-Provided Separation Data Sample File ........................................................... B-62

B.1.55 (MOC-71) Data Recorder Model Report Sample File ............................................................... B-63

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LIST OF FIGURES

Figure Page Figure 2-1 LRO Ground System Overview Diagram .................................................................. 2-3 Figure 2-2 LRO Communications Architecture .......................................................................... 2-6 Figure 2-3 LRO MOC Logical Architecture ............................................................................... 2-8 Figure 4-1 FDF Maneuver Plan Header Concept ...................................................................... 4-54 Figure 4-2 FDF Maneuver Plan Initial Thruster Data Concept ................................................. 4-54 Figure 4-3 FDF Maneuver Plan Final Thruster Data Concept .................................................. 4-55 Figure 4-4 Solar Conjunction Geometry Examples ................................................................... 4-69 Figure 4-5 SMEX/LEOT Telemetry Header ............................................................................. 4-85 Figure 4-6 Common SLE Format Header Structure ................................................................ 4-109 Figure 4-7 Instrument FSW Load File Structure ..................................................................... 4-121 Figure 4-8 Missing Segment Boundaries ................................................................................. 4-162 Figure 4-9 Missing and Deleted Segment Boundaries ............................................................ 4-163 Figure 4-10 ITOS Annotation Header Layout ......................................................................... 4-167 Figure 4-11: Recorder Model Scenario .................................................................................... 4-175 Figure 4-12 EOS Ground Message Header ............................................................................. 4-179 Figure B.1-1 Sample INP-2 Acquisition Data File ..................................................................... B-1 Figure B.1-2 Sample OEM Acquisition Data File ...................................................................... B-2 Figure B.1-3 Sample Laser Ranging Prediction Data File ......................................................... B-3 Figure B.1-4 Sample Space Network Acquisition Data File ...................................................... B-4 Figure B.1-5 Sample Ground Station View Period Predicts Data File ....................................... B-5 Figure B.1-6 Sample LRO Beta Angle Predict File ................................................................... B-6 Figure B.1-7 Sample LRO Definitive Ephemeris File ................................................................ B-7 Figure B.1-8 Sample Lunar Orbit Ascending and Descending Node Predicts File .................... B-8

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Figure B.1-9 Sample Lunar Orbit Terminator Crossing Predicts Data File ............................... B-9 Figure B.1-10 Sample Mission Eclipse Predicts Data File ....................................................... B-10 Figure B.1-11 Sample Lunar Ephemeris Data File ................................................................... B-11 Figure B.1-12 Sample Orbiter Thruster Maneuver Plans Data File ......................................... B-12 Figure B.1-13 Sample Orbiter Post Maneuver Report Data File .............................................. B-13 Figure B.1-14 Sample Post Separation Report Data File (Page 1 of 2) .................................... B-14 Figure B.1-15 Sample Post Separation Report Data File (Page 2 of 2) .................................... B-15 Figure B.1-16 Sample Predicted LRO Ephemeris File ............................................................. B-16 Figure B.1-17 Sample Predicted Lunar Ground Track File ...................................................... B-17 Figure B.1-18 Sample Definitive Lunar Ground Track File ..................................................... B-18 Figure B.1-19 Sample LRO State Vector Table Data File ....................................................... B-19 Figure B.1-20 Sample Thruster Calibration Data File .............................................................. B-20 Figure B.1-21 Sample Solar Conjunction File .......................................................................... B-21 Figure B.1-22 Sample Target Thruster Vector File .................................................................. B-22 Figure B.1-23 Sample LR Ground Station View Period File ................................................... B-23 Figure B.1-24 Sample Trajectory Insertion Data File .............................................................. B-24 Figure B.2-1 Sample Station Support Schedules File ............................................................... B-25 Figure B.2-2 Sample Station Weather Data File ...................................................................... B-26 Figure B.2-3 Sample Ka-Band RF Receiver Data File ............................................................. B-27 Figure B.3-1 Sample LRO Operations Activity Request File .................................................. B-28 Figure B.3-2 Sample Target Requests File ............................................................................... B-29 Figure B.3-3 Sample DLRE Scan Table Load File .................................................................. B-30 Figure B.3-4 Sample DLRE FSW Load File ............................................................................ B-31 Figure B.3-5 Sample LAMP Instrument FSW Load File ......................................................... B-32 Figure B.3-6 Sample LOLA Improved Lunar Gravity Model .................................................. B-33

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Figure B.3-7 Sample LOLA Instrument FSW Load File ......................................................... B-34 Figure B.3-8 Sample LOLA Processed Laser Ranging Data File ............................................ B-35 Figure B.3-9 Sample Lunar Laser Retro-Reflector Avoidance Event File ............................... B-36 Figure B.3-10 Sample Laser Ranging Schedule Data File ....................................................... B-37 Figure B.3-11 LROC Daily Command Sequence File ............................................................. B-38 Figure B.3-12 Sample Mini-RF Load File ................................................................................ B-39 Figure B.3-13 Sample Mini-RF Command Timeline File ........................................................ B-40 Figure B.4-1 Sample Daily Command Load Report File ......................................................... B-41 Figure B.4-2 Sample RTS Command Load Report File ........................................................... B-42 Figure B.4-3 Sample SCLK SPICE Clock Correlation File (page 1 of 2) ............................... B-43 Figure B.4-4 Sample SCLK SPICE Clock Correlation File (page 2 of 2) ............................... B-44 Figure B.4-5 Sample SPICE FK – Frame Kernel ..................................................................... B-47 Figure B.4-6 Sample SPICE CK File Comments (Page 1 of 2) ............................................... B-48 Figure B.4-6 Sample SPICE CK File Comments (Page 2 of 2) ............................................... B-49 Figure B.4-7 Sample Mini- Operations Opportunity File ......................................................... B-50 Figure B.4-8 Sample Meta-Summary Report (No Gaps) ......................................................... B-51 Figure B.4-9 Sample Meta-Summary Report (Missing Data Segments) ................................. B-51 Figure B.4-10 Sample Meta-Summary Report (Deleted Data Segments) ................................ B-52 Figure B.4-10 Sample LROC Science Meta-Summary Report (No Missing Data Segments) B-53 Figure B.4-11 Sample Propulsion System Data File ................................................................ B-54 Figure B.4-12 Sample Definitive Spacecraft Body Frame Attitude File .................................. B-55 Figure B.4-13 Sample Spacecraft HGA Motion File ................................................................ B-56 Figure B.4-14 Sample Spacecraft Solar Array Motion File ..................................................... B-57 Figure B.4-15 Sample OBC Generated Attitude Data File ....................................................... B-58 Figure B.4-16 Sample LRO Thruster Data File ........................................................................ B-59

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Figure B.4-17 Sample Predictive LRO Spacecraft Body Attitude File .................................... B-60 Figure B.4-18 Sample Laser Ranging Go-NOGO Flag File..................................................... B-61 Figure B.4-19 Sample LRO-Provided Separation Data File .................................................... B-62 Figure B.4-20 Sample Data Recorder Model Report File ........................................................ B-63

LIST OF TABLES

Table Page Table 2-1 MOC Functional Component Information .................................................................. 2-7 Table 3-1 LRO External Interface Products Cross Reference ..................................................... 3-1 Table 4-1 FDF File Naming Convention ................................................................................... 4-25 Table 4-2 FDF – SCN Acquisition Data Description ................................................................ 4-27 Table 4-3 FDF – Laser Ranging Prediction Data Description ................................................... 4-34 Table 4-4 FDF – IIRV TTY SN Acquisition Data Description ................................................. 4-36 Table 4-5 FDF – Ground Station View Period Data Description .............................................. 4-39 Table 4-6 FDF – Ground Station No View Period Data Description ........................................ 4-40 Table 4-7 FDF – LRO Beta Angle Data Description ................................................................ 4-42 Table 4-8 FDF – LRO Definitive Ephemeris Data Description ................................................ 4-43 Table 4-9 FDF – LRO Ascending Descending Node Data Description .................................... 4-46 Table 4-10 FDF – LRO Lunar Orbit Terminator Crossing Predicts Data Description ............. 4-48 Table 4-11 FDF – LRO Mission Eclipse Data Description ....................................................... 4-49 Table 4-12 FDF – Lunar Ephemeris Data Description .............................................................. 4-50 Table 4-13 FDF – LRO State Vector Table Data Description ................................................... 4-52 Table 4-14 FDF – LRO Post Separation Report Data Description Information ........................ 4-60 Table 4-15 FDF – LRO Predictive Ephemeris Data Description Information .......................... 4-61 Table 4-16 FDF – LRO Predicted Ephemeris Data Description Information ........................... 4-63 Table 4-17 FDF – LRO Definitive Lunar Ground Track Description Information ................... 4-64 Table 4-18 FDF – Solar Conjunction Data Description ............................................................ 4-71

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Table 4-19 FDF – Laser Ranging View Period Data Description ............................................. 4-76 Table 4-20 FDF – Trajectory Insertion Data Description .......................................................... 4-80 Table 4-21 LRO Operations Activity Request Definitions........................................................ 4-81 Table 4-22 SMEX/LEOT Field Definitions and Expected Values ............................................ 4-85 Table 4-23 SCN Station Support Schedule Field Definitions ................................................... 4-88 Table 4-24 WS1 Raw Tracking Data File Field Definitions ..................................................... 4-91 Table 4-25 Station Weather Data Field Definitions ................................................................ 4-103 Table 4-26 WS1 Ka-Band Receiver Data Field Definitions.................................................... 4-106 Table 4-27 SLE Telemetry Header Structure Definitions ....................................................... 4-110 Table 4-28 LRO Operations Activity Request Definitions...................................................... 4-114 Table 4-29 Instrument FSW Load Directive File Data Definitions ......................................... 4-122 Table 4-30: Current Set of Available LROC Commands........................................................ 4-136 Table 4-32 SOC File Naming Conventions and Descriptions ................................................. 4-157 Table 4-33 Meta-Summary Report Description ...................................................................... 4-163 Table 4-33 Meta-Summary Report Description for LROC and Mini-RF Science Files ......... 4-165 Table 4-34 ITOS Annotation Header Field Definitions .......................................................... 4-167 Table 4-35 Data Recorder Memory Model Description .......................................................... 4-176 Table 4-36 EOS Ground Message Header Definitions ............................................................ 4-180 Table 4-37 Best Estimated Separation Data Description ......................................................... 4-193 Table 4-41 OBC Calculated Attitude Data File (MOC-68) Description ................................. 4-202 Table 4-42 Propulsion Data File (MOC-72) Description ........................................................ 4-205

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1.0 INTRODUCTION

The Interface Control Document for the Lunar Reconnaissance Orbiter Ground System (431ICD-000049) is one of three documents produced by the Lunar Reconnaissance Orbiter (LRO) ground system team that provides the foundation for the development and operations of the ground system for all mission phases. The other documents are the Lunar Reconnaissance Orbiter Detailed Mission Requirements Document (431-RQMT-000049) and the Lunar Reconnaissance Orbiter Mission Design Handbook (431-HDBK-000486). This document provides the Level-3 mission interface requirements and identifies the products, which are noted in that document and provided within the scope of this document.

1.1 PURPOSE AND SCOPE

The ICD specifies the interface that the LRO ground system (GS) has with the Space Communications Network (SCN) and the various science centers, as well as the external interfaces with other LRO mission operations center (MOC) elements.

This ICD documents the interfaces and products among the various external elements and is valid during the pre-mission phase through the end of the prime mission phase. The project will reevaluate the interfaces and required products for the LRO Extended Mission phase.

1.2 DOCUMENT ORGANIZATION

The document organization provides details regarding the various ground system elements and the interfaces and products between the external LRO elements and the LRO ground system.

Section 2.0 contains a brief description of the mission, ground system architecture, and identifies the various ground system elements. More detailed and specific information on the orbiter, launch vehicle, schedules, and mission phases is provided by the LRO Mission Concept of Operations (MCO).

Section 3.0 provides the cross reference of the external products to/from the LRO MOC; it provides a mapping of DMR requirements and the cross reference to other document sections, which is linked to provide more specific details.

Section 4 provides the call out of each external interface and the associated products that are transferred between LRO external elements and the LRO ground system elements.

Outstanding open items within the ICD are identified as “To Be Determined” (TBD), “To Be Supplied” (TBS), or “To Be Resolved” (TBR). Open items are documented in the List of TBDs/TBRs section in the front of the document.

1.3 REQUIREMENTS TRACEABILITY METHODOLOGY

The ground system interfaces specified in this document are derived from the Lunar Reconnaissance Orbiter Detailed Mission Requirements Document (431-RQMT-0000048), which identified the specific instance associated with the interface description.

1.4 APPLICABLE DOCUMENTS

The following LRO project documents apply only to the extent they are cited in this document.

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431-RQMT-000174 431-RQMT-000048 Lunar Reconnaissance Orbiter Mission Assurance Requirements Lunar Reconnaissance Orbiter Detailed Mission Requirements Document
431-HDBK-000052 Lunar Reconnaissance Orbiter Telemetry and Command Formats Handbook
431-HDBK-000053 Lunar Reconnaissance Orbiter Telemetry and Command Database Handbook
431-PLAN-000050 LRO Ground System Mission Operations Support Plan (MOSP)
431-SPEC-000078 431-HDBK-000486 431-RQMT-000113 453-ICD-GN/WS1 451-MOA-002960 Lunar Reconnaissance Orbiter CCSDS File Delivery Protocol Specification Lunar Reconnaissance Orbiter Mission Design Handbook LRO Pointing and Alignment Requirements Interface Control Document for the White Sands One Ground Station (WS1) FDF-GS&O Operations Agreement

1.5 REFERENCED DOCUMENTS

The following NASA and GFSC documents are used as supporting and reference documents only.

NASA NPR 2810.1a NASA Security of Information Technology; Revalidated 12 August 2004

STDN-724 Spaceflight Tracking and Data Network (STDN) Tracking and Acquisition Handbook; 1990

820-013 0163-Telecomm DSN Space Link Extension Forward Link Service and Return Link Service; Revision A – February 15, 2004

820-13 TRK 2-33 DSN document to define external interface for SPICE SPK, Type 13 820-13, 0168 Service Management Interface document 887-117 SPS Portal Operation Manual CCSDS 502.0-B-1 Orbit Data Messages, September 2004 RTL-ICD-T720HDR, Rev1.2 High Data Rate Receiver Interface Control Document

1.6 OTHER DOCUMENTED REFERENCES

Format data concepts specifically needed to support the laser ranging sites

http://ilrs.gsfc.nasa.gov/products_formats_procedures/crd.html http://ilrs.gsfc.nasa.gov/products_formats_procedures/predictions/cpf.html

http://naif.jpl.nasa.gov/naif/about.html https://spsweb.fltops.jpl.nasa.gov

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2.0 GROUND SYSTEM OVERVIEW

The Lunar Reconnaissance Orbiter (LRO)’s primary objectives are to conduct investigations that support future human exploration of the Moon.

LRO specific objectives are:

  • Characterize the lunar radiation environment, biological impacts, and potential mitigation

  • Determine a high resolution global, geodetic grid of the Moon in three dimensions

  • Assess in detail the resources and environments of the Moon’s polar cap regions

  • Perform high spatial resolution measurement of the Moon’s surface The LRO instrument complement includes six instruments. Together, all six instruments allow

LRO to meet the mission objectives. The following text provides an overview description of the six instruments:

  • Lunar Orbiter Laser Altimeter (LOLA): LOLA will determine the global topography of the lunar surface at high resolution, measuring landing site slopes and search for polar ice in shadow regions.

  • Lunar Reconnaissance Orbiter Camera (LROC): LROC will acquire targeted images of the lunar surface capable of resolving small-scale features that could be landing site hazards. LROC will also produce wide-angle images at multiple wavelengths of the lunar poles to document the changing illumination conditions and potential resources.

  • Lunar Exploration Neutron Detector (LEND): LEND will map the flux of neutrons from the lunar surface to search for evidence of water ice and provide measurements of space radiation environment which can be useful for future human exploration.

  • Diviner Lunar Radiometer Experiment (DLRE): DLRE will map the temperature of the entire lunar surface at 300-meter horizontal scales to identify cold-traps and potential ice deposits.

  • Lyman-Alpha Mapping Project (LAMP): LAMP will observe the entire lunar surface in the far ultraviolet (UV). LAMP will search for surface ice and frost in the Polar Regions and provide images of permanently shadowed regions illuminated only by starlight.

  • Cosmic Ray Telescope for Effects of Radiation (CRaTER): CRaTER will investigate the effect of galactic cosmic rays on tissue-equivalent plastics as a constraint on models of biological response to background space radiation.

LRO will also fly a technology demonstration instrument called the Mini-Radio Frequency (RF). The purpose of the Mini-RF is to demonstrate new radar technology for future use in planetary resource mapping. The mini-RF payload will operate on a non-interference basis throughout the mission.

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The LRO spacecraft bus will be built at Goddard Space Flight Center (GSFC). Integration of the measurement instruments to the orbiter system as well as orbiter environmental testing will be performed at GSFC.

The orbiter will be launched aboard an evolved expendable launch vehicle (EELV) from the Eastern Range at the Kennedy Space Center (KSC). The Launch Vehicle (LV) will inject LRO into a cis-lunar transfer orbit. LRO will be required to perform a series of Lunar Orbit Insertion (LOI) maneuvers to enter into the orbiter commissioning orbit of 30x216 kilometers (km). After orbiter commissioning is complete, LRO will be maneuvered into a 50 km circular orbit.

Once LRO is in the final mission orbit, the six instruments will start to collect measurement data for the mission. Measurement data along with housekeeping (HK) data will be dumped to the LRO Ground System (GS). Once the data are received at the MOC, the MOC is responsible for distribution of the data to the individual science operations centers (SOCs). The SOCs will receive and process the data to create level 1 data products. The LRO GS and SOCs also have the responsibility to transfer the processed data products to the Planetary Data System (PDS) for long term archival.

The details of the mission with the identification of the mission phases and the activities with each phase are provided in the Lunar Reconnaissance Orbiter Mission Design Handbook (431HDBK-000486)

2.1 GROUND SYSTEM ARCHITECTURE

The LRO GS is comprised of several main elements as shown in Figure 2-1 LRO Ground System Overview Diagram:

  • The LRO Space Communications Network, which consists of an S/Ka Band ground station at White Sands and various USN-provided S-Band only ground stations located throughout the world. It includes the Deep Space Network for use as a contingency/emergency network and a laser ranging facility, which is used to provide improved orbit knowledge for the orbiter. The LRO mission uses the Space Network (SN) asset for the first several hours post-launch to provide any necessary support until the first ground station coverage.

  • Mission Operations Center (MOC)

  • Flight Dynamics (FD), which supports maneuver planning, orbit determination, and attitude determination and sensor calibration processing

  • SOC for each instrument; while not actually part of the LRO Ground System, they are identified as residing within the LRO Ground Segment

  • Communications network which provides voice and data connectivity between each of these

elements LRO elected to use a combined S/Ka ground station at White Sands because of the high data volume that the Orbiter will produce and the requirements to use the Ka-band for the downlink of the measurement data. The measurement data are collected at the ground station and rate buffered to the MOC post-pass for data processing/accountability. The MOC at GSFC will distribute the measurement files along with other mission products that are needed for

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processing to each of the instrument SOCs. The MOC is the focal point for all orbiter operations including health and safety monitoring. All commands to the orbiter are generated at the MOC. The SOCs support instrument operations including instrument command sequence inputs, measurement data processing, transferring measurement products to the PDS, and instrument housekeeping and performance trending.

Each LRO Ground System element, as listed in Figure 2-1, is briefly described in the following subsections.

2.1.1 The LRO Space Communications Network

The LRO Space Communications Network (SCN) consists of a prime and backup station located at White Sands Complex. White Sands One (WS1) is identified the prime antenna for LRO support; LRO uses the Solar Dynamics Observatory (SDO) backup antenna (STSS) in the event of WS1 facility or equipment outages of a short duration.

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LRO uses the commercial S-Band ground stations to provide S-band TT&C support. The Jet Propulsion Laboratory (JPL)/DSN ground stations provide for backup/emergency support to the LRO SCN for the LRO mission, which includes maneuver support. The SN supports any post-launch contacts within the first several hours after launch that are required before either the WS1 station or the USN or DSN stations have a contact with the LRO Orbiter.

While not officially part of the SCN, there are several laser ranging sites to provide one-way laser time of flight data and support, through the LOLA SOC, the development of an improved lunar gravity model.

The WS1 ground station is capable of receiving 100 megabits per second (Mbps) downlink on Ka-Band frequency of measurement data files produced by the instruments and supporting real-time commands and telemetry on S-Band frequency. Due to susceptibility to Ka from weather, White Sands provides the optimal location due to its minimal precipitation levels. Because LRO requires near continuous tracking data for orbit determination, additional S-Band sites are needed. The S-Band only sites will provide real-time telemetry and commands capabilities along with tracking data. The S-Band stations could be used to dump low rate measurement files in a contingency mode. LRO plans to use the Deep Space Network for emergency/backup support. The emergency/backup support will utilize only the S-Band frequency.

2.1.2 LRO Mission Operations Center

The MOC will be located at GSFC. It is the main telemetry and command interface to the orbiter. The MOC will process housekeeping data to monitor health and safety of the orbiter. The MOC will also distribute measurement data to the individual SOCs along with other required mission products. The MOC provides data storage for all raw measurement data for the life of the mission. The MOC will receive any required instrument command sequences from the SOCs and process them before uplink. The MOC will also distribute real-time telemetry to the SOCs.

The LRO MOC provides the following types of control functions as listed below; these functional components will be further described and identified in later sections.

  • Telemetry& Command (T&C) System

  • Mission Planning System

  • Trending System

  • Attitude Ground System (AGS)

  • Data Processing System

  • Data Management System

  • Monitoring and Alert System

2.1.3 The Science Operations Centers

The six SOCs and the Mini-RF technology demonstration operations center provide the hardware and software to support the following functions:

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  • Instrument command sequence generation/request

  • Support orbiter calibration planning/coordination

  • Measurement data processing (level 0 and higher)

  • Measurement data product archiving and transfer to the PDS

  • Maintain instrument flight software/tables

The SOCs themselves are not controlled and developed by the LRO ground system. The ground system responsibility ends with the interfaces to/from each of the SOCs

2.1.4 Flight Dynamics Facility

Flight Dynamics Facility (FDF) is hosted at GSFC; it has separate facilities that provide support for the standard orbit determination and product generation and the mission design, maneuver planning and trajectory support.

Flight dynamics (FD) supplies three FD teams, Orbit Team (made up of MOMS contractors in the FDF), Maneuver Team (made up of civil servants from Code 595,) and the Attitude Team (made up of a combination of MOMS contractors and 595 civil servants) to provide support for the LRO mission.

The Orbit Team and Maneuver Team provide LRO support from the Flight Dynamics Facility (FDF) in building 28. From the FDF facility, the Maneuver Team will have access to the orbit determination solutions, the MOC data sent to the FD Product Center (FDPC), the FDPC for outgoing maneuver plans and the FDF network for placing predicted trajectory data for planning products. For orbit determination, FD will receive the tracking data from the ground network and generate mission products. Besides pre-mission trajectory and orbit planning, FD will also monitor and plan for trajectory maneuvers during the cruise, Lunar Orbit Insertion burns, and station-keeping maneuvers; FD supplies these maneuver plans to the MOC for command uplink and Orbiter execution.

The Attitude Team will provide LRO support during early mission from the LRO MOC. FD will also provide attitude verification and planning support for slews. At a negotiated time after launch, the attitude support transitions to the LRO mission operations team.

2.1.5 Ground System Communications

The ground system communication network provides voice and data connectivity between each of the ground system elements. It will provide the necessary communication lines between the ground networks, MOC and SOCs.

Figure 2-2 depicts the communication architecture among the various LRO elements. It includes the space communications networks, the Kennedy Space Center (KSC), the GSFC MOC, and the seven science centers, which are located at various sites within the continental US. The communication links consist of dedicated communications lines, circuits, and routers.

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Communication among the I&T GSE, GS elements, the various science centers, and dedicated ground station at the White Sands Complex (WSC), the JPL/DSN backup/emergency ground stations, and the commercial S-Band network is accomplished through the Nascom Division and the NASA Integrated Services Network (NISN). NISN maintains both a secure or “closed” Internet Protocol (IP) Operational Network (IONet), an unsecured or “open” IONet, and a hybrid Restricted IONet (RIONet).

All LRO MOC GS elements are on the restricted IONet; the FDF component, located at GSFC in Building 28, resides on the closed IONet; FDF provides access to other FDF-related services, which reside on the Open IONet. NISN supplies the IP access connection from the closed, restricted, and open IONets and to the Center Network Environment (CNE) Wide Area Network (WAN).

If the MOC needs to send any real-time data from the restricted IONet to any external network, the MOC will provide this data using a socket connection through a secure applications gateway, as depicted in Figure 2-2.

LRO SE personnel conducted a trade study and selected the secure copy (scp) mechanism for non real-time data transfers. All files into and out of the MOC will use this identified protocol. The LRO MOC will scp files from the MOC to an agreed upon directory locations that the external elements have identified. Conversely, the external elements will scp their files to a standard input directory structure within the LRO MOC. The MOC and external elements will negotiate these details as part of future Operations Agreements.

2.2 LRO MOC OPERATIONAL SYSTEMS

The LRO orbiter monitoring and control functions of the GS are performed within the LRO MOC by the Mission Operations Team (MOT). The ITOS GS element typically performs its functions in real time during an LRO spacecraft ground contact and is located within the real-time portion of the MOC. The LRO GS architecture is depicted in Figure 2–4.

LRO mission planning, command load generation, trend analysis, and attitude determination functions of the GS also are performed within the LRO MOC by the LRO MOT. These elements perform their functions using data from prior spacecraft passes and other sources. The products of these elements may be used during a LRO spacecraft ground contact and are located within the offline portion of the MOC.

This set of GS elements that support both real-time and offline functionality are defined and identified in the following table:

Table 2-1 MOC Functional Component Information

Functional Element Component Provider Section Reference
Telemetry and Command ITOS GOTS – GSFC 584 Section 2.2.1
Mission Planning FlexPlan COTS – GMV Section 2.2.4
Trending and Analysis ITPS GOTS – GSFC 583 Section 2.2.6

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Functional Element Component Provider Section Reference
Data Processing System ITOS/DPS GOTS – GSFC 584 Section 2.2.2
Data Management System DMS GOTS – GSFC 584 Section 2.2.3
Monitoring and Alert System ATTENTION COTS – Attention SW, Inc Section 2.2.7
Attitude Ground System AGS GOTS – Code 595 Section 2.2.5

Figure 2-3 depicts a logical representation of the MOC architecture and provides the scope of what HW/SW elements are located within the MOC as well as the security boundary as noted by the routers and firewalls.

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Figure 2-3 LRO MOC Logical Architecture

2.2.1 ITOS-Supported Real-time Telemetry and Commanding

The real-time telemetry and command portion of ITOS receives virtual channel (VC) telemetry identified as VC0 and VC1. ITOS processes the engineering data and displays it to the MOT for monitoring the health and safety of the LRO spacecraft. ITOS processes the VC0 data and generates attitude data files for use by the AGS. ITOS archives engineering data files for later

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trending analysis by ITPS. ITOS performs the following real-time functions in support of the spacecraft health and safety:

  • Receive command files from FlexPlan

  • Performs real-time commanding using the received files from the FlexPlan

  • Transmits real-time data packets to instrument ground support equipment (IGSE) during L&EO

  • Transmits real-time packet data to the various science centers

  • Performs real-time commanding

  • Generates log files for spacecraft health and safety monitoring by Attention

  • Subsets the data packets into usable files for ingest by the ITPS

  • Provides a file (or files) of attitude data to the AGS component for use in the single board computer (SBC) attitude verification, to perform sensor calibrations, and to support other attitude maneuver functions

2.2.2 Data Processing System

ITOS provides the functionality of the Data Processing System (DPS); this is the primary interface to the station front end units for receiving and processing files transmitted using the Consultative Committee for Space Data Systems (CCSDS) File Delivery Protocol (CFDP). The DPS is responsible for ensuring a reliable transfer of data and that the data received on the ground is in the same format in which it was stored on the spacecraft.

There will be two active units, one at the station for high data rate capture and one at the MOC for low data rate capture and uplink of table and memory files. The system located within the LRO MOC is identified as the MOC Data Processing System (MDPS); the system resident at the White Sands station is referenced as the station DPS (SDPS). The station and MOC DPS are both setup and controlled by the ITOS system at the MOC and all commanding is coordinated and funneled through the ITOS for uplink to the spacecraft.

The WS1 DPS will provide temporary data storage and deliver data products to the Data Management System after processing is complete for a file. The WS1 DPS can receive the science data in any virtual channel (nominally it is commanded to be downlinked in either VC2 or VC3, but the spacecraft could be commanded to downlink the data in any VC), and performs data accountability. The MOC DPS nominally receives spacecraft housekeeping files on VC1; however, the spacecraft can be commanded to downlink science data in VC1 also. ITOS/DPS then distributes the data to the ITOS/DMS component for eventual transmission to the appropriate science team for further data analysis.

2.2.3 Data Management System

The DMS performs data file management for all mission products archived in the MOC, with the added functionality of marking products required for review with electronic signatures. The DMS system interfaces directly with all MOC systems and the storage array to accomplish all desired tasks. All product flows are the result of a DMS transaction and recorded in the DMS database.

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This component provides the data file archiving, data file dissemination, and provides a mechanism that can be used to track the delivery of data file products, which the LRO MOC transfers to the other LRO ground segment elements, such as the Ground Networks, the SOCs and the PDS. DMS receives the corresponding files from another source, such as FDF or the DPS components (for VC1, VC2, and VC3 data files) and performs data transfer and accountability to ensure that the files are delivered to the correct recipient and delivered error free.

2.2.4 Mission Planning System

FlexPlan was chosen as the mission planning system; it provides the short term daily planning and the long term projected planning for mission operations. FlexPlan receives science planning information from the science centers, maneuver planning data from FDF, and spacecraft health and safety commands from the operations team. The LRO mission planner uses the FlexPlan to generate and maintain daily planning activities as well as spacecraft command files that are forwarded to the ITOS for uplink to the spacecraft.

2.2.5 Attitude Ground System

The AGS provides the attitude determination validation and attitude sensor calibration; it is a COTS/GOTS system developed by the Flight Dynamics Branch at GSFC. It receives the onboard attitude quaternion data from the LRO spacecraft via DMS, performs sensor calibration, applies biases and misalignment information to the data, and validates the on-board calculated attitude solutions from the spacecraft.

The AGS creates the unified set of commanded attitude quaternion data that is associated with all orbiter off-nadir slews or for orbit-adjust maneuvers and momentum management requests.

2.2.6 Trending and Analysis System

The LRO Ground System and Operations team choose the Integrated Trending and Plotting System (ITPS) as the trending system; it provides the capability to ingest, store, analyze and display spacecraft health and safety data. ITPS will ingest and archive all mission housekeeping and engineering data to perform full data analysis and will also process the data to provide a reduced resolution data containing min/max/mean & standard deviation.

2.2.7 Monitoring and Alert System

The LRO Ground System and Operations team choose the Attention COTS product as the Monitoring and Alert System. This system is resident in the LRO MOC and it provides a comprehensive solution for spacecraft and ground system monitoring. The system interfaces with all MOC ground components, monitoring system events and software tasks. Upon recognizing anomalous events, the Monitor and Alert System initiates the pre-defined notification and reporting procedures to ensure that a proper response is received. The MAS ensures that data are accumulated to support the MOT in their research activities and to assists the MOT to correct the anomalous behavior. For spacecraft supports the monitoring system creates pass summaries to keep a record of all supports including commands sent; procedures executed, and specified event messages. The monitoring system compares entries in these pass log files against a predefined set of limits and checks. If an event or data value is flagged as a

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problem, the monitoring system issues a notification to one of a selected group of operations personnel of a spacecraft anomaly and providing an informative, textual message identifying the anomaly situation.

2.3 FLIGHT DYNAMICS FACILITY

The FDF provides the prime support for all orbit determination, generation of predictive and definitive orbital products, and generation of acquisition data. The FDF is located in Building 28 at GSFC.

During all phases of the LRO mission, the FDF receives the station-tracking data, which includes two-way Doppler tracking, laser ranging data, and ranging data. FDF determines the spacecraft orbit and generates predicted and definitive spacecraft ephemerides. The predicted ephemeris is used to provide acquisition data to all ground stations. FDF will supply the operations team with all mission planning aids. The laser ranging data will not be used for day-to-day navigation support of the mission. It will be used during post-processing (likely several months after real-time) to improve the orbital solutions at higher accuracy.

The FDF provides processing and control for all maneuvers and generates the trajectory maneuver commands for all mission phases.

2.4 MISSION OPERATIONS TEAM

The MOT personnel are responsible for managing the health and safety of the spacecraft following initial acquisition. They are the focal point of LRO GS operations during the life of the mission. In this capacity, they

  • Coordinate the various operational entities

  • Conduct operational tests with the spacecraft during the prelaunch phase

  • Conduct operational testing of the LRO MOC facility systems

  • Lead the GS operations efforts for the life of the mission

2.5 FLIGHT SOFTWARE MAINTENANCE FACILITY

The Flight Software and Maintenance Facility (FSMF) interfaces with the LRO program’s I&T GSE system. It is responsible for maintaining the onboard flight software (FSW) starting approximately 60 days after launch until the end of the mission.

2.6 LRO SPACE COMMUNICATIONS NETWORK

The LRO mission requires support from a variety of networks identified as the Space Communications Network (SCN):

  1. The Ka and S-Band antennas located at WS1 will provide the prime station support for the LRO mission. LRO uses the Solar Dynamics Observatory (SDO) backup antenna, which is collocated at the White Sands area. LRO will use the SDO/LRO STSS S-Band backup Station, as negotiated with SDO, in the event that there is an outage of the WS1 antenna.

  2. A second network will provide commercial S-band support for the LRO mission. The LRO mission contracted this support to the Universal Space Network (USN). The USN

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Network Management Center (NMC) is located in Horsham, Pennsylvania. For the LRO mission, USN uses two prime remote ground stations (RGSs) located at Dongara, Australia and Weilham, Germany. USN maintains two backup stations to support the LRO mission; these stations are located at South Point, Hawaii, and Kiruna, Sweden.

  1. The DSN, operated by the JPL located in Pasadena, California, maintains three stations at Goldstone, California; Madrid, Spain; and Canberra, Australia. DSN is designated for emergency/backup support for telemetry, tracking, and command interface during the initial acquisition, during any orbit maneuvers, or at any other times when a spacecraft emergency is identified.

  2. Laser Ranging facility, which is located in Greenbelt, Maryland, provides one-way laser time of flight data and supports, through the LOLA SOC, the development of an improved lunar gravity model. In support of using the Laser Ranging facility, the LRO MOC will provide some products to the Crustal Dynamics Data Information System (CDDIS); this facility acts as a clearing house to provide LRO data to potential other laser ranging sites around the world.

The Space Network (SN) will be used for launch support and for post separation coverage. The SN shall provide S-band (DG2 mode 2) telemetry and command services post separation through the first two hours of the mission.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

3.0 LRO GS EXTERNAL INTERFACE PRODUCT SYNOPSIS

This section provides a listing of all external products used by, generated by, or stored by the LRO MOC or other Ground Segment Elements, such as FDF to DSN interface products. Table 3-1 provides a comprehensive listing of all LRO external interfaces defined to date. This table reflects the product name, identifies who created the product and who uses the product, and provides a cross-reference to a DMR identifier to track where this interface product originates and who uses this interface product within their processing flow. It also provides a mapping to another document section in which a user can lookup more details regarding a product. As reference within this table and throughout this document, there may appear to be missing product identifiers. These Product IDs were deleted as a result of combining some products into a common format.

Table 3-1 LRO External Interface Products Cross Reference

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
1 CRaTER-1 LRO Operations Activity Request CRaTER Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
2 DLRE-1 LRO Operations Activity Request DLRE Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
3 DLRE-2 DLRE FSW Loads DLRE Section 4.3.3 DMR-51, DMR-52, DMR-573
4 DSN-1 DSN Tracking Data DSN Section 4.2.12 DMR-354, DMR-52,

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No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
5 DSN-2 DSN-3 Real-Time VC0 or VC1 telemetry data DSN Section 4.2.13 DMR-52, DMR-348, DMR-365
6 DSN-4 DSN Station Status Packets DSN Section 4.2.15 DMR-52, DMR-346, DMR-374
7 DSN-5 DSN-6 Archived VC0 or VC1Telemetry Data DSN Section 4.2.14 DMR-52, DMR-348
8 FDF-3 LRO Beta Angle Predict File FDF/OD Section 4.1.8 DMR-51, DMR-52, DMR-594
MOC/DMS
9 FDF-4 LRO Definitive Ephemeris File FDF/OD Section 4.1.9 DMR-52, DMR-595
10 FDF-5 DSN Predict-Grade SPK Data FDF/OD Section 4.1.3 DMR-596, DMR-325
11 FDF-41 DSN Long Term Scheduling Grade SPK Data FDF/OD Section 4.1.4 DMR-701

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No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
12 FDF-6 INP2 Station Acquisition Data FDF/OD Section 4.1.1 DMR-571, DMR-325
GNSO
13 FDF-10 OEM Station Acquisition Data FDF/OD Section 4.1.2 DMR-571, DMR-325
GNSO
14 FDF-7 Laser Ranging Site Prediction Data FDF/OD Section 4.1.5 DMR-52, DMR-597, DMR-625, DMR-650, DMR-653
DMS
15 FDF-8 Space Network Acquisition Data FDF/OD Section 4.1.6 DMR-641, DMR-325
16 FDF-9 Ground Station View Period Predicts FDF/OD Section 4.1.7 DMR-52, DMR-598
17 FDF-13 Lunar Orbit Ascending and Descending Node Predicts FDF/OD Section 4.1.12 DMR-52, DMR-599
MOC/DMS

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
18 FDF-14 Lunar Orbit Terminator Crossing Predicts FDF/OD Section 4.1.13 DMR-52, DMR-600
MOC/DMS
19 FDF-15 Mission Eclipse Predicts FDF/OD Section 4.1.14 DMR-52, DMR-601
MOC/DMS
20 FDF-16 Lunar Ephemeris FDF/OD Section 4.1.15 DMR-52, DMR-602
21 FDF-17 Orbiter Thruster Maneuver Plans FDF/Man Section 4.1.17 DMR-52, DMR-603
22 FDF-18 Post-Separation Report FDF/OD Section 4.1.19 DMR-52, DMR-606
23 FDF-19 Orbiter Post Maneuver Report FDF/Man Section 4.1.18 DMR-52, DMR-605
MOC/DMS
24 FDF-20 Predicted LRO Ephemeris File FDF/OD Section 4.1.20 DMR-52, DMR-607

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
25 FDF-21 Predicted Lunar Ground Track File FDF/OD Section 4.1.21 DMR-52, DMR-608
MOC/DMS
26 FDF-22 Definitive Lunar Ground Track File FDF/OD Section 4.1.22 DMR-52, DMR-680
MOC/DMS
27 FDF-23 Orbiter State Vector Table FDF/OD Section 4.1.16 DMR-52, DMR-613
28 FDF-25 Thruster Calibration Data FDF/Man Section 4.1.23 DMR-52, DMR-610
29 FDF-29 LRO Definitive SPICE SPK File FDF/OD Section 4.1.10 DMR-52, DMR-614
MOC/DMS
30 FDF-30 LRO Predictive SPICE SPK File FDF/OD Section 4.1.11 DMR-52, DMR-615
MOC/DMS
31 FDF-36 FDF Reprocessed SPICE Definitive Ephemeris Data SPK FDF Section 4.1.24 DMR-52, DMR-617
MOC/DMS

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
32 FDF-37 Solar Conjunction File FDF Section 4.1.25 DMR-52, DMR-685
MOC/DMS
33 FDF-38 Target Thruster Vector File FDF/Man Section 4.1.26 DMR-52, DMR-603
34 FDF-39 Laser Ranging Site View Period Predicts FDF/OD Section 4.1.27 DMR-52, DMR-699
DMS
35 FDF-40 Definitive GTDS Ephemeris FDF/OD Section 4.1.28 DMR-52, DMR-700
36 FDF-42 FDF Time Coefficients File FDF/OD Section 4.1.29 DMR-52, DMR-702
37 FDF-44 Trajectory Insertion Data FDF/OD Section 4.1.30 DMR-52, DMR-706
38 FDF-45 LRO Operations Activity Request FDF Section 4.1.31 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
39 GNSO-1 SCN Support Schedules WOTIS Section 4.2.1 DMR-5, DMR-52, DMR-308, DMR-649
DMS
40 WS1-1 WS1 Station Status Packets WS1 Section 4.2.7 DMR-52, DMR-316, DMR-320, DMR-374
41 WS1-2 WS1 Weather Data WS1 Section 4.2.8 DMR-52, DMR-574
MOC/DMS
42 WS1-3 WS1-4 Ka-Band telemetry WS1 Section 4.2.9 DMR-26, DMR-12, DMR-52, DMR-637, DMR-312, DMR-221
43 WS1-5 WS1 Raw Tracking Data WS1 Section 4.2.2 DMR-5, DMR-4, DMR-52, DMR-322
MOC/DMS
44 WS1-6 WS1-7 Real-time Orbiter telemetry WS1 Section 4.2.6 DMR-26, DMR-28, DMR-12, DMR-52, DMR-617, DMR-311
45 WS1-8 Ka-Band RF Receiver Data WS1 Section 4.2.10 DMR-5, DMR-52,

3-7

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TO VERIFY THAT THIS IS THE CORRECT VERSION PRIOR TO USE.

LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
46 WS1-10 Archived VC0 telemetry data WS1 Section 4.2.3 DMR-5, DMR-13, DMR-52, DMR-575
47 WS1-11 Archived VC1 telemetry data WS1 Section 4.2.4 DMR-5, DMR-13, DMR-52, DMR-575
48 WS1-12 WS1-13 Archived telemetry data File WS1 Section 4.2.5 DMR-5, DMR-13, DMR-52, DMR-575
49 WS1-14 WS1-16 Raw Telemetry File Data WS1/SDPS Section 4.2.11 DMR-52, DMR-227
50 USN-1 USN Station Status Packets USN Section 4.2.7 DMR-52, DMR-334, DMR-374
51 USN-2 USN Weather Data USN Section 4.2.8 DMR-5, DMR-52, DMR-574
MOC/DMS
52 USN-3 Raw Tracking Data Files USN Section 4.2.2 DMR-4, DMR-5, DMR-52, DMR-340
MOC/DMS
53 USN-4 USN-5 Real-time Orbiter telemetry USN Section 4.2.6 DMR-37, DMR-38, DMR-52, DMR-322

3-8

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
54 USN-6 Archived VC0 telemetry data USN Section 4.2.3 DMR-5, DMR-13, DMR-52, DMR-575
55 USN-7 Archived VC1 telemetry data USN Section 4.2.4 DMR-5, DMR-13, DMR-52, DMR-575
56 KSC-1 KSC2 Real-time Orbiter telemetry KSC Section 4.8.1 DMR-51, DMR-52, DMR-204
57 KSC-3 Archived VC0 telemetry data KSC Section 4.8.2 DMR-51, DMR-52, DMR-204
58 KSC-4 Archived VC1 telemetry data KSC Section 4.8.3 DMR-51, DMR-52, DMR-204
59 KSC-5 Archived VC2 telemetry data KSC Section 4.8.4 DMR-51, DMR-52, DMR-204
60 KSC-6 Archived VC3 telemetry data KSC Section 4.8.5 DMR-51, DMR-52, DMR-204
61 SN-1 Real-time VC0 Orbiter Telemetry SN Section 4.2.6 DMR-52, DMR-658

3-9

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
62 LAMP-1 LRO Operations Activity Request LAMP Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
63 LAMP-3 LAMP Instrument FSW Loads LAMP Section 4.3.3 DMR-52, DMR-573
64 LV-1 Launch Vehicle Post-Sep Vector LV, via KSC Launch Support Team Section 4.8.6 DMR-557. DMR-655
65 LEND-1 LRO Operations Activity Request LEND Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
66 LOLA-1 LRO Operations Activity Request LOLA Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
67 LOLA-2 LOLA Gravity Model LOLA Section 4.3.4 DMR-52
DMS
68 LOLA-3 LOLA Instrument FSW Loads LOLA Section 4.3.3 DMR-52, DMR-573

3-10

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
69 LOLA-4 LOLA Processed OD information LOLA Section 4.3.5 DMR-52
DMS
70 LOLA-5 LOLA Target Request LOLA Section 4.3.2 DMR-52, DMR-77
71 LOLA-6 LOLA Processed LR Data LOLA Section 4.3.6 DMR-51, DMR-52,
72 LOLA-7 Lunar Laser Retro-Reflector Events LOLA Section 4.3.7 DMR-51
73 LR-1 Laser Ranging Schedule LR (via LOLA SOC) Section 4.3.8 DMR-52, DMR-649
DMS
74 LROC-1 LRO Operations Activity Request LROC Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
75 LROC-2 LROC Instrument Initialization Command Sequence LROC Section 4.3.9 DMR-51, DMR-52, DMR-77

3-11

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
76 LROC-3 LROC Command Timeline LROC Section 4.3.10 DMR-51, DMR-52, DMR-77
77 LROC-4 LROC Target Request LROC Section 4.3.2 DMR-51, DMR-52, DMR-77
78 MIRF-1 LRO Operations Activity Request Mini-RF Section 4.3.1 DMR-51, DMR-52, DMR-218, DMR-77, DMR-573
79 MIRF-2 Mini-RF Load Files Mini-RF Section 4.3.3 DMR-51, DMR-52, DMR-573
80 MIRF-3 Mini-RF Command Timeline Mini-RF Section 4.3.11 DMR-51, DMR-52, DMR-77
81 MIRF-4 Mini-RF Target Requests Mini-RF Section 4.3.2 DMR-51, DMR-52, DMR-77
82 MOC-2 SPICE SCLK – Clock Correlation File MOC Section 4.5.2 DMR-51. DMR-670

3-12

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
83 MOC-3 CRaTER -Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
84 MOC-4 CRaTER HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
85 MOC-5 CRaTER Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261
86 MOC-6 CRaTER Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255, DMR-256, DMR-257
87 MOC-73 Archived CRaTER VC0 Telemetry File MOC/DMS Section 4.5.14 DMR-51
88 MOC-7 Daily Command Load Report MOC/DMS Section 4.5.1 DMR-51
89 MOC-62 RTS Command Load Report MOC/DMS Section 4.5.16 DMR-51

3-13

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
90 MOC-8 DLRE - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
91 MOC-9 DLRE HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
92 MOC-10 DLRE Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261
93 MOC-11 DLRE Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255, DMR-256, DMR-257
94 MOC-12 LAMP - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
95 MOC-13 LAMP HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
96 MOC-14 LAMP Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261

3-14

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
97 MOC-15 LAMP Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255
98 MOC-16 LEND - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
99 MOC-17 LEND HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
100 MOC-18 LEND Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261
101 MOC-19 LEND Real-time VC0 HK data MOC/DMS Section 4.5.13 DMR-51, DMR-392, DMR-255
102 MOC-20 LOLA - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
103 MOC-21 LOLA HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
104 MOC-22 LOLA Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261

3-15

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
105 MOC-23 LOLA Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255
106 MOC-24 LROC Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255, DMR-256, DMR-257
107 MOC-25 LROC - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254
108 MOC-26 LROC HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
109 MOC-27 LROC NAC Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261-
110 MOC-39 LROC WAC Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261
111 MOC-28 Mini-RF - Spacecraft HK Data File MOC/DMS Section 4.5.9 DMR-51, DMR-254

3-16

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
112 MOC-29 Mini-RF HK Data Files MOC/DMS Section 4.5.10 DMR-51, DMR-254, DMR-259
113 MOC-30 Mini-RF Operations Opportunity MOC Section 4.5.15 DMR-51
114 MOC-31 Mini-RF Raw Measurement Data Files MOC/DMS Section 4.5.11 DMR-51, DMR-254, DMR-259, DMR-261
115 MOC-32 Mini-RF Real-time VC0 HK data MOC/ITOS Section 4.5.13 DMR-51, DMR-392, DMR-255, DMR-256, DMR-257
116 MOC-33 SPICE Event Kernel MOC/DMS Section 4.5.3 DMR-51. DMR-699
117 MOC-34 MOC-36 Real-time Orbiter Commands (WS1, USN and SN) MOC/ITOS Section 4.6.1 DMR-51, DMR-30, DMR-40, DMR-319, DMR-337, DMR-640, DMR-663, DMR-300
118 MOC-35 DSN Real-Time orbiter commands MOC/ITOS Section 4.6.2 DMR-51, DMR-347, DMR-458, DMR-459

3-17

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
119 MOC-37 Commands to KSC MOC/ITOS Section 4.9.2 DMR-51
120 MOC-38 Telemetry to KSC MOC/ITOS Section 4.9.1 DMR-51, DMR-392
121 MOC-40 SPICE FK – Frame Kernels Multiple LRO Groups Section 4.5.4 DMR-51, DMR-621
122 MOC-41 SPICE Predicted CK (Predicted S/C Orientation) AGS Section 4.5.5 DMR-51. DMR-619
MOC/DMS
123 MOC-42 SPICE Definitive CK (Definitive S/C Orientation) AGS Section 4.5.6 DMR-51, DMR-620
MOC/DMS
124 MOC-43 SPICE Definitive HGA Orientation CK AGS Section 4.5.7 DMR-51, DMR-616, DMR-259
MOC/DMS
125 MOC-44 SPICE Definitive SA Orientation CK AGS Section 4.5.8 DMR-51, DMR-616, DMR-259
MOC/DMS

3-18

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
126 MOC-46 CRaTER HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
127 MOC-47 CRaTER Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
128 MOC-48 DLRE HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
129 MOC-49 DLRE Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
130 MOC-50 LAMP HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
131 MOC-51 LAMP Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
132 MOC-52 LEND HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259

3-19

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
133 MOC-53 LEND Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
134 MOC-54 LOLA HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
135 MOC-55 LOLA Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
136 MOC-56 LROC HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
137 MOC-57 LROC NAC Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
138 MOC-58 LROC WAC Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
139 MOC-59 Mini-RF HK Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259

3-20

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
140 MOC-60 Mini-RF Measurement Meta Summary Report DMS Section 4.5.12 DMR-51, DMR-688, DMR-259
141 MOC-63 Propulsion System Data DMS Section 4.10.1 DMR-51
142 MOC-64 Laser Ranging Go Flag DMS Section 4.11.1 DMR-625
143 MOC-65 Definitive Spacecraft Body Frame Attitude File AGS Section 4.10.2 DMR-51, DMR-703
DMS
144 MOC-66 Spacecraft HGA Motion File AGS Section 4.10.3 DMR-51, DMR-704
DMS
145 MOC-67 Spacecraft Solar Array Motion File AGS Section 4.10.4 DMR-51, DMR-705
DMS
146 MOC-68 OBC Generated Attitude Data File DMS Section 4.10.5 DMR-51

3-21

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
147 MOC-69 LRO Provided Separation Data AGS Section 4.9.3 DMR-51, DMR-709
DMS
148 MOC-71 Data Recorder Model Report MOC Section 4.5.17 DMR-51
149 MOC-72 LRO Propulsion Data MOC Section 4.10.6 DMR-51
150 MOC-74 Predictive LRO Spacecraft Body Attitude File MOC/AGS Section 4.10.7 DMR-51
DMS
151 FSWM-1 Orbiter FSW Load Files FSWM Section 4.4.1 DMR-51, DMR-52,
152 NAIF-1 SPICE Planetary SPK JPL/NAIF Section 4.7.1 DMR-51, DMR-52,
MOC/DMS
153 NAIF-2 SPICE LSK (Leap Second Kernel) JPL/NAIF Section 4.7.2 DMR-51, DMR-52,
MOC/DMS

3-22

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049 Revision – C

No. ID Product Name Source Destination(s) Section Reference DMR Reference
C R a T E R D L R E L A M P L E N D L O L A L R O C M i n i -R F K S C C D D I S M D P S M O C /D M S M O C /I T O S N A I F /P D S F D F D S N S C N S D P S S C N /G N S O U S N S N
154 NAIF-3 SPICE Generic PCK (Planetary JPL/NAIF Section 4.7.3 DMR-51, DMR-52,
Constants) MOC/DMS
155 NAIF-4 SPICE High Precision Lunar Orientation PCK JPL/NAIF Section 4.7.4 DMR-51, DMR-52,
MOC/DMS

3-23

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4.0 LRO GROUND SYSTEM EXTERNAL INTERFACES AND PRODUCT

The following sections provide specific information regarding each product as listed in Table 3

1. For each product, this ICD will provide the following details:

Product Details Detail Description
Time interval Step size within the file, if applicable. Such as: data point every minute, every 10 minutes
File duration Total time contained within the file or total number of days contained within the file
File or Data Generation Frequency How often is the file generated; daily, weekly, per pass
Delivery method (real-time, SCP, FTP, etc) Real-time TCP socket Real-time UDP socket File delivery with secure copy (SCP) Standard File Transfer Protocol (FTP)
Data Volume Total amount of data in either Kbytes, Mbytes, or GBytes)
Accuracy (if it applies) Accurate to second, degrees, Km, etc (could be NA)
Other pertinent details Provides additional details for the data product, if applicable; otherwise, set to NA

The LRO MOC supports 2 standard delivery protocols to support data delivery to/from the MOC. The LRO MOC uses a standard TCP/IP socket connection to support the transfer of real-time telemetry or commands or other real-time status information.

The USN and SN stations initiate the socket connection with the MOC’s telemetry and command system. The LRO MOC issues the socket connection to the various SOCs; the MOC’s telemetry distribution element will retry these connections a configurable number of times in the event of any dropped sockets.

4.1 FLIGHT DYNAMICS FACILITY PRODUCTS

This section provides the details of the products that the Flight Dynamics Facility creates to support the LRO mission. FDF creates these products on a regular basis to provide data for:

  • station acquisition data,

  • science operations center planning purposes,

  • attitude and maneuver planning

  • general reports to the Mission Operations Team

4-24

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For products destined to the MOC, FDF generates these products using a standard naming convention as defined by the following concepts of a file name and a file extension separated by the standard period (.):

<file name>.<file extension>; where

<file name> Î FDFnn_YYYYDDD_YYYYDDD_fnn; where

Table 4-1 FDF File Naming Convention

FDFnn => 5 ASCII characters in which the nn refers to the identifier listed as the LRO Ground System Product Matrix; for example FDF03 = LRO Beta Angle Predict File FDF14 = Lunar Orbit Terminator Crossing Predicts
Start Date of product YYYYDDD => 7 ASCII characters YYYY => 4 ASCII characters for the year (2008 – 2013) DDD => 3 ASCII characters for day of year designator (001 – 366); followed by the underscore (_) character
Stop Date of product YYYYDDD => 7 ASCII characters YYYY => 4 ASCII characters for the year (2008 – 2013) DDD => 3 ASCII characters for day of year designator (001 – 366); followed by the underscore (_) character
f => Flag to indicate if maneuvers are modeled or included within the product B => Maneuvers are modeled. For definitive products, all maneuvers are modeled. For predictive products, at least one future maneuver is modeled. N => No maneuvers are modeled. For predictive products, the propagation includes no spacecraft perturbations and represents the product as if no spacecraft maneuvers are performed within the time span of the product
nn => 2 ASCII Digits to represent the version number for the file.

The initial creation of a file will be represented by version number 01; a subsequent version is 02, 03, etc. The YYYYDDD designation identifies the start date and the end date for which data are contained within the file. FDF generates the products to start at 0000Z on the start date and end at 0000Z on the end date so that there is always an overlap between products in the event that FDF was down and could not generate a new product until the previous had completely expired. FDF generates a product that has a start time of 0000Z for the start date and actually ends at 0000Z. In the example of a 10 day product (e.g., SCN Station Acquisition Data – FDF-6), the duration is 10 complete days, but the product includes 0000Z for the eleventh day.

For example, the name for the LRO Beta Angle Predict File, based on these concepts, is identified as FDF03_2009015_2009194_N01.txt. This assumes that the first data point represents a starting time of 0000Z on January 15, 2009 and an end date of July 14, 2009 at 0000Z and it was the first generation of the file and that no maneuvers were modeled.

<file extension> Î 3-4 ASCII characters representing the type of file; e.g., txt, for a text file inp2 for the FDF generated SCN acquisition data product (version 2 of INP)

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bsp, for a binary SPICE (SPK) file bc, for a binary SPICE Attitude (CK) file NOTE: this naming convention does not apply to the FDF generated INP Acquisition data product. For that specific product, FDF generates unique files names base on the 4-character station identifier, as noted in Section 4.1.1.

This naming convention is the standard, except where a different naming convention is noted that based upon other required mission concepts. These special cases will be explicitly called out in the corresponding sections.

This section of the ICD captures the FDF product creation and delivery schedule for the LRO mission from the beginning of commissioning orbit to the end of the nominal mission. The FDFGS&O Operations Agreement (451-MOA-002960) documents the prelaunch, launch, and post launch products through the final Lunar Orbit Insertion maneuver. During this period of time, FDF will provide a subset of the nominal set of products needed to support LRO operations. Due to time constraints, these products do not have the same durations as specified below for the nominal mission.

4.1.1 (FDF-6) INP Station Acquisition Data

This product file contains acquisition information for the WS1, the SDO backup antenna, and the 2 USN owned ground station supporting the LRO telemetry and measurement data downlink or command uplink. FDF creates separate INP2 files that contain the station acquisition data for the specified station supporting the LRO mission.

When the WOTIS Scheduling Office receives the INP2 product, their systems automatically send the products to the corresponding WS1 or SDO backup antennas or to the USN sites.

4.1.1.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration 10 days of station acquisition data starting at 0000Z Wednesday for nominal deliveries Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Weekly, on Wednesday of the week, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FTP to WOTIS scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) WOTIS FTP-es the INP2 files to USN, WS1S, and STSS stations
Data Volume Variable; approximately 500 -700 Kbytes based on number of views per station and duration for each station view for each of the INP2 data file
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Acquisition data are consistent with the predicted ephemeris data based upon the most recent tracking information

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4.1.1.2 Format

FDF generates the INP2 product as an ASCII text file. The file contains the acquisition data for each contact for the station; FDF generates one file for each station that contains the acquisition data. The file will have 1:N lines of header information that identifies the file description information. This is followed by 1:N lines of station acquisition information. The standard fields and field description (for the 1:N lines of acquisition data) are listed in the following table. Data will be provided down to an identified station masking elevation angle.

Table 4-2 FDF – SCN Acquisition Data Description

Field name Field Characteristics
Strand name 43 ASCII text characters representing the facility/station name to satellite/0059 (LRO). The station name is represented by the 4 ASCII text characters representing the unique station identifier. The field appears as follows: Facility/NNNN to Satellite/0059/Sensor/Omni Where NNNN represents the 4 character ASCII station name and 0059 is the 4digit NASA SIC code for LRO. NNNN = WS1S for LRO White Sands S-band Station STSS for SDO S-Band backup Station USPS for USN Dongara, Australia USHS for USN South Point, Hawaii
Timetag information: year day of year and time of day YYYYDDD.HHMMSS (GMT) ; 14 ASCII digits with a period between the first 7 and last 6; where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) HHMMSS => 6 ASCII digits representing the hours, minutes, and seconds of day
Range RRRRRR.ddddd (Km) RRRRRR => 6 ASCII digits for whole range (0 – 999999)Note 1 ddddd => 5 ASCII digits for decimal portion of range (00000 – 99999)
Range rate RR.dddddd (Km/s) RR => 2 ASCII digits for whole range rate (0 – 99) Note 1 dddddd => 6 ASCII digits for decimal portion of range (000000 – 999999)
Azimuth angle AAA.ddd (Degree) AAA => 3 ASCII digits for whole angle measurement (0 – 360) ddd => 3 ASCII digits for decimal portion of range (000 – 999)
Elevation angle EEE.ddd (Degree) EEE => 3 ASCII digits for whole angle measurement (0 – 90) ddd =>3 ASCII digits for decimal portion of range (000 – 999)
Note 1 : Field is actually floating point and the value will vary in magnitude

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A sample file name for the first generation of this data file has the following convention: <File name>_<Start Date>_<Stop Date>_<Maneuver Model Flag><version number>.<file extension>

where File Name = [10 Characters], which includes an underscore character (_); the following field definitions are used to define the fields
Station Identifier =>5 total ASCII Characters
4 ASCII Characters used to represent the stations supporting the LRO mission; followed by a 1 character underscore; see Table 4-2 above for the list of the 4 character station IDs
Spacecraft Identifier = > 5 total ASCII Characters 4 ASCII Digits used to identify the spacecraft = 0059; followed by a 1 ASCII character (_)
Start Date = [8 ASCII Digits] used to represent the start date associated with the first station acquisition; in the form of: YYYYDDD; followed by a 1 character underscore
Stop Date = [8 ASCII Digits] used to represent the start date associated with the first station acquisition; in the form of: yyyyddd; followed by a 1 character underscore
Maneuver Model Flag = [1 characters] One ASCII character that indicates whether maneuvers were modeled for this product
B => Maneuvers are modeled
N => No maneuvers are modeled
version number = [2 characters] Two ASCII character version number. The initial version is 01, next is 02 … up to 99.
file extension = [4characters] inp2 to represent the second format version of the (Internet Predict) INP data product

For example, a sample file name for the acquisition data (INP2 product version) corresponding to the WS1 Dual Ka/S Band station (for the 10 day duration of Thursday, January 15, 2009 at 0000Z through Sunday, January 25, 2009 at 0000Z would have the following file name convention: WS1S_0059_2009015_2009022_N01.inp2

An INP-2 sample station acquisition data product is provided as a reference in Appendix B, Figure B.1-1.

4.1.2 (FDF-10) OEM Station Acquisition Data

For the USN collaborative sites, FDF generates an acquisition data product using a standard CCSDS format identified as an Orbital Ephemeris Message (OEM) Data Product. FDF generates this product based on an “earth-centered” reference frame.

When the WOTIS Scheduling Office receives the OEM product, their systems automatically send the products to the corresponding USN sites.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.1.2.1 Product Details
Time interval Data samples provided at 1 minute increments
File duration 10 days of station acquisition data starting at 0000Z Wednesday for nominal deliveries Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Weekly, on Wednesday of the week, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FDF FTP-es to WOTIS WOTIS FTP-es the OEM file to USN scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 1.5 MBytes for an OEM data file
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Acquisition data are consistent with the predicted ephemeris data based upon the most recent tracking information EME2000 is the reference frame

4.1.2.2 Format

The OEM Data product format is defined within the CCSDS Blue Book CCSDS 502.0-B-1, Orbit Data Messages, September 2004; Section 4 of that document defines the specific details for the OEM format, content and structure. As such, no format definitions are listed within this document.

FDF will generate the OEM data product as an earth-centered vector. This file corresponds to the standard FDF-generated file name, so no additional details are required to document the file name concept.

A sample file name for the first generation of this data file has the following convention:

<File name>_<Maneuver Model Flag><version number>.<file extension> A sample file name for the OEM acquisition data for the 10 day duration of Thursday, January 15, 2009 at 0000Z through Sunday, January 25, 2009 at 0000Z would have the following file name convention: FDF10_2009015_2009025_N01.oem

An OEM sample station acquisition data product is provided as a reference in Appendix B, Figure B.1-2.

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4.1.3 (FDF-5) DSN Predict-Grade SPK Data

The DSN “Predict-Grade” site acquisition data describes the FDF-generated information necessary to allow the DSN 34-meter subnet to acquire the LRO spacecraft; this is the SPICE data that DSN uses to schedule the 34-m subnet antennas to support LRO contacts. This is the standard file that DSN uses to support nominal LRO operational activities, which include any emergency or routine/backup operations and monthly maneuvers.

The FDF-GS&O Operations Agreement (451-MOA-002960) documents the prelaunch, launch, and post launch products through the final Lunar Orbit Insertion maneuver and identifies any products that FDF is required to deliver to DSN.

FDF generates the DSN SPICE SPK prediction data that the DSN stations use as pointing information to track LRO and ensure data acquisition.

4.1.3.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration 10 days of station acquisition data starting on at 0000Z Wednesday for nominal deliveries Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Weekly, on Wednesday of the week, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FDF accesses the DSN Deep Space Mission System (DSMS) Service Preparation System (SPS) web- portal and posts the data file and associated meta data
Data Volume Approx 6 Mbytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Acquisition data are consistent with the predicted ephemeris data based upon the most recent tracking information DSN requires user authentication to access the SPS web site.

4.1.3.2 Format

The format is the predicted SPICE SPK Transfer Format file; this format is consistent with the information listed at the following URL:

https://spsweb.fltops.jpl.nasa.gov

The file name conforms to the standard DSN-generated file name specifications and not the FDF concept as originally noted above. The file naming convention is defined as follows:

<File name>.<file extension>;

There is a period (.) used as the standard separator between the file name and file extension. The file name confirms to the following convention:

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<Spacecraft Designator>_<SPK type>_<Duration>_<Start Date>_<version #>; the underscore (_) character is used as the separator between the file name qualifiers.

The table below provides the definitions for the file name and file extension qualifiers:

where Spacecraft Designator = [3 ASCII Digits]; defaults to 085 for LRO Designation
SPK Type = [8 ASCII Characters]; default to the following SPK type: baseline
Duration = [5 ASCII Characters/Digits] in the form of nnday; where nn = the file duration qualifier (01 – 99), followed by 3 ASCII character “day”
Start Date = [8 ASCII Digits] in the form of yyyymmdd; where yyyy = 4 ASCII digits for start year (2008 – 2013) mm – 2 ASCII digits for start month (01 – 12) dd = 2 ASCII digits for start day (01 -31)
Version # = [2 ASCII Digits]; 01 to 99
File Extension = 3 ASCII Characters]; defaults to xsp to represent the SPK Transfer Format Type

.

For example, a sample file name for the SPICE file (for the 10 day duration during the nominal mission phase of Thursday, January 15, 2009 at 0000Z) would have the following file name convention: 085_baseline_10day_20090115_01.xsp

Another reference for SPICE SPK data formats is:

http://naif.jpl.nasa.gov/naif

The SPICE ID for LRO is 125 (octal) or -85 (decimal). The SPK file will be type 13 with order of interpolation equal to 3. Since this product is a binary file, no sample product is listed in Appendix B.

4.1.4 (FDF-41) DSN Long-Term Scheduling Grade SPK Data

To maintain DSN mission readiness, FDF will provide a long-term “Scheduling-Grade” SPK Product to assist DSN in load planning and analysis efforts. The DSN Long-Term Scheduling Grade SPK Product has 6-month duration with no implied accuracy after the first 28 days since FDF does not model any maneuvers after the first 28-days. FDF generates this file using a numerical integration with a more accurately known and representable force model for the first 28 days. After that 28-day period, FDF still generates the file using a numerical integration technique, except that the force model is not as accurate.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.1.4.1 Product Details
Time interval Data samples provided at 10 minute increments
File duration 6 months days of station acquisition data starting at 0000Z Thursday for nominal deliveries
File or Data Generation Frequency Monthly, on the first Wednesday of the week, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FDF accesses the DSN Deep Space Mission System (DSMS) Service Preparation System (SPS) web- portal and posts the data file and associated meta data
Data Volume Approx 11 MBytes
Accuracy (if it applies) Same accuracy as for the FDF05 product within the first 28 days No implied accuracy after the first 28 days
Other pertinent details DSN requires user authentication to access the SPS web site.

4.1.4.2 Format

The format is the predicted SPICE SPK Transfer Format file; this format is consistent with the information listed at the following URL:

https://spsweb.fltops.jpl.nasa.gov

The file name conforms to the standard DSN-generated file name specifications and not the FDF concept as originally noted above. This file has the following conventions.

<File name>_<version number>.<file extension>

where File Name = [29 Characters], which includes the field delimiters of either an underscore

character (_); the following field definitions are used to define the fields

File Qualifier => 13 ASCII characters

3 ASCII Digits (followed by underscore), followed by 9 ASCII

characters

= 085_baseline for LRO baseline SPICE Transfer SPK

Duration => 6 ASCII Digits and Characters

= nnnday; where nnn = number of days within the file; followed by the

underscore (_) character.

Start Date => 8 ASCII Digits/Characters in the form of:

YYYYDDD; 7ASCII Digits used to represent the start date

associated with the first station acquisition; followed by a 1 character

underscore (_) character

version number = [2 characters] Two ASCII character version number. The initial version is 01, next is 02 … up to 99.

file extension = [3characters] .xsp, for the SPICE transfer format.

For example, a sample file name for the SPICE file (for the 180 day duration of Thursday, January 15, 2009 at 0000Z) would have the following file name convention: 085_baseline_180day_YYYYDDD_01.xsp

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This file is only the nominal trajectory and not the plus/minus 3-sigma

Another reference for SPICE SPK data formats is:

http://naif.jpl.nasa.gov/naif

The SPICE ID for LRO is 125 (octal) or -85 (decimal). The SPK file will be type 13 with order of interpolation equal to 3. Since this product is a binary file, no sample product is listed in Appendix B.

4.1.5 (FDF-7) Laser Ranging Site Prediction Data

The laser ranging site prediction data describes the FDF-generated information used by the laser ranging site; it provides detailed information to point the laser accurately to the spacecraft and to put the laser pulses in the LOLA earth range window. This information provides times, position vectors, and other necessary information to allow the laser ranging site to locate the LRO spacecraft and begin the laser ranging functions.

4.1.5.1 Product Details

Time interval Receiver position vector data samples provided at 1 minute increments
File duration 10 days of Laser Site Prediction data starting 0000Z of the current day for normal updates Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FDF delivers product via the FDPC (MOC performs the scp pull) MOC scp pushes to the LOLA SOC; who then forwards the file to the CDDIS repository
Data Volume Approximately 1.2 MBytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Acquisition data are consistent with the predicted ephemeris data based upon the most recent tracking information. This predictive compares are not applicable across spacecraft maneuvers

4.1.5.2 Format

The laser ranging site acquisition data format provides the required information for a laser ranging site to be able to perform laser ranging activities to the LRO spacecraft. The LRO Laser Ranging Prediction information is the LRO position vector (in meters) at the signal receive time computed based on a transmission from the geocenter, rotated to the International Terrestrial Reference Frame (ITRF) at the signal transmit time, and timetagged at the signal transmit time. This record is repeated at 1 minute intervals. The format is the Consolidated Laser Prediction Format, Version 1.02. It consists of the following header and data record fields:

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Table 4-3 FDF – Laser Ranging Prediction Data Description

Field name Field Characteristics
Header type 1 Many of these fields are standard, such as the record type (H1), CPF, format version, year, month, day, hour of ephemeris production. The ephemeris source will be “FDF”. The target name representing LRO is TBD from the laser group, although “LRO” is suggested. The notes field will contain comments.
Header type 2 Many of these fields are standard, such as IDs. The SIC ID for LRO is “0059”. The target type will be “TBD”. The other IDs will be assigned at successful separation from the launch vehicle.
Header type 3 Not supplied.
Header type 4 Not supplied.
Header type 5 Not supplied.
Header type 9 End of header trailer, will be supplied.
Record type 10-1 Receiver position vector (X, Y, Z) in meters at the signal receive time computed based on a transmission from the geocenter, rotated to the ITRF frame at the signal transmit time, and timetagged at the signal transmit time. This record is repeated at 1 minute intervals for the duration of the ephemeris prediction period.
Records type 99 Ephemeris trailer record.

This file does not conform to the FDF-standard file name conventions; it conforms to the CDDIS-identified standard file name concepts. The following table identifies the convention used for this file:

<Sat-ID>_<File Type>_<Start Date>_<version number>.<file source>

where Sat-ID = [3 ASCII Characters], which identifies the spacecraft; default to lro (all lowercase) File Type = File Format => 3 ASCII Characters default to cpf (all lowercase)

Start Date = [6 ASCII Digits]; in the form of YYMMDD; where YY = 2 digits of year (08 – 13) MM = 2 digits for the month (01 – 12) DD = 2 digits for the day (01 – 31)

version number = [4 ASCII Digits], in the form of nnnv, which identifies the ephemeris version number and the version within a day. nnn = day of year + 500 to distinguish CPFs from TIVs in time bias and other messages. The .500. can be dropped when TIVs are discontinued. This field is three digits with zero leading fill and v = one ASCII digit for version number, the initial version is 1

file source = [3characters] .fdf, that indicates that this is an FDF generated file.

A sample file name (for the 10 day duration of Thursday, January 15, 2009 at 0000Z through Sunday, January 25, 2009 at 0000Z) and corresponding for the first generation of this data file is given as lro_cpf_090125_5251.fdf

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A sample Laser Ranging Site Prediction Data file is provided as a reference in Appendix B, Figure B.1-3.

4.1.6 (FDF-8) Space Network Acquisition Data

This product file contains the LRO spacecraft acquisition data for the Space Network’s TDRSS support during the launch and early orbit phase prior to ground station contacts.

4.1.6.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Approximately 24 hours of data for the launch day
File or Data Generation Frequency Delivered L-3 days and for any launch delays over 1 day
Delivery method (real-time, SCP, FTP, etc) FDF delivers product to the WSC TDRSS Scheduling Office
Data Volume FDF delivers IIRVs as independent vectors and as such, the data volume aspect is NA
Accuracy (if it applies) best available for launch predict
Other pertinent details FDF will provide the SN Acquisition Data only for the L&EO mission phase or for pre-launch tests with SN SN support will be less than several hours in duration

.

4.1.6.2 Format

The SN acquisition data are formatted as an Improved InterRange Vector (IIRV) file in accordance with the STDN 724.

This product is generated on an as-needed basis to support either the mission tests/rehearsals or for the L&EO mission phase. The product contains approximately 2 hour of acquisition data for the TDRSS contact to support the L&EO mission phase (though it is likely that 24 hours of acquisition data will be sent).

The IIRV character layout is shown for reference in the following table.

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Table 4-4 FDF – IIRV TTY SN Acquisition Data Description

Line Character Explanation
1 ----Optional text message.
2 GIIRV A rrrr Start of message (fixed). A Alphabetic character indicating originator of message: ASCII space = GSFC Z = WLP E = ETR L = JPL, W = WTR J = JSC, P = PMR A = CSTC, K = KMR C = CNES rrrr Destination routing indicator. Specifies the site for which the message was generated. If for more than one station, this field should contain "MANY."
3 V S 1 C Sic (4 chars) bb nnn doy hhmmsssss ccc Vector type: 1 = Free flight (routine on-orbit), 2 = Forced (special orbit update) 3 = Spare, 4 = Maneuver ignition, 5 = Maneuver cutoff 6 = Reentry, 7 = Powered flight, 8 = Stationary, 9 = Spare S = Source of data: 1 = Nominal/planning, 2 = Real-time, 3 = Off-line, 4 = Off-line/mean NOTE: Nominal/planning sets cannot be sent to White Sands Ground Terminal (WSGT) from the NCC. 1 Fixed one (1) C = Coordinate system: 1 = Geocentric True-of-Date Rotating 2 = Geocentric mean of 1950.0 (B1950.0). 3 = Heliocentric B1950.0. 4 = Reserved for JPL use (non-GSFC). 5 = Reserved for JPL use (non-GSFC). 6 = Geocentric mean of 2000.0 (J2000.0). 7 = Heliocentric J2000.0. sic (4 chars) SIC bb Body number/VID (01-99). nnn Counter incremented for each vector in a set of vector data on a per-station per-transmission basis. doy Day of year (001 = January 1). hhmmsssss Vector epoch in UTC with resolution to nearest millisecond. (The implied decimal point is three places from the right). ccc Checksum of the decimal equivalent of the preceding characters on Line 3: 0 through 9 = face value.; Minus (-) = 1; ASCII Space = 0.
4 S xxxxxxxxxx yyyyyyyyyy zzzzzzzzzz ccc s Sign character: ASCII Space = positive or Minus sign = negative xxxxxxxxxxxx = X component of position (meters) yyyyyyyyyyyy = Y component of position (meters) zzzzzzzzzzzz = Z component of position (meters) ccc Checksum of the decimal equivalent of the preceding characters on Line 4: 0 through 9 = face value.; Minus (-) = 1; ASCII Space = 0.

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Line Character Explanation
5 S xxxxxxxxxx yyyyyyyyyy zzzzzzzzzz ccc s Sign character (same as above) xxxxxxxxxxxx · = X-component of velocity yyyyyyyyyyyy ·= Y-component of velocity zzzzzzzzzzzz ·= Z-component of velocity NOTE: All velocity components are in meters/second with resolution to the nearest millimeter/second. The implied decimal point is three places from the right. ccc Checksum of the decimal equivalent of the preceding characters on Line 5: 0 through 9 = face value.; Minus (-) = 1; ASCII Space = 0.
6 mmmmmmmmmm aaaaa kkkk S rrrrrr ccc Mass of spacecraft in kilograms with resolution to 1/10 of a kilogram. The implied decimal point is one place from the right. Contains all zeros when not used. Average spacecraft cross-sectional area in square meters with resolution to the nearest hundredth of a square meter. The implied decimal point is two places from the right. Contains all zeros when not used. Dimensionless drag coefficient. The implied decimal point is two places from the right. Contains all zeros when not used. Sign character for coefficient of solar reflectivity ASCII Space = positive or Minus Sign = negative Dimensionless Solar Reflectivity coefficient. The implied decimal point is six places from the right. Contains all zeros when not used. Checksum of the decimal equivalent of the preceding characters on Line 6: 0 through 9 = face value.; Minus (-) = 1; ASCII Space = 0.
7 oooo ITERM End of message (fixed) Originator routing indicator

FDF delivers the IIRVs as independent vectors to the Data Services Management Center (DSMC) at White Sands using conventional FDF transmission protocols and not in a file concept; as such, there is no file naming convention to document.

Appendix B, Figure B.1-4 provides a sample IIRV as a reference.

4.1.7 (FDF-9) Ground Station View Period Predicts File

The Ground Station View Period Predict file contains specific data associated with the High Gain antenna and the data associated with the omni antenna.

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FDF uses the different station elevation mask information to identify different station views for the Ka-Band antenna as compared for the S-Band antenna. FDF uses a 20 degree station mask for the Ka-Band and a 5 degree minimum elevation mask for the S-band antenna.

FDF uses a DSN masking of six (6) degrees for a horizon mask. FDF will generate actual station masking files as they receive the masking data from each of the sites.

4.1.7.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration 28 days starting at 0000 Hours on Thursday Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Delivered weekly, on Wednesday by noon-time Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) FDF initiates ftp to the WOTIS to transfer file scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Variable; approximately 500 -700 Kbytes based on number of views per station and duration for each station view
Accuracy (if it applies) The file contents should have accuracy over the 84-hours prediction, of less than 800 m in along-track error.
Other pertinent details Station elevation masking information is unique for each station Contains both HGA and Omni views for each available station

4.1.7.2 Format

This file contains the data associated with view periods for all supporting ground stations used to provide LRO with Tracking, Telemetry, & Command (TT&C) support during the various mission phases. It consists of the station identifier and the view period information for that station based on a fixed minimum elevation angle of 5 degrees.

The general format of this file consists of the following information:

1:N Header lines that provide the Station Name and date that FDF generated the file, and header lines that provide the field description; the file then contains N lines of data for each station view period.

The N lines of data contain the following fields:

Start Time Stop Time Duration Start Pass # Max Elev. Degrees Maximum Elevation Time; where these fields are defined in the following table:

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Table 4-5 FDF – Ground Station View Period Data Description

Field name Field Characteristics
Station name 42 – 43 ASCII text characters representing the unique station identifier, with the following format: Facility-NNNN-To-Satellite-0059-Sensor-TTTT; where NNNN = WS1S for LRO White Sands S-band Station WS1K for White Sands Ka-Band Station STSS for SDO backup STSK for the SDO backup Ka-Band USPS for USN Dongara USHS for USN South Point, Hawaii KU1S (or KU2S) for Kiruna, Sweden WU1S (or WU2S) for Wilheim, Germany DS24 for the DSN 34-m at Goldstone, Ca DS27 for the High-Speed Beam Wave Guide site at Goldstone, Ca, DS34 for the DSN-34m at Canberra, Australia D34K for the DSN 34m Ka-Band site at Canberra, Australia DS45 for the High-Efficiency site at Canberra, Australia DS54 for the DSN 34-m at Madrid, Spain DS65 for the High- Efficiency site at Madrid, Spain and TTTT can either be referenced as: Omni – for the S-Band Omni View HGA – for the High Gain Antenna S- or Ka-Band View.
Start time information: YYYYDDD.HHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Stop time information: YYYYDDD.HHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Station View Duration (in SSSSS.mmm (9 ASCII digits), where
seconds) SSSSS => 5 ASCII characters representing the whole seconds; followed by a period(.) mmm => 3 ASCII characters for the milliseconds of station contact
Pass Number 7 ASCII characters representing a monotonically increasing Orbit Number (1 to 9999999) NOTE: This field is only valid after lunar insertion; this field should be ignored prior to LOI
Max elevation angle EE.ddd EE => 2 ASCII digits for whole angle measurement (0 – 90) dd => 3 ASCII digits for decimal portion of range (000 – 999)

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Field name Field Characteristics
Time of Maximum Elevation YYYYDDD.HHMMSS, where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.) HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day

There will be certain instances in which the FDF-generated view period product does not contain valid view period information for a specific station because of the orbital geometry. In that event, FDF uses a different format that discussed in Table 4-5. In this event, the FDF-generated information conforms to the following format, as noted in Table 4-6

Table 4-6 FDF – Ground Station No View Period Data Description

Field name Field Characteristics
Station name 42 – 43 ASCII text characters representing the unique station identifier, with the following format: Facility-NNNN-To-Satellite-0059-Sensor-TTTT; where NNNN = WS1S for LRO White Sands S-band Station WS1K for White Sands Ka-Band Station STSS for SDO backup STSK for the SDO backup Ka-Band USPS for USN Dongara USHS for USN South Point, Hawaii KU1S (or KU2S) for Kiruna, Sweden WU1S (or WU2S) for Wilheim, Germany DS24 for the DSN 34-m at Goldstone, Ca DS27 for the High-Speed Beam Wave Guide site at Goldstone, Ca, DS34 for the DSN-34m at Canberra, Australia D34K for the DSN 34m Ka-Band site at Canberra, Australia DS45 for the High-Efficiency site at Canberra, Australia DS54 for the DSN 34-m at Madrid, Spain DS65 for the High- Efficiency site at Madrid, Spain and TTTT can either be referenced as: Omni – for the S-Band Omni View HGA – for the High Gain Antenna S- or Ka-Band View.
No Data Found Descriptor 3 lines (Carriage returns terminate each line); the first 2 lines are blank lines the Third line has 15 ASCII Characters to indicate No Access Found

A sample file name for the first generation of the View Period data file is given as FDF9_ 2009015_2009043_N01.txt.

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A sample Ground Station View Period Predict Data file is provided as a reference in Appendix B, Figure B.1-5. This sample product shows both instances that indicate view period data and no view period data for a station.

4.1.8 (FDF-3) LRO Beta Angle Predict File

The LRO Beta Angle Predict File provides the angle information between the LRO lunar orbit plane and the sun with the following definition. When the sun is in the orbit plane, this results in a zero degree (0°) angle. If the sun and orbit plane are perpendicular to each other; then this results in a beta angle of ninety degrees (90°). In this specific instance, the LRO spacecraft is in continuous full sun.

4.1.8.1 Product Details

Time interval Data samples provided at 6 hour increments
File duration 6 months, starts on the Wednesday at 0000Z Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Monthly, on the first Wednesday of the month, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approx 24 Kbytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available. No implied accuracy after the first 28 day predict
Other pertinent details This product is consistent with the predicted ephemeris data based upon the most recent tracking information This file is generated using a 3-body after a 28 day interval

FDF will generate this file for all post-LOI mission phases.

4.1.8.2 Format

The LRO Beta Angle Predict file is an ASCII-formatted file in which the fields are space delimited; the number of spaces between each data field is variable. The file contains the time of the sample, the Beta angle information (given in degrees and hundredths of degree) and the sun quadrant information that provides information as to whether the angle is increasing or decreasing. A positive Beta Angle correlates to the spacecraft oriented to a positive orbit normal reference frame. FDF does not guarantee any inherent accuracy for this data product after the first 28 days since it does not model any other maneuvers. FDF performs a numerical integration within the first 28 days of the data product; after the first 28 days of the files, FDF uses a 3-body point mass to model the predictions;

The file contains the time, beta angle, and quadrant information; the following table provides a brief description of each field:

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Table 4-7 FDF – LRO Beta Angle Data Description

Field name Field Characteristics
Time information: year day of year and time of day YYYYDDD.HHMMSS. (GMT) 14 total ASCII Characters with a period between the first 7 and last six; where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) HHMMSS => 6 ASCII digits (hours, minutes, and seconds of day)
Beta Angle SBB.bb => (degrees) 6 total ASCII characters with a period between the first 3 and last 2 the first character is a sign value (positive or negative angles) a Blank = Positive Orbit Normal reference - = Negative Orbit Normal reference the next 2 are the whole decimal degrees of the beta angle last 2 are the decimal portion of the Beta angle
Quadrant N => 1 ASCII character that identifies the quadrant information related to the Beta Angle definition. Allowable values are: 1 – 4 inclusive

A sample file name for the first generation of this data file is given as FDF03_2009015_2009195_N01.txt

A sample LRO Beta Angle File data file is provided as a reference in Appendix B, Figure B.1-6.

4.1.9 (FDF-4) LRO Definitive Ephemeris File

The LRO Definitive Ephemeris file contains the LRO spacecraft’s position and velocity information in an inertial, mean J2000 coordinate reference frame. The coordinate frame will be Earth-centered for pre-LOI mission phases and moon-centered for post-LOI mission phases.

4.1.9.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Previous 24 hours (day basis) from 0000Z to 0000Z
File or Data Generation Frequency Delivered daily by noon-time, Eastern
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approx 1200 Kbytes
Accuracy (if it applies) Accurate to 500 meters
Other pertinent details Ephemeris data are consistent with the predicted ephemeris data based upon the most recent tracking information

4.1.9.2 Format

The Definitive Ephemeris file is an ASCII-formatted file in which the fields are space delimited; the number of spaces between each data field is variable. The file contains the time of the sample, the X,Y, Z position information (given in Kilometers, or Km) and the X, Y, and Z

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velocity components (given in Kilometers per second, or Km/sec). The file entries are generated at one minute increments. The following table provides a brief description of each field:

Table 4-8 FDF – LRO Definitive Ephemeris Data Description

Field name Field Characteristics
Time information: year day of year and time of day YYYYDDD.HHMMSS (GMT), 14 total ASCII Characters with a period between the first 7 and last six; where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) HHMMSS => 6 ASCII digits (hours, minutes, and seconds of day)
X-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 first signed 6 are the whole portions of the X-component of LRO’s position* last 6 are the decimal portion of the X-component position
Y-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 first signed 6 are the whole portions of the Y-component of LRO’s position* last 6 are the decimal portion of the Y-component position
Z-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 first signed 6 are the whole portions of the Z-component of LRO’s position* last 6 are the decimal portion of the Z-component position
X-Velocity SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 6 are the whole portions of the X-component of the LRO’s velocity* last 6 are the decimal portion of the X-component velocity
Y-Velocity SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 2 are the whole portions of the Y-component of the LRO’s velocity* last 6 are the decimal portion of the Y-component velocity
Z-Velocity (Km/s) SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 2 are the whole portions of the Z-component of the LRO’s velocity* last 6 are the decimal portion of the Z-component velocity
* - Field is actually a floating value so the value will vary significantly over the course of the mission.

A sample file name for the first generation of this data file is given as FDF04_2009015_2009022_N01.txt

A sample LRO Definitive Ephemeris File data file is provided as a reference in Appendix B, Figure B.1-7.

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4.1.10 (FDF-29) LRO Definitive SPICE SPK File

This file contains the SPICE “kernel” information for the definitive LRO spacecraft ephemeris data. This kernel file contains the definitive LRO spacecraft position and velocity information for the previous day based only on the received S-Band tracking data. This product will be Earth-centered J2000 and Moon-centered J2000 following LOI (or as needed).

4.1.10.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Previous 24 hours (day basis) from 0000Z to 0000Z
File or Data Generation Frequency Delivered daily by noon-time, Eastern
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approx .08 Mbytes
Accuracy (if it applies) Accurate to less than 500 meters
Other pertinent details Pre-LOI product is Earth-centered J2000 Post LOI product is Moon-centered J2000

4.1.10.2 Format

The Definitive Spice file is a binary SPICE file and will require the use of the SPICE Toolkit, which can be accessed from the Navigation and Ancillary Information Facility (NAIF) web site. This web site is located at the following URL: http://naif.jpl.nasa.gov/naif/index.html

For example, a sample file name for the first generation of this data file for the previous day of January 8, 2009 is fdf29_2009008_2009009_n01.bsp (binary SPICE format).

The SPICE ID for LRO will be -85, as assigned by JPL.

The SPK file will be type 13 and interpolation order 11; since this is a binary file, no sample product is provided in Appendix B.

4.1.11 (FDF-30) LRO Predictive SPICE SPK File

This file contains the SPICE “kernel” information for the predictive LRO spacecraft ephemeris data. This kernel file contains the LRO spacecraft positions and velocity information based upon the processed tracking data. This file will contain the LRO Predictive ephemeris data; FDF can model any upcoming LRO station keeping maneuvers that are to occur in within this 28 day time period.

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4.1.11.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Contains 28 days starting on 0000Z of the current day for nominal deliveries Pre-LOI phase only contains a time span for pre-LOI (approx 4-5 days) Post-LOI phase contains the remainder of the 28 day duration Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approx 2 Mbytes
Accuracy (if it applies) Over the 84-hours prediction, of less than 800 m in along-track error. Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details The SPICE ID for LRO is -85, as assigned by JPL. The SPK file will be type 13 and interpolation order 11;

4.1.11.2 Format

This product will be Earth-centered J2000 and Moon-centered J2000 following LOI (or as needed). The Predictive Spice file is a binary SPICE file and will require the use of the SPICE Toolkit, which can be accessed from the Navigation and Ancillary Information Facility (NAIF) web site. This web site is located at the following URL: http://naif.jpl.nasa.gov/naif/index.html

The SPICE ID for LRO is 125 (octal) or -85 (decimal). The SPK file will be type 13 with order of interpolation equal to 3.

A sample file name for the first generation of this data file is given as FDF30_2009015_2009043_N01.bsp for a binary file.

Since this is a binary formatted file, no sample product will be shown in Appendix B.

4.1.12 (FDF-13) Lunar Orbit Ascending and Descending Node Predicts

This file contains the lunar-nodal crossing predicts associated when the LRO orbit either crosses the ascending node or the descending node.

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4.1.12.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Next 7 days starting at 0000Z of the current day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approximately 9 KBytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Only created for post-LOI mission phases

4.1.12.2 Format

This is a file that contains 1-week’s worth of nodal crossing predicts. The file is an ASCII text file in which the fields are separated by standard white space characters. The file contains 1:n lines of file header information followed by the nodal crossing time, the nodal crossing type, and the corresponding lunar longitude, and the orbit number; these fields are separated by tabs. The following table provides a brief description of each field:

Table 4-9 FDF – LRO Ascending Descending Node Data Description

Field name Field Characteristics
timetag information: year day of year and time of day YYYYDDD.HHMMSS (GMT), where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding a period HHMMSS => 6 ASCII digits representing hours, minutes and seconds of day
Node Crossing Type 1 Character ASCII flag to indicate if the type of nodal crossing A => Ascending Node Crossing Type D => Descending Node Crossing Type
Lunar Longitude AAA.dd (degrees, East Longitude) AAA => 3 ASCII digits for whole angle measurement (0 – 360) dd => 2 ASCII digits for decimal portion of longitude angle (00 – 99) The lunar longitude is consistent with the DE421 coordinate system
Lunar Orbit 5 ASCII Characters to represent a monotonically increasing orbit number from 1 .. 99999. Orbit number increments at ascending node crossing beginning at lunar insertion NOTE1: The orbit number is only provided at the Ascending Node Crossing time

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Field name Field Characteristics
Lighting Condition 3-5 ASCII Characters that identify the lighting conditions, such as = Day – LRO is in a daylight (sun lit) condition = Night – LRO is in a nighttime (not sun lit) condition

A sample file name for the first generation of this data file is given as FDF13_2009015_2009022_N01.txt

FDF will generate this product on a daily basis or after a maneuver has occurred. The product will contain 7 days of data.

A sample LRO Ascending Descending Node data product is provided as a reference in Appendix B, Figure B.1-8.

4.1.13 (FDF-14) Lunar Orbit Terminator Crossing Predicts

This is a file that contains lunar terminator crossing predicts associated when the LRO spacecraft crosses the lunar terminator line.

4.1.13.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Next 7 days starting at 0000Z of the current day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approximately 7 KBytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Only created for post-LOI mission phases

.

4.1.13.2 Format

This is a file that contains 1-week’s worth of lunar terminator crossing predicts. The file is an ASCII text file in which the fields are separated by standard white space characters. The file contains the actual terminator crossing time and the corresponding terminator type; the following table provides a brief description of each data field:

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Table 4-10 FDF – LRO Lunar Orbit Terminator Crossing Predicts Data Description

Field name Field Characteristics
time information: year day of year and time of day YYYYDDD.HHMMSS (GMT), where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding a period HHMMSS => 6 ASCII digits representing hours, minutes and seconds of day
Lunar Terminator Type 1 Character ASCII flag to indicate if the type of terminator crossing N => Into Lunar night (going from Lunar day into night) D => Into Lunar day (going from Lunar night into day )

A sample file name for the first generation of this data file is given as FDF14_2009015_2009022_N01.txt.

FDF will generate this product on a daily basis or after a maneuver has occurred. The product will contain 7 days of data.

A sample LRO Lunar Terminator Crossing data product is provided as a reference in Appendix B, Figure B.1-9.

4.1.14 (FDF-15) Mission Eclipse Predicts

This file contains the predictive information associated when the LRO spacecraft is put into a shadow resulting from either a lunar or Earth caused eclipse.

4.1.14.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Next 90 days starting at 0000Z on the Wednesday delivery day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Weekly on Wednesday, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approximately 470 KBytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details 3-body propagation after 28 days

4.1.14.2 Format

FDF generates this file as an ASCII-formatted file in which the fields are separated by standard white space characters. The format for this file can consist of 1:N lines that identify the mission eclipses that result in both a partial eclipse (LRO is flying in the penumbra shadow) and a full eclipse (LRO is flying in the umbra shadow). The umbra is always a subset of the penumbra phase and as such the start/stop times and durations will be contained within the penumbra. The

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usual configuration is that a penumbra is followed immediately by an umbra then a penumbra as LRO enters, transits, and exits the eclipse. The file has the following field information: Start Time, Stop Time, Shadow Flag, Duration, and Occultation Flag, and Total Duration; these fields are defined in the following table:

Table 4-11 FDF – LRO Mission Eclipse Data Description

Field name Field Characteristics
Start time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
Stop time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
Current Condition Penumbra or Umbra
Duration of Current Condition SSSSS.MM (seconds) SSSSS => 5 ASCII digits for whole portion of seconds (0 – 99999) MM => 2 ASCII digits for decimal portion of seconds (00 – 99)
Occultation Occulting Body Earth or Moon
Total Duration Total duration of penumbra and umbra on current orbit (seconds) SSSSS.MM SSSSS => 5 ASCII digits for whole portion of seconds (0 – 99999) MM => 2 ASCII digits for decimal portion of seconds (00 – 99)

A sample file name for the first generation of this data file is given as FDF15_2009015_2009104_N01.txt.

A sample LRO Mission Eclipse data product is provided as a reference in Appendix B, Figure B.1-10.

4.1.15 (FDF-16) Lunar Ephemeris

This file contains the Lunar Ephemeris, which is used to update the on-board attitude/orbit flight software tables used by the Attitude Control System (ACS) FSW.

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4.1.15.1 Product Details

Time interval Data samples provided at 10 minute increments
File duration Next 10 days beginning the current day
File or Data Generation Frequency Daily, by noon-time, Eastern
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 177 KBytes
Accuracy (if it applies) Lunar position data are accurate to 100 meters.
Other pertinent details The lunar ephemeris vectors will be in the Earth Centered Inertial (ECI) reference frame for all mission phases

4.1.15.2 Format

The format for this file is an ASCII Formatted file in which the fields are separated by standard white space characters. The file contains multiple lines that provide the ephemeris information for the moon’s position and velocity. The file consists of the following field: Time, X- Position, Y- Position, Z- Position, X-Velocity, Y- Velocity, and Z- Velocity; where the fields are defined in the following table

Table 4-12 FDF – Lunar Ephemeris Data Description

Field name Field Characteristics
Time information: year day of year and time of day YYYYDDD.HHMMSS (GMT), 14 total ASCII Characters with a period between the first 7 and last six; where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) HHMMSS => 6 ASCII digits (hours, minutes, and seconds of day)
X-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 Sign plus the first 6 are the whole portions of the X-component of moon’s position* last 6 are the decimal portion of the X-component position
Y-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 Sign plus the first 6 are the whole portions of the X-component of moon’s position* last 6 are the decimal portion of the Y-component position
Z-Position SRRRRRR.rrrrrr (Km) => 14 ASCII characters including the period between the first 6 and last 6 Sign plus the first 6 are the whole portions of the X-component of moon’s position* last 6 are the decimal portion of the Z-component position

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Field name Field Characteristics
X-Velocity SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 6 are the whole portions of the X-component of the LRO’s velocity* last 6 are the decimal portion of the X-component velocity
Y-Velocity SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 2 are the whole portions of the Y-component of the LRO’s velocity* last 6 are the decimal portion of the Y-component velocity
Z-Velocity (Km/s) SRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 3 and last 6 first signed 2 are the whole portions of the Z-component of the LRO’s velocity* last 6 are the decimal portion of the Z-component velocity
* - Field is actually a floating value so the value will vary significantly over the course of the mission.

A sample file name for the first generation of this data file is given as FDF16_2009015_2009024_N01.txt.

A sample of the Lunar Ephemeris data product is provided as a reference in Appendix B, Figure B.1-11.

4.1.16 (FDF-23) Orbiter State Vector Table

The LRO State Vector Table provides the predicted set of OD state information for the LRO spacecraft for the upcoming referenced time period, nominally 1-weeks of predicted OD state information. These data are used by the on-board computer to update its attitude flight SW system.

4.1.16.1 Product Details

Time interval Data samples provided at 10 minute increments
File duration Next 10 days starting the current day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 177 KBytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details The product must be Earth Centered Inertial for all mission phases

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4.1.16.2 Format

The file is an ASCII formatted file that provides the State Vector data file in which the fields are space delimited; the number of spaces between each data field is variable. The table is a multiline file that contains both meta-data and state vector data. The meta-data corresponds to when the report was generated, the start and stop times and other information related to the state vector generation. The file contains a reference time, and x-, y-, and z-position data and the corresponding x-, y-, and z-velocity data. The LRO position information is given in Kilometers (or Km), the LRO velocity components given in Kilometers per second, or Km/sec). The file entries are time centered every 10 minutes. The following table provides a brief description of each field:

Table 4-13 FDF – LRO State Vector Table Data Description

Field name Field Characteristics
time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
X-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period first signed 6 are the whole number of X-position vector information (0- 999999) * last 6 are the degree decimal of the X-position (000000- 999999)
Y-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period first signed 6 are the whole degrees of Y-position vector information (0999999)* last 6 are the degree decimal of the Y-position (000000- 999999)
Z-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period first signed 6 are the whole degrees of Z-position vector information (0999999)* last 6 are the degree decimal of the Z-Position (000000- 999999)
X-Velocity SRRRRRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 6 and last 6 first signed 6 are the whole portions of the X-component of the LRO’s velocity* last 6 are the decimal portion of the X-component velocity
Y-Velocity SRRRRRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 6 and last 3 first signed 6 are the whole portions of the Y-component of the LRO’s velocity* last 6 are the decimal portion of the Y-component velocity
Z-Velocity SRRRRRR.rrrrrr (km/sec) => 10 ASCII characters including the period between the first 6 and last 3 first signed 6 are the whole portions of the Z-component of the LRO’s velocity* last 6 are the decimal portion of the Z-component velocity
* - Value is actually floating point and will vary in length due to mission phase

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A sample file name for the first generation of this data file is given as FDF23_2009015_2009024_N01.txt

A sample LRO State Vector Table is provided as a reference in Appendix B, Figure B.1-19.

4.1.17 (FDF-17) Orbiter Thruster Maneuver Plans

This file contains the data information for the upcoming LRO maneuver related to the required start thruster firing time, the thruster sequence, initial attitude, stop thruster firing time. This MOC uses this file to create the commands that are uploaded to the spacecraft that identify the proposed maneuver configuration – duration, thruster setup, start/stop times, just to name some of the data required to define the LRO maneuver.

4.1.17.1 Product Details

Time interval NA
File duration NA; covers the time interval associated with the set of planned maneuvers
File or Data Generation Frequency Varies based on type of maneuver; data generation frequency is listed in the FDF-GS&O Operations Agreement (451-MOA-002960)
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 5 Kbyte
Accuracy (if it applies) The data accuracy is best-estimated since this is a predicted maneuver plan
Other pertinent details Product is only applicable for upcoming maneuver

4.1.17.2 Format

This product consists of one file detailing the parameters required to characterize any LRO thruster maneuver.. The file is a multi-line ASCII file that provides the maneuver metadata, which includes the file creation time and the start and stop of the maneuver, the anticipated pre- and post-burn fuel used and spacecraft mass, the planned delta-V, duration, and planned fuel mass, and the maneuver configuration. The header data also contains other file references, such as the Orbiter Ephemeris and thruster plan data files, that the FD maneuver team used to create this Maneuver Plan.

The following figure provides an example of the fields within this “header area”:

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The file then provides 15 lines for each of the planned initial thruster data and the planned final thruster data. Because this is the maneuver plan, the repeating group associated with the initial thruster data and the final thruster data have the identical values for the records.

The following figure provides the details related to the initial thruster configuration and expected performance.

The same 15 lines are repeated to identify the final thruster data. As note above, since this is the “planned” maneuver data, the initial and final data records and values are identical.

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Each group of data consists of these entries, as defined by the following table:

Figure 4-3 FDF Maneuver Plan Final Thruster Data Concept

Field name Field Characteristics
Thruster Bank Data 4 ASCII Characters/Digits (separated by blanks) in the form of NT1 1 or NT2 2 ATn 1 or ATn 2; where n = 1 through 8 inclusive
Bank Data 1 ASCII Digits to identify which thruster bank is used for this maneuver; values are either 1 or 2
Pressure (Pa) 13 ASCII Digits in the form of: PPPP.pppppppp, which corresponds to the whole and decimal portion for the tank pressure
Temperature (C) 11 ASCII Digits in the form of: TT.tttttttt, which corresponds to the whole and decimal portion for the tank temperature
Calculated ISP (sec) 12 ASCII Digits in the form of: NNN.nnnnnnnn, which corresponds to the whole and decimal portion for the maneuver thruster impulse
Calculated Thrust (N) 10-11 ASCII Digits in the form of: NN.nnnnnnnn, which corresponds to the whole and decimal portion for the thrust for each thruster bank
Thrust Efficiency (unitless) 10 ASCII Digits in the form of: N.nnnnnnnn, which corresponds to the whole and decimal portion for the thrust for each thruster bank (100 percent = 1.0000000
Effective Thrust (N) 10-11 ASCII Digits in the form of: NN.nnnnnnnn, which corresponds to the whole and decimal portion for the thrust for each thruster bank For this product, both the calculated thrust and the effective thrust are equal since this is the anticipated results of the maneuver
Duty Cycle (%) 10-12 ASCII Digits in the form of: NNN.nnnnnnnn, which corresponds to the whole and decimal portion for the duty cycle required by each thruster (max value is 100.00000000)

This file does not conform to the FDF-standard file name conventions. The following table identifies the convention used for this file: <File Name Qualifier>_<Maneuver Type>_<Start Date>_<Stop Date>_<version number>.<file extension>

where File Name = [5 Characters], for file designator character followed by underscore Qualifier (_) character; e.g., FDF17_

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Maneuver Type = [4-5 Characters] for the type of planned maneuver in the form of MCCn – Mid-course correction maneuver #n or
LOIn – Lunar Orbit Insertion maneuver #n
MOIn – Mission Orbit Insertion maneuver #n
SKnna – Station keeping maneuver #nn [either “a“ or “b” as each station keeping maneuver will consist of 2 parts], for example SK01a, SK01b,
Additionally, the “n” for the MCC, LOI, MOI can have the suffix of “E” to represent that this is an engineering pre-burn to test the thrusters prior to the official maneuver
Start Date = [8 characters] Eight ASCII digit for the start date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for start year DDD = 3 ASCII Digits for start day of year; followed by the underscore (_) character
Stop Date = [8 characters] Eight ASCII digit for the stop date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for stop year DDD = 3 ASCII Digits for stop day of year; followed by the underscore (_) character
version number = [2 characters] Two ASCII digits for version number. The initial version is 01, next is 02 … up to 99; followed by the period (.)
file extension or source = [3characters] .txt, that indicates that this is a textual file that FDF generated.

A sample file name for the first generation of the Orbiter Thruster Maneuver Plan file that corresponds to the first Lunar Orbit Insertion maneuver is given as FDF17_LOI1_2008307_2008308_01.txt

A sample of the Orbiter Thruster Maneuver Plan product is provided as a reference in Appendix B, Figure B.1-12.

4.1.18 (FDF-19) Orbiter Post Maneuver Report

This file contains the data generated to show a comparison of the predicted and actual performance and provides a calculation of the fuel used and an estimate of the remaining fuel available. FDF generates this report after the completion of each thruster maneuver.

This report provides a reconstruction at how well the spacecraft executed the maneuver. However, FDF may not have all available/required tracking data needed to create orbit solutions or have all of the available maneuver-related telemetry when FDF creates this report.

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4.1.18.1 Product Details

Time interval NA
File duration NA
File or Data Generation Frequency At the completion of each identified thruster maneuver within best available time; data generation frequency is listed in the FDF-GS&O Operations Agreement (451-MOA-002960)
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC scp pushes the file to the LOLA SOC
Data Volume Approximately 5 Kbyte
Accuracy (if it applies) The data accuracy is best-estimated since this maneuver plan report may be generated without the complete set of required products or the most up-to-date products
Other pertinent details Product is only applicable after maneuvers

4.1.18.2 Format

The report is an ASCII formatted file in which the fields are space delimited; the number of spaces between each data field is variable. The report provides the thruster profile and compares the planned versus actual thruster information, the fuel used and the remaining on-board fuel, and the estimated and actual spacecraft mass following the thruster maneuver.

This file contains the exact same information as defined for the FDF-17 (Thruster Maneuver Plan) as listed in 4.1.17.2. However, for this data product, the report provides the actual spacecraft and thruster data associated with the completion of the maneuver as well as the original, planned maneuver spacecraft and thruster maneuver data.

Since the data format is identical to the FDF-17 product, the format is not repeated.

This file does not conform to the FDF-standard file name conventions. The following table identifies the convention used for this file: <File Name Qualifier>_<Maneuver Type>_<Start Date>_<Stop Date>_<version number>.<file extension>

where File Name = [5 Characters], for file designator character followed by underscore Qualifier (_) character; e.g., FDF19_

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Maneuver Type = [4-5 Characters] for the type of planned maneuver in the form of MCCn – Mid-course correction maneuver #n
LOIn – Lunar Orbit Insertion maneuver #n
MOIn – Mission Orbit Insertion maneuver #n
SKnna – Station keeping maneuver #nn [either “a“ or “b” as each station keeping maneuver will consist of 2 parts], for example SK01a, SK01b,
Additionally, the “n” for the MCC, LOI, MOI can have the suffix of “E” to represent that this is an engineering pre-burn to test the thrusters prior to the official maneuver
Start Date = [8 characters] Eight ASCII digit for the start date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for start year DDD = 3 ASCII Digits for start day of year; followed by the underscore (_) character
Stop Date = [8 characters] Eight ASCII digit for the stop date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for stop year DDD = 3 ASCII Digits for stop day of year; followed by the underscore (_) character
version number = [2 characters] Two ASCII digits for version number. The initial version is 01, next is 02 … up to 99; followed by the period (.)
file extension or source = [3characters] .txt, that indicates that this is a textual file that FDF generated.

A sample file name for the first generation of the Orbiter Post-Maneuver Report file that corresponds to a Lunar Orbit Insertion maneuver is given as FDF19_LOI1_2008307_2008308_01.txt

A sample of the Orbiter Post Maneuver Report product is provided as a reference in Appendix B, Figure B.1-13.

4.1.19 (FDF-18) Post Separation Report

This report provides a comparison of the launch separation vector that the launch vehicle support team reports against the launch separation vector that FDF calculates based on the updated launch information.

The report compares the time-slipped nominal separation vector (or if available the FDF-determined separation vector from inertial guidance telemetry or radar data) versus the EELV-vendor supplied actual separation vector.

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4.1.19.1 Product Details

Time interval NA
File duration NA
File or Data Generation Frequency Best effort immediately following the launch vehicle separation With nominal (within 3 sigma separation), report is created within 1 hour
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 1 KBytes
Accuracy (if it applies) The accuracy will be to the best available from the data
Other pertinent details Product is only applicable after Orbiter separation from launch vehicle

4.1.19.2 Format

The report is an ASCII formatted file in which the fields are space delimited; the number of spaces between each data field is variable. The report fields provide the comparison between the reported launch vehicle separation vector and the FDF-calculated launch vehicle separation vector (updated to reflect the actual launch epoch). The report is a multi-line file, which contains the two original vectors (and their magnitudes) and then the position and velocity magnitudes of the differences. This information is identified in the following table:

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Table 4-14 FDF – LRO Post Separation Report Data Description Information

Report Section Data Fields
Section 1 Epoch and Vectors of Actual Separation State X (km) Y (km) Z (km) DX (km/sec) DY (km/sec) DZ (km/sec) SMA (km) ECC INC (deg) RAAN (deg) AP (deg) TA (deg)
Section 2 Epoch and Vectors of Nominal Separation State X (km) Y (km) Z (km) DX (km/sec) DY (km/sec) DZ (km/sec) SMA (km) ECC INC (deg) RAAN (deg) AP (deg) TA (deg)
Section 3 Comparison fields Date/Time Range 1 (km) Range 2 (km) Radial (km) Cross-track (km) Along-Track (km) Total Delta-R (km) True Anomaly (deg)
Section 4 Summary of Comparisons Minimum Position Differences by Component and Total Maximum Position Differences by Component and Total Minimum Velocity Differences by Component and Total Maximum Velocity Differences by Component and Total Position RMS by Component and Total Velocity RMS by Component and Total

A sample file name for the first generation of this data file (for a launch date of 28 October 2008) is given as FDF18_2008302_2008302_B01.txt

A sample of the Post Separation Report product is provided as a reference in Appendix B, Figure B.1-15.

4.1.20 (FDF-20) Predicted LRO Ephemeris File

This file contains predictive LRO ephemeris data for the spacecraft position and velocity information centered at one minute increments. The file is generated in an inertial, mean Earth-Centered J2000 coordinate reference frame. This file is only used internally by the MOC-AGS element

4.1.20.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Next 10 days starting on the current day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approx 1.7 Mbytes

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Accuracy (if it applies) accuracy over the 84-hours prediction, of less than 800 m in along-track error. Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Product is always Earth-centered J2000 and only used by AGS element

4.1.20.2 Format

The Predictive LRO Ephemeris file is an ASCII-formatted file in which the fields are space delimited; the number of spaces between each data field is variable. The file contains the time of the sample, the X,Y, Z position information (given in Kilometers, or Km) and the X, Y, and Z velocity components (given in Kilometers per second, or Km/sec). The file entries are generated at five minute increments. The following table provides a brief description of each field:

Table 4-15 FDF – LRO Predictive Ephemeris Data Description Information

Field name Field Characteristics
time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
X-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period Signed first 6 whole portions of the X-component of LRO’s position* last 6 are the decimal portion of the X-component position
Y-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period Signed first 6 are the whole portions of the Y-component of the LRO’s position* last 6 are the decimal portion of the Y-component position
Z-Position SRRRRRR.rrrrrr (km) => 14 ASCII characters including the period Signed first 6 are the whole portions of the Z-component of the LRO’s position* last 6 are the decimal portion of the Z-component position
X-Velocity SRRRRRR.rrrrrr (km/sec) => 14 ASCII characters including the period Signed first 6 are the whole portions of the X-component of the LRO’s velocity* last 6 are the decimal portion of the X-component velocity
Y-Velocity SRRRRRR.rrrrrr (km/sec) => 14 ASCII characters including the period Signed first 6 are the whole portions of the Y-component of the LRO’s velocity * last 3 are the decimal portion of the Y-component velocity
Z-Velocity SRRRRRR.rrrrrr (km/sec) => 14 ASCII characters including the period Signed first 6 are the whole portions of the Z-component of the LRO’s velocity* last 6 are the decimal portion of the Z-component velocity
* - Signed whole number is floating point and could be from 1 to 7 characters for LRO

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A sample file name for the first generation of this data file is given as FDF20_2009015_2009022_N01.txt

A sample Predictive LRO Ephemeris File data file is provided as a reference in Appendix B, Figure B.1-16.

4.1.21 (FDF-21) Predicted Lunar Ground Track File

This file contains the predictive LRO ground track against the lunar surface. The Predicted Lunar Ground Track provided this information in the principal axis (PA) reference frame.

4.1.21.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Next 7 days starting on the current day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approx 887 Kbytes
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Generated for post-LOI mission phases only

4.1.21.2 Format

The Predictive Lunar Ground Track file is an ASCII-formatted file in which the fields are separated by spaces. The file contains the time of the sample, the lunar Longitude and Latitude position, the LRO altitude, and ground track velocity every 60 seconds. The longitude and latitude information is based on the DE421 reference frame. The LRO altitude is given in Kilometers (Km), the LRO ground track velocity magnitude given in Kilometers per second, (Km/sec). The file entries are generated at one minute increments. The following table provides a brief description of each field:

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Table 4-16 FDF – LRO Predicted Ephemeris Data Description Information

Field name Field Characteristics
Time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
Lunar Longitude RRR.rrr (degrees) => 7 ASCII characters including the period between the first 3 and last 3 first 3 are the whole degrees of Longitude East (0- 360) last 3 are the degree decimal of Longitude (000-999)
Lunar Latitude SRR.rrr (degrees) => 6 ASCII characters including the period between the first 3 and last 3 first character is the sign (blank = Northern Lats; - = Southern Lats) next 2 are the whole degrees of Latitude (0- 90) last 3 are the degree decimal of Latitude (000- 999)
LRO Altitude RRR.rrr (km) => 7 ASCII characters including the period between the first 3 and last 3 first 3 are the whole portions of the LRO’s altitude in floating point (expected values for LRO are 000 – 999 km) last 3 are the decimal portion of the LRO’s altitude (in hundredths of Km, 000 – 999)
Ground Track-Velocity Magnitude SRRRRRR.rrr (km/sec) => 10 ASCII characters including the period between the first 6 and last 3 first 6 are the whole portions of the X-component of the LRO’s velocity (floating point value, expected value for LRO is single digit) last 3 are the decimal portion of the X-component velocity

A sample file name for the first generation of this data file is given as FDF21_2009015_2009022_N01.txt

A sample LRO Predictive Lunar Ground Track File is provided as a reference in Appendix B, Figure B.1-17.

4.1.22 (FDF-22) Definitive Lunar Ground Track File

This file contains the definitive LRO ground track against the lunar surface based on the most recent definitive ephemeris. The Definitive Lunar Ground Track file provides this information in the PA reference frame.

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4.1.22.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Previous 24 hours 0000Z previous day to 0000Z current day
File or Data Generation Frequency Daily, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approx 127 Kbytes
Accuracy (if it applies) Data accuracy is within 500 meters over the def product timespan
Other pertinent details Generated for post-LOI mission phases only

4.1.22.2 Format

The Definitive Lunar Ground Track file is an ASCII-formatted file in which the fields are separated by standard white space characters. The file contains the time of the sample, the lunar Longitude and Latitude position, the LRO altitude, and ground track velocity every 60 seconds. The longitude and latitude information is based on the DE421 reference frame. The LRO altitude is given in Kilometers (Km), the LRO ground track velocity magnitude given in Kilometers per second, (Km/sec). The file entries are generated at one minute increments. The following table provides a brief description of each field:

Table 4-17 FDF – LRO Definitive Lunar Ground Track Description Information

Field name Field Characteristics
time information: year day of year and time of day YYYYDDD.HHMMSS (GMT) where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366) preceding period. HHMMSS => 6 ASCII digits representing hours, minutes, and seconds of day
Lunar Longitude RRR.rrr (degrees) => 7 ASCII characters including the period between the first 3 and last 3 first 3 are the whole degrees of Longitude East (0- 360) last 3 are the degree decimal of Longitude (000-999)
Lunar Latitude SRR.rrr (degrees) => 7 ASCII characters including the period between the first 3 and last 3 first character is the sign (blank = Northern Lats; - = Southern Lats) next 2 are the whole degrees of Latitude (0- 90) last 3 are the degree decimal of Latitude (000- 999)

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LRO Altitude RRR.rrr (km) => 7 ASCII characters including the period between the first 3 and last 3 first 3 are the whole portions of the LRO’s altitude in floating point (in Km, 000 – 999) last 3 are the decimal portion of the LRO’s altitude (in hundredths of Km, 000 – 999)
Ground Track Velocity Magnitude SRRRRRR.rrr (km/sec) => 11 ASCII characters including the period between the first 6 and last 3 first signed 6 are the whole portions of the X-component of the LRO’s velocity in floating point (value will typically be 1.6) last 3 are the decimal portion of the X-component velocity

A sample file name for the first generation of this data file is given as FDF22_2009014_2009015_N01.txt

A sample Definitive Lunar Ground Track File is provided as a reference in Appendix B, Figure B.1-18.

4.1.23 (FDF-25) Thruster Calibration Data

This is a report that includes updated parameters for the thruster calibration based on all available information received about past maneuvers. This is an informational report that provides the Post-Maneuver Calibration. It provides the final assessment of how well the maneuver was executed and it uses best pre-maneuver and post-maneuver orbit solutions, and telemetry (pressures, duty cycles, & attitude) to determine a thrust scale factor that can be used to plan future maneuvers (as long as they use the same thruster set NT x AT).

4.1.23.1 Product Details

Time interval NA
File duration NA
File or Data Generation Frequency At the completion of each identified thruster maneuver; data generation frequency is listed in the FDF-GS&O Operations Agreement (451-MOA-002960)
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approximately 5 Kbyte
Accuracy (if it applies) NA
Other pertinent details NA

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4.1.23.2 Format

This file contains identical types of information as defined for the FDF-17 (Thruster Maneuver Plan) and the FDF-19 (Orbiter Post Maneuver Report) and follows the similar format as noted for those products. The format and content are listed in Section 4.1.17.2. However, for this data product, the report provides the actual spacecraft and thruster data associated with the completion of the maneuver as well as the original, planned maneuver spacecraft and thruster maneuver data. Since the data format is identical to the FDF-17 product, the format is not repeated. This file does not conform to the FDF-standard file name conventions. The following table identifies the convention used for this file:

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<File Name Qualifier>_<Maneuver Type>_<Start Date>_<Stop Date>_<version number>.<file extension>

where File Name Qualifier = [5 Characters], for file designator character followed by underscore (_) character; e.g., FDF25_
Maneuver Type = [4-5 Characters] for the type of planned maneuver in the form of MCCn – Mid-course correction maneuver #n
LOIn – Lunar Orbit Insertion maneuver #n
MOIn – Mission Orbit Insertion maneuver #n
SKnna – Station keeping maneuver #nn [either “a“ or “b” as each station keeping maneuver will consist of 2 parts], for example SK01a, SK01b,
Additionally, the “n” for the MCC, LOI, MOI can have the suffix of “E” to represent that this is an engineering pre-burn to test the thrusters prior to the official maneuver
Start Date = [8 characters] Eight ASCII digit for the start date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for start year DDD = 3 ASCII Digits for start day of year; followed by the underscore (_) character
Stop Date = [8 characters] Eight ASCII digit for the stop date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for stop year DDD = 3 ASCII Digits for stop day of year; followed by the underscore (_) character
version number = [2 characters] Two ASCII digits for version number. The initial version is 01, next is 02 … up to 99; followed by the period (.)
file extension or source = [3characters] .txt, that indicates that this is a textual file that FDF generated.

A sample file name for the first generation of the Thruster Calibration Data file that corresponds to the first Mission Orbit Insertion maneuver is given as FDF25_MOI1_2009015_2009016_01.txt

A sample Thruster Calibration Data File is provided as a reference in Appendix B, Figure B.1-20

4.1.24 (FDF-36) FDF Reprocessed SPICE Definitive Ephemeris Data SPK

The FDF Reprocessed SPICE Definitive ephemeris data SPK file provides the LRO ephemeris based upon a DE421 reference frame. FDF creates this product using the LRO OD reprocessing

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results which will include both laser tracking measurements and LOLA OD and Improved gravity model products.

This reprocessed SPICE transfer format SPK file is based upon both S-band and laser tracking. Since FDF generates a 55-hour solution arcs for the LRO orbit determination (with 7-hr overlap periods), ephemeris data will be generated in 48-hr non-contiguous segments. This product will only be generated in post-processing using the laser data, not for day-to-day navigation support of the mission. The MOC sends this product to the NAIF/PDS for permanent archival.

This product is based on a Moon-centered J2000 based on the ME reference frame.

4.1.24.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Weekly files
File or Data Generation Frequency Generated twice during the mission after it receives the LOLA Improved Gravity Model, which occurs twice during the mission. FDF generates the files approximately 2 months after receipt of the LOLA Improved Gravity Model
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull) MOC “scp” push to SOCs
Data Volume Approximately .5 MBytes
Accuracy (if it applies) Data accuracy is within 500 meters over the definitive product timespan
Other pertinent details Only generated for post-LOI mission phases

4.1.24.2 Format

The FDF Reprocessed SPICE Definitive SPK file is a binary formatted file generated by the SPICE Toolset. The SPICE ID for LRO is -85, as assigned by JPL. The format of this file is consistent with the other FDF-generated SPK files for ephemeris data.

A sample file name for the first generation of this data file is given as fdf36_2009015_2009022_n01.bsp for a binary file. The product will include all definitive portions of the mission since LOI. SPK file will be type 13 and interpolation order 11; since this is a binary formatted file, no sample product will be shown in Appendix B.

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4.1.25 (FDF-37) FDF Solar Conjunction File

The Solar conjunction File contains the periods whenever the sun, Orbiter and earth align such that the sun will cause radio frequency interference. In these instances, there will be solar Radio Frequency interference (RFI) that affects the scheduled station contact. The following table provides a quick reference to the Solar Conjunction Type and the corresponding geometry. Figure 4-1 provides the geometry for the two solar conjunction types.

SC Type Affected Communication Geometry
Type 1 Uplink Sun position “inline with the earth to Orbiter vector” Reported when angle between facility and SUN is less than 3º (three degrees)
Type 2 Downlink Sun position “inline with the orbiter to earth vector” Reported when angle between LRO and SUN is less than facility defined angle for each station

The solar conjunction predictions will contain all upcoming conjunctions on both the uplink and the downlink within the product span. For many of the deliveries, no solar conjunctions may be present during the product span. If there are no times of solar conjunction, the file will only contain the initial file header information (date generation information and header line).

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4.1.25.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration next 28 days starting at 0000Z on the current generation day Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Weekly, on Wednesday, by noon-time, Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approx 10 Kbytes; variable based on whether there are any Solar Conjunctions for the requested time period
Accuracy (if it applies) Data accuracy is within 800 meters over the 84 hour predicts; Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Only generated for post-LOI mission phases if there are no periods of solar RFI, the file only contains the base header information for each station

4.1.25.2 Format

The solar Conjunction File is an ASCII text formatted file in which the fields are separated by a variable number of blanks. The solar conjunction file will contain the start time, stop time and a flag to indicate what type of solar conjunction (e.g., Type 1 or Type 2 as an example). The file contains 3-4 lines of header details that identify the file generation information and the file contents. There are 3-4 more lines that provide the format details for the following data fields. After these lines, the file consists of 1:N lines of solar conjunction information.

The following table provides a description of the fields within the file.

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Table 4-18 FDF – Solar Conjunction Data Description

Field name Field Characteristics
Station name 4 ASCII text characters representing the unique station identifier, with the following format: NNNN ; where NNNN = WS1S for LRO White Sands S-band Station WS1K for White Sands Ka-Band Station STSS for SDO backup STSK for the SDO backup Ka-Band USPS for USN Dongara USHS for USN South Point, Hawaii KU1S (or KU2S) for Kiruna, Sweden WU1S (or WU2S) for Wilheim, Germany DS24 for the DSN 34-m at Goldstone, Ca DS27 for the High-Speed Beam Wave Guide site at Goldstone, Ca DS34 for the DSN-34m at Canberra, Australia D34K for the DSN 34m Ka-Band site at Canberra, Australia DS45 for the High-Efficiency site at Canberra, Australia DS54 for the DSN 34-m at Madrid, Spain DS65 for the High- Efficiency site at Madrid, Spain
Start Time information: YYYYDDD.HHMMSS (GMT), 14 total ASCII Characters with a period between
year the first 7 and last six; where
day of year and YYYY => 4 ASCII digits of year (2008 – 2013)
time of day DDD => 3 ASCII digits for day of year (1 – 366)
HHMMSS => 6 ASCII digits (hours, minutes, and seconds of day)
Stop Time information: YYYYDDD.HHMMSS (GMT), 14 total ASCII Characters with a period between
year the first 7 and last six; where
day of year and YYYY => 4 ASCII digits of year (2008 – 2013)
time of day DDD => 3 ASCII digits for day of year (1 – 366)
HHMMSS => 6 ASCII digits (hours, minutes, and seconds of day)
Duration (seconds) [9 ASCII Digits] SSSSS.mmm; separated by the period (.) character SSSSS = 5 ASCII digits for whole number of seconds in the duration mmm = 3 ASCII digits for the millisecond portion of the duration
Solar Interference [6 or 8} ASCII Characters; where 6 ASCII Characters identified with Uplink or 8 ASCII Characters identified with Downlink
Solar Conjunct Type 1 ASCII Digit n; where n = 1 or 2 depending on the solar conjunction geometry 1 = Uplink, 2 = Downlink

A sample file name for the first generation of this data file is given as FDF37_2009015_2009043_N01.txt

A sample of the Solar Conjunction product is provided as a reference in Appendix B, Figure B.1

21.

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4.1.26 (FDF-38) Target Thruster Vector File

The Target Thruster Vector File includes the specified thrust vector data for the upcoming maneuver. FDF generates the Target Thruster Vector File in support of creating an attitude slew plan used during LRO maneuver execution

4.1.26.1 Product Details

Time interval NA
File duration Only applicable for the upcoming maneuver
File or Data Generation Frequency Varies based on type of maneuver; data generation frequency is listed in the FDF-GS&O Operations Agreement (451-MOA-002960)
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Variable based on maneuver support; can be up to approximately 330 Kbytes
Accuracy (if it applies) NA
Other pertinent details NA

4.1.26.2 Format

The Target Thruster Vector File is an ASCII formatted file that provides the direction of the spacecraft Body-X axis (essentially the thrust axis) during the maneuver. The report is a multiline file containing the four columns of space-delimited data. The first column has time in the format of YYYYDOY.HHMMSS. The next 3 columns provide the LRO Body axis vector in Earth-centered, J2000 coordinates; the second column provides J2000 X component of the Body X-axis vector, the third column is the J2000 Y component of the Body X-axis vector, the fourth column is the J2000 Z component of the Body X-axis vector.

This file does not contain any header information; the data are listed at whole second intervals. The following table provides the field designations.

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Field name Field Characteristics
Time 14 ASCII Characters/Digits in the form of: YYYYDOY.HHMMSS; where YYYY = 4 ASCII Digits for the year designation for the data DOY = 3 ASCII Digits for the day of year designator HHMMSS = 6 ASCII digits for the hours, minutes seconds for the data NOTE: The YYYDOY and HHMMSS are separated by the period (.) character
LRO Body-X axis vector in 12 ASCII digits and characters to represent the Signed unit vector; in the form of:
Earth-centered, J2000 (s)0.nnnnnnnnn; where:
coordinates (X component of the Body X-axis vector) (s) = 1 ASCII character; either a blank (represents a positive value or -, which indicates a negative value 0.nnnnnnnnn = 11 ASCII Digits and characters; 1 digit before the decimal place and 9 digits after the decimal place
LRO Body-X axis vector in 12 ASCII digits and characters to represent the Signed unit vector; in the form of:
Earth-centered, J2000 (s)0.nnnnnnnnn; where:
coordinates (Y component of the Body X-axis vector) (s) = 1 ASCII character; either a blank (represents a positive value or -, which indicates a negative value 0.nnnnnnnnn = 11 ASCII Digits and characters; 1 digit before the decimal place and 9 digits after the decimal place
LRO Body-X axis vector in 12 ASCII digits and characters to represent the Signed unit vector; in the form of:
Earth-centered, J2000 (s)0.nnnnnnnnn; where:
coordinates (Z component of the Body X-axis vector) (s) = 1 ASCII character; either a blank (represents a positive value or -, which indicates a negative value 0.nnnnnnnnn = 11 ASCII Digits and characters; 1 digit before the decimal place and 9 digits after the decimal place

This file does not conform to the FDF-standard file name conventions. The following table identifies the convention used for this file: <File Name Qualifier>_<Maneuver Type>_<Start Date>_<Stop Date>_<version number>.<file extension>

where File Name = [5 Characters], for file designator character followed by underscore Qualifier (_) character; e.g., FDF38_

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Maneuver Type = [4-5 Characters] for the type of planned maneuver in the form of MCCn – Mid-course correction maneuver #n or
LOIn – Lunar Orbit Insertion maneuver #n
MOIn – Mission Orbit Insertion maneuver #n
SKnna – Station keeping maneuver #nn [either “a“ or “b” as each station keeping maneuver will consist of 2 parts], for example SK01a, SK01b,
Additionally, the “n” for the MCC, LOI, MOI can have the suffix of “E” to represent that this is an engineering pre-burn to test the thrusters prior to the official maneuver
Start Date = [8 characters] Eight ASCII digit for the start date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for start year DDD = 3 ASCII Digits for start day of year; followed by the underscore (_) character
Stop Date = [8 characters] Eight ASCII digit for the stop date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for stop year DDD = 3 ASCII Digits for stop day of year; followed by the underscore (_) character
version number = [2 characters] Two ASCII digits for version number. The initial version is 01, next is 02 … up to 99; followed by the period (.)
file extension or source = [3characters] .txt, that indicates that this is a textual file that FDF generated.

A sample file name for the first generation of this data file is given as FDF38_LOIE_2008333_2008334_01.txt

A sample Target Thruster Vector File is provided as a reference in Appendix B, Figure B.1-22.

4.1.27 (FDF-39) Laser Ranging Site View Period Predicts

The Laser Ranging Site View Period Predict file contains specific view periods for the various laser ranging sites that will support the LRO mission. FDF uses a standard laser-ranging station elevation mask of 10 degrees, to identify the different laser ranging station view periods.

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4.1.27.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration 28 days starting at 0000 Hours on current generation day (Wednesday) Post-maneuver updates will start at 00:00 GMT on the current day
File or Data Generation Frequency Delivered weekly, on Wednesday by noon-time Eastern After maneuvers within best-effort available
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)) LRO MOC scp pushes the file to the LOLA SOC, which then scp-pushes the data product to the CDDIS for eventual use in laser ranging support
Data Volume Approximately 100 Kbytes
Accuracy (if it applies) The file contents should have accuracy over the 84-hours prediction, of less than 800 m in along-track Across maneuvers (orbit adjust or momentum unloads) accuracy is best available
Other pertinent details Station elevation masking information is unique for each station Contains HGA views for each available laser ranging site

4.1.27.2 Format

This file contains the data associated with view periods for all supporting laser ranging ground sites that support the LRO mission. The general format of this file consists of the following information:

1:N Header lines that provide the Station Name and date that FDF generated the file, and header lines that provide the field description; the file then contains N lines of data for each station view period.

The N lines of data contain the following fields:

Start Time Stop Time Duration Start Pass # Max Elev. Degrees Maximum Elevation Time; where these fields are defined in the following table:

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Table 4-19 FDF – Laser Ranging View Period Data Description

Field name Field Characteristics
Station name 43 ASCII text characters representing the unique station identifier, with the following format: Facility-NNNN-To-Satellite-0059-Sensor-HGA; where NNNN = GO1L, SLR2000 at Greenbelt, MD (previously GGAO) MDOL, McDonald Observatory at Ft. Davis, TX MONL, Monument Peak, California MATM, Matera Laser Ranging Observatory, Matera, Italy ZIML, Zimmerwald, Switzerland STL3, Mount Stromlo at Canberra, Australia HERL, Herstmonceaux, England GRSM, Grasse, France WETL, Wettzel, Germany HARL, Hartebeesthoek, South Africa (MOBLAS-6) YARL, Yarragadee, Dongara, Australia (MOBLAS-5) KOGC, Koganei, Tokyo, Japan
Start time information: YYYYDDD.HHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Stop time information: YYYYDDD.HHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Station View Duration (in SSSSS.mmm (9 ASCII digits), where
seconds) SSSSS => 5 ASCII characters representing the whole seconds; followed by a period(.) mmm => 3 ASCII characters for the milliseconds of station contact
Pass Number 7 ASCII characters representing a monotonically increasing Orbit Number (1 to 9999999) NOTE: This field is only valid after lunar insertion; this field should be ignored prior to LOI
Max elevation angle EE.ddd EE => 2 ASCII digits for whole angle measurement (0 – 90) dd d=> 3 ASCII digits for decimal portion of elevation angle (000 – 999)
Time of Maximum Elevation YYYYDDD.HHMMSS, where YYYY => 4 ASCII digits of year (2008 – 2013) DDD => 3 ASCII digits for day of year (1 – 366), followed by a period (.) HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day

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This file follows the standard FDF file naming convention; a sample file name for the first generation of the laser Ranging View Period data file is given as FDF39_2009015_2009043_N01.txt.

A sample Laser Ranging View Period Predict Data file is provided as a reference in Appendix B, Figure B.1-23.

4.1.28 (FDF-40) Definitive Goddard Trajectory Determination System (GTDS) Ephemeris File

This file contains definitive GTDS-formatted LRO ephemeris data for the spacecraft position and velocity information earth-centered data. FDF generates this file for the MOC/AGS use only; no other systems should use this data file.

4.1.28.1 Product Details

Time interval Data samples provided at 1 minute increments
File duration Continually appended until predefined limit reached (at approximately 200 Mbytes for file size)
File or Data Generation Frequency Daily, by noon-time
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Not to exceed 200 Mbytes
Accuracy (if it applies) accuracy is approximately 500 m RSS total
Other pertinent details Data format is consistent with Code 500 GTDS format

4.1.28.2 Format

The Definitive LRO GTDS Ephemeris file is an EBCDIC/binary formatted file that is consistent with the standard Code 500 formatted ephemeris data files; the file is identified as a big-Endian format. The FDF Product Guide provides the file data contents and format; therefore this document will not redefine these parameters.

FDF continually concatenates data onto the end of this file and it will continue to grow in file size. When the file reaches to approximately 200 MByte file size limit, FDF create a new file that contains a 2-3 day overlap and starts adding data to the file. This file does not conform to the FDF-standard file name conventions. The following table identifies the convention used for this file:

<File Name Qualifier>_<Start Date>_<version number>.<file extension>

where File Name = [5 Characters], for file designator character followed by underscore Qualifier (_) character; e.g., FDF40_

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Start Date = [8 characters] Eight ASCII digit for the start date in the form of YYYYDDD; where YYYY = 4 ASCII Digits for start year DDD = 3 ASCII Digits for start day of year; followed by the underscore (_) character
version number = [2 characters] Two ASCII digits for version number. The initial version is 01, next is 02 … up to 99, followed by the period (.)
file extension or source = [3characters] .txt, that indicates that this is a textual file that FDF generated.

A sample file name for the first generation of the Definitive GTDS data file is given as FDF40_2008320_01.bin

Since this file contains data in a binary/EBCDIC form, there is no sample product listed in Appendix B.

4.1.29 (FDF-42) FDF Time Coefficient File

The FDF Time coefficient file contains the lunar/planetary coefficients and time coefficients; such as the leap-seconds; time offsets between UTC and UT1 reference times and polar motion data (x, and y positional data) updates.

4.1.29.1 Product Details

Time interval One entry for each day
File duration File is updated on a daily basis and could contains up to approximately 20 years of data from both a historical (time) and predicted (polar motion) contains up to the limit of the data span
File or Data Generation Frequency Daily; by noon-time
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approx 1 MByte
Accuracy (if it applies) Data are accurate based on the retrieved data from United States Naval Observatory (USNO)
Other pertinent details NA

4.1.29.2 Format

The data format for this file is a binary data file. The data consists of the predicted polar motion and historical time offsets. This file following the standard file name conventions as listed previous with the minor exception that the maneuver flag is removed from the file name since this file never implies or has any maneuver concepts involved with the internal data.

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For example, the first file version generated on January 25, 2009 is:

FDF42_2009025_00.bin; since this file is a binary formatted file, no sample product is listed in Appendix B.

4.1.30 (FDF-44) Trajectory Insertion Data

FDF provides the trajectory insertion data as a file to the MOC for inclusion with orbital elements that the MOC eventually transfers back to the United Launch Alliance (ULA)

4.1.30.1 Product Details

Time interval data are time stamped at the separation epoch
File duration NA; file is generated once post-launch
File or Data Generation Frequency FDF generates product once within 3-4 days of launch
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Approx 100 bytes
Accuracy (if it applies) accuracy is 500 m RSS total
Other pertinent details NA

4.1.30.2 Format

FDF provides the derived instantaneous trajectory insertion data as specified in the following table; these data will represent the most accurate orbit data available for an epoch propagated back to LRO separation and prior to any LRO impulsive maneuver. The FD generated file contains 2-3 lines of header information that identifies the file creation meta-data information; each of the header lines are preceded with the hash (#) symbol in the first column to denote a comment line. The file then contains the following data lines for the True equinox of date and the Orbital parameters as defined by the Keplerian orbital information as defined within this table.

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Table 4-20 FDF – Trajectory Insertion Data Description

Field name Field Characteristics
Date of launch vehicle separation) 8 ASCII digits that represent the True equinox of date; with the following format: MMDDYYYY =
Time of launch vehicle separation 6 ASCII digits that represent the True equinox of date; with the following format HHMMSS
Semi-major Axis (Km) Floating point value, format: nnnnnnnnn.nnnnnn
Eccentricity (Unitless) Floating point value; format 0.nnnnnnnnnnn
Inclination (Degrees) Floating point value: format: nnn.nnnnnn; not zero padded
Right Ascension of Ascending Node (Degrees) Floating point value: format: nnn.nnnnnn; not zero padded
Argument of perigee (Degrees) Floating point value: format: nnn.nnnnnn; not zero padded
True Anomaly (Degrees) Floating point value: format: nnn.nnnnnn; not zero padded

The file following the standard FDF-generated file name convention previous listed with the exception that the file name does not require any maneuver flag as part of the file name. A sample file name is identified as: FDF44_2008302_2008302_00.txt. Appendix B, Figure B.1-24 provides a sample of the file content.

4.1.31 (FDF-45) LRO Operations Activity Request

This is the LRO Operations Activity Request, which FDF can use to identify routine requests of standard activities, such as commands, guidance, navigation, and control procedure activation, ground support, or any other features that FDF and the LRO MOC have identified as possible routine operations that have been thoroughly checked and validated during the spacecraft integrations and test phase.

FDF generates the LRO Operations Activity Request and forwards the inputs to the LRO MOC. The MOT merges any this Activity Requests with command input for the spacecraft and orbiter health and safety commands and any specific maneuver commands based on mission profile support phases.

If the activity requests contains any commands, the commands in the file must be defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053). If the command contains submnemonics, they must be specified with the command.

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4.1.31.1 Product Details

Time interval NA
File duration NA
File or Data Generation Frequency File delivered 48 hours prior to the requested activity, assuming the activity currently exists. Otherwise best effort based on time required to generate new procedures or test new instrument commands. Additional time required if FDF delivers via backup protocol
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC via the FD Communications Server; the backup uses the FDPC (MOC performs the scp pull)
Data Volume Variable; based on contents, but nominally less that 1KBytes
Accuracy (if it applies) NA
Other pertinent details NOTE: The time interval will be relaxed if the request is based on an Orbiter anomaly

4.1.31.2 Format

The Activity Request File is intended to capture all information necessary to execute the activity described. All fields identified are required, if a field is not required enter “NA”, this includes the initial submission of an activity request number field. The following sections describe each field. A linefeed character terminates each field and a blank line should separate each field. The following table identifies the file contents and provides additional information on the data entered for each field

Table 4-21 LRO Operations Activity Request Definitions

Field name Field Characteristics
OAR Request Date Date when the requestor submitted the OAR to the MOC; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 – 31) with leading zeros The OAR requestor is required to enter this field.
OAR Approved Date Date when the MOT approves the OAR to the MOC; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -32) with leading zeros The OAR requestor should enter NA for this field.

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Field name Field Characteristics
OAR Planned Execution Date This field will contain the MOT identified expected date when the OAR is expected to execute; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -32) with leading zeros The OAR requestor should enter NA for this field.
OAR Status This field contains the indication as to whether the MOT has accepted/rejected the OAR; the MOT completes this field The OAR requestor should enter NA for this field.
OAR Status Detail This field contains the explanation if the MOT “rejects” OAR; otherwise, the MOT enters an NA The OAR requestor should enter NA for this field.
OAR Name This field contains the name of the activity that the SOC is requesting. The field is a short description of the activity. When possible, this field should identify an existing LRO Flight Procedure Document. The OAR requestor is required to enter this field.
OAR Number This field is intended for tracking purposes. The MOT assigns the OAR number when received. The MOT will assign numbers for both approved and unapproved OARs. The OAR requestor should enter NA for this field.
OAR Requested By Name of person making the request. The LRO Operations Agreement with each organization will identify the individuals, a primary and backup. The MOT will only act on requests submitted by those individuals identified in the approved LRO Operations Agreement The OAR requestor is required to enter this field.
OAR Requestor Phone Number The OAR Requestor must provide a telephone number in this field. As the MOT reviews and implements the request, the MOT will contact the requestor at the telephone number provided to answer any questions regarding the request. The OAR requestor is required to enter this field.
OAR Requestor Email Address The Requestor must provide an email address in this field. The MOT will send an email to this address and all email addresses on record for this requesting organization, which verifies MOT receipt of the OAR. The MOT will send another email when the OAR is approved or rejected The OAR requestor is required to enter this field.
OAR Request Org The Requesting organization indicates the affiliation of the person requesting the change The OAR requestor is required to enter this field.

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Field name Field Characteristics
OAR Type The activity type field gives an indication to the MOT as to which area is affected by the request. One of the following types: GROUND OPERATION – activity will affect only ground assets; e.g., requesting the MOT to generate a specific product INSTRUMENT OPERATION – activity will affect the instrument; e.g., sending a command, updating a FSW Table, downlinking a specific memory location SPACECRAFT OPERATION – activity will affect the spacecraft; e.g., sending specific commands, updating C&DH flight software or changing a table onboard the spacecraft The OAR requestor is required to enter this field. NOTE: FDF-generated OARs should NEVER use INSTRUMENT OPERATION as a type
OAR Execution Window This field identifies the window for when the FDF requests execution of the requested activity. The OAR requestor can supply one of the following valid inputs: NA NET yyyy-mm-dd; NLT yyyy-mm-dd where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -31) with leading zeros NOTE: The MOT will schedule the request at the next available opportunity if the requestor enters an ‘NA’ in this field.
OAR Constraints 1:N lines of free form text describing constraints for executing activity, e.g. Only during eclipse The activity constraints field identifies to the MOT limitations on when the activity may be executed. In most instances, flight procedure documents will identify constraints related to the operation. If additional constraints are required, they should be included in this field. The OAR requestor can either supply NA or enter a valid constraint data into this field.
OAR Sequence This field specifies the activity to be executed. The MOT will execute the activity according to the instructions provided. Instructions can be as simple as execute Flight Procedure XYZ at next available ground station contact. When the Flight Procedure already exists and is approved for operational use, the MOT will execute the procedure at the time specified. When it is necessary to execute the activity at a specific time, the Requestor should identify absolute times in the format of YYYY-DOY-HH:MM:SS for each step in the activity where applicable. All absolute times in this field shall be represented in Coordinated Universal Time (UTC). The OAR requestor is required to enter this field.

A sample LRO Operations Activity Request is provided in Appendix B, Figure B.3-1.

The following file-naming convention is used for the OAR files transmitted between FDF and the LRO MOC. The filename consists of up to 22 characters; it also contains a three -character file 4-83

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extension name. There is an underscore (_) between the first four fields and a period (.) between the last two fields. The form of the filename is as follows:

<FILENAMEDESIGNATOR>_YYYY_DOY_NN.<file extension>

where File name designator = [10 ASCII characters]; defaults to LROFDF_OAR for FDF Ops Activity request
Date = YYYY_DOY; where
YYYY = 4ASCII digits for year DOY – 3 ASCII digits for day or year NOTE: Date field identifies when FDF generated request
Version = NN; where nn= 2 ASCII Digits to reflect the version number within a day; first version = 01; this allows for multiple files in the same day
file extension = [3 characters] Standard file extension for all text input files txt to indicate that the file is text information

A sample FDF-generated LRO Activity Request file name is: LROFDF_OAR_YYYY_DOY_NN.txt.

4.2 STATION PRODUCTS AND DESCRIPTIONS

The following sections provide the details on the interface products generated by the various ground stations used to support the LRO mission. The following several products are derived by or created by various groups that fall under the general category of the Space Communications Network. They provide specific information required by the LRO mission and are used either in support of the Mission Operations Center or by various entities within the LRO mission.

DSN is used for early mission launch critical supports activities and for any mission maneuver; DSN provides regularly scheduled proficiency supports. Outside of these supports, DSN is used solely to provide an emergency, or contingency, supports in the event that the commercial S-band stations are down.

The Space Network (SN) Tracking and Data Relay Satellites (TDRS) system supports the LRO mission; its support is limited for the several hours immediately after launch.

The following sections identify the interfaces sent by the LRO MOC to the various ground stations supporting the LRO mission. Nominally, these interfaces are used to transmit command from the LRO MOC to the corresponding station. The command structure that the LRO MOC uses is dependant upon the station that is scheduled to be the interface for sending commands to the LRO spacecraft. The following conventions are used by the LRO MOC to support the interface with each of the corresponding stations:

• SMEX/LEOT Header is used for transferring telemetry from either the WS1, SN or USN stations to the LRO MOC

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  • The Data Storage System (DSS) provides the interface from the HDR to the Station Data Processing System for the transfer of high-speed VC2 and VC3 telemetry VCDUs. The DSS will forward only VCDUs with frame sync, the DSS does not provide any additional headers or trailers.

  • Space Link Extension (SLE) telemetry structure for interfacing with DSN stations The SMEX/LEOT Telemetry header is 10 bytes long and has the following data structure as

identified in Figure 4-5; Table 4-22 provides a reference definition for the fields contained within the SMEX/LEOT Telemetry Header.

The ground station will decommutate the Channel Access Data Units (CADU) received from the spacecraft and perform Reed Solomon decoding for eventual delivery of the Virtual Channel Data Unit (VCDU) to the MOC. The SMEX/LEO-T Telemetry header is a 10 byte header attached to every VCDU that is forwarded in real-time to the MOC’s T&C system. The details for the CADU & VCDU definition are documented in the T&C Formats Handbook. In the figure below, the fields are represented in bits, not bytes.

Figure 4-5 SMEX/LEOT Telemetry Header Table 4-22 SMEX/LEOT Field Definitions and Expected Values

Field Name Size (bits) LRO Value Nominal Values
Version 2 ‘01’ Value = 01, frame data
Message Length 14 1798 decimal for LRO = 1798 bytes (includes frame synch and SMEX/LEOT Header)
Reed-Solomon Enable Flag 1 ‘1’ Value = 0, RS not enabled; 1, RS enabled Will be 1 for LRO
Reed-Solomon Error Flag 1 variable Value = 0, no RS errors 1, RS errors
CRC Enable Flag 1 ‘1’ Value = 0, CRC not enabled; 1, CRC enabled
CRC Pass/Fail 1 variable Value = 0, pass; 1, fail
Master channel sequence (MCS) checking enabled flag 1 ‘0’ Value = 0, MCS not enabled; 1, MCS enabled Not applicable for LRO
MCS number error 1 ‘0’ Value = 0, number increased monotonically; 1, number increased by 2 or more; Not applicable for LRO

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Field Name Size (bits) LRO Value Nominal Values
Data inversion flags 2 variable Value = 00, data true; 01, data inverted; 02, data inverted and corrected
Frame sync mode flags 2 variable Value = 00, search frame; 01, check frame; 02, lock frame; 03, flywheel frame
Data forward/reverse flag 1 variable Value = 0, data forward; 1, data reversed
Data Class 5 ‘01’ or ’02’ Value = 01, spacecraft telemetry 02, spacecraft command (will be used to identify the station status packet) 03, tracking data (N/A for LRO)
Earth received time of data (PB-5 format): flag bit 1 ‘0’ 1 PB5 flag bit; value = 0
Earth received time of data (PB-5 format): truncated Julian day 14 variable 2-15 Truncated Julian day; 14 bits; truncate the most significant decimal digits, retaining only the four least significant decimal digits ranging from 0000 to 9999. The current Julian day epoch begins on is Jan 01, 2001
Earth received time of data (PB-5 format): seconds of day 1 variable 16 Seconds of day; 17 bits; most significant bit
Earth received time of data (PB-5 format): seconds of day 16 variable 1-16 Seconds of day; 17 bits total; remaining 16 bits from word 3, bit 16, above. Value is variable; range is 0 to 86,399; binary unsigned integer
Earth received time of data (PB-5 format): milliseconds of a second 10 variable 1-10 Milliseconds of a second; value is variable; range is 0 to 999; binary unsigned integer
Fill / spare 6 0 16 Fill/spare

4.2.1 (GNSO-1) SCN Support Schedules

This is a schedule file that contains 1 week of station contacts that support LRO; this support schedule includes WS1, USN, and DSN and SN contacts when required. This support schedule is the version that the Mission Planning System ingests as part of its timeline generation function.

When the LRO MOC receives the WOTIS-generated Operational schedules from the GNSO, it will transfer the product via the scp protocol to FDF Product Center and to the LOLA SOC for eventual transfer to the CDDIS for use by the laser ranging facilities. The MOC merely acts as a conduit to pass on this information to the CCDIS and FDF and does not modify this Operational schedule.

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The Station support schedule is three separate files that are created to cover various Monday – Sunday weekly activity schedules. The basic concepts for the mission schedule identifies three working versions that are used to identify the over all station support schedules for future weeks as noted here:

  • Strawman Schedule – generated and delivered to the LRO MOC approximately 28 days prior to the start of that week’s operational supports and planned scheduled station contacts

  • Forecast Schedule – generated and delivered to the LRO MOC approximately 2 weeks prior to the start of that week’s operational supports and planned scheduled station contacts

  • Operational Schedule – generated and delivered to the LRO MOC on the Thursday prior

to the start of the operational scheduled events; this schedule is conflict free. In the event the MOC requires changes to the schedule, the MOC will create a schedule file in the same format as described here and send the update request back to WOTIS. The MOC will revise the file name and change the first character in the filename changed to a ‘U’. The MOC will make changes to the file as required, which for example, may include changing the TR code or a start and stop time.

4.2.1.1 Product Details

Time interval NA
File duration Standard Strawman, Forecast, and Operational schedules are 7 days, GNSO can create any file duration for LRO MOC requested schedule updates
File or Data Generation Frequency Weekly
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC MOC “scp” pushes to FDF (via the FD Communications Server; the backup uses the FDPC) and all SOCs, except for Mini-RF
Data Volume Variable; based on number of identified station contacts for the week in question
Accuracy (if it applies) Contact times are accurate to 1 second; based on data from FDF View Period File
Other pertinent details NA

4.2.1.2 Format

The Station Support Schedule file is an ASCII-formatted file and consists of the station name, start time, stop time, duration, and configuration identified for the requested station support; the following table provides a brief description of each field: The support activity codes, as initially defined within Error! Reference source not found., are only used to identify a preliminary set

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of TR codes. The LRO operations team and WOTIS scheduling personnel will coordinate the actual codes and how the codes reference Ka-band and S-band Station contacts.

Table 4-23 SCN Station Support Schedule Field Definitions

Field name Field Characteristics
Support Activity Tag Up to 15 ASCII Characters, assigned by WOTIS to uniquely identify each specific station contact
Station Name 4 ASCII Characters that uniquely identify the station, ; in the form of: NNNN; where the 4 character NNNN is one of the station designators: WS1S for LRO White Sands S-band Station WS1K for White Sands Ka-Band Station STSS for SDO backup STSK for the SDO backup Ka-Band USPS for USN Dongara USHS for USN South Point, Hawaii KU1S (or KU2S) for Kiruna, Sweden WU1S (or WU2S) for Wilheim, Germany DS24 for the DSN 34-m at Goldstone, Ca DS34 for the DSN-34m at Canberra, Australia D34K for the DSN 34m Ka-Band site at Canberra, Australia DS54 for the DSN 34-m at Madrid, Spain DS27 for the High-Speed Beam Wave Guide site at Goldstone, Ca, DS45 for the High-Efficiency site at Canberra, Australia DS65 for the High- Efficiency site at Madrid, Spain
Start time: YYYYDDDHHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Stop time: YYYYDDDHHMMSS, where
year YYYY => 4 ASCII digits of year (2008 – 2013)
day of year and DDD => 3 ASCII digits for day of year (1 – 366)
time of day HHMMSS => 6 ASCII digits for the hours, minutes, and seconds of day
Support Activity Code 3-4 ASCII Character that identifies the station configuration used to support the LRO station contact; allowable values are: TR1 – TR99; The actual LRO TR codes are listed in the Error! Reference source not found.
Orbit Number 1-5 ASCII Characters representing a monotonically increasing orbit counter; this field is only valid after the first lunar orbit insertion maneuver.
Band 2 ASCII Characters representing the support contact type; where S1 = S-band Support K1= Ka-Band Support

A sample Station Support Schedule file is identified with the following naming conventions:

<S><Mission ID><Year/Date Information><Schedule Duration><Schedule Type>.ext; where

S => 1 Character Schedule Type Identifier

= s to indicate this is a schedule file from WOTIS

= u to indicate a MOC request to update the schedule

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Mission ID => 3 characters to identify the mission = lro

Year/Date Information => 7 characters in the form of YYYYDDD, where

YYYY – start year designator (2008 – 2013) DDD – start day of year (Monday) for the first station contact in the schedule file

Schedule Duration => 3 characters d07, d14, where last 2 characters represent the number of days (duration) of the file; nominally set for 7 days

Schedule Type => 1 character to identify the specific schedule

o = operational f = Forecast s = Strawman

Extension => 9 characters

xxxxxxxxx, nominally represents the DOYHHMMSS of the file creation; this is used to uniquely identify the file

A sample file name for the Support Schedule is defined as follows:

slroYYYYDOYd07o.xxxxxxxxx – sample file name for the Operational schedule slroYYYYDOYd07f.xxxxxxxxx – sample file name for the Forecast schedule slroYYYYDOYd14s.xxxxxxxxx - sample file name for the Strawman schedule NOTE: Because of MOC internal processing requirements, this file name construct is translated to all upper case characters, where appropriate. All downstream users (all SOCs and FDF) receive the file name in an upper case format as noted here: SLROYYYYDOYd07O.xxxxxxxxx A sample Station Support Schedule file is provided as a reference in Appendix B, Figure B.2-1.

4.2.2 (WS1-5) (USN-3) Station Raw Tracking Data

The Station Raw Tracking Data provides the LRO Flight Dynamics Facility with the data required to support tracking of the orbiter and generation of orbit and mission products. These data are also transferred to the LRO MOC for eventual distribution to the LOLA SOC.

Each ground station (WS1 and the USN stations) that supports tracking for the LRO mission will create the data in a format identified as the Universal Tracking Data Format (UTDF) as defined in the STDN Tracking and Acquisition Handbook (STDN-724, 1990).

4.2.2.1 Product Details

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Time interval Doppler data every 5 seconds; Range data, if available, at same 5 second data interval
File duration 5 minutes
File or Data Generation Frequency Every station tracking support
Delivery method (real-time, SCP, FTP, etc) WS1 and USN “scp” the data files to the LRO MOC (Stations scp “push”) WS1 and USN stations FTP the files to the FDF Comm Server LRO MOC scp pushes the file to the LOLA SOC
Data Volume 75 bytes of data – every 5 seconds – for 5 minutes
Accuracy (if it applies) Best Effort given station contact geometry conditions
Other pertinent details NA

4.2.2.2 Format

This data will be consistent with STDN-724; WS1 can provide the tracking data either as a real-time data source to FDF or as a post-pass file to both FDF and to the LRO MOC. However, the ICD identifies that WS1 should provide LRO tracking data via the file delivery method.

USN always provides the data via a post-pass file transfer.

The tracking data are in a binary form; one datum contains seventy-five (75) bytes of information as identified in the Tracking and Acquisition Handbook. The following table provides the fields and field definitions for the station tracking data. FDF does not reference the data contained within byte 45 or byte 47. Since FDF does not use these two fields, the stations should default these two values to represent the closest antenna size used to support the LRO missions.

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Table 4-24 WS1 Raw Tracking Data File Field Definitions

Byte Format Description
1 0D(16) Fixed
2 0A(16) Fixed
3 01(16) Fixed
4-5 ASCII Tracking Data Router 4141=AA=GSFC 4444=DD=GSFC
6 Binary Last two digits of current year
7-8 Binary Satellite Identification Code (SIC)
9-10 Binary Vehicle Identification (VID)
11-14 Binary Seconds of year
15-18 Binary Microseconds of second
Note: For bytes 19-22/23-36, convert angle data to decimal form. Angle data are given in fractions of a circle. To express raw angle in degrees, multiply decimal angle by 8.381903173 x 10-8 (360 degrees divided by 232)
19-22 FOC Angle 1: X or az
23-26 FOC Angle 2; Y or el (angle 2 byte/bit format is the same as for bytes 1922.)
27-32 Binary RTLT in 1/256 nsec (MSB = 524288 ns; LSB = 0.00390625 ns)
33-38 Binary Bias Doppler, counts of: 240 MHz +1000 fd1 LSB - 1 count
39-40 Binary AGC (an integer * (-150/8192) AGC-50=dBm)
41-44 Binary Transmit frequency information in 10's of Hz

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Byte Format Description
45 Discrete MSD = antenna size (xmit) as follows: 0(16) = less than 1 m 1(16) = 3.9 m 2(16) = 4.3 m 3(16) = 9 m 4(16) = 12 m 5(16) = 26 m 6(16) = TDRSS ground antenna 7(16) = 6 m 8(16) = 7.3 m 9(16) through Feet = spares LSD = antenna geometry (xmit) as follows: 0(16) = az-el 1(16) = X-Y (+X-south) 2(16) = X-Y (+X-east) 3(16) = RA-DEC 4(16) = HR-DEC 5(16) through F(16) = spares
46 Binary Pad ID (xmit)
47 Discrete Antenna size (rcv) – (see byte 45)
48 Binary Pad ID (rcv)
49-50 Discrete Mode-system unique (refer to Table 2)
51 Discrete Data Validity Bit 8 = (MSB) sidelobe (1-sidelobe) 7 = destruct R (1 = destruct) 6 = refraction correction to R, R (1corrected) 5 = refraction correction to angles (1 =corrected) 4 = angle data correction (1 =corrected) 3 = angle valid (1=valid) 2 = Rº valid (1=valid) 1 = (LSB) R valid (1=valid)
52 Discrete MSD = frequency band, as follows: 1(16) = VHF 2(16) = UHF 3(16) = S-band 4(16) = C-band 5(16) = X-band 6(16) = Ku-band 7(16) = visible 8(16) through F(16) = spares

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Byte Format Description
LSD = data transmission type, as follows: 0(16) = test 1(16) = spare 2(16) = simulated 3(16) = resubmit 4(16) = RT (real time) 5(16) = PB (playback) 6(16) through F(16) = spares
53-54 Discrete MSD - tracker type Byte 53, bits 8 thru 5: 0(16) = C-band pulse track 1(16) = SRE (S-band and VHF) or RER 2(16) = X-Y angles only (data acquisition antenna) 3(16) = spare 4(16) = SGLS (AFSCN S-band trackers) 5(16) = spare 6(16) = TDRSS 7(16) through F(16) = spares
Byte 54, bit 4: 1 = last frame of data
Byte 53, bits 3 thru 1 and eight bits of byte 54: 11 bits for transmission rate (positive indicates the binary seconds between samples up to a maximum of 1023; negative indicates the two's complement of the number of samples per second).
55-72 Spare
73 04(16) Fixed
74 04(16) Fixed
75 04(16) Fixed

WS1 stores these UTDF data records into a file based on the 5-minute duration and then forwards the file to both the FDF and LRO MOC facility. Similarly, the USN station provides the same support capabilities and delivery concepts for transferring the data to the LRO MOC and to FDF.

A UTDF Tracking data file is identified with the following naming conventions:

<File Qualifier>_<Spacecraft Designations>_<Receiver PADID>_<Date Information>.<ext>; where

File Qualifier => 6 ASCII characters to identify the type of UTDF data = LSUTDF (indicates low-speed UTDF data)

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Spacecraft Designations => 6 ASCII Digits (SSSSVV) to identify the spacecraft designation, where SSSS = Spacecraft ID (0059 for LRO) VV = Vehicle ID (01 for LRO)
Receiver PADID => 3ASCII Digits to identify the station receive PAD identifier 188 for the White Sands station
189 for the SDO Backup station 103 for USPS for USN Dongara 105 for USHS for USN South Point, Hawaii 126 for KU1S (or KU2S) for Kiruna, Sweden 128 for WU1S (or WU2S) for Wilheim, Germany
Date Information => 11 ASCII digits, separated by the underscore (_) Character, in the form of YYYY_DDD_HHMM; where YYYY = 4 ASCII digits for year (2008 -2013) DDD = 3 ASCII digits for day of year (001 – 366) HHMM = 4 ASCII digits (24 Hour time qualifier) to represent the hours and minutes of when the station closed the file
File Extension => 3 ASCII Characters; default to trk

A sample file name for the first WS1 generated low-speed UTDF tracking data file that corresponds to a file that the station closed at 0957GMT on 25 January 2009 is defined as follows: LSUTDF_005901_188_2009_025_0957.trk

The station tracking data file is a binary formatted file and as such, no sample is provided in Appendix B.

4.2.3 (WS1-10) (USN-6) Archived VC0 Telemetry Data

This interface consists of the downlinked data that are stored in a file format at a station upon receipt of the real-time spacecraft housekeeping telemetry. These data are stored with the fill data (VC63) removed. These files are stored at the ground station using their local storage functionality. The stations store the files for up to seventy-two (72) hours in the event of a possible retransmission to the LRO MOC upon request by the LRO operations team; this would normally be considered within a contingency support concept.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.2.3.1 Product Details
Time interval Variable based on Orbiter VC0 Data collection filters and per APID
File duration Based on station contact interval WS1 file duration limited to 60 minutes
File or Data Generation Frequency Per station contact; WS1 create 1:N files per station contact USN creates 1 file per station contact
Delivery method (real-time, SCP, FTP, etc) MOC scp pulls from the WS1 station USN scp pushes the files to the MOC upon MOC request
Data Volume Variable; based on APIDs and downlink rate
Accuracy (if it applies) NA; based on data mnemonics for specified APIDs
Other pertinent details WS1/USN sites archive data for 72 hour retention

4.2.3.2 Format

The Archived VC0 Telemetry Data are stored with the VC63 (fill data) removed. The station archives the VC0 data stream (the downlinked VCDUs) using the station generated SMEX/LEOT Header.

A sample Archived VC0 Telemetry Data File is a binary file of the downlinked telemetry data; as such, no sample product is listed in Appendix B.

When, or if requested, by the LRO MOT, the station would transfer the archived VC0 Telemetry file back to the LRO MOC facility using the secure copy mechanism. The archive files that WS1 creates are based on configurable time duration; this configurable duration is set for the LRO mission at 60 minutes. However, the LRO Mission Operations Support Plan (MOSP), 431PLAN-000050, will finalize the details of this file size duration and identify any instances when and how the MOT could request a different file size limit.

The archive files that the USN stations create are not configurable based on a time duration; USN creates one archive file that corresponds to the complete station contact interval.

An Archived VC0 telemetry file name is identified with the following naming conventions:

<SID>_<SIC>_<Data Source>_<Scheduled AOS Time>_<File Number>.vc0; where

SID => 3-4 ASCII Characters for the station ID

WS1 for White Sands

USPS for USN Dongara, Australia

USHS for USN South Point, Hawaii

KU1S (or KU2S) for Kiruna, Sweden

WU1S (or WU2S) for Wilheim, Germany

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SIC => 4 ASCII Digits to identify the spacecraft ID

= 0059 Data Source => 4 ASCII characters for the source of the data

= rcp1 or rcp2 (from WS1)

= REC1 for USN stations Schedule AOS time => 13 ASCII characters in the form of

YYYYDOY_HHMMSS, where

YYYY – start year designator (2008 – 2013)

DDD – start day of year (0 – 366)

HHMMSS – Hours, Minutes and seconds of AOS File Number => 4 ASCII digit number to indicate the sequence of the file in

the segmented series of files for a particular pass

= (0001 - 9999)

NOTE: Does not apply for USN stations and is not used in

the file name conventions extension => 4 ASCII characters, vcnn; where nn = 00, (used to represent the Virtual Channel 0)

For example, for an LRO pass captured at the WS1 station that began on DOY 223 at 12:15:07 in the year 2008, where the data was received from High data-rate receiver #1, and the segment time is set to 3600 seconds (as is expected for LRO), the filename would be:

WS1_0059_rcp1_2008223121507_0001.vc00

If there were multiple files associated with one pass, the files would be named as follows: WS1_0059_rcp1_2008223121507_0001.vc00 WS1_0059_rcp1_2008223121507_0002.vc00 WS1_0059_rcp1_2008223121507_0003.vc00 WS1_0059_rcp1_2008223121507_0004.vc00

For an LRO VC0 Archive file captured at the Dongara station that began on DOY 223 at

21:12:50 in the year 2008, the file name would be identified as: USPS_0059_REC1_2008223211250.vc00

4.2.4 (WS1-11) (USN-7) Archived VC1 Telemetry Data

This interface consists of the downlinked VC1 data that are stored in a file format at a station upon receipt of the spacecraft housekeeping telemetry. These data are stored with the fill data (VC63) removed. These files are stored at the ground station using their local storage functionality. The files are stored for up to seventy-two (72) hours in the event of a possible retransmission to the LRO MOC upon request by the LRO operations team; this would normally be considered within a contingency support concept.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.2.4.1 Product Details
Time interval Variable based on Orbiter VC1 Data collection filters and per APID
File duration Based on station contact interval WS1 file duration limited to 60 minutes
File or Data Generation Frequency Per station contact
Delivery method (real-time, SCP, FTP, etc) MOC scp pulls from the WS1 station USN scp pushes the files to the MOC upon MOC request
Data Volume Variable; based on APIDs and downlink rate
Accuracy (if it applies) NA; based on data mnemonics for specified APIDs
Other pertinent details WS1/USN sites archive data for 72 hour retention

4.2.4.2 Format

The Archived VC1 Telemetry Data File is stored with the VC63 (fill data) removed. The station archives the VC1 data stream (the downlinked VCDUs) using the station generated SMEX/LEOT Header. The archive files that WS1 creates are based on configurable time duration; this configurable duration is set for the LRO mission at 60 minutes. However, the LRO MOSP, 431-PLAN-000050, will finalize the details of this file size duration and identify any instances when and how the MOT could request a different file size limit.

A sample Archived VC1 Telemetry Data File is a binary file of the downlinked telemetry data; as such, no sample product is listed in Appendix B.

An Archived VC1 telemetry file name is identified with the following naming conventions:

<SID>_<SIC>_<Data Source>_<Scheduled AOS Time>_<File Number>.vc1; where

SID => 3-4 ASCII Characters for the station ID

WS1S for White Sands

USPS for USN Dongara, Australia

USHS for USN South Point, Hawaii

KU1S (or KU2S) for Kiruna, Sweden

WU1S (or WU2S) for Wilheim, Germany

SIC => 4 ASCII Digits to identify the spacecraft ID = 0059

Data Source => 4 ASCII characters the source of the data as provided by the

MCS

= rcp1 or rcp2 (from WS1)

= RECn, where n=1,2 for USN stations

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Schedule AOS time => 13 ASCII characters in the form of YYYYDOYHHMMSS, where
YYYY – start year designator (2008 – 2013) DDD – start day of year (0 – 366) HHMMSS – Hours, Minutes and seconds of AOS
File Number => 4 ASCII digit number to indicate the sequence of the file in the segmented series of files for a particular pass = (0001 - 9999) NOTE: Does not be applicable for USN archived data files and is not used in the file name conventions
extension => 4 ASCII characters, vcnn; where nn = 01, (to represent the Virtual Channel 1)

For example, for an LRO pass that began on DOY 223 at 12:15:07 in the year 2008, where the data was received from High data-rate receiver #2, and the segment time is set to 3600 seconds (as is expected for LRO), the archived VC01 filename would be:

WS1S_0059_rcp2_2008223121507_0001.vc01

If there were multiple files associated with one pass, the files would be named as follows: WS1S_0059_rcp2_2008223121507_0001.vc01 WS1S_0059_rcp2_2008223121507_0002.vc01 WS1S_0059_rcp2_2008223121507_0003.vc01 WS1S_0059_rcp2_2008223121507_0004.vc01

For an LRO VC1 Archive file captured at the Dongara station that began on DOY 223 at

21:12:50 in the year 2008,, the file name would be identified as: USPS_0059_REC1_2008223211250.vc01

4.2.5 (WS1-12) (WS1-13) Archived Telemetry Data File

This interface consists of the downlinked data that are stored in a file format at a station upon receipt of any telemetry that is downlinked in either VC2 or VC3. These data are stored with the fill data (VC63) removed. These files are stored at the ground station using their local storage functionality; this storage takes place before the data are routed to the LRO SDPS. The files are stored for up to seventy-two (72) hours in the event of a possible retransmission to the LRO MOC upon request by the LRO operations team; this would normally be considered within a contingency support concept.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.2.5.1 Details
Time interval Variable based on specified Data collection filters and per APID for any data downlinked via VC2 or VC3
File duration Based on station contact interval WS1 file duration limited to 60 minutes
File or Data Generation Frequency 1:N files per station contact
Delivery method (real-time, SCP, FTP, etc) MOC scp pulls the data from the WS1 Data Storage System
Data Volume Variable; based on APIDs and downlink rate
Accuracy (if it applies) NA; based on data mnemonics for specified APIDs
Other pertinent details WS1 archive data for 72 hour retention

4.2.5.2 Format

The Archived Telemetry Data File is stored with the VC63 (fill data) removed. The station archives the data stream (the downlinked VCDUs) with attached frame sync. Only good quality frames are recorded and all R-S check symbols are removed. The archive files that WS1 creates are based on configurable time duration; this configurable duration is set for the LRO mission at 60 minutes. However, the LRO MOSP, 431-PLAN-000050, will finalize the details of this file size duration and identify any instances when and how the MOT could request a different file size limit.

A sample Archived Telemetry Data File is a binary file of the downlinked telemetry data; as such, no sample product is listed in Appendix B.

An Archived telemetry data file name is identified with the following naming conventions:

<SID>_<SIC>_<Data Source>_<Scheduled AOS Time>_<File Number>.vcn; where

SID => 4 ASCII Characters for the station ID = WS1S for White Sands

SIC => 4 ASCII Digits to identify the spacecraft ID = 0059

Data Source => 4 ASCII characters the source of the data as provided by the MCS = HDR1 or HDR2

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Schedule AOS time => 13 ASCII characters in the form of YYYYDOYHHMMSS, where

YYYY – start year designator (2008 – 2013) DDD – start day of year (0 – 366) HHMMSS – Hours, Minutes and seconds of AOS

File Number => 4 ASCII digit number to indicate the sequence of the file in the segmented series of files for a particular pass = (0001 - 9999)

extension => 4 ASCII characters, vcnn; where nn = 00, 01, 02, or 03 (to represent the virtual Channel ID)

For example, for an LRO pass that began on DOY 223 at 12:15:07 in the year 2008 and where VC2 data are received from High data-rate receiver #1, and the segment time is set to 3600 seconds (as is expected for LRO), the filename would be:

WS1S_0059_HDR1_2008223121507_0001.vc02

If there were multiple files associated with one pass, the files would be named as follows: WS1S_0059_HDR1_2008223121507_0001.vc02 WS1S_0059_HDR1_2008223121507_0002.vc02 WS1S_0059_HDR1_2008223121507_0003.vc02 WS1S_0059_HDR1_2008223121507_0004.vc02 An Archived VC3 telemetry data file is not shown as an example since it follows a similar file name concept.

4.2.6 (WS1-6) (WS1-7) (USN-4) (USN-5) (SN-1) Real-time Orbiter Telemetry Data

This is the real-time data stream that is sent from the stations to the LRO MOC during a real-time station contact; the data stream consists of the Virtual Channel Data Units (VCDUs) that the Orbiter downlinks during this support. The real-time data are Reed-Solomon decoded by the station prior to the transfer to the LRO MOC. This interface applies for both the real-time VC0 and the VC1 data that are downlinked during the station contact.

4.2.6.1 Product Details

Time interval Variable based on Orbiter VC0 or VC1 Data collection filters and per APID
File duration NA
File or Data Generation Frequency NA
Delivery method (real-time, SCP, FTP, etc) Real-time TCP socket connection MOC-ITOS issues connection requests to SN, DSN, and WS1 USN stations issue connection requests to MOC-ITOS

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Data Volume Variable; based on APIDs and downlink rate
Accuracy (if it applies) NA; based on data mnemonics for specified APIDs RF link is operating at nominal conditions as per the RF ICD
Other pertinent details The station performs R-S decoding and only ships VC0 data that passes the R-S decoding; the station will not send any data that fails the R-S decoding.

4.2.6.2 Format

The real-time data product for the virtual channel (VC) format is defined in the LRO Telemetry and Command Formats Handbook (LRO-HDBK-000052). The station inserts the VCDUs into a structure that has a SMEX/LEOT header.

This interface is the real-time VC telemetry stream that contains the downlinked telemetry in the VCDUs; this is a stream of binary data and as such, will not be represented in the Appendix B.

4.2.7 (WS1-1) (USN-1) Station Status Packets

This interface consists of status packets, which contain the general station status information, the downlink performance related to data quality, data statistics, RF status, and uplink time. This information is sent in a CCSDS fixed data packets; each station is assigned a unique APID to provide this station status packet data.

4.2.7.1 Product Details

Time interval Every 1 second for all WS1 and USN sites
File duration NA
File or Data Generation Frequency Status Packet delivered Every 1 second as noted above
Delivery method (real-time, SCP, FTP, etc) Real-time TCP socket connection from station to the prime MOC-ITOS
Data Volume 88 bytes per status packet for the USN Station Status Packets 236 bytes for WS1 Station Status packets
Accuracy (if it applies) NA; based on data mnemonics for specified APIDs
Other pertinent details NA

4.2.7.2 Format

The Station Status Packets contains the real-time quality and monitoring statistics for the telemetry and command functions. The data statistics are contained within a standard CCSDS packet and defined as a standard APID so that the LRO T&C system (ITOS) can decommutated the packet and display the monitor information.

These station status packets are formatted within the standard CCSDS primary packet header (6 bytes) and secondary packet header (6 bytes). These CCSDS primary and secondary packet headers are defined within the CCSDS Blue Book; they will not be re-referenced here.

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These data quality statistics are reset before the next station contact. The station status packets are identified by APIDs in the LRO Telemetry and Command Handbook - Database (431HDBK-000053) and are binary data packets; as such, no sample product is provided in Appendix

B.

The USN ICD 1A00846, USN to LRO ICD, is the governing document for the content of the USN stations status packets. The WS1 ICD (453-ICD-GN/WS1) is the governing document for the WS1 Station Status packet definition.

4.2.8 (WS1-2) (USN-2) Weather Data

This file contains the weather information per pass, such as the temperature, barometric pressure, and relative humidity, and wind speed collect during the WS1 or USN station contact.

4.2.8.1 Product Details

Time interval Data sampled every 5 minutes
File duration Based on station contact times
File or Data Generation Frequency Every station contact
Delivery method (realtime, SCP, FTP, etc) scp post pass from supporting station to LRO MOC MOC scp pushes the data to the LOLA SOC
Data Volume ~ 5 Kbytes per file
Accuracy (if it applies) Temperature accurate to tenths of a degree Celsius Pressure accurate to tenths of a millibar of pressure Relative humidity accurate to the tenths of a percentage point Wind speed accurate to the nearest whole value in Kilometers per hour
Other pertinent details NA

4.2.8.2 Format

The Weather data are an ASCII formatted, space-delimited, information sent in a file format. It consists of multiple lines in which the first line contains start date (YYYYMMDD), Day of Year (DDD), and station identifier information and then there are 1:N repeating lines that provide the following information: Time reference, temperature, Pressure, Relative Humidity, and Wind Speed

The following table defines the format of the weather file product:

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Field name Field Characteristics
First Line of File
Date/Day of Year/Station Identifier 17 ASCII Characters with the following format: YYYYMMDD DDD NNNN; where: YYYYMMDD, defined as YYYY => 4 ASCII digits of year (2008 – 2013) MM => 2 ASCII digits for the month (01 – 12) DD => 2 ASCII digits for the day (01 – 31) DDD => 3 ASCII digits for day of year (1 – 366) NNNN => 4 ASCII Characters for the Station Identifier (e.g., WS1S for White Sands 1 Ka/S-Band Station USPS = USN Dongara USHS for USN Hawaii KI3S for Kiruna, Sweden WG1S for Wilheim, Germany
Repeating Lines (1:N) of File
Time Reference (UTC Formatted) => 5 ASCII characters with the following format: HH:MM; where HH => 2 ASCII digits for hours (01- 23) MM => 2 ASCII digits for minutes (00-59)
temperature (in Degrees Celsius)) 5 ASCII characters; First ASCII Character is the sign indicator of the temperature; where BLANK = positive temperature - = Negative temperature Next 2 ASCII Character represent the whole temperature value (0 -99) Next character is the decimal point separator (.) Last 1 Character is the tenths of a degree temperature (0 – 9)
Barometric Pressure (in millibars of Mercury) 6 ASCII characters; 4 ASCII Character represent the whole value of pressure (0000 -1200); with leading zeros, if necessary Next character is the decimal point separator (.) Last 1 Character is the tenths of the pressure (0 – 9)
Relative humidity (%) 5 ASCII characters with the following definition 3 ASCII Character represent the whole value of relative humidity (000 -100); with leading zeros, if necessary Next character is the decimal point separator (.) Last 1 Character is the tenths of a percentage of the relative humidity (0 – 9)
Wind Speed (Km/Hr) 2 ASCII Digits represent the whole value of wind speed (00 - 99)
Note1: In the field definition above, all fields are a fixed number of characters; leading zeroes (or blanks) should be used where appropriate. An ASCII space is inserted between each of the defined fields for the repeating line elements. NOTE2: For condition where there may be invalid weather data or no weather data for any particular sample period, the option is to skip the entry for that sample period.

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Table 4-25 Station Weather Data Field Definitions

The file name has the following naming convention: <Station ID>_<Station AOS Contact Time>.wea Station ID => 4 ASCII Characters for the station ID

WS1S = White Sands USPS = USN Dongara USHS = USN Hawaii KI3S = Kiruna, Sweden WG1S = Wilheim, Germany; followed by the

underscore (_) character

Schedule AOS time => 12 ASCII Digits in the form of YYYYDOY_HHMM, where

YYYY – start year designator (2008 – 2013) DDD – start day of year (0 – 366) HHMM – Hours and Minutes of AOS

HH = (00 – 23)

MM = (00 – 59) Note: There is an underscore (_) separator between the DDD and the HH fields

extension => 3 ASCII characters, wea (to represent this is a weather file); file extension is represented as lower-case letters

For example, the file name for the weather product from White Sands has the following file sample: WS1S_2009040_0824.wea.

A sample Weather Data file is provided as a reference in Appendix B, Figure B.2-2.

4.2.9 (WS1-3) (WS1-4) Ka-Band Telemetry

This interface is the real-time data stream consisting of either the VC2 or VC3 VCDUs, which the WS1 high-rate data receiver (HDR) transfers through the Data Storage System to the LRO Station Data Processing System. This product consists of VCDUs with frame sync mark and are transferred from the DSS to the DPS via a socket connection.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.2.9.1 Product Details
Time interval Variable based on Instrument VC2 or VC3 Data collection filters
File duration NA
File or Data Generation Frequency VC2 and VC3 VCDUs delivered as received from Orbiter during ground station contact
Delivery method (real-time, SCP, FTP, etc) Real-time socket from station High Rate Data Receiver to LRO Station DPS element
Data Volume Variable
Accuracy (if it applies) NA
Other pertinent details The WS1 Data Storage System filters any data that fails the Reed-Solomon decoding checks; The station DPS only receives good quality data.

4.2.9.2 Format

The Ka-Band Telemetry Data are a composite of VCDUs received at the station and transmitted to the SDPS element. The VCDUs are composed of specific APIDs for each science instrument. The VCDU formats the underlying APIDs are defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053); these products are binary data packets and are not shown as a sample product in Appendix B.

4.2.10 (WS1-8) Ka-Band RF Receiver Data

The Ka-Band RF Receiver Data are the RF Strength data from Ka-Band receiver that will be used for HGA calibration.

4.2.10.1 Product Details

Time interval Data samples provided at 1 Hz frequency during WS1 Ka Band station contact
File duration Variable, based on Ka-band contact (20 – 60) minutes
File or Data Generation Frequency Every WS1 station contact during the HGA Cal phase Nominally during Orbiter commissioning; might be 1-2 times during normal operations, if required
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC at the completion of the station contact
Data Volume Variable based on station contact duration; approx 200 Kbytes for a 20 minute duration contact
Accuracy (if it applies) Receiver strength accuracy is identified by the intrinsic 32-bit floating point value that provides the receiver strength Timetag accurate to 0.1 second
Other pertinent details NA

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4.2.10.2 Format

The Ka-Band RF Receiver Data File is an ASCII formatted file in which commas separate the fields within the file. The file contains multiple data records, which is formatted as an ITOS-like sequential print file.

The 1:N lines of data records have the following details as identified in the following table. .

Table 4-26 WS1 Ka-Band Receiver Data Field Definitions

Field name Field Characteristics
APID [5 ASCII Digits]; defaults to 00000
Separator [1 ASCII Character]; a comma character to separate the APID from the time tag field
Date, Time Field [24 ASCII digits and characters to identify the UTC time stamp for the data; formatted as: YYYY-DOY-HH:MM:SS.mmmuuu; [8 ASCII digits/characters for the year and day of year; the 2 fields are separated by the hyphen (-) character [15 ASCII Digits/Characters] to identify the hours, minutes seconds, and milliseconds and microseconds for the time stamp; fields are separated by the colon (:) or period (.) designators
Separator [1 ASCII Character]; a comma character to separate the time tag field from the first mnemonic
Mnemonic Name for KA-Band Receiver Strength [11 ASCII Characters] Default to GSHDRIFLVL1
Separator [1 ASCII Character]; a comma character to separate the first mnemonic from the first blank field
Blank Field [3 ASCII Characters] default to 3 ASCII spaces
Separator [1 ASCII Character]; a comma character to separate the first blank field first from the mnemonic data value
Mnemonic Value for Ka-Band Receiver Strength [13 – 14 ASCII Digits/characters] representation of the Ka-Band Receiver data; encoded in a representation, between -128 to 127 dBm; in the form of: -nnn.mmmmmmmmm to nnn.mmmmmmmmm; includes the leading minus sign for negative values and a blank for positive values (See Note 1)
Separator [1 ASCII Character]; a comma character follows the last field in the data record
Note 1: value is accurate only to approximately 6 decimal digits of precision.

A sample Ka-Band RF Receiver Data file is provided as a reference in Appendix B, Figure B.2

3. The sample file naming format is identified as Follows:

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<Station Name>_<Data Source>_<Station AOS>.<karf>, where:

Station Name => 4 ASCII Characters for the station name followed by an underscore; = WS1S to denote the White Sands station; followed by the underscore (_) character
Data Source => 4 ASCII characters the source of the data as provided by the MCS
= HDR1 or HDR2 for the White Sands stations; followed by the underscore (_) character
Scheduled AOS Time => YYYYDOYHHMM; followed by a period; where YYYY is the 4 digit year representation (2008 – 2013) DOY is the 3 digit representation for day of year (1 – 366) HHMM is the 4 digit scheduled AOS time for that specific station contact (24 Hour time reference; e.g., 0000 to 2359)
extension => 4 ASCII characters
karf; used to represent this file represents Ka-band RF receiver status data; the file extension is represented in lower case letters

For example, for an LRO pass that began on DOY 333 at 12:15:07 in the year 2008, where the White Sands’ High Data-Rate receiver #2 provided the source of the data, the filename would be identified with the following naming convention:

WS1S_HDR2_20083331215.karf

4.2.11 (WS1-14) (WS1-16) Raw Telemetry File Data

This interface consists of the data downlinked using either the VC2 or VC3 channel that are stored in a file format at a station upon receipt of the corresponding instrument telemetry. These data are stored with the fill data (VC63) removed. These files are the transmitted products between the SDPS, located at the WS1 station, and the LRO MOC. These files are the raw data files as they existed on board the spacecraft.

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4.2.11.1 Product Details

Time interval Variable based on VC2/VC3 Data collection filters and per APID from any file that the MOT commanded down using VC2/VC3
File duration Variable, based on 1MByte, 1 hour, or instrument commanded limits
File or Data Generation Frequency Every WS1 KaBand Station contact
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC
Data Volume Variable; based on file durations as defined above
Accuracy (if it applies) NA, based on specific data product and mnemonic values as defined in T&C Handbook
Other pertinent details NA

4.2.11.2 Format

The Raw Telemetry File Data is formatted to contain a series of Virtual Channel Data Units (VCDUs) for that specific VC. The VCDU format and the file naming conventions are defined in the LRO Telemetry and Command Formats Handbook (LRO-HDBK-000052).

This file contains the selected APIDs downlinked via the VC2/VC3 channel. This file contains the data in a binary format; as such, no sample product is provided as a reference in Appendix B.

4.2.12 (DSN-1) DSN Tracking Data

The DSN Tracking Data File provides the LRO Flight Dynamics Facility with the data required to support tracking of the orbiter and generation of orbit and mission products.

4.2.12.1 Product Details

Time interval Data (Range point) collected every 40 seconds
File duration NA
File or Data Generation Frequency Every DSN station contact
Delivery method (real-time, SCP, FTP, etc) Near Real-time socket using UDP/IP protocols to FDF (SFDU format) via Closed IONet
Data Volume Variable
Accuracy (if it applies) Based on TRK-2-34 format
Other pertinent details DSN, which supports LRO through the 34 meter subnet, will provide this data such that it is consistent with the TRK-2-34 format.

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4.2.12.2 Format

This data will be consistent with DSN formatted tracking data as identified via the TRK-2-34 format. The data product is a binary file and as such, no sample product is provided in Appendix

B.

4.2.13 (DSN-2) (DSN-3) Real-time Telemetry Data

The real-time data consists of the orbiter housekeeping telemetry data packets that the spacecraft downloads to the DSN station in real-time. This interface consists of the downlinked packet data that are transferred with the fill data (VC63) removed.

The SLE service uses three types of messages using a common format for exchange of data over an established TCP connection:

  • An SLE PDU message for transfer of SLE PDUs;

  • A context message to transmit initialization parameters;

• A heartbeat message periodically used to probe an idle TCP connection. The following figure identifies the SLE structure for the telemetry interfaces with the LRO MOC.

The following table identifies the fields used within this figure:

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Table 4-27 SLE Telemetry Header Structure Definitions

Field Representation
Type ID 8 bits that identify the SLE Message PDU type =1 represents an SLE PDU Message =2 represents a Context Message =3 represents a Heartbeat Message
Reserved 24 bits, reserved and set to all zeros (0)
Length (octets) 32 bits that provide the message body length; represented as a binary unsigned integer value
Message Body 1:N 32 bit octets of PDU message data

The MOC issues a “Return Channel Frames (RCF)” to request a selective return of either VC0 or VC1; the MOC would issue 2 RCFs Service Binds to request DSN to return VC0 and VC1 as two separate connections. The LRO MOC will request the “online timely” option for the VC0 data transfer from DSN. The “online timely” description implies that the currency of the data is more important than its completeness. The LRO MOC will request the “online complete” option for the VC1 transfers from DSN. The “online complete” implies that the completeness of the data is more important than its currency. LRO and DSN have negotiated all other bind options for the service instance identifier, such as IP addresses, port numbers, destination and host machines. The LRO and DSN operations teams control these values; the DSN Operations team fully tests the service instances before entering them into the operational environment. The LRO MOC will first issue a bind request using the type ID =2; the message body will contain the heartbeat interval and dead factor and described within the DSN telecommand document, DSN 820-013 0163-Telecomm Interface Document. That document identifies the information that the MOC would use to instantiate the SLE connection with DSN. After a successful RCF SLE Bind connection and an associated RCF Start request, the LRO MOC will wait for DSN to send the SLE PDU messages.

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4.2.13.1 Product Details

Time interval Variable based on VC0 or VC1 Data collection filters and per APID
File duration NA
File or Data Generation Frequency Every DSN station contact SLE using either the Return all Frames (RAF) or Return Channel Frames (RCF) option
Delivery method (real-time, SCP, FTP, etc) Real-time socket to LRO MOC from JPL telemetry recorder Near real-time as the data are received
Data Volume Variable
Accuracy (if it applies) NA
Other pertinent details SLE formatted data stream.

4.2.13.2 Format

The Real-time VC0 Telemetry Data are formatted to contain a series of Virtual Channel Data Units (VCDUs) for VC0. The VCDU format is defined in the LRO Telemetry and Command Formats Handbook (LRO-HDBK-000052).

Since this is a stream of real-time packets, which are sent in a binary format consistent with the LRO Telemetry and Command Formats Handbook (LRO-HDBK-000052), and via the CCSDS SLE interface. There are no sample products listed in Appendix B; the user may reference DSN 820-013 0163-Telecomm interface document for additional details.

4.2.14 (DSN-5) (DSN-6) Archived Telemetry Data

Nominally, DSN delivers both the VC0 and VC1 data to the LRO MOC in near real-time. The DSN station also stores the downlinked data for up to 72 hours in the event that the LRO MOT requests a retransmission of the data; this would normally be considered within a contingency support concept.

This interface consists of the downlinked data that are stored in a file format at the DSN upon receipt of the real-time spacecraft housekeeping telemetry. These data are stored with the fill data (VC63) removed.

This interface is for a contingency request to retransmit specified data after the original station contact. The MOT would request a post-pass transfer of data from the DSN’s storage facility. This request is treated as another “real-time” connection to transfer a specified set of APIDs. The MOC would request a RCF Service Bind option (for a specified channel) and would identify a specified time interval. This offline transfer assumes that DSN provides a complete set of data in the post-pass transfer.

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4.2.14.1 Product Details

Time interval Variable based on VC0 or VC1 Data collection filters and per APID
File duration NA
File or Data Generation Frequency Can be accessed for every DSN station contact
Delivery method (real-time, SCP, FTP, etc) As requested by MOC (Post-pass) using Real-time socket to LRO MOC SLE using Return Channel Frames (RCF) option
Data Volume Variable
Accuracy (if it applies) NA
Other pertinent details SLE formatted data stream. From the archived file

4.2.14.2 Format

The Archived Telemetry Data File is stored at JPL’s storage facility as it is received from the station with VC63 (fill data) removed. The format of this data contains VCDU formatted APIDs and is defined in the LRO Telemetry and Command Formats Handbook (LRO-HDBK-000052).

A sample Archived Telemetry Data File is a binary file of the downlinked telemetry data; as such, no sample product is listed in Appendix B; the user may reference DSN 820-013 0163Telecomm interface document for additional details.

DSN returns the Archived telemetry data via a socket connection to the LRO MOC as an off-line data transfer; this transfer is similar in nature to the real-time data delivery, except that it occurs post-pass and the LRO MOC’s initiating telemetry and command system might not be the prime telemetry and command element. DSN routes the archived Telemetry data back to the LRO MOC via the CCSDS SLE interface.

4.2.15 (DSN-4) DSN Station Monitor Packets

This interface consists of the DSN status packets, which contain the general station information, the downlink performance related to data quality, data statistics, RF status, and uplink time.

4.2.15.1 Product Details

Time interval Every 5 seconds
File duration NA
File or Data Generation Frequency Every DSN station contact
Delivery method (real-time, SCP, FTP, etc) Real-time UDP socket to LRO MOC

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Data Volume Variable
Accuracy (if it applies) Based on DSN-MON-0158 documentation
Other pertinent details Based on DSN-MON-0158 documentation Quality Status reset before next station contact DSN Quality statistics are defined per antenna pad identifier, not just a station qualifier

4.2.15.2 Format

The DSN Station Status Packets contain the data as specified by the DSN MON-0158 format. For each DSN station contact, the station provides the data quality statistics, as listed in DSNMON-0158) every 5 seconds. The station status packets are encased within Standard Formatted Data Units (SFDU) Block.

These data quality statistics are reset before the next station contact. Since the data sent as a binary form, no sample product is reference in Appendix B.

4.3 SCIENCE OPERATION CENTER PRODUCTS AND DESCRIPTIONS

This section contains the interface products generated by the seven SOCs. These products are all sent to the LRO Mission Operations Center. The LOLA SOC transmits the LOLA Improved Gravity Model to the Flight Dynamics Facility, and to the LRO MOC, to assist in the improved orbit determination process. Each science center has its own unique subsection to define the specific products that the SOCs generate and send to the MOC.

For products that the SOCs generate, they are normally identified as either command files or specific instrument command sequences; these are command products that need to be sent to the MOC for uplink to the corresponding instrument.

4.3.1 (CRaTER-1) (DLRE-1) (LAMP-1) (LEND-1) (LOLA-1) (LROC-1) (MIRF-1) LRO Operations Activity Request

This is the LRO Operations Activity Request, which any SOC can use to identify routine requests of standard activities, such as commands, instrument procedures activation, ground support, or any other features that the SOC and LRO MOC have identified as possible routine operations that have been thoroughly checked and validated during the instrument integrations and test phase.

Each SOC generates the LRO Operations Activity Request and forwards the inputs to the LRO MOC. The MOT merges any SOC Activity Requests with command input for the spacecraft and orbiter health and safety commands and any specific maneuver commands based on mission profile support phases.

If the activity requests contains any commands, the commands in the file must be defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053). If the command contains submnemonics, they must be specified with the command.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.3.1.1 Product Details
Time interval NA
File duration NA
File or Data Generation Frequency File delivered 48 hours prior to the requested activity, assuming the activity currently exists. Otherwise best effort based on time required to generate new procedures or test new instrument commands. Additional time required if SOC delivers via backup protocol
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC Backup is via Fax/email
Data Volume Variable; based on contents, but nominally less that 1KBytes
Accuracy (if it applies) NA
Other pertinent details NOTE: The time interval will be relaxed if the request is based on an Orbiter anomaly

4.3.1.2 Format

The Activity Request File is intended to capture all information necessary to execute the activity described. All fields identified are required, if a field is not required enter “NA”, this includes the initial submission of an activity request number field. The following sections describe each field. A linefeed character terminates each field. The following table identifies the file contents and provides additional information on the data entered for each field

Table 4-28 LRO Operations Activity Request Definitions

Field name Field Characteristics
OAR Request Date Date when the requestor submitted the OAR to the MOC; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -31) with leading zeros The OAR requestor is required to enter this field.
OAR Approved Date Date when the MOT approves the OAR to the MOC; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -31) with leading zeros The OAR requestor should enter NA for this field.

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Field name Field Characteristics
OAR Planned Execution Date This field will contain the MOT identified expected date when the OAR is expected to execute; in yyyy-mm-dd format; where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -31) with leading zeros The OAR requestor should enter NA for this field.
OAR Status This field contains the indication as to whether the MOT has accepted/rejected the OAR; the MOT completes this field The OAR requestor should enter NA for this field.
OAR Status Detail This field contains the explanation if the MOT “rejects” OAR; otherwise, the MOT enters an NA The OAR requestor should enter NA for this field.
OAR Name This field contains the name of the activity that the SOC is requesting. The field is a short description of the activity. When possible, this field should identify an existing LRO Flight Procedure Document. The OAR requestor is required to enter this field.
OAR Number This field is intended for tracking purposes. The MOT assigns the OAR number when received. The MOT will assign numbers for both approved and unapproved OARs. The OAR requestor should enter NA for this field.
OAR Requested By Name of person making the request. The LRO Operations Agreement with each organization will identify the individuals, a primary and backup. The MOT will only act on requests submitted by those individuals identified in the approved LRO Operations Agreement The OAR requestor is required to enter this field.
OAR Requestor Phone Number The OAR Requestor must provide a telephone number in this field. As the MOT reviews and implements the request, the MOT will contact the requestor at the telephone number provided to answer any questions regarding the request. The OAR requestor is required to enter this field.
OAR Requestor Email Address The Requestor must provide an email address in this field. The MOT will send an email to this address and all email addresses on record for this requesting organization, which verifies MOT receipt of the OAR. The MOT will send another email when the OAR is approved or rejected The OAR requestor is required to enter this field.
OAR Request Org The Requesting organization indicates the affiliation of the person requesting the change The OAR requestor is required to enter this field.

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Field name Field Characteristics
OAR Type The activity type field gives an indication to the MOT as to which area is affected by the request. One of the following types: GROUND OPERATION – activity will affect only ground assets; e.g., requesting the MOT to generate a specific product INSTRUMENT OPERATION – activity will affect the instrument; e.g., sending a command, updating a FSW Table, downlinking a specific memory location SPACECRAFT OPERATION – activity will affect the spacecraft; e.g., sending specific commands, updating C&DH flight software or changing a table onboard the spacecraft The OAR requestor is required to enter this field. NOTE: The SOCs should NEVER use the SPACECRAFT OPERATIONS type. The only allowable values in the SOC-generated OAR are GROUND OPERATION or INSTRUMENT OPERATION.
OAR Execution Window This field identifies the window for when the SOC requests execution of the requested activity. The OAR requestor can supply one of the following valid inputs: NA NET yyyy-mm-dd; NLT yyyy-mm-dd where yyyy = 4 digit year designation (2008 – 2013) mm = 2 digit month designator (01 – 12), with leading zeros dd = 2 digit day of month designator (01 -31) with leading zeros NOTE: The MOT will schedule the request at the next available opportunity if the requestor enters an ‘NA’ in this field.
OAR Constraints 1:N lines of free form text describing constraints for executing activity, e.g. Only during eclipse The OAR constraints field identifies to the MOT limitations on when the activity may be executed. In most instances, flight procedure documents will identify constraints related to the operation. If additional constraints are required, they should be included in this field. The OAR requestor can either supply NA or enter a valid constraint data into this field.
OAR Sequence This field specifies the activity to be executed. The MOT will execute the activity according to the instructions provided. Instructions can be as simple as execute Flight Procedure XYZ at next available ground station contact. When the Flight Procedure already exists and is approved for operational use, the MOT will execute the procedure at the time specified. When it is necessary to execute the activity at a specific time, the Requestor should identify absolute times in the format of YYYY-DOY-HH:MM:SS for each step in the activity where applicable. All absolute times in this field shall be represented in Coordinated Universal Time (UTC). The OAR requestor is required to enter this field.

A sample LRO Operations Activity Request is provided in Appendix B, Figure B.3-1. 4-116

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The following file-naming convention is used for files transmitted between the various SOC facilities and the LRO MOC. The filename consists of up to 22 characters; it also contains a three -character file extension name. There is an underscore (_) between the first four fields and a period (.) between the last two fields. The form of the filename is as follows:

<FILENAMEDESIGNATOR>_YYYY_DOY_NN.<file extension>

where File name designator = [8 – 10 characters] CRAT_OAR for CRaTER DLRE_OAR for Diviner LAMP_OAR for LAMP LEND_OAR for LEND LOLA_OAR for LOLA LROC_OAR for LROC MINIRF_OAR for Mini-RF
Date = YYYY_DOY; where
YYYY = 4ASCII digits for year DOY – 3 ASCII digits for day or year NOTE: Date field identifies when SOC generated request
Version = NN; where nn= 2 ASCII Digits to reflect the version number; first version = 01
file extension = [3 characters] Standard file extension for all text input files received from SOC;

txt to indicate that the file is text information A sample LRO Activity Request file name for each of the SOCs is provided:

CRaTER SOC CRAT_OAR_YYYY_DOY_NN.txt
DLRE SOC DLRE_OAR_YYYY_DOY_NN.txt
LAMP SOC LAMP_OAR_YYYY_DOY_NN.txt
LEND SOC LEND_OAR_YYYY_DOY_NN.txt
LOLA SOC LOLA_OAR_YYYY_DOY_NN.txt
LROC SOC LROC_OAR_YYYY_DOY_NN.txt
MINI RF SOC MINIRF_OAR_YYYY_DOY_NN.txt

4.3.2 (LOLA-5), (LROC-4), (MIRF-4) Target Request

This is file that contains target request from the specified SOC to perform imaging; the MOC uses this information to develop the attitude slew plan, which is eventually incorporated into the composite command load.

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The SOC-generated target requests contain the information related to when the SOC is requesting an off-nadir slew, the corresponding slew angle and time durations at the off-nadir slew.

4.3.2.1 Product Details

Time interval NA; based on when off-nadir requests are scheduled
File duration Up to 3-4 days of future target requests (current day to current day + 4)
File or Data Generation Frequency Daily; NLT Noon local
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC
Data Volume Variable; based on contents, but nominally less that 1KBytes
Accuracy (if it applies) Target time and duration accurate to 1 second Off-nadir angle accurate to .01 degree
Other pertinent details File delivered no later than noon, Eastern for scheduling the first day’s command sequences into the command uplink

4.3.2.2 Format

The file is a comma-delimited, ASCII file that contains the time of the requested target, a corresponding off-nadir angle, and a time duration for staying off-nadir; the fields are defined in the following table:

Field name Field Characteristics
Timetag: year day of year and time of day YYYY-DDD–HH:MM:SS, (Time is UTC time representation), where YYYY => 4 ASCII digits of year (2008 – 2013); followed by the hyphen (-) character DDD => 3 ASCII digits for day of year (1 – 366); followed by the hyphen (-) character HH:MM:SS => 6 ASCII digits, separated by the : (colon) character; used to represent the hours, minutes, and seconds of day
Off-nadir angle 7 ASCII Characters representing the targeted off-nadir angle; where first character is a positive/negative sign indicator (+ or -) Next 2 characters represent the whole value of angle (0 to 90) Next character is the decimal separator Next 3 characters represent the decimal portion for the angle (0 – 999)
Off-nadir duration Up to 5 ASCII Characters representing the duration (in seconds) for the off-nadir angle; where 5 characters represent the duration time (in seconds) (0 – 99999)

The following file-naming convention is used for files transmitted between the LROC SOC and the LRO MOC. The filename consists of 25 characters; it also contains a three-character file extension name. There underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<YYYYDOY>_<yyyydoy>_<version number>.<file extension>

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where instrument id = [4 characters] LROC for the LROC SOC LOLA for the LOLA SOC MINI for the MINI-RF SOC

file content = [7 characters] Intent of the command load. TARGETS

Start Date = YYYYDOY where YYYY => 4 ASCII digits of year (2008 – 2013) DOY => 3 ASCII digits for day of year (1 – 366) Note: DOY represents the start time of data within the file, not the file creation time

Stop Date = yyyydoy where yyyy => 4 ASCII digits of year (2008 – 2013) doy => 3 ASCII digits for day of year (1 – 366) Note: DOY represents the stop time of data within the file, not the file creation time

version number = [3 characters] V, followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.

file extension = [3 characters] Standard file extension for all input files received from SOC; it will be named for the input file type:

txt => for textual files A sample file name for an LROC generated target request is defined as LROC_TARGETS_2009131_2009133_V00.txt.

Similarly, both MINI-RF and LOLA would have a similar file name concept with their specific instrument ID as noted in the above table (e.g., LOLA_TARGETS_2009147_2009149_V01.txt or MINI_TARGETS_2009150_2009152_V00.txt

A sample Target Request is provided in Appendix B, Figure B.3-2.

4.3.3 (DLRE-2) (LAMP-2) (LOLA-3) (MIRF-2) Instrument FSW Load

This file contains the FSW image and tables for the specified instrument; it contains the tested and verified files that the SOC will send on an as needed basis, as required to correct/update instrument Flight Software table and/or files.

The corresponding SOC facility generates its unique FSW load request and forwards the image file to the LRO MOC.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.3.3.1 Product Details
Time interval NA
File duration NA; FSW Load contains no time frame data
File or Data Generation Frequency As needed to meet needs of SOC group to upload new instrument loads
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC
Data Volume Variable; based on contents, but nominally less that 64 KBytes
Accuracy (if it applies) NA
Other pertinent details File delivered 2-3 days prior to requested uplink to allow sufficient time to verify load against the FLATSAT simulator The DLRE FSW Load is rate buffered based on a parameter provided within the FSW Load file (Data Record #2); see below

4.3.3.2 Format

The Instrument FSW Load consists of the complete file/table image to be re-loaded, or a starting address, number of bytes to load and then the new table/file image portion.

In a load file, comments begin with either semi-colon (;) or hash (#) and continue to the end of the line. The MOC’s T&C system ignores any blank lines and lines containing only comments. The first non-blank, non-comment line is the abstract record; this is copied to the formatted image load file but otherwise ignored. It is intended as a comment to identify the load file name.

Figure 4-7 provides a representation of each field within an Instrument FSW Load file. As noted in this figure there are several lines at the start of the load file that provide reference information related to the file name and other mission or instrument specific processing parameters. There may be several comment lines as listed in the figure, but these lines are not required and as noted above, the LRO T&C system will ignore these lines.

The remainder of the file contains the load image in a hexadecimal data form; the load data begins with the “X” and must contain an even number of hex data characters. The lines are terminated by the line feed (LF) character; the load image data lines can have an optional semicolon (;) character, which are used to provide any additional comments. The line then terminates with the LF character. The LAMP Flight SW Load contains an extra space after the last hexadecimal data character and just prior to the semi-colon and LF characters.

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Table 4-29 provides a more detailed explanation of each field as noted within the above figure.

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Table 4-29 Instrument FSW Load Directive File Data Definitions

Parameter Name Parameter value
File name The SOC-generated ASCII File name corresponding to Instrument FSW Load file as defined in the following table below
mission name This field is ignored by the ITOS LOAD directive. Set to LRO
image ID This field is ignored by the ITOS LOAD directive. Load ID
Date Copied to the formatted image load file but otherwise ignored. UTC Time of the of the Load generation
Version This field is ignored by the ITOS LOAD directive. Numerical value
Source This field is ignored by the ITOS LOAD directive. This is the location for the Load such as RAM or EEPROM DLRE could set this field to the following possible values: “INRAM”, “XRAM”, and “SCANTABLES”
Pkt size Maximum packet size. When the LOAD directive formats the raw image load file into packets, this is the maximum number of data bytes in each packet. The SOCs provide this value in a hexadecimal representation DLRE should set this field to a decimal value of 240; hex = 00F0
swap Indicates whether or not the LOAD directive should swap bytes when generating the formatted image load file. Byte swapping is only performed if this field has one of the values SWAPBYTES or UI085. NOTE: SWAPBYTES is the preferred value; the SOCs could use UI085, but it is a non-standard usage. The SOCs should sue the term NOSWAP to result in no byte swapping; however, any value other than SWAPBYTES or UI085 results in no byte swapping.
Data Size An optional field, which gives the size in bytes of data items to be loaded; can be ‘1’, ‘2’,’4’ This option controls how the load program sets the ADDRESS or OFFSET and NUMBYTES fields in the load command. For DLRE, this field is set to an empty value
Rate Specifies the uplink rate at which the MOC will forward load directive commands to the spacecraft, to be forwarded to the instrument; in terms of 1 command every <Rate> Time (in seconds) in the event that the instrument can not receive the commands as fast as the MOC can send them. For example, for DLRE, this can be set to 3, which indicates that the MOC T&C system will send 1 DLRE FSW Command every 3 seconds until the file is completely uplinked.
Select Command If required, the SOC should provide the correspond “Select Command” as identified from the LRO Command Database. If no select command is required, the SOC should set this field to NOSELECT DLRE should always set this field to NOSELECT

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Parameter Name Parameter value
Instrument Load Command This provides the “Instrument Load Command” mnemonic as defined within the LRO Command database
Commit Command If required to commit the load, the field should contain the commit command as contained/formatted within the LRO command database. If no commit command is required set the field to NOCOMMIT DLRE should always set this field to NOCOMMIT
Instrument Data X – All data load lines should start with the hexadecimal delimiter X. Each load line must contain an even number of hexadecimal characters Each line should be limited to 60 load file characters

The following file-naming convention is used for the files transmitted between the SOCs and the LRO MOC. The filename consists of 24 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<YYYYDOY>_<version number>.<file extension>

where instrument id = [4 characters] DLRE, LAMP, or LOLA, MINI
file content = [4 or 7 characters] Intent of the instrument loads. LOAD to indicate it’s a FSW Load for Mini-RF
FSWLOAD; to indicate a FSW load for the other instruments, except for FSW Loads from the Diviner SOC
Date = YYYYDOY
DOY = Identifies the file creation date since this is a load file and
does not contain any date/time related commands
version number = [3 characters] V followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.
file extension = [3characters] Standard file extension for all input files received from a SOC; it will be named for one of the following two input file type: bin; to represent a binary load file for the FSW load for LAMP, LOLA, and Mini-RF SOCs ld; to represent the File type for the DLRE FSW Load

The following paragraphs provide the sample file name concepts for CRaTER, LAMP, LEND, LOLA, LROC, and Mini-RF instrument loads and identify the corresponding Appendix B cross reference for the partial sample file.

A sample file name for a LAMP-generated FSW Load is

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LAMP_FSWLOAD_YYYYDOY_Vnn.bin; a partial sample LAMP Instrument FSW Load is provided in Appendix B, Figure B.3-5.

A sample file name for a LOLA-generated FSW Load is LOLA_FSWLOAD_YYYYDOY_Vnn.bin; a partial sample LOLA Instrument FSW Load is provided in Appendix B, Figure B.3-7

Sample file name is MINI_Load_YYYYDOY_Vnn.bin A sample Mini-RF Load File is provided in Appendix B, Figure B.3-12 DLRE follows a different file naming scheme, which provides a unique file name concept for

each of the various flight software tables that they can modify. The DLRE scheme using the following concepts:

<instrument id>_<file content>_<table descriptor>_<YYYYDOY>_<version number>.<file extension>

where instrument id = [4 characters] DLRE
file content = [7 characters] Intent of the instrument loads. FSWLOAD; to indicate a DLRE FSW load
Table descriptor = [unlimited ASCII characters]; free format for field length or file descriptor length, etc. Provides the specific intent for which table the DLRE SOC plans to modify
Date = YYYYDOY
DOY = Identifies the file creation date since this is a load file and
does not contain any date/time related commands
version number = [3 characters] V followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.
file extension = [3characters] Standard file extension for all input files received from a SOC; it will be named for one of the following two input file type: bin; to represent a binary load file for the FSW load for LAMP, LOLA, and Mini-RF SOCs ld; to represent the File type for the DLRE FSW Load

DLRE provides two separate files to support both a flight software update and for a scan table update. Appendix B, Figure B.3-3, provides the sample concepts for each of these products.

The sample file name for the first DLRE FSW table load for the ramping patch load is identified as: DLRE_FSWLOAD_ramping_patch_2009090_V01.ld;

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4.3.4 (LOLA-2) LOLA Improved Lunar Gravity Model

The LOLA Gravity Model is a file that contains the updated Lunar Gravity Model that the LOLA science team generates from its internal data processing. This file is sent to both the Flight Dynamics Facility and to the LRO MOC.

This data contains an improved lunar gravity model based on the continual processing of the correlated laser ranging one-way transmit times and using S-Band and other LOLA instrument data. FDF will use the improved Lunar Gravity Model to reprocess the orbit data and to create new definitive SPICE File and ephemeris information.

The Gravity model file shall consist of coefficients of a spherical harmonic expansion of the lunar potential up to resolution of (120 x 120) degrees. The LOLA SOC should ensure that the coefficients within the file are normalized; LOLA should also ensure that the updated lunar gravity constant and reference radius are included. LOLA should provide the title of the lunar gravity field. The LOLA SOC will not provide any corrections to the coefficients based on solid lunar tides.

4.3.4.1 Product Details

Time interval NA
File duration NA
File or Data Generation Frequency LOLA generates on a best effort basis to approach every 2 months starting at L+2 Months
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC MOC scp to FDF via the FD Communications Server; the backup uses the FDPC (MOC performs the scp push)
Data Volume Variable; based on contents, but approximately 2 KBytes
Accuracy (if it applies) NA
Other pertinent details NA

4.3.4.2 Format

The LOLA SOC creates the LOLA Improved Gravity Model File; this is an ASCII-formatted file based on the LOLA processing. This file includes new lunar gravity model data including the standard deviation values for the updated parameters.

The following file-naming convention is used for files transmitted between the LROC SOC and the LRO MOC. The filename consists of 26 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<YYYYDOY>_<version number>.<file extension>

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where instrument id = [4 characters] LROC

file content = GRAVMODEL – used to denote this is the newly calculated LOLA Gravity Model Information

Date = YYYYDOY based on UTC Timeframe DOY = is the creation date

version number = [3 characters] V followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.

file extension = [3 characters] Standard file extension for all input files received from SOC; it will be named for the input file type:

bsp; to represent a binary SPK file A sample LROC Activity Request file name for an ATS request is LOLA_GRAVMODEL_YYYYDOY_Vnn.txt

A sample Improved Lunar Gravity Model data file is provided as a reference in Appendix B, Figure B.3-6.

4.3.5 (LOLA-4) LOLA Processed OD Information

This file contains the LOLA–calculated Orbit Determination from data processing based on the telemetry data that LOLA receives from the LRO MOC as part of the real-time and post-pass s/c and instrument housekeeping and measurement telemetry, as well as the tracking data that the MOC provides to LOLA.

4.3.5.1 Product Details

Time interval Data centered at 1 minute increments
File duration File is a set of daily files
File or Data Generation Frequency Files are created on an as-available basis
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC MOC scp to FDF via the FD Communications Server; the backup uses the FDPC (MOC performs the scp push)
Data Volume Approximately 2 Mbytes per weekly file
Accuracy (if it applies) 50 m along track, 50 m across track, and less than 1 m radial
Other pertinent details NA

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4.3.5.2 Format

The LOLA Processed OD Information is a set of SPK formatted files based on the LOLA Orbit Determination calculations. The LOLA SOC creates these files on a weekly basis from the data gathered over the last seven days. This SPK is consistent with other OD-like SPK files previously discussed in the FDF section.

The filename consists of 20 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<YYYYDOY>_<version number>.<file extension>

where instrument id = [4 characters] LOLA
file content = SPK – used to denote this is a LOLA Processed SPICE SPK File
Date = YYYYDOY based on UTC Timeframe
DOY = start date corresponding to when new Processed OD Data is valid and not the creation date
version number = [3 characters] V, followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.
file extension = [3characters] Standard file extension for all input files received from SOC; it will be named for the input file type: bsp; to represent a binary SPK file

A sample LOLA Processed OD Information file name is LOLA_SPK_YYYYDOY_Vnn.bsp

Since the LOLA Processed OD Information is a binary SPK file, no sample product is provided in Appendix B.

4.3.6 (LOLA-6) LOLA Processed Laser Ranging Data

This file contains the LOLA–processed one-way laser ranging fire time from data processing based on the telemetry that LOLA received from the LRO MOC as part of the real-time and post-pass s/c and instrument housekeeping and measurement telemetry.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.3.6.1 Product Details
Time interval Data centered at 1 second increments when laser ranging activities occur
File duration File is 1 day of data Nominally from 0000 GMT to 0000 GMT
File or Data Generation Frequency 1 file per day
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC and to the CDDIS (LOLA does the scp “push” MOC scp to FDF via the FD Communications Server; the backup uses the FDPC (MOC performs the scp push)
Data Volume Approximately 6 Mbytes per daily file
Accuracy (if it applies) < 10 centimeters precision for the 1 second data interval (for each normal point)
Other pertinent details NA

4.3.6.2 Format

The LOLA processed laser ranging information is consistent with the details as provided in the Consolidated Laser Ranging Data Format (CRD) document. This product consists of several “header” records that are used to provide general information, such as station, target, and start time; these “header” records are fixed format and similar in content to those of the Consolidated Laser Ranging Prediction Format; version 1.0 referenced document. The file also contains “configuration” records, which contain an expanded version of data previously described by the System Configuration Indicator (SCI) and system CHange Indicator (SCH) fields. The file contains the “data: records, which provide the laser transmit and receive times, and other highly dynamic information. Both the configuration and data records are free format with spaces between entries. The filename consists of 14 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<YYYYMMDD>.<file extension>

where instrument id = [5 characters] used to define the mission and the laser ranging station site for example LROLR

Date = YYYYMMDD ; where YYYY = 4 digit year (2009 – 2013) MM = 2 digit month (01 – 12) DD = 2 digit day (01 – 31)

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file extension = [3characters] Standard file extension for a Normal Point generated file: npt;

A sample LOLA Processed laser Ranging data file corresponding to January 20, 2009 in normal point mode is LROLR_20090120.npt

Appendix B, Figure B.3-8 provides a sample version of this product.

4.3.7 (LOLA-7) Lunar Laser Retro-Reflector Event Information

This file contains the calculated times during which the LOLA instrument potentially could be damaged. When the LRO spacecraft enters an area near one of the lunar-based laser retroreflectors, a lunar laser ranging experiment independent of the LRO project might send high-level laser pulses, which the LR telescope could receive. The file provides the estimated event start time and duration for which the LRO mission ops team will maneuver the HGA to avoid any harmful impact to the LOLA telescope electronics as a result of receiving a much higher laser energy level, which would damage the LOLA telescope electronics.

4.3.7.1 Product Details

Time interval Time interval is NA since the actual event times are based on LRO and lunar geometry conditions; they occur about twice a month and are clustered together
File duration File contains the next 28 days of retro-reflector avoidance times
File or Data Generation Frequency LOLA creates this file on a weekly basis after receipt of the FDF predicted ephemeris
Delivery method (real-time, SCP, FTP, etc) LOLA SOC scp pushes the file to LRO MOC
Data Volume Less than 1 Kbyte per weekly file
Accuracy (if it applies) Event start times and durations are accurate to the second
Other pertinent details Used internally by the MOC’s MPS system to identify when the HGA is commanded to an offset so as to avoid the high-energy laser impulses.

4.3.7.2 Format

The file will consist of 1-n lines of optional free-form Header data; this is used as information only and is not required for eventual ingest as a product. The file then contains N lines of data that provides the calculated event start and duration using the following format.

# Event Start Duration

YYYY-DOY-HH:MM:SS,ddd

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The event duration is blank padded to 3 ASCII characters/digits and there is a comma (,) character between the Event Start and the Event Duration fields.

In the event that the file does not contain any avoidance events, the file only contains the header rows information. This empty file concept would not contain any of the data rows listed above.

The filename consists of 25 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the complete file name and file extension. The form of the filename is as follows:

<SOC product id>_<Start Date><Stop Date>_<Version Number>.<file extension>

where SOC product id = [5 characters] ; defaults to LOLA7 Start Date = [7 ASCII digits], in the form of: YYYYDOY ; where YYYY = 4 digit for the start year (2009 – 2013) DOY = 3 digits for the start day of year (01 – 366) Stop Date = [7 ASCII digits], in the form of: yyyydoy ; where yyyy = 4 digit for the stop year (2009 – 2013) doy = 3 digits for the stop day of year (01 – 366) Version = [3 ASCII digits/characters]; in the form of: Number Vnn; where nn = 2 ASCII digits to represent the version number for this file; first version =01, and increments by 1 for each new version that LOLA needs to create with the same start/stop information file extension = [3ASCII characters] standard file extension for a text file: txt;

A sample filename for the first generation of the LOLA Lunar Laser Retro-reflector Event file that corresponds to a start date of May 20, 2009 and covers the next 28 days of events is: LOLA7_2009071_2009099_V01.txt

Appendix B, Figure B.3-9 provides a sample version of this product.

4.3.8 (LR-1) Laser Ranging Schedule Information

This file contains the proposed times at which a laser ranging site has view of the LRO spacecraft and will support laser ranging activities. The laser ranging group creates this schedule of all laser sites that can support the LRO mission and perform laser ranging to the spacecraft.

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LRO Ext. Sys. ICD for (LRGS) 431-ICD-000049
Revision – C
4.3.8.1 Product Details
Time interval Data provides AOS – LOS time intervals for each possible laser ranging site
File duration File is valid for the upcoming week; contains 10 days of laser ranging schedule data
File or Data Generation Frequency Created by the Friday before the week in question
Delivery method (real-time, SCP, FTP, etc) LR FTP-es the file to the CDDIS LOLA SOC scp (pulls) the file from the CCDIS and then scp push to LRO MOC MOC DMS Scp pushes the file to the FDPC
Data Volume Approximately 6 Kbytes per weekly file
Accuracy (if it applies) Station AOS/LOS times are accurate to the second
Other pertinent details NA

4.3.8.2 Format

The file contains the AOS/LOS times corresponding to when a particular laser site has view of the LRO antenna and is able to provide support to conduct laser ranging to the spacecraft.

Each line in the scheduling file will contain information regarding one scheduled pass for a system. Blank characters are used to separate the fields within the file. The following table describes each pass record contained in each line of the file:

Field name Field Characteristics
LR Pad Identifier [4 ASCII Digits] – represents the International Laser Ranging Service Pad ID the following is the convention for Pad ID assignments to LR sites: 7125 – GO1L, SLR2000 at Greenbelt, MD 7080 – MDOL, McDonald Observatory at Ft. Davis, TX 7110 – MONL, Monument Peak, California 7941 – MATM, Matera Laser Ranging Observatory, Matera, Italy 7810 – ZIML, Zimmerwald, Switzerland 7825 – STL3, Mount Stromlo at Canberra, Australia 7840 – HERL, Herstmonceaux, England 7845 – GRSM, Grasse, France 8834 – WETL, Wettzel, Germany 7501 – HARL, Hartebeesthoek, South Africa (MOBLAS-6) 7090 – YARL, Yarragadee, Dongara, Australia (MOBLAS-5) 7308 – KOGC, Koganei, Tokyo, Japan
LR AOS Pass Date 7 ASCII Digits representing the scheduled start pass date in the form of YYYYDDD; where YYYY = start year designator (2008 - 2013) DDD – start day of year designator (1 – 366)

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Field name Field Characteristics
LR AOS Pass Time 5 ASCII Digits representing the scheduled start pass time; in the form of HH:MM
first 2 character represent the start time in hours of the LR station contact (00
– 23)
Next 2 characters represent the start time in minutes of the LR station contact
(00 – 59)
LR LOS Pass Date 7 ASCII Digits representing the scheduled stop pass date in the form of YYYYDDD; where YYYY = start year designator (2008 - 2013) DDD – start day of year designator (1 – 366)
LR LOS Pass Time 5 ASCII Digits representing the scheduled stop pass time; in the form of HH:MM
first 2 character represent the start time in hours of the LR station contact (00
– 23)
Next 2 characters represent the start time in minutes of the LR station contact
(00 – 59)
LR Station Qualifier [4 ASCII Characters]; used to uniquely identify the LR station name;: GO1L NGSLR, Greenbelt, MD MDOL McDonald Observatory, Ft. Davis, TX MONL Monument Peak, California MATM Matera Laser Ranging Observatory, Matera, Italy ZIML Zimmerwald, Switzerland STL3 Mount Stromlo, Canberra, Australia HERL Herstmonceaux, England GRSM Grasse, France WETL Wettzel, Germany HARL Hartebeesthoek, South Africa YARL Yarragadee, Dongara, Australia KOGC Koganei, Tokyo, Japan
Comments [1 – 37 ASCII characters]; free form text used to provide specific information for LR stations regarding the scheduled LR station pass; such as: High Priority; could also be blank

The following file-naming convention is used for files transmitted between the Laser Ranging group and the LRO MOC. The filename consists of 29 ASCII characters and digits. There are underscores (_) between each of he file name fields. The form of the filename is as follows:

<system id>_<file content>_<YYYYDOY>_<YYYYDOY>__<version number>

where system id = [2 characters]
LR
file content = [8 characters]
schedule

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Start Date = [8 characters] based on UTC Timeframe in the form of YYYYDOY; where
YYYY = start year of corresponding first entry in the LR schedule
DOY = start day of year corresponding to the first entry in the LR schedule
Stop Date = [8 characters] based on UTC Timeframe in the form of YYYYDOY; where
YYYY = start year of corresponding first entry in the LR schedule
DOY = start day of year corresponding to the last entry in the LR schedule
version number = [1 ASCII Digit] N, where N is 1-9 to represent the possible versions.

For a first version of a laser ranging schedule that is valid for the January 24 thru February 2, 2008, the sample Laser Ranging Schedule file name is identified as LR_schedule_2008024_2008033_1

Appendix B, Figure B.3-10 provides a sample product reference.

4.3.9 (LROC-2) LROC Instrument Initialization Command Sequence

This file is one of eight initialization command loads that LROC SOC could use to initialize the LROC instrument during a startup sequence. This file is delivered electronically to the LRO MOC; the LRO MOC uplinks this file into the LROC directory location using the CFDP protocol. The instrument initialization command sequence is used to identify which set of command to use whenever the LROC instrument is initialized.

All commands in the file must be defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053). If the command contains submnemonics, they must be specified with the command.

4.3.9.1 Product Details

Time interval Command time sequences are variable; based on LROC identified startup concepts
File duration NA; file is a set of relative-based time sequences for LROC initialization
File or Data Generation Frequency LROC will generate up to 8 files Initially generated prelaunch (required 2 months prior to launch, preferred 4 months prior to launch After launch on an as-needed basis
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC

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Data Volume Variable; based on contents, but nominally less that 256 KBytes
Accuracy (if it applies) NA
Other pertinent details Files will be delivered on an as-needed basis File delivered 2-3 days prior to requested uplink to allow sufficient time to verify load against the FLATSAT simulator

4.3.9.2 Format

The LROC Instrument initialization command sequence provides the LROC instrument FSW load that the LROC SOC wants to load at startup; this file is a binary content that the instrument uses during the initialization process.

The operations team generates command that are used to load these files into the Orbiter’s solid state recorder LROC directory structure. The following file-naming convention is used for files transmitted between the LROC SOC and the LRO MOC. The filename consists of 31 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<File Number>_<version number>.<file extension>

where instrument id = [4 characters] LROC, followed by the underscore character (_)
file content = [7 characters] Intent of the instrument loads. FSWLOAD; followed by the underscore character (_)
File Number = [1 ASCII Digit] n = 1 thru 8 to identify the appropriate load file; followed by the underscore character (_)
version number = [3 characters] V, followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.
file extension = [3 characters] Standard file extension for all input files received from SOC; it will be named for the input file type: bin to indicate instrument command load

Sample LROC File names that correspond to the first iteration of the eight allowable command initializations sequences:

LROC_FSWLOAD_1_V00.bin

LROC_FSWLOAD_2_V00.bin

LROC_FSWLOAD_3_V00.bin;

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LROC_FSWLOAD_8_V00.bin;

The LROC Instrument Initialization Command Sequence is a binary formatted file and as such, there is no sample product provided in Appendix B.

4.3.10 (LROC-3) LROC Daily Command Sequence

This file is the text version of daily LROC sequence that identifies times of imaging and other instrument-related command parameters. This file is delivered electronically to the LRO MOC, specifically the MPS element. This file is used for visual verification of the commands that the LROC SOC transmitted within the binary command load file referenced in the previous subsection.

All commands in the file must be defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053). If the command contains submnemonics, they must be specified with the command.

4.3.10.1 Product Details

The LROC SOC will provide support through all mission phases.

Time interval Variable based on WAC/NAC camera image commands
File duration 3-4 days of daily command sequences
File or Data Generation Frequency daily
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC
Data Volume Variable; based on number of command sequences, but nominally less that 256 KBytes
Accuracy (if it applies) Times accurate to 1 second
Other pertinent details File delivered no later than noon, Eastern for scheduling the first day’s command sequences into the command uplink

4.3.10.2 Format

The LROC Daily Command Sequence is comma delimited, ASCII file that consists of a set of absolute time sequenced (in UTC) command mnemonics and any required sub-mnemonics. All commands in the file must be defined in the LRO Telemetry and Command Formats Handbook (431-HDBK-000052). If the command contains submnemonics, they must be specified with the command.

The fields are defined in the following table:

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Field name Field Characteristics
Timetag: year day of year and time of day YYYY-DDD-HH:MM:SS where, YYYY => 4 ASCII digits of year DDD => 3 ASCII digits for day of year HH:MM:SS => 8 ASCII digits for hour, minutes, and seconds with a “:” delimiter. Note the “-” delimiter” separating YYYY, DDD, and HH:MM:SS.
Image Priority Number 1 digit integer number (1-5) with 1 being the highest and 5 being the lowest
Command with Sub-Mnemonic Valid LROC Command and Sub-Mnemonics as defined within the T&C Formats Handbook CMD, SUB1=VAL1, SUB2=VAL2,… There is a comma delimiter separating the command name and sub-mnemonic name(s)/value(s). Sub-mnemonic names are followed by a “=” and then the value of the sub-mnemonic. All command, sub-mnemonics, and sub-mnemonic values should be in capital letters except when specifying hex (notation is 0x)

The following table provides the current set of LROC identified commands. The command names and parameters presented in the tables may change over time; however, we will not modify this ICD. The official source of commands is the latest LRO command database, which the MOT delivers to the SOCs and MPS each time the MOT modifies the command database.

The “Required” column indicates whether the SOC needs to specify the sub-mnemonic. If the field reads “Exclude”, the sub-mnemonic value is fixed to one number and therefore should not be included when using the corresponding command in a sequence/timeline. If the field reads “Include”, the sub-mnemonic value must be set even if the operator wants to use the default value for the command. The “Discrete” column indicates whether the sub-mnemonic has discrete value definitions. If the field has an “X”, the SOC must specify the discrete value and not the corresponding fixed value. For example, if the sub-mnemonic is assigned values of “OFF” and “ON” with converted values of 0 and 1 respectively, the SOC must use “OFF” or “ON” and not 0 or 1.

Table 4-30: Current Set of Available LROC Commands

Sub-Mnemonic Required Data Type Discrete Default Value Min Value Max Value
CMD LRLOADFILE
SUB SADD Exclude U1 0x5C 0x5C
SUB VERS Exclude U1 0x00 0x00
SUB CMDID Exclude U1 0xF3 0xF3
SUB PAD1 Exclude U1 0x00 0x00
SUB XID Include U12 0xAAAA
SUB FILENAME Include S1 "INIT"

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Sub-Mnemonic Required Data Type Discrete Default Value Min Value Max Value
SUB PAD2 Exclude U1 0x00 0x00
SUB PAD3 Exclude U1 0x00 0x00
SUB PAD4 Exclude U1 0x00 0x00
SUB PAD5 Exclude U1 0x00 0x00
SUB PAD6 Exclude U1 0x00 0x00
SUB PAD7 Exclude U1 0x00 0x00
SUB PAD8 Exclude U1 0x00 0x00
SUB PAD9 Exclude U1 0x00 0x00
SUB PAD10 Exclude U1 0x00 0x00
SUB PAD11 Exclude U1 0x00 0x00
SUB PAD12 Exclude U1 0x00 0x00
SUB PAD13 Exclude U1 0x00 0x00
SUB PAD14 Exclude U1 0x00 0x00
SUB PAD15 Exclude U1 0x00 0x00
SUB PAD16 Exclude U1 0x00 0x00
CMD LRNAC
SUB SADD Exclude U1 0x5C 0x5C
SUB VERS Exclude U1 0x00 0x00
SUB CMDID Exclude U1 0xF4 0xF4
SUB PAD Exclude U1 0x00 0x00
SUB XID Include U12 0xAAAA
SUB TIME Include TIME44
SUB IMAGEID Include U1234 0xFFFFFFFF
SUB EXTIME Include U12 0
SUB LINES Include U12 1
SUB CPNDSEL Include U1 0
SUB RESERVED Exclude U1 0x00 0x00
SUB TESTPAT Include U1 X NO_TEST
SUB SUM Include U1 X NO_SUM
SUB COMP Include U1 X NO_COMPRESS
SUB NACSEL Include U1 X BOTH
SUB RSTLVLL Include U1 0
SUB RSTLVLR Include U1 0
SUB OFFAL Include U12 0
SUB OFFAR Include U12 0
SUB OFFBL Include U12 0
SUB OFFBR Include U12 0

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Sub-Mnemonic Required Data Type Discrete Default Value Min Value Max Value
CMD LRWAC
SUB SADD Exclude U1 0x5C 0x5C
SUB VERS Exclude U1 0x00 0x00
SUB CMDID Exclude U1 0xF5 0xF5
SUB PAD Exclude U1 0x00 0x00
SUB XID Include U12 0xAAAA
SUB TIME Include TIME44
SUB IMAGEID Include U1234 0xFFFFFFFF
SUB EXTIME Include U12 0
SUB FRMS Include U12 8
SUB CPNDSEL Include U1 0
SUB RESERVED Exclude U1 0x00 0x00
SUB TESTPAT Include U1 X NO_TEST
SUB WACPWR Include U1 X NO_CHANGE
SUB POLAR Include U1 X NO_POLAR
SUB COMP Include U1 X NO_COMPRESS
SUB BAND Include U1 X ALL_BANDS
SUB IFRMTIME Include U1 0

The following file-naming convention is used for files transmitted between the LROC SOC and the LRO MOC. The filename consists of 20 characters; it also contains a three-character file extension name. There are underscores (_) between the file name fields and a period (.) between the file name and file extension fields. The form of the filename is as follows:

<instrument id>_<file content>_<YYYYDOY>_<yyyydoy>_<version number>.<file extension>

where instrument id = [4 characters] LROC

file content = [3 characters] Intent of the instrument loads. For LROC this is identified as DCS = Daily Command Sequence

Start Date = YYYYDOY where YYYY => 4 ASCII digits of year (2008 – 2013) DOY => 3 ASCII digits for day of year (1 – 366) Note: DOY represents the start time of data within the file, not the file creation time

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Stop Date = yyyydoy where yyyy => 4 ASCII digits of year (2008 – 2013) doy => 3 ASCII digits for day of year (1 – 366) Note: doy represents the stop date of the time of data within the file, not the file creation time

version number = [3 characters] V followed by a two-digit version number. The initial version is 00, next is 01 … up to 99.

file extension = [3 characters] Standard file extension for all input files received from SOC; it will be named for the input file type:

ict for instrument command timeline A sample file names for the LROC generated daily command load file that corresponds to the first iterations of daily commands for 25 January 2009 through 28 January 2009 is LROC_DCS_2009025_2009028_V00.ict

A sample LROC Daily Command Sequence File is provided in Appendix B, Figure B.3-11.

4.3.11 (MIRF-3) Mini-RF Command Timeline

This file contains a set of command sequences that the MOC uses to create a daily load for uplink to the Mini-RF instrument.

All commands in the file must be defined in the LRO Telemetry and Command Handbook – Database (431-HDBK-000053). If the command contains submnemonics, they must be specified with the command.

4.3.11.1 Product Details

Time interval Variable based on Mini-RF commands
File duration 24 hours
File or Data Generation Frequency As needed whenever Mini-RF is operating
Delivery method (real-time, SCP, FTP, etc) scp to LRO MOC
Data Volume Variable; based on number of command sequences, but nominally less that 256 KBytes
Accuracy (if it applies) Times accurate to 1 second
Other pertinent details File delivered no later than noon, Eastern for uplink within the same day

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4.3.11.2 Format

The Mini-RF Command Timeline is a comma-delimited, ASCII file that consists of a set of absolute time sequenced (in UTC) command mnemonics and any required sub-mnemonics. All commands in the file must be defined in the LRO Telemetry and Command Formats Handbook (431-HDBK-000052).

The fields are defined in the following table:

Field name Field Characteristics
Timetag: year day of year and time of day YYYY-DDD-HH:MM:SS where, YYYY => 4 ASCII digits of year DDD => 3 ASCII digits for day of year HH:MM:SS => 8 ASCII digits for hour, minutes, and seconds with a “:” delimiter. Note the “-” delimiter” separating YYYY, DDD, and HH:MM:SS.
Command with Sub-Mnemonic Valid Mini-RF Command and Sub-Mnemonics as defined within the T&C Formats Handbook CMD, SUB1=VAL1, SUB2=VAL2,… There is a comma delimiter separating the command name and sub-mnemonic name(s)/value(s). Sub-mnemonic names are followed by a “=” and then the value of the sub-mnemonic. All command, sub-mnemonics, and sub-mnemonic values should be in capital letters except when specifying hex (notation is 0x)

The following table provides the current set of Mini-RF identified commands. The command names and parameters presented in the tables may change over time; however, we will not modify this ICD. The official source of commands is the latest LRO command database, which the MOT delivers to the SOCs and MPS each time the MOT modifies the command database.

The “Required” column indicates whether the SOC needs to specify the sub-mnemonic. If the field reads “Exclude”, the sub-mnemonic value is fixed to one number and therefore should not be included when using the corresponding command in a sequence/timeline. If the field reads “Include”, the sub-mnemonic value must be set even if the operator wants to use the default value for the command. The “Discrete” column indicates whether the sub-mnemonic has discrete value definitions. If the field has an “X”, the SOC must specify the discrete value and not the corresponding fixed value. For example, if the sub-mnemonic is assigned values of “OFF” and “ON” with converted values of 0 and 1 respectively, the SOC must use “OFF” or “ON” and not 0 or 1.

Table 4-31: Available Mini-RF Commands

Sub-Mnemonic Required Data Type Discrete Default Value Min Value Max Value
CMD MRACTIVATE
SUB EOH Exclude U12 0x5A5A 0x5A5A
SUB BOARD Include U1 X 0x00 0xFF
CMD MRDEACTIVATE

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Sub-Mnemonic Required Data Type Discrete Default Value