22 - 1 NASA’s Goddard Space Flight Center Lunar Reconnaissance Orbiter Ground System Requirements.

22 - 1NASA’s Goddard Space Flight Center

Lunar Reconnaissance Orbiter

Ground System Requirements


LRO Ground System Document Tree(Key Ground System Requirements Documents)

LRO Level 1 Requirements Development Document

Detailed Mission Requirements(431-RQMT-000048)

3.1 Ground Network3.2 Testing and Verification3.3 Mission Operations Center3.4 Communications3.5 Data Distribution3.6 Flight Dynamics

Mission Operations Center

Specifications(431 -SPEC -000055 )

LRO Mission Requirements Document

(431-RQMT-000004)

LRO Mission Concept of Operations

(431-OPS-000042)

Level 1

Level 2

Level 3

Level 4

Ground Network Specifications

( 431 -SPEC -000056 )

ITOS Specifications

(431 -SPEC -000057 )

TrendingSpecifications

( 431 -SPEC -000059 )

Mission Planning System

Specifications(431 -SPEC -000060 )

Flight Dynamics Ground System Specifications

(431 -SPEC -000063 )


Level 2 Req. Level 3: Requirements Concept/Compliance

Paragraph Requirement

431-RQMT-000004

MRD-039

MRD-041

MRD-121

MRD-151

431-RQMT-000048

3.1.1.4

DMR-4

Ground network shall provide S-Band tracking (Doppler and Ranging) for a minimum of 30 minutes per orbit.

Complies – all ground stations supporting LRO will have the capability to provide tracking data for orbit determination.

431-RQMT-000048

3.1.1.6

DMR-6

The ground network shall send tracking data measurements to flight dynamics equal to or less than every 5 minutes during early mission phase.

Complies – the ground network will either send the tracking data in real-time or send tracking files every 5 minutes during early mission support.

431-RQMT-000004

MRD-122

MRD-151

MRD-152

431-RQMT-000048

3.1.1.7

DMR-7

The S-Band system shall support a command uplink rate of 4 kbps using the S-Band frequency of 2091.3967 MHz.

Complies – the ground network shall support a command uplink rate of 4 kbps.

431-RQMT-000004

MRD-039

MRD-041

MRD-121

MRD-151

431-RQMT-000048

3.1.1.8

DMR-8

The S-Band system shall provide tracking data with an accuracy equal to or less than 8 mm/sec (TBR).

Complies – all ground stations will be capable of supply tracking data at the accuracy and frequency needed for flight dynamics processing.431-RQMT-000048

3.1.1.9

DMR-9

The S-Band system Doppler measurement samples shall be performed over a 10 second integration period.

Lunar Reconnaissance Orbiter (LRO)

Ground System Level 2 Flow Down KeyRequirements

(Ground Networks General Driving Requirements)




431-RQMT-000004

MRD-039

MRD-041

MRD-121

MRD-151

431-RQMT-000048

3.1.1.10

DMR-10

The S-Band system shall provide Range tracking data with an accuracy equal to or less than 15 meters.

Complies – the ground network will send range tones on the uplink and receive the turn-around tones from the spacecraft. Ranging shall have an accuracy of 15 meters or less and be measured every 40 seconds.

431-RQMT-000048

3.1.1.11

DMR-11

The S-Band system range measurement samples shall be collected every 40 seconds.

431-RQMT-000004

MRD-155

MRD-136

MRD-138

431-RQMT-000048

3.1.1.15

DMR-15

The combination of different ground stations within all supporting networks shall provide at least two separate S-Band ground stations to perform telemetry capture, command uplink, and tracking functions during all mission critical activities.

Complies – the ground network consist of 6 separate ground stations. DSN will also provide backup capability throughout the mission. All mission critical activities shall have redundant station coverage.



(Ground Networks General Driving Requirements)




(White Sands Complex Ground Station Driving Requirements)



431-RQMT-000004

MRD-038

MRD-124

MRD-136

MRD-150

431-RQMT-000048 3.1.2.1.1

DMR-19

The Ka Band system shall support variable downlink rates up to a maximum rate of 100 Mbps using the Ka-Band frequency of 25.65 GHz.

Complies – the WSC ground station shall have variable Ka-Band receivers that can support the 100 Mbps and lower rates.

431-RQMT-000004

MRD-126

MRD-150

MRD-151

MRD-152

431-RQMT-000048

3.1.2.1

DMR-18

The S/Ka Band ground station shall support simultaneous S and Ka band frequency

Complies – The WSC ground antenna will have a dual feed S and Ka system that will allow simultaneous S and Ka operations.

431-RQMT-000004

MRD-121

MRD-150

431-RQMT-000048 3.1.2.1.2

DMR-20

The Ka Band system shall support a receive G/T of not less than 45 dB/K in the presence of full lunar noise

Complies – The WSC ground station shall meet or exceed the 45 dB/K Ka-Band receive requirement.

431-RQMT-000004

MRD-110

MRD-140

MRD-150

431-RQMT-000048 3.1.2.1.3

DMR-21

The Ka-Band system shall support CFDP operations on the maximum Ka-Band telemetry rate.

Complies – The WSC ground station CFDP processor shall operate at all Ka-Band telemetry rates for LRO.




(White Sands Complex Ground Station Driving Requirements)



431-RQMT-000004

MRD-123

MRD-151

MRD-152

431-RQMT-000048 3.1.2.1.6

DMR-24

The S-Band system shall support a receive G/T of not less than 27 dB/K in the presence of full lunar noise.

Complies – The WSC ground station shall meet or exceed the 27 dB/K receive S-Band requirement.

431-RQMT-000004

MRD-122

MRD-151

MRD-152

431-RQMT-000048

3.1.2.1.7

DMR-25

The S-Band system shall provide an S-Band transmit EIRP of not less than 79 dBW.

Complies – The WSC ground station shall have 2 kW transmitter that allows the antenna to meet the 79 dBW EIRP.

431-RQMT-000004

MRD-042

MRD-043

MRD-136

431-RQMT-000048

3.1.2.2.3

DMR-30

The ground station shall timetag all commands transmitted on the S-Band uplink and forward the time stamp to the MOC using the status packets as defined in the LRO Ground System Interface Control Document (431-ICD-000049)

Complies – The WSC ground station will contain a time capture unit for commands. Information will be included in general station status packets.




(S-Band Network Ground Station Driving Requirements)



431-RQMT-000004

MRD-123

MRD-136

MRD-151

MRD-152

431-OPS-000042

4.4.2

431-RQMT-000048 3.1.3.1.1

DMR-33

The S-Band system shall support a maximum downlink rate of 300 kbps during early mission phase (Launch and Early Cruise Phase).

Complies – the S-Band network shall support the 300 kbps and lower rates and forward the data in real-time to the MOC.

431-RQMT-000004

MRD-123

MRD-136

MRD-151

MRD-152

431-OPS-000042

6.2.5

431-RQMT-000048 3.1.3.1.2

DMR-34

The S-Band system shall support a maximum downlink rate of 128 kbps during the nominal mission phases using the spacecraft HGA.

Complies – the S-Band network provides enough link margin to support the 128 kbps telemetry rate during the nominal mission and forward the data in real-time to the MOC.

431-RQMT-000004

MRD-123

MRD-150

MRD-151

431-RQMT-000048 3.1.3.1.3

DMR-35

The S-Band system shall support a receive G/T of not less than 20.3 dB/K (TBR) in the presence of full lunar noise.

Complies – the S-Band network shall meet or exceed the 24 dB/K receive requirement.




(S-Band Network Ground Station Driving Requirements)



431-RQMT-000004

MRD-122

MRD-150

MRD-151

431-RQMT-000048 3.1.3.1.4

DMR-36

The S-Band system shall provide an S-Band transmit EIRP of not less than 79 (TBR) dBW.

Complies – the S-Band network transmitters will be upgraded to support the EIRP requirement of 79 dBW.

431-RQMT-000004

MRD-042

MRD-043

MRD-136

431-RQMT-000048 3.1.3.2.3

DMR-40

The S-Band ground network shall provide at least one station capable of time stamping all commands transmitted on the S-Band uplink and forward the time stamp to the MOC using the status packets as defined in the LRO Ground System Interface Control Document (431-ICD-000049)

Complies – The time capture unit will be deployed to one of the ground stations for backup/redundant capability.




(Emergency/Backup Network Ground Station Driving Requirements)



431-RQMT-000004

MRD-122

MRD-123

MRD-138

MRD-136

MRD-151

MRD-152

431-OPS-000042

6.2.5

431-RQMT-000048

3.1.4.1

DMR-42

The Deep Space Network (DSN) shall provide a ground network capable of performing S-Band TT&C through the spacecraft omni antenna and supporting the higher S-Band telemetry rates through the HGA.

Complies – DSN capabilities allow TT&C through either the Omni or HGA at all different S-Band telemetry modes.

The LRO Ground System team will work with DSN to develop an operations agreement and support plan.

431-RQMT-000004

MRD-123

MRD-138

MRD-151

MRD-152

431-RQMT-000048 3.1.4.1.1

DMR-43

The S-Band system shall support a receive G/T of not less than 31.53 dB/K (TBR) in the presence of full lunar noise.

Complies – DSN S-band system shall meet or exceed the 31.53 dB/K receive requirement.

431-RQMT-000004

MRD-122

MRD-138

MRD-151

MRD-152

431-RQMT-000048 3.1.4.1.2

DMR-44

The S-Band system shall provide an S-Band transmit EIRP of not less than 87.78 (TBR) dBW.

Complies – DSN S-Band system shall meet or exceed the 87.78 dBW EIRP requirement.




(Mission Operations Center Driving Requirements)



431-RQMT-000004

MRD-155

MRD-136

MRD-141

MRD-142

431-RQMT-000048

3.3.1

DMR-50

The LRO MOC shall perform orbiter telemetry and command, mission planning, trending and paging, data storage and distribution functions required to support all mission phases.

Complies – The MOC will provide separate systems for T&C, trending, mission planning, paging, data storage and distribution.

431-RQMT-000004

MRD-056

431-RQMT-000048

3.3.1.5

DMR-57

Details of the LRO command data formats and coding shall have restricted access.

Complies – the ground system team will limit access to command database and control command format documents.

The ground system security team is also working with the project and GSFC’s Space Asset Protection Team to ensure that appropriate measures are in place to protect LRO from intentional or unintentional disruption, exploitation, or attack.

431-RQMT-000004

MRD-141

MRD-144

431-RQMT-000048

3.3.2.1

DMR-58

The T&C system shall forward all commands to the orbiter via the ground network during flight.

Complies – The MOC T&C system will generate and forward all commands to the orbiter. Ground network will be configured to accept commands from only the T&C system.







431-RQMT-000004

MRD-136

MRD-141

431-RQMT-000048

3.3.2.2

DMR-59

The T&C system shall provide the interface to the LRO orbiter during pre-launch I&T and flight operations.

Complies – The T&C system shall be used during spacecraft and orbiter I&T. The MOC will have communication interfaces to I&T facilities for testing and training.

431-RQMT-000004

MRD-155

MRD-136

MRD-141

431-RQMT-000048

3.3.2.7

DMR-64

The T&C System shall decomm real-time housekeeping data and monitor health and safety of the orbiter.

Complies – The T&C system shall receive and decomm all real-time housekeeping data for health and safety monitoring.

431-RQMT-000004

MRD-110

MRD-140

431-RQMT-000048 3.3.2.8.1

DMR-65

The T&C system shall be compatible with CCSDS AOS version 2 telemetry.

Complies – The T&C system shall provide command and telemetry handling that complies with the CCSDS standards for the exchange of telemetry and commands. The T&C system shall also use CCSDS COP-1 protocol for reliable commanding.

431-RQMT-000048 3.3.2.8.2

DMR-66

The T&C system shall be compatible with CCSDS Telecommand format.

431-RQMT-000048 3.3.2.8.3

DMR-67

The T&C system shall support the CCSDS COP-1 protocol







431-RQMT-000004

MRD-140

MRD-141

MRD-150

431-RQMT-000048

3.3.2.9

DMR-68

The T&C system shall support remote configuration and control of the CFDP processor located at the White Sands ground station.

Complies – The T&C system shall support remote configuration and control of the CFDP processor at WSC. The CFDP processor will be an module added to the current T&C system.

431-RQMT-000004

MRD-138

431-RQMT-000048

3.3.1.6

DMR-58

The ground system shall develop and maintain a backup control center facility to monitor and maintain orbiter health and safety.

Complies – The ground system is planning to perform a trade study to select the best location. The backup MOC will contain limited capability, only those systems required to maintain mission health and safety.

431-RQMT-000004

MRD-136

MRD-118

431-RQMT-000048

3.3.7.1

DMR-200

The flight operations team shall be required to respond to an orbiter emergency within 2 hours.

Complies – The operations team staffing and support plan will respond to all anomalies within 2 hrs.




(Flight Dynamics Driving Requirements)



431-RQMT-000004

MRD-136

MRD-149

431-RQMT-000048

3.6.1.2

DMR-278

Flight Dynamics Facility and Flight Dynamics Analysis Branch shall provide mission products as defined in the Lunar Reconnaissance Orbiter Ground System Interface Control Document (431-ICD-000049).

Complies – Flight Dynamics shall generate required mission products to support mission planning and data processing.

Implementation details for mission products are not yet defined but will be documented in the LRO Ground System Interface Control Document (431-ICD-000049).

431-RQMT-000004

MRD-147

MRD-148

431-RQMT-000048

3.6.2

DMR-279

Flight Dynamics Facility (FDF) shall provide OD support to LRO through all mission phases.

Complies – Flight Dynamics Facility shall ingest tracking data and generate updated orbit state vector to support the LRO mission.

431-RQMT-000048

3.6.2.2

DMR-281

FDF shall perform OD processing each day (TBR), Sunday through Saturday, and after any orbiter maneuver.

Complies – Flight Dynamics Facility will perform orbit determination seven times per week using the previous ~48 hours of tracking data.




(Flight Dynamics Driving Requirements)



431-RQMT-000004

MRD-148

431-RQMT-000048

3.6.3

DMR-282

FDF shall provide AD support to LRO through all mission phases.

Complies – Flight Dynamics Facility shall provide attitude determination support throughout the mission including orbiter slews planning, attitude verification, and calibrations.

431-RQMT-000004

MRD-146

431-RQMT-000048

3.6.4

DMR-285

The Flight Dynamics Analysis Branch shall provide trajectory and maneuver support to LRO through all mission phases.

Complies – The Flight Dynamics Analysis Branch (FDAB) shall provide trajectory and orbit trending and planning. FDAB will plan all trajectory, orbit, station-keeping, and momentum maneuvers.


Ground System Architecture OverviewInstrument ModulePropulsion Module

ULTRAFLEXSolarArray

High Gain AntennaAvionics ModuleXYZ

Instrument ModulePropulsion Module

ULTRAFLEXSolarArray

High Gain AntennaAvionics ModuleXYZXYZ

Deep Space

Network

S-Band

System

S-Band Sites

S-BandSystem

LRO WSC Ground

Station

S-BandSystem

Ka -BandSystem

S-BandCmd & Tlm

S- BandCmd & Tlm

S- BandCmd & Tlm

Ka- BandTlm

Ground Network

Orbiter Cmds

Real-Time Housekeeping

Telemetry

Stored Measurement

Data Files

Stored HousekeepingData Files

Station Status

Packets

CFDP Control

And Status

Acq.

Data

Tracking

Data

LROC SOC

(Univ. NW )

LOLA SOC(GSFC )

LAMP SOC

(SwRI , CO)

CRaTER SOC

(Univ. Boston )

Diviner SOC(JPL )

LEND SOC

(Moscow , Russia )

HKTlm

Flight Dynamics

Products

SpacecraftTelemetry

Mission

ProductsHKTlm

Mission

Products

Mission Products

HK

Tlm

MissionProducts

MissionProducts

Planetary Data System (PDS )

Measurement

Products

Measurement

Products

Measurement

Products

Measurement

Products

Measurement

Products

Measurement

Products

Flight Dynamics

OrbitDetermination

AttitudeDetermination

Maneuver

Legend

Real-time Link

Delayed /Post -processing Link

LRO Ground System Element

External Interfaces

Mission Operations Center

T&C System

ITOS /CFDPØ Telemetry

MonitoringØ Command

ManagementØ Automated

OperationsØ CFDP processing

Trending System

Ø Ingest raw dataØ Trend data pointsØ Produce plots and

reportsØ Remote access

Data Storage

Ø Central storage system

Ø Accessible for all systems

Ø Short/Long term storage

Data Distrbution

Ø Distribute measurement data

Ø Distribute mission products

Mission Planning

Ø Plan daily eventsØ Create event plansØ Generate daily

loadsØ Display short/long

term planning events

Ø Web viewable timeline

MissionProducts

Laser Ranging Network

LaserRanging

Mini-RF(APL)

MissionProducts


Ground System Preliminary Verification Approach

• Ground system verification and readiness will be performed through a series of ground system verification tests, operations tests and simulations.

Test Level Test Type Description

Level 3 Ground System Readiness Tests •Verifies integration of the ground system elements by interface data flows between the elements through to the full integrated end-to-end validation.

•Demonstrates/proves that the ground system satisfies the level 3 requirements.

•Demonstrates element-to-element interfaces as defined in the ground system ICD.

•Establishes ground system compatibility with orbiter and external systems.

RF Compatibility Tests •Verifies links between the spacecraft and ground networks during orbiter integration.

Ground Network Tracking Certifications

•Flight dynamics will provide tracking certifications on all new or upgraded ground network sites.

•Verifies tracking requirements are met.

Mission Operations Simulations •Small simulations focus mostly for the flight operations team that covers all mission phases.

Mission Rehearsals •Full simulations with all mission team personnel. Rehearsals will cover all critical events throughout the mission.

Level 4 Element Level Tests •Software/Hardware provider system testing based on level 4 specs

Acceptance Tests •Acceptance testing to verify system functionality and performance based on level 4 specs.

Operations Readiness Exercises •Simulations focus at the procedure/activity level that will verify the operations team individual flight procedures and activities.


Summary

• A baseline mission concept of operations for the mission and ground system have been developed

• Current LRO Ground System concept supports the LRO development schedule and Mission concepts

• Additional ground system reviews will be performed• Ground System Requirements Review

• Ground System Design Review

Ground System requirements are sufficiently defined and the design is ready to proceed to detailed ground system requirements and design review

Ground System requirements are sufficiently defined and the design is ready to proceed to detailed ground system requirements and design review

22 - 1 NASA’s Goddard Space Flight Center Lunar Reconnaissance Orbiter Ground System Requirements.

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Transcript of 22 - 1 NASA’s Goddard Space Flight Center Lunar Reconnaissance Orbiter Ground System Requirements.