exomars/trace gas orbiter - fsw workshopflightsoftware.jhuapl.edu/files/2010/fsw10_lapointe.pdf ·...

ExoMars/Trace Gas ExoMars/Trace Gas Orbiter

Architecting Software Across International Partnerships

*

Jason LaPointe

g p

Jason LaPointeDecember 10th, 2010

Jet Propulsion Laboratoryp yCalifornia Institute of Technology

Pasadena, CA

2010 Workshop on Spacecraft Flight Software

This document has been reviewed and determined not to contain export controlled technical data.© 2010 California Institute of Technology. Government sponsorship acknowledged.

* Proposed Mission. Pre-decisional - for planning and discussion purposes only

OutlineOutline

Proposed Mission Overview Instruments, Electra, and Ka‐band Mission Phases Mission Phases Key FSW Requirements Common To All Instruments FSW Inheritance I t f Bl k Di Interface Block Diagram Communication Protocols Cmd/Tlm Database integration F l P i Fault Protection Data Volume Constraints Data Reduction

Pre-decisional - for planning and discussion purposes only.This document has been reviewed and determined not to contain export controlled technical data.

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Proposed Mission Overview

The proposed ExoMars/Trace Gas Orbiter would be a /new and exciting joint NASA/ESA mission to Mars to be

launched in 2016. The mission elements would include a science orbiter and a demonstration lander. ESA is responsible for providing the orbiter bus and landerwhile JPL is to provide four out of five sciencewhile JPL is to provide four out of five science instruments and spacecraft telecommunications hardware for Ka‐band, X/Ka‐band antenna, and UHF Electra. NASA/JPL would also provide the launch vehicle. ESA has the lead in the overall mission operations.

JPL would lead the science operations from the Science, Relay and Aerobraking (SRA) center at JPL. The telecommunications hardware including Ka‐Band and Electra would be integrated into the orbiter to provide deep space link and relay functionality from ground to both the demonstration lander and potential future landed assets on Mars.


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Instrument SuiteInstrument Suite

MAGIE (NASA/JPL/MSSS)Mars Atmospheric Global Imaging

HiSci (NASA/JPL/UA/BATC)High Resolution Stereo Color Imager

MATMOS (NASA/JPL/CSA)Mars Atmospheric Trace MoleculeMars Atmospheric Global Imaging

ExperimentHigh Resolution Stereo Color Imager Mars Atmospheric Trace Molecule

Occultation Spectrometer


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EMCS (NASA/JPL)ExoMars Climate Sounder

NOMAD (BIRA-IASB)Nadir and Occultation for Mars Discovery

ElectraElectra

NASA/JPL would provide two redundant Electra boxes (including FSW) to be used for communication with ground assets. These boxes would be


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connected to a single UHF antenna provided by ESA.

Ka-BandKa Band

• NASA/JPL to provide:A i l 2 2 HGA– A single 2.2 m HGA

– 2 x Ka‐band TWTAs– Antenna pointing mechanism– Antenna pointing mechanism (including FSW)

• ESA to provide:– 2 x X‐band TWTAs– X/Ka‐band switching


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– X/Ka‐band transponders

Mission PhasesMission Phases

• Baselined to launch out of Cape Canaveral in January, 2016• Cruise (10 months in 2016)• EDL Demonstration Module experiment upon arrival (8 days in 2016)

– Use Electra for communication with EDM• Aerobraking (6 months in 2016‐2017)g ( )• Nominal orbiter science operations (2 years; 2017 ‐ 2019)

– 74 degree inclinationObserve during day and night– Observe during day and night

– Nadir and limb/sun occultation observation modes• Relay Support for future orbiters (through 2022)


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Key FSW Requirements Common T All ITo All Instruments

• Software simulation model• Patch capabilities• Event reports under anomalous conditions• FSW parameter modification• Distinct areas of memory for code, constants, and variable parameters.y p• Fault protection (intrinsic as well as support of system FP)• Support for safe and nominal modes• 1553 (Cmd and RT Tlm) and Spacewire (Science & SSOH) interfaces• 1553 (Cmd and RT Tlm) and Spacewire (Science & SSOH) interfaces


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FSW InheritanceFSW Inheritance

EM/TGOI t t

Heritage I t t

HeritageMi i

% FSW I h it dInstrument Instruments Mission Inherited

EMCS MCS MRO > 85%

HiSci OLI LANDSAT > 50%

MAGIE MARCI,Mastcam, MAHLI,MARDI

MRO, MSL > 80%

MARDI

Electra N/A MAVEN > 90%


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Interface Block DiagramScience

Instruments

MATMOS X/Ka Band

1553 C/D X/Ka RF InterfaceNASA

Provided

Legend(Self-contained

FSW)(Self-contained

FSW)

NOMAD

Orbiter Bus

Spacewire(100 Mbps) BIRA

Provided

ESA

(Self-contained FSW)

EMCS

Orbiter Bus Module1553 A

(500 Kbps)

1553 B

ESAProvided

1553 bus

Spacewire


(ESA orbiter bus FSW only. No instrument, Ka band, or Electra

FSW)

MAGIE

Electra

LVDS (12 Mbps)

LVDS (10 Mbps)

El t ( 2)

p

LVDS

RF Interface


Note: All interfaces


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ElectraElectra (x2)(Self-contained

FSW)


Note: All interfacesare preliminaryand subject to change

Communication Protocols

• MIL‐STD‐1553B– Instrument/Electra commanding– Instrument/Electra time sync– Instrument/Electra R/T Telemetry– Ka‐band gimbal control commandingg g

• ECSS‐E‐ST‐50‐12C (Spacewire)– Instrument science data

Instrument SSOH data– Instrument SSOH data• Science Protocol(SP)/CCSDS File Delivery Protocol (CFDP)

– Electra forward and return link relay data


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Cmd/Tlm Database Integration

• The s/c CTDB is owned by ESA.B th NASA d NASA i t t t• Both NASA and non‐NASA instrument teams to provide inputs to JPL, which would, in turn,

id i t t d CTDB i t t ESAprovide integrated CTDB inputs to ESA. • The format of these inputs has not yet been determined.


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Fault ProtectionFault Protection

• Multi‐tiered FP design approach.I t t t h dl l l t• Instruments to handle local events.

• Real time telemetry provided to orbiter bus FSW to handle system level FP and mode changes .


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Data Volume ConstraintsData Volume Constraints

Instrument % Allocation of8 Gbit/day Avg.(Science Data only)

Instrument Data Volume Usage(Gbits/day)(Science Data only)

HiSci 36%

MATMOS 24%

(Gbits/day)

NOMAD 16%

MAGIE 4%

EMCS 2%

Total 82%

* Unused portion is based on an 8Gb/day allocation to all instruments


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Data ReductionData Reduction

In order to meet the tight data volume requirements instruments would employ state‐requirements, instruments would employ state‐of‐the‐art compression and/or on‐board data reduction techniques such as binning averagingreduction techniques such as binning, averaging, and on‐board science data processing.


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MATMOS Data Reduction

• Raw interferograms are converted to spectra on orbit via L0 – L1B processing on 2 x RAD 750s.A 100 1 d i i d i hi bl b bi i f h f ll i• A 100:1 reduction in data is achievable by a combination of the following:– On board processing– 2:1 lossless compression– 12 bit spectral resolution– Averaging– Intermediate products (L0, L1A) are discardedIntermediate products (L0, L1A) are discarded– Removal of non‐useful spectral regions

• Raw data is occasionally downlinked to ground to verify on‐board processing algorithms


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processing algorithms.

The proposed ExoMars/Trace Gas Orbiter promises to be an exciting mission. The detection of methane and other trace gases is an essential next step in the search for life on Mars The imaging instrumentssearch for life on Mars. The imaging instruments would continue essential mapping that would otherwise not exist when MRO and other orbiters reach their EOL. The on‐board Electra & Ka‐band electronics would provide a basis for


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electronics would provide a basis for communications with future NASA/ESA Mars ground assets.


Contact Info/LinksContact Info/Links

Jason LaPointeE M /TGO P j t S ft S tExoMars/TGO Project Software Systems

Engineer

Jet Propulsion LaboratoryPasadena, CA818‐393‐2569

Further Reading: http://solarsystem.jpl.nasa.gov/missions/profile.cfm?MCode=ExoMars&Display=ReadMore


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ESA Web Site: http://exploration.esa.int

Image CreditsImage Credits

• Title page, Mars horizon: NASA/JPL‐Caltech• Title page, orbiter: artist’s concept, ESA

Mi i O i bit ESA• Mission Overview, orbiter: ESA• Instrument Suite

– MAGIE instrument: MSSSHiSCI i t t UA BATC– HiSCI instrument: UA, BATC

– NOMAD instrument: BIRA‐IASB– MATMOS/EMCS instruments: NASA/JPL‐CaltechEl t NASA/JPL C lt h• Electra: NASA/JPL‐Caltech

• Ka‐band: NASA/JPL‐Caltech• Conclusions, background: artist’s concept, ESA


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