Spacecraft development

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Gaia power systemSolar arrayLi-ion battery• Triple Junction GaAs cells on solar arrays• Lithium ion batteries based on standard Sony cells• 28 V regulated and maximum power point tracker to minimise instabilityPower Conditioning and Distribution Unit Design approach‣ 1st step: Selection of frequency• Imposed by regulation agency (ITU),• Function of mission type and orbit• Gaia from L2: X band (8 GHz) TM/TC , 10 MHz max TM bandwidthCommunications‣ 2nd step; Definition of communication scenarios• Gaia:» Cebreros 35 m ESA station 8 hour/day outside galactic plane scans» Cebreros and New Norcia 35 m ESA stations during galactic plane scans‣ 3rd step: resources sizing (iterative)• Ground/spacecraft link capabilities: preliminary link budgets as function of distance, antennageometry, memory capability, data availability requirement, protocol• Antenna, amplifiers, transponders selection in iteration with spacecraft configuration, powerresources and thermal control capabilities‣ 4th step: on board architecture definition:• Interconnection schemes• Redundancy, reconfiguration,• Detailed link budgets, system budgets
CCSVM MIL-STD-1553B Bus NGaia CommunicationsystemCCCCSVM MIL-STD-1553B Bus RCC4ks/s 10Ms/s4ks/s10 Ms/sDiscreteTM/TCDiscreteTM/TCDiscreteTM/TCDiscreteTM/TC28V28V28V28VDC/DCCV ART-ADiscreteTM/TCRT-BDC/DCCV BTCDC/DC DiscreteCVTM/TCTMRTDiscrete TCDC/DCCV TM/TCTMRTControlfunctionAEPIC AControlfunctionBEPIC BX-Band X-BandRx TxX-BandRxX-BandTxTRSP-1TRSP-2BM1 SSPAQuadri-Module1RF Splitter 2:7BM2 SSPAQuadri-Module2BM3 SSPAQuadri-Module3BM4 SSPAQuadri-Module4BM5 SSPAQuadri-Module5BM6 SSPAQuadri-Module6BM7 SSPAQuadri-Module7+ X LGARFswitchDiscreteTM/TCSHPHK TMRFswitchPhased Array Antenna electronics- X LGA-1- X LGA-2PAA radiating conePAATT&CChoked horn LGAX band transponder In charge of spacecraft management‣ HW / SW interface, data acquisition and processing‣ AOCS• Sensors, Actuators, Control laws, mode management‣ Data management• Data handling (services, mailboxes, priorities, events, interruptions,…)• Bus management (PLM and SVM 1553 buses, SpaceWire bus)• Mission Time Line• TM generation, TC acknowledge and processing, tasks scheduling• Dump / Patch‣ Thermal• Thermal control loops management‣ Electrical• LCL management, Pyro sequences‣ Communications• Earth ephemeris for PAA beam orientation‣ Monitoring• Detect the failure• Isolate the suspected units• Reconfigure on safe configurationsCentral software
Page 2 and 3: Gaia programme overview1995 - 2004:
Page 5 and 6: The specification treePArequirement
Page 7 and 8: Mechanical and electrical integrati
Page 9 and 10: Physical measurementsGaia on its ho
Page 11 and 12: Spacecraft design approach Although
Page 13 and 14: Gaia mechanical architecture Decoup
Page 15 and 16: Gaia thermal architectureDSA stowed
Page 17: Gaia AOCSGaia AOCSAstroStar tracker
Page 21 and 22: Specific on Gaia: Timing architectu
Page 23 and 24: Final preparationPropellant fueling
Page 25 and 26: LaunchAnd spacecraft operations are
Page 27 and 28: General ApproachRequired performanc
Page 29 and 30: Major features of the study design
Page 31 and 32: Astro Beam (2/4)Astro Beam (3/4)
Page 33 and 34: APT Beam (1/4)APT Beam (2/4)
Page 35 and 36: Payload accommodationDimensions com
Page 37 and 38: GAIA mechanical modelGAIA mechanica
Page 39 and 40: Gaia configuration : 2002PLMSVMSuns
Page 41 and 42: 2002 Astrometric Instrument Configu
Page 43 and 44: 2002 FEM results: PLM eigenfrequenc
Page 45 and 46: Modal analysis resultsLateral mode
Page 47 and 48: Gaia configuration: 2005Satellite d
Page 49 and 50: Focal Plane Assembly A cold part at
Page 51 and 52: The mechanical SVM The thermal tent
Page 53 and 54: Torus designFPA design

Spacecraft development

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