Spacecraft development

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2002 Payload Optimisation Reduce mass and size for being compatible with Soyouz launcher Total launch mass ~ 2270 kg (A5) : mass objective < 1500 kg ( - 34%) Reduce the PLM mass ~ 900 kg: Astro focal plane assemblies ~ 168 kg (with video electronics) mass decrease obtained by reducing the number of CCDs Optics with their mounts ~ 270 kg : mass decrease is obtained by reducing the reflector sizes Structure ~ 290 kg structure mass decrease is a consequence of size and supported mass reduction Mass reduction objective is in conflict with accuracy requirement. Design improvement is mandatory for Soyouz compatibility. Reduce overall complexity and cost– Try to harmonise CCD definitions– Minimise hardware tests– Suppression of mechanisms whenever possible2002 Design Features Astrometric Instrument– Superimpose the two focal planes, by making use of a focal plane combinerlocated close to the exit pupil– Increase the overall optical path length for practically suppressing opticaldistortion– Enlarge CCDs along scan (~ 60 mm x 45 mm)– Passive cooling of the FPA detectors down to 160 K – 170 K (radiation) Spectrometric Instrument– Along scan dispersion for RVS– Suppression of RVS mechanism– RVS spectral resolution improved by a factor 2– Medium Band Photometry improved
2002 Astrometric Instrument ConfigurationAstro focalplaneM1M3FPAradiatorM2M4(1/2 focal planecombiner)M5, M6(commonreflectors) 6 mirrors in total M4, M5 and M6 connected or common to both paths Focal plane common to both paths2002 Spectrometer baselineScanaxisM1M3M2255.10 MMAlong scan disp. - Horizontal telescope Scale: 0.10 AsF 11-Mar-02RVS – MBP not shown Needs more optimisation to : Try to reduce diameters / mass / number of lenses Get more realistic air gaps and lens thicknesses13 lenses for the RTVS optic
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 and 18: Gaia AOCSGaia AOCSAstroStar tracker
Page 19 and 20: CCSVM MIL-STD-1553B Bus NGaia Commu
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: Gaia configuration : 2002PLMSVMSuns
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

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