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X-Ray Gratings Mission

X-Ray Gratings Mission. Deep into that darkness peering, long I stood there, wondering, fearing , doubting, dreaming dreams no mortal ever dared to dream before. Edgar Allan Poe. Mechanical Sara Riall Dave Peters 19 – 23 March 2012. OVERVIEW. CCDS. SHIELD. DTU (2X). ANTENNA.

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X-Ray Gratings Mission

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  1. X-Ray Gratings Mission Deep into that darkness peering, long I stood there, wondering, fearing, doubting, dreaming dreams no mortal ever dared to dream before. Edgar Allan Poe Mechanical Sara Riall Dave Peters 19 – 23 March 2012

  2. OVERVIEW CCDS SHIELD DTU (2X) ANTENNA RIU (2X) FMA COVER METERING STRUCTURE IAU(2X) CDU FMA DPU(2X) TANK(2X) RMU PSE PO(2X) BATTERY SOLAR ARRAY

  3. Configuration(s) • Design shown in the following slides is for the off-pointing (OP) design • Deltas for the Critical Angle Transmission (CAT) design • Mass of the Focal Mirror Assembly remains the same - 213kg • Mass of the Instrument suite reduces from - 197.9kg to 84.5kg • These changes will affect the mass properties of the observatory. • Possible design changes to correct for this mass decrease & the CP/CG offset include • Reconfiguration of the solar array. • If changes to the solar array reduces the size enough that it can no longer serve as the sunshade for the FMA, addition of a sunshade will need to be incorporated OR, • Addition of balance mass to the instrument deck OR, • A combination of both.

  4. Requirements • Launch Vehicle • Mission needs to supply their own Payload Adapter Fitting (PAF) and their own separation. • Custom design separation system (sep-nut) – 9.41kg • Custom design PAF – 124.5 kg • Mating to Falcon launch vehicle is done in the horizontal position • Encapsulating with the fairing is done in the horizontal position • General • All mechanisms and deployables are single fault tolerant • Focus mechanisms carried on AXSIO mechanical are now part of the instrument.

  5. Observatory Coordinate System

  6. Launch Configuration

  7. Deployed Configuration

  8. Joint Detail

  9. Mass Properties (stowed) C.G. 145 cm origin

  10. Mass Properties (deployed) C.G. 163 cm origin

  11. Center of Pressure C.G. 128.9 cm origin

  12. Composite Material – M55J data sheet

  13. Mass Rack-up & sanity check

  14. Ray Trace Original Configuration 45°

  15. FUTURE WORK • Trade between solar array length and sunshade capability • If shorter solar array is optimal, moving solar array to remove cp/cg offset is critical • Placement of electronics and momentum wheels to optimized the weight distribution in the bus • Deck will need ccd contamination control door • Deck may also need to be reviewed for added complexity due to integration of heat pipes

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