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Mechanical Sara Riall Dave Peters 2 – 4 May 2012

X-Ray Gratings Mission Delta NOTE: Original Gratings data through slide 15, then Gratings Redux configuration. Change is inevitable - except from a vending machine.  ~Robert C. Gallagher. Mechanical Sara Riall Dave Peters 2 – 4 May 2012. OVERVIEW. CCDS. SHIELD. DTU (2X). ANTENNA.

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Mechanical Sara Riall Dave Peters 2 – 4 May 2012

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  1. X-Ray Gratings Mission DeltaNOTE: Original Gratings data through slide 15,then Gratings Redux configuration Change is inevitable - except from a vending machine.  ~Robert C. Gallagher Mechanical Sara Riall Dave Peters 2 – 4 May 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

  16. X-Ray Mission Redux Mechanical Dave Peters Sara Riall 2-4 May 2012

  17. X-ray gratings redux

  18. Stowed in Falcon 9

  19. Stowed in Taurus II

  20. Bus layout DTU(2) IAU(2) DPU(2) PSE FMA RADIATORS(2) S/A REACTION WHEELS(4) PROP TANK(2) BUS CDU RMU RIU BATTERY PO(2)

  21. Instrument Deck Layout RIU CAMERA(2) DEA SUN SHIELD DPA

  22. Cp/CG Offset

  23. X-ray Grating Metering Structure Comparison

  24. Mass Rack Up Redux

  25. Acronym List CTE- coefficient of thermal expansion • FMA- flight mirror assembly • SMAD- space mission analysis and design • S/A –solar array • Cp-center of pressure • Cg- center of gravity • s/c –space craft • MS- mechanical structure • CCW- counterclockwise • HGA- High gain antenna • IAU- Integrated avionics unit • RIU- Remote interface unit • PO-precision unit • CDU-COMSEC decryption unit • DPA-data processing assembly • RMU- redundancy management unit

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