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SPICA / AIV&T issues Spacecraft test program & model philosophy

SPICA / AIV&T issues Spacecraft test program & model philosophy. Rev. C, Mar. 13 th , 2010 by H. Matsuhara, N. Takahashi, T. Nakagawa. Revised points (from Feb 19 ESA-JSAS telecon.) are indicated by red. ＳＰＩＣＡ Telescope Assembly (STA). 3m-class cooled telescope Monolithic Mirror

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SPICA / AIV&T issues Spacecraft test program & model philosophy

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  1. SPICA / AIV&T issuesSpacecraft test program & model philosophy Rev. C, Mar. 13th, 2010 by H. Matsuhara, N. Takahashi, T. Nakagawa Revised points (from Feb 19 ESA-JSAS telecon.) are indicated by red

  2. ＳＰＩＣＡ Telescope Assembly (STA) • 3m-class cooled telescope • Monolithic Mirror • Ceramic material (SiC) • No deployable mechanism • Simple, Feasible, Reliable • Smooth PSF • Essential for Coronagraph • Herschel & AKARI Heritage • AKARI: WFE 0.35μm, 6K (70cm) • Herschel: WFE 6μm, 80K (3.5m) •  SPICA: WFE 0.35μm, 5K (3.5m)

  3. STA models & proposed delivery (tentative plan) • STM (Structure Thermal Model) • Proposed delivery : Oct. 2012 (beginning of 3Q of FY2012) • AIT plan • Integrated as PLM (STM) • Thermal test at cold (@Tsukuba 13m chamber) • Integrated into Spacecraft (STM) • Spacecraft Mechanical Environmental test & Thermal Vacuum Test • FM • Proposed delivery : Jan. 2017 (beginning of 4Q 2016)

  4. STAOptical Performance test at cold (1) • Date & duration： • 1Q of CY2017, 1-2 months • Place : • 6m Space Chamber in Tsukuba Space Center • Configuration • IOB（ＦＭ dummy）＋STA(FM) • Additional thermal sheild in the chamber • Purposes: • Optical performance evaluation of ＳＴＡ at <10K • Multiple measurements are connected by the Stitching Method

  5. STAOptical Performance test at cold (2) Flat-mirror STA 5-axis stage

  6. PLM Thermal Test at cold (STM and FM) • Purpose • Evaluation of PLM cooling system performances • Alignment measurement between STA and FPIA with FPC? • Date & Duration • STM: April 2013 • FM: Dec. 2017, ~2months • Method • Additional shields in the existing 13m space chamber in Tsukuba • Shields are externally lifted by mechanical coolers

  7. SPICA AIV&T timeline (tentative) Consistency need to be checked with Industries’ estimates !!

  8. Key issues for FPI AIV&T • FPI’s system-level test plan should take account of the critical issues as below: • (a) FPI is cooled to <5K with J-T coolers under extremely careful Spacecraft thermal design. • (b) disturbance and interference from J-T coolers and AOCS (such as RW, gyro) • To assure high-sensitivity (low-noise) in orbit • (c) Co-operation with FPC-G to establish the pointing stability • Interferences? Alignment? • (d) Co-focus among FPIs (especially MIR’s) • Since STA 2ry cannot be adjusted so frequently in orbit

  9. FPI Model philosophy • Cold FPIs • Minimum number of Models required for the system level test (in the previous page) is: • FM (Flight Model) (& its spare) • STM : structure thermal model • CQM : cold qualification model • Warm Electronics • Similar as above, except for the terminology (CQM  PM (proto-model) • A concern about SAFARI Warm Electronics STM : can the requested heat dissipation be simulated by a heater? • Spacecraft DHS simulator(SpaceWire I/F) will be developed, and distributed hopefully before 2014 ( under discussion)

  10. STM (Structure Thermal Model) for FPIs • Purposes • Evaluate their mechanical (at ambient temp.) & thermal compliances at cold, in the system level (PLM or Spacecraft) • Evaluate transfer function of mechanical disturbances originated from FPIs • Required Function • Same mechanical I/F specifications to FM • Same thermal I/F specifications to FM • Equipped with thermometers, acceleration sensors for measurement of I/F environmental condition • Simulate mechanical disturbance according to the system operation modes • Proposed Delivery • Oct. 2012 : before starting of assembly of PLM(STM) for the system Mechanical & Thermal Test

  11. CQM (Cold Qualification Model) for FPIs • Purposes • Evaluate thermal compliance at cold with J-T(PM) cooler • Evaluate susceptibility to mechanical disturbances from J-T (disturbance simulator) and AOCS simulator • Evaluate electrical interferences among FPIs, J-T, AOCS • Required Function • Same thermal, mechanical, electrical I/F specifications to FM • Equipped with detectors operable at low-temperature, with the same noise performance as that of FM • Simulate heat-dissipation (load to J-Ts), mechanical disturbance according to the system operation modes • Equipped with a optical image, to check the co-focus among FPIs • Proposed Delivery • Apr. 2015 : when the PLM(FM) is available for us to test the items in page 2. • Earlier delivery enables us to feedback for the design of FM

  12. FM (Flight Model) for FPIs • Purposes • For on-orbit observations; for our scientific objectives, of course! • After delivery and assembly to FPIA, FM will go to the “evaluation at cold” in the dedicated chamber for evaluation of interferences, co focus among FPIs • Required Function • Science Grade optical, noise, and sensitivity performances! • Note that after the test called “FPI evaluation at cold”, long-wavelength channel detectors cannot be operated (even may not be switched on??) - so how to verify its health during the long waiting time before launch/cooling in orbit? • Delivery date of FM: June 2016 (August 2016 at worst) in the proposed scenario.

  13. FPI: ＳＰＩＣＡ system test plan • With STM: • Mechanical Environmental test & thermal test at cold at the PLM level • Mechanical Environmental test & Thermal balance test at Spacecraft level • Measure disturbance at FPI from J-T cooler/AOCS • With CQM: • Cooling compliance test with J-T (PM) most important • Evaluate susceptibility to mechanical disturbances from J-T (disturbance simulator) and AOCS simulator, • Co-focus is also checked to some level at cold (tbd) • Evaluate electrical interferences among FPIs, J-T, AOCS in the 1st whole FM V&T in 2016 if FM is not available yet • With FM • FPI evaluation at cold (optical & electrical) • STA optical performance test at cold • Thermal test at cold at PLM level

  14. FPI(CQM or FM) test config. in the 1st Whole FM V&T • 1Q-2Q FY2016, checkout with FM Bus Module Electronics before assembly/integration of FM Bus System IOB FPI FPI LHe Mech. Cooler (commercial)

  15. Focal Plane Instrument Assembly (FPIA) = IOB+FPI TOB：Telescope Optical Bench IOB: Instrument Optical Bench 2300 mm

  16. FPI Evaluation at cold • Date & Duration: • latter half of CY2016, 1-2 months • Place： • 6m Space Chamber at Tsukuba Space Centre (tbd) • Configuration: • IOB(FM)＋FPI(FM)＋cooler(TBD – probably not necessary)＋FPI warm electronics (FM) (＋STASimulator..) • Purposes: • With all FM FPIs together, all functional, electrical & optical performance evaluation at cold (operating temperature in orbit) as well as interference test. • Optical performance will be measures with a STA simulator.

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