Nov. 19, 2009 prepared by H. Matsuhara, N. Takahashi, T. Nakagawa SPICA / AIV&T issues Spacecraft test program & model philosophy (tentative plan) Nov. 19, 2009 prepared by H. Matsuhara, N. Takahashi, T. Nakagawa

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

FPI Model philosophy 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 Delivery date of FM: June 2016 (August 2016 at worst) in the proposed scenario.

STM : Structure Thermal Model Description Mechanical I/F specifications (including disturbance sources) is equivalent to that of FM Required Function Same mechanical I/F specifications to FM Nearly the same thermal I/F (TBD, for spacecraft(PM) thermal test) Equipped with thermometers, acceleration sensors for measurement of I/F environmental condition Simulate mechanical disturbance according to the system operation modes Proposed Delivery Jan. 2013 : before starting of assembly of spacecraft (PM) for the system Mechanical Thermal Test

CQM : Cold Qualification Model Description Nearly equivalent to FM incorporating with detectors operable at low-temperature expected in orbit 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 Proposed Delivery Apr. 2015 : when the PLM(FM) is available for us to test the items (a), (b), & (c) in page 2.

ＳＰＩＣＡ system test plan With STM: With CQM: With FM Measure disturbance at FPI from J-T/AOCS under Spacecraft MTM test in 2014 With CQM: Cooling test with J-T (PM) (in PLM (PM)) Evaluate effect of mechanical disturbances from J-T/AOCS simulator, electrical interferences among FPIs, J-T, AOCS in the latter half of FY2015 With FM FPI evaluation at cold (optical & electrical) STA optical performance test at cold PLM thermal test

SPICA AIV&T timeline (tentative)

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

FPI Evaluation at cold (1) Date & Duration: latter half of 2016, 1-2 months Place： 6m Space Chamber at Tsukuba Space Centre(tbd) Configuration: IOB(FM dummy)＋FPI(FM)＋cooler(TBD)＋FPI-E(FM)＋STA Simulator 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.

FPI Evaluation at cold (2) IOB FPI LHe Mech. cooler

ＳＰＩＣＡ Telescope Assembly (STA) 3.5m is technically a good choice Monolithic Mirror Ceramic material (SiC) No deployable mechanism Simple, Feasible, Reliable Smooth PSF Essential for Coronagraph Herschel & AKARI Heritage SPICA: WFE 0.35μm, 5K (3.5m) AKARI: WFE 0.35μm, 6K (70cm) Herschel: WFE 6μm, 80K (3.5m)

STA Optical Performance test at cold (1) Date & duration： 1st harf of 2017, 1-2 months Place : 6m Space Chamber in Tsukuba Space Center Configuration IOB（ＦＭ）＋STA(FM) Additional thermal sheild in the chamber Purposes: Optical performance evaluation of ＳＴＡ at <10K Multiple measurements are connected by the Stitching Method

STA Optical Performance test at cold (2)

PLM Thermal Test Purpose Method Evaluation of PLM cooling system performances Method Additional shields in the existing 13m(?) space chamber in Tsukuba Shields are externally lifted by mechanical coolers

Q & A : AIV (1) Definition of spacecraft level test program and consequent requirements on the instrument models delivered to JAXA - including alignment concept for spacecraft level integration. See previous pages. (related Q) the proposed schedule for SAFARI instrument models:     STM  : Jan 2013     CQM  : April 2015 (August 2015 at worst)     FM   : June 2016  (i.e. 2.5 yrs before launch)

Q & A: AIV (2) What are the ground test thermal conditions? Can we use lots of power for the mechanisms? To be answered by Sugita-san, Takahashi-san, Murakami-san More or less described above.

Q & A: AIV (3) Are the different orientations of the FPU during the test campaign on system and satellite level well known?. 1st system AIV : STA (& FPIA) in vertical FPI evaluation at cold : TBD, vertical? STA evaluation at cold : horizontal in 6m chamber PLM Thermal test & Final system V&T: vertical