1. 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

2. 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

3. 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 (August 2016 at worst) in the proposed scenario.

4. 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 : before starting of assembly of spacecraft (PM) for the system Mechanical Thermal Test

5. 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 : when the PLM(FM) is available for us to test the items (a), (b), & (c) in page 2.

6. 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

7. SPICA AIV&T timeline (tentative)

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

9. 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.

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

11. 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)

12. 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

13. STA Optical Performance test at cold (2)

14. 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

15. 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     CQM  : April 2015 (August 2015 at worst)     FM   : June 2016  (i.e. 2.5 yrs before launch)

16. 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.

17. 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