1. SPICA / AIV&T issues Spacecraft 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 (beginning of 3Q of FY2012)
AIT plan
Integrated as PLM (STM)
Thermal test at cold 13m chamber)
Integrated into Spacecraft (STM)
Spacecraft Mechanical Environmental test & Thermal Vacuum Test FM
Proposed delivery : Jan (beginning of 4Q 2016)

4. STA Optical 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. STA Optical 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 Warm Electronics
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 : 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 : 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 (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
IOB
FPI
LHe
Mech. Cooler (commercial)
1Q-2Q FY2016, checkout with FM Bus Module Electronics before assembly/integration of FM Bus System

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

16. FPI Evaluation at cold Date & Duration: Place： Configuration:
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) (＋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.