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SPICA / AIV&T issues Spacecraft test program & model philosophy (tentative plan). Feb. 19 2010 revised Nov. 19, 2009 1 st draft by H. Matsuhara, N. Takahashi, T. Nakagawa. SPICA Telescope Assembly (STA). 3m-class cooled telescope Monolithic Mirror Ceramic material (SiC) - PowerPoint PPT Presentation
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SPICA / AIV&T issuesSpacecraft test program & model philosophy (tentative plan)
Feb. 19 2010 revised
Nov. 19, 2009 1st draft
by
H. Matsuhara, N. Takahashi, T. Nakagawa
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 SPICA: WFE 0.35μm, 5K (3.5m) AKARI: WFE 0.35μm, 6K (70cm) Herschel: WFE 6μm, 80K (3.5m)
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 TestFM
Proposed delivery : Jan. 2017 (beginning of 4Q 2016)
STA Optical Performance test at cold (1)
4
Date & duration : 1Q of CY2017, 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)
5
Anti-Vibration Table
Test Specimen Mount Table (with Shroud)
Pillar of V
acuum V
essel
Independent Foundation
Cryo Sorption Pumps
AC
F
Turbo Molecular Pumps
Gear
Motor
Interferometer
GHe
LN2
LN2 Shroud
GHe Shroud
AC
F
1
2
34
5
67
8
STA Flat-mirror
5-axis stage
PLM Thermal Test at cold
Purpose Evaluation of PLM cooling
system performances 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
6
SPICA AIV&T timeline (tentative)
7
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 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
Delivery date of FM: June 2016 (August 2016 at worst) in the proposed scenario.
Warm Electronics Similar as above, except for the terminology (CQM PM
(proto-model) Spacecraft DHS simulator(SpaceWire I/F) will be developed,
and distributed hopefully before 2014 ( under discussion)
STM (Structure Thermal Model) for FPIs
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
Oct. 2012 : before starting of assembly of PLM(STM) for the system Mechanical & Thermal Test
CQM (Cold Qualification Model) for FPIs
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 8.
FPI: SPICA system test plan
With STM: Mechanical Environmental test & thermal test at cold at the
PLM level Mechanical Environmental test & Thermal vacuum test at
Spacecraft level Measure disturbance at FPI from J-T cooler/AOCS
With CQM: Cooling compliance test with J-T (PM) Evaluate effect of mechanical disturbances from J-T (PM) and
AOCS simulator, Evaluate 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 Thermal test at cold at PLM level
12
Focal Plane Instrument Assembly (FPIA) = IOB+FPI
TOB : Telescope Optical Bench
IOB: Instrument Optical Bench
13
2300
FPI Evaluation at cold (1)
Date & Duration: latter half of CY2016, 1-2 months
Place : 6m Space Chamber at Tsukuba Space Centre (tbd)
Configuration: IOB(FM dummy) + FPI(FM) + cooler(TBD) + 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.
14
IOB
FPI FPI
LHe
Mech. cooler
FPI Evaluation at cold (2)
15