spica / aiv&t issues spacecraft test program & model philosophy (tentative plan)
DESCRIPTION
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 PresentationTRANSCRIPT
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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
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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)
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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)
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STA Optical Performance test at cold (1)
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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
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STA Optical Performance test at cold (2)
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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
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5
67
8
STA Flat-mirror
5-axis stage
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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
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SPICA AIV&T timeline (tentative)
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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
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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)
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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
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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.
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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
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Focal Plane Instrument Assembly (FPIA) = IOB+FPI
TOB : Telescope Optical Bench
IOB: Instrument Optical Bench
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2300
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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.
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IOB
FPI FPI
LHe
Mech. cooler
FPI Evaluation at cold (2)
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