optical performance of sot: test report for the flight telescope kiyoshi ichimoto (naoj) and
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Optical Performance of SOT: Test Report for the Flight Telescope Kiyoshi Ichimoto (NAOJ) and SOT-Team. Optical Performance Tests of SOT:. ◇ Wavefront measurement of OTA - Initial alignment canceling the gravitation - Under the thermal condition in orbit - PowerPoint PPT PresentationTRANSCRIPT
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Optical Performance of SOT:Test Report for the Flight Telescope
Kiyoshi Ichimoto (NAOJ)and
SOT-Team
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
◇ Wavefront measurement of OTA - Initial alignment canceling the gravitation - Under the thermal condition in orbit - Mechanical launch loads
◇ Pointing stability against microvibration in S/C
◇ Polarization characterization
Optical Performance Tests of SOT:
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
OTA flight model integration
Target mirror
clinometer Vertical meter
Six axisstage
Reference flat
Telescope Up
M1
M2
OTA
InterferometerMiniFiz
Optical bench
Dummy OBU
Alignment cube
OTA is integrated on a test tower. Interferometoric measurement with reference flat at the top. OTA is both in upside top and upside down to cancel gravity.
Rotation mechanism
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
OTA upside top
Gravitational deformation of OTA optics
Average of upside top and upside down giving Zero-G WFE
Initial alignment of M1,M2 and CLUOTA WFE map at T=20C uniform
20nm rms ~ /32 rms @633nm
= Strehl ~ 0.96
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
OTA Optical Thermal Test: 2005.3.11-20
Optical performance of OTA under the thermal condition in orbit
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
It is expected that when the M1 temperature reaches ~55C, the optical performance of OTA degrades to Strehl ~ 0.8 @500nm. The temperature increase of M1 is caused by contamination of M1, and the ‘mission life’ of OTA is estimated to be > 3yr, which is realized by the extensive baking of the components.
WFE ~15nm rms
Cold case:
Optical performance of OTA under the thermal condition in orbitDifference of WFE map from T=20C uniform
Hot case
M1 ～ +20C , upper truss ～ 30C
WFE ~11nm rms
M1 ～ +30C, upper truss ～ C
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Solar-B on shake machine, Oct. 2005
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
21.5nm rms 19.1nm rms 5.5nm rms
Pre-vibration differencePost-vibration
WFE before and after S/C vibration test, Oct.005
Defocus, tile subtracted
You will find more info. in poster presentations;Y. Suematsu “On the Evaluation of Optical Performance of Observing Instruments”Y. Suematsu, etal. “Optical Performance of Optical Telescope Assembly of SOT: Confirmation of Diffraction-Limited Performance”
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Microvibration Transmissibility Test
There are various sources of mechanical disturbance in the spacecraft:
- Momentum wheels- IRU-A & B (Gyro)- Moving mechanisms in mission
instruments
.
FPP
IRU-BOX
IRU-B -
IRU-A
MWTo evaluate the possible pointing error of SOT, microvibration transmissibility test was performed
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Strehl degradation due to image jitter
Strehl degradation due to optical error
(requirement)
Image stability; SOT requirement = 0.09” (3 = 0.042” (0-p)
psf with sinusoidal jitter, = 390nm
(sinusoidal jitter)
0.09” (3
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
dolly
Laser beam was induced from the OTA entrance and pointing error is measured optically.
PSD
theodolite
630nm tunable laser
Test configuration
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
FG-CCD
FPP
CT-CCD
Image plane
PSDData logger
Acc. sensors
Insertion pipe
180oBS
Optical layout
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
EIC/MIC
2004.11
Before vib.
2005.9.28
Post-vib.
2005.10.26
Post-TV
2006.4
FPP-NFI-FW
(110-120Hz)
PSD-X 0.0021 0.0019 0.0034
PSD-Y 0.0132 0.0076 0.0090
FPP-BFI-FW
(110-120Hz)
PSD-X 0.0009 0.0019 0.0028
PSD-Y 0.0127 0.0076 0.0091
XRT-VLS
(no cont.rotation)
PSD-X 0.18 (0-p) 0.10 (0-p) 0.09 (0-p)
PSD-Y 0.20 (0-p) 0.09 (0-p) 0.09 (0-p)
XRT-FW1
(63-72Hz)
PSD-X 0.0052 0.0015 0.0075
PSD-Y 0.0220 0.0042 0.0096
XRT-FW2
(63-72Hz)
PSD-X 0.0106 0.0054 0.0032
PSD-Y 0.0217 0.0194 0.0103
EIS-SHT
(no cont.rotation)
PSD-X Neg. Neg. Neg.
PSD-Y Neg. Neg. Neg.
EIS-F-Mirr
(no cont.rotation)
PSD-X Neg. Neg. Neg.
PSD-Y Neg. Neg. Neg.
IRU-A
(110-120Hz)
PSD-X 0.0015 0.0012 0.0011
PSD-Y 0.0011 0.0015 0.0014
IRU-B1/2
(150-160Hz)
PSD-X 0.0066 0.0064 0.0081
PSD-Y 0.0070 0.0059 0.0076
Record of induced pointing error (SOT requirement = 0.03”rms) (by the PSD sensor from continuous rotation measurement, unit=arcsec rms)
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Disturbance level of XRT-VLS Final Strehl ~ 0.59
(requirement)
Pointing disturbance caused by XRT-VLS shutter
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
OTA
OBU
FPP
OTA-FPP integrated on OBU ( 2005 May)
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Reflected light from 2FSHeliostat window
Natural Sunlight Test: 2005.6End-to-End functional test of SOT as a magnetograph
Sheet polarizer (LP, RCP, LCP)
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Xincidentproduct
V
U
Q
I
xxxx
xxxx
xxxx
xxxx
V
U
Q
I
33231303
32221202
31211101
30201000
0.3333 0.3333 0.2500 0.0010 0.0500 0.0067 0.0050 0.0010 0.0067 0.0500 0.0050 0.0010 0.0067 0.0067 0.0500
are determined for SP and NFI with an accuracy
‘SOT Polarization Response Matrix’ X
Crosstalks among I,Q,U,V will be negligible at = 0.1%
X <
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
See poster by Lites etal.
Left CCD 1.0000 0.2205 0.0187 -0.0047 0.0012 0.4813 0.0652 -0.0014 0.0001 0.0513 -0.4803 -0.0057 -0.0025 0.0032 -0.0046 0.5256
Right CCD 1.0000 -0.2112 -0.0170 -0.0051 -0.0025 -0.4875 -0.0560 0.0022 -0.0001 -0.0426 0.4907 0.0060 0.0027 -0.0008 0.0042 -0.5301
Median Mueller matrix
X matrix of SP at the scan center; CCD image each element is scaled to median + tolerance, x00 (=1) is replaced by I-image
The X matrix can be regarded as uniform over the CCD and scan position.
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Sensitivity of NFI on polarization and detection limit of the weak magnetic field
Wavelength
(nm)
geff Pol. Sensitivity(diagonal element of
x)
Detection limit of B
( = 0.001, Gauss)
remark
V QU Bl Bt
MgI 517.2 1.75 0.577 0.452 86 656 Chrom. B
FeI 525.0 3.00 0.266 0.609 18 106 Photos. B
FeI 557.6 0.00 - - - - Photos.Dopp.
NaI 589.6 1.33 0.633 0.297 40 (670) Chrom. Bl
FeI 630.2 2.50 0.526 0.503 12 122 Photos. B
HI 656.3 1.33 0.402 0.073 119 >2000 Chrom. Str/Dopp.SOT is now a well calibrated polarization instrument!
See poster by Ichimoto etal.
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Other verification items of the sunlight test presented in posters
- Throughput / Light level Shimizu etal. “Estimate on SOT light level in flight with
throughput measurements in SOT sun test.”
- System function as a magnetograph/Dopplergraph Katsukawa, etal . “Calibration of SOT
Dopplergrams”
- Mutual alignments / image scale between SP/NFI/BFI Okamoto, etal. “Examinations of the relative alignment of
the instruments on SOT”
- Vignetting/Ghost etc.
Solar-B Science Meeting, 2005.11.8-11 in Kyoto
Thank you!