Optical Performance of SOT Test Report for the

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

Optical Performance Tests of SOT: ◇ Wavefront measurement of OTA - Initial alignment canceling the gravitation - Under thermal condition in orbit - Mechanical launch loads ◇ Pointing stability against microvibration in S/C ◇ Polarization characterization Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

OTA flight model integration clinometer Vertical meter Target mirror Reference flat Alignment cube M 2 Dummy OBU OTA Interferometer Mini. Fiz Six axis stage s OTA is integrated on a test tower. s Interferometoric measurement with reference flat at the top. s OTA is both in upside top and upside down to cancel gravity. M 1 Telescope Up Optical bench Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto Rotation mechanism

Initial alignment of M 1, M 2 and CLU OTA WFE map at T=20 C uniform OTA upside top Gravitational deformation of OTA optics Average of upside top and upside down giving Zero-G WFE 20 nm rms ~ l/32 rms @633 nm = 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 thermal condition in orbit Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

Optical performance of OTA under thermal condition in orbit Difference of WFE map from T=20 C uniform Cold case: M 1～ +20 C , upper truss ～ -30 C DWFE ~15 nm rms Hot case M 1～ +30 C, upper truss ～ + 2 C DWFE ~11 nm rms It is expected that when the M 1 temperature reaches ~55 C, the optical performance of OTA degrades to Strehl ~ 0. 8 @500 nm. The temperature increase of M 1 is caused by contamination of M 1, and the ‘mission life’ of OTA is estimated to be > 3 yr, which is realized by the extensive baking of the components. 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

WFE before and after S/C vibration test, Oct. 005 Pre-vibration Post-vibration - 21. 5 nm rms difference = 19. 1 nm rms 5. 5 nm rms 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 FPP IRU-B - There are various sources of mechanical disturbance in the spacecraft: - Momentum wheels - IRU-A & B (Gyro) - Moving mechanisms in mission instruments IRU-BOX MW IRU-A. Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto To evaluate the possible pointing error of SOT, microvibration transmissibility test was performed

Image stability; SOT requirement = 0. 09” (3 s) = 0. 042” (0 -p) (sinusoidal jitter) (requirement) Strehl degradation due to optical error Strehl degradation due to image jitter psf with sinusoidal jitter, l = 390 nm Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto 0. 09” (3 s)

Test configuration 630 nm tunable laser Laser beam was induced from the OTA entrance and pointing error is measured optically. theodolite PSD dolly Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

Optical layout FPP FG-CCD CTCCD 180 o. BS Acc. sensors Data logger Insertion pipe Imag PSD e plane Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

Record of induced pointing error (SOT requirement = 0. 03”rms) (by the PSD sensor from continuous rotation measurement, unit=arcsec rms) EIC/MIC 2004. 11 Before vib. 2005. 9. 28 Post-vib. 2005. 10. 26 FPP-NFI-FW (110 -120 Hz) PSD-X 0. 0021 0. 0019 0. 0034 PSD-Y 0. 0132 0. 0076 0. 0090 FPP-BFI-FW (110 -120 Hz) 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) XRT-FW 1 (63 -72 Hz) PSD-X 0. 0052 0. 0015 0. 0075 PSD-Y 0. 0220 0. 0042 0. 0096 XRT-FW 2 (63 -72 Hz) PSD-X 0. 0106 0. 0054 0. 0032 PSD-Y 0. 0217 0. 0194 0. 0103 EIS-SHT (no cont. rotation) PSD-X Neg. PSD-Y Neg. EIS-F-Mirr (no cont. rotation) PSD-X Neg. PSD-Y Neg. IRU-A (110 -120 Hz) PSD-X 0. 0015 0. 0012 0. 0011 PSD-Y 0. 0011 0. 0015 0. 0014 IRU-B 1/2 PSD-X 0. 0066 (150 -160 Hz) Solar-B Science Meeting, PSD-Y 2005. 11. 8 -11 in 0. 0070 Kyoto 0. 0064 0. 0081 0. 0059 0. 0076 Post-TV 2006. 4

Pointing disturbance caused by XRT-VLS shutter (requirement) Disturbance level of XRT-VLS Final Strehl ~ 0. 59 Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

OTA-FPP integrated on OBU ( 2005 May) OTA FPP OBU Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

Natural Sunlight Test: 2005. 6 End-to-End functional test of SOT as a magnetograph Sheet polarizer (LP, RCP, LCP) Reflected light from 2 FS Heliostat window Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

‘SOT Polarization Response Matrix’ X X are determined for SP and NFI with an accuracy d. X < 0. 0010 0. 3333 0. 0500 0. 0067 0. 3333 0. 0067 0. 0500 0. 0067 0. 2500 0. 0050 0. 0500 Crosstalks among I, Q, U, V will be negligible at e = 0. 1% Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto

X matrix of SP at the scan center; CCD image each element is scaled to median + tolerance, x 00 (=1) is replaced by I-image The X matrix can be regarded as uniform over the CCD and scan position. Median Mueller matrix 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 See poster by Lites etal. Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto 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

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 (e = 0. 001, Gauss) V QU Bl Bt remark Mg. I 517. 2 1. 75 0. 577 0. 452 86 656 Chrom. B Fe. I 525. 0 3. 00 0. 266 0. 609 18 106 Photos. B Fe. I 557. 6 0. 00 - - Na. I 589. 6 1. 33 0. 633 0. 297 40 (670) Chrom. Bl Fe. I 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. Photos. 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! Solar-B Science Meeting, 2005. 11. 8 -11 in Kyoto