Opto-mechanical-thermal integration analysis of Doppler asymmetric spatial heterodyne interferometer
doi: 10.37188/CO.2023-0234
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摘要:
为提高地基多普勒非对称空间外差(DASH)干涉仪在恶劣温度下的探测精度，对系统进行了光机热集成分析。首先，依据干涉仪的工作原理和相位算法建立了相位与温度的关联依据。接着，设计了光机热分析模型和热变形数据获取模型，采用温度负载仿真分析给出了干涉模块和成像光学系统在不同温度下的变形数据，拟合得到热变形所导致的相位误差。最后，基于各部件热变形造成的风速误差，给出合理的温控方案。结果表明，干涉模块占据主因，必须确保温度控制在（20±0.05） °C内，并针对温度敏感部件进行温度控制，此时，该部件造成的风速误差为3.8 m/s。成像光学系统放大倍数的热漂移、成像光学系统和探测器相对位置的热漂移占据次因，应将其控制在（20±2） °C以内，此时该部件造成的风速误差为3.05 m/s。通过以上措施可以将干涉模块、成像光学系统、成像光学系统与探测器的相对位置三者共同造成的风速测量误差控制在6.85 m/s内。本文的分析方案和温控措施可以为DASH干涉仪工程应用提供理论依据。
Abstract:In order to improve the detection accuracy of Doppler asymmetric spatial heterodyne (DASH) interferometer in harsh temperatures, an opto-mechanical-thermal integration analysis is carried out. Firstly, the correlation between the interference phase and temperature is established according to the working principle and the phase algorithm of the interferometer. Secondly, the optical mechanical thermal analysis model and thermal deformation data acquisition model are designed. The deformation data of the interference module and the imaging optical system at different temperatures are given by temperature load simulation analysis, and the phase error caused by thermal deformation is obtained by fitting. Finally, based on the wind speed error caused by thermal deformation of each component, a reasonable temperature control scheme is proposed. The results show that the interference module occupies the main cause, the temperature must be controlled within (20±0.05) °C, and the temperature control should be carried out for the temperature sensitive parts, and the wind speed error caused by the part is 3.8 m/s. The thermal drift between the magnification of the imaging optical system and the thermal drift of the relative position between the imaging optical system and the detector should occupy the secondary cause, which should be controlled within (20±2) °C, and the wind speed error caused by the part is 3.05 m/s. In summary, the wind measurement error caused by interference module, imaging optical system, and the relative position between the imaging optical system and the detector can be controlled within 6.85 m/s. The analysis and temperature control schemes presented in this paper can provide theoretical basis for DASH interferometer engineering applications.
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Figure 7. Schematic diagram of interference module. γ: wedge angle of the spacer, α: vertex angle of the field-widening prism, η: wedge angle of the grating spacer
Figure 8. Structural diagram of interference module. (a) Optical model; (b) interference module physical diagram
Figure 9. (a) Optical-mechanical model; (b) interference module optical-mechanical structure
Figure 18. Relationship between Littrow angle and temperature for (a) G1 arm; (b) G2 arm
Figure 19. Relationship between Littrow wavenumber and temperature for (a) G1 arm; (b) G2 arm
Figure 20. The variance of interference phase error caused by the drift of the G1 arm and G2 arm at different temperatures
Figure 21. Relationship between the thermal drift value of the optical path difference and temperature
Figure 22. Relationship between phase thermal drift caused by optical path difference and temperature thermal drift
Figure 23. Relationship between wind speed error caused by G1 and G2 thermal drift and temperature
Figure 24. Relationship between wind speed error caused by optical path difference and temperature
Figure 28. Magnification error of the imaging optical system at different temperatures
Figure 29. Relationship between phase error caused by thermal drift of magnification and temperature
Figure 30. Thermal analysis cloud map of relative positions of the imaging optical system and the detector
Figure 31. Variation of the changes of relative position between the imaging optical system and the detector with temperature
Figure 32. Variation of phase thermal drift caused by the changes of relative position between the imaging optical system and the detector with temperature
Figure 33. Wind speed error caused by thermal drift of magnification at different temperatures
Figure 34. Wind speed error caused by the changes of relative position between the imaging optical system and the detector at different temperatures
Table 1. Index parameters of DASH interferometer
Attribute Parameter Fore-optical system Field of view 5.314°×4° Clear aperture diameter 35 mm Interferometer module Littrow wavelength/nm 557.137 Target line wavelength/nm 557.7 Groove spacing/(gr·mm−1) 600 Littrow angle/(°) 9.6216 Interferometer offset/cm 1.75 Imaging-optical system F/# 7.35 Total length 223.5 mm Magnification 0.5899 Transmissivity 0.93 Detector CCD pixel size/μm 13 CCD pixel number 1024 
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Table 2. Material characteristics of interferometer
Elements Materials Young’s modulus (MPa) Poisson’s ratio Thermal conductivity
($ \mathrm{W}\cdot {\mathrm{m}\mathrm{m}}^{-1}\cdot {\mathrm{K}}^{-1} $)CET
($ {10}^{-7}\cdot {\mathrm{K}}^{-1} $)Beam splitting(BS) H-K9LAGT 81450 0.209 0.00075 72 Field-widening Prism(F1,F2) H-LaK2A 94150 0.295 0.00075 80 Gratings(G1,G2) Fused-Silica 74000 0.17 0.00138 5.1 Spacer(W1) H-FK6 70070 0.3 0.00075 131 Spacer(W2) Fused-Silica 740000 0.17 0.00138 5.1 Parallel bias(P1) H-K9LAGT 81450 0.209 0.00075 72 Mechanical shell,Work platform Al alloy2A12 72000 0.3 0.203 230
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