红外与激光工程, 2019, 48 (7): 0718004, 网络出版: 2019-08-07   

空间遥感器反射镜背部支撑结构设计

Back support structure design of mirror of space remote sensor
作者单位
中国科学院长春光学精密机械与物理研究所, 吉林 长春 130033
摘要
鉴于空间遥感器反射镜组件需要具有高面形精度、高可靠性和高稳定性支撑的性能, 设计了一种应用于天基反射镜的三点背部支撑结构, 该支撑结构包括锥套、柔节和修研垫。对三点背部支撑的支撑原理以及工程实现开展了深入研究。对引起三点背部支撑反射镜组件面形误差变化的误差源进行了归纳总结, 研究了各个误差源引起面形变化的作用机理, 对支撑结构开展相应的设计来缓解各个误差源导致的反射镜的面形精度的变化。首先采用有限元仿真的方法对设计结果开展静、动力学仿真, 然后对加工装配完成的反射镜组件开展了试验测试。测试结果表明, 在工作状态下采用该三点支撑结构的镜组件的面形误差优于λ/60(λ=632.8 nm), 镜体刚体位移小于0.01 mm, 镜体转角小于2″, 质量小于4.5 kg。整个组件具有合理的模态分布, 基频是254 Hz, 大大高于设计要求值120 Hz。镜组件在正弦振动和随机振动下的最大放大倍率为1.73倍, 在正弦振动和随机振动下的最大应力为369 MPa, 远低于选用材料的屈服极限。
Abstract
In view of the functional requirements of high surface shape error accuracy, high reliability and high stability of mirror support for space remote sensor, a three-point back support structure applied in the mirror support in the field of space was designed, the back support structure included taper sleeve, flexible segment and adjusting pad. The in-depth study was done about support principle and engineering realization of the three-point back support structure. The error source which caused the variation of surface shape error of the three-point back supporting mirror component was summarized, the theory of surface shape variation caused by various error sources was studied, and the corresponding design of the supporting structure was carried out to alleviate the variation of the surface shape error of the mirror caused by various error sources. Firstly, the static and dynamic simulation of the design results were carried out by means of finite element analysis, then the assembled and processed mirror assembly was tested. The results show that the surface shape error of mirror with the three-points support structure is better than λ/60(λ=632.8 nm), the rigid body displacement of mirror is smaller than 0.01 mm, the dip angle is smaller than 2″, the mass of the mirror component is smaller than 4.5 kg. The component has a reasonable distribution of modal, the fundamental frequency is 254 Hz, which is higher than the requirement of 120 Hz. The maximum magnification rate of the mirror assembly under sine vibration and random vibration is 1.73 times, and the maximum stress under sine vibration and random vibration is 369 MPa, far lower than the yield limit of the selected material.
参考文献

[1] Shao Jun. Investigation on supporting structure of spacial reflector[J]. Infrared, 2006, 27(4): 36-41. (in Chinese)

[2] Jiao Shiju. Achievement and prospect of satellite remote sensing technology in China[C]//Proceedings of SPIE, 1998, 3505: 26-30.

[3] Li Shenhua, Guan Yingjun, Xin Hongwei, et al. Lightweight designand flexible support of large diameter mirror in space camera[J]. Laser & Infrared, 2017, 47(11): 1422-1427. (in Chinese)

[4] Wang Kejun. Research on the lightweight design and compound support of the large-aperture mirror for space-based telescope[D]. Changchun: University of Chinese Academy of Sciences, 2016. (in Chinese)

[5] Li Zhilai, Xu Hong, Guan Yingjun, et al. Structural design of 1.5 m mirror subassembly for space camera[J]. Optics and Precision Engineering, 2015, 23(6): 1635-1641. (in Chinese)

[6] Cui Yongpeng, He Xin, Zhang Kai, et al. The support design of reflected mirror from the principle of three points supported[J]. Optical Instruments, 2012, 34(6): 56-61. (in Chinese)

[7] Yang Fei, Liu Guojun, An Qichang. Error allocation of opto-mechanical system for large aperture telescopebased on structure function[J]. Optics and Precision Engineering,2015, 23(1): 119-221. (in Chinese)

[8] Wang Kejun, Dong Jihong, Xuan Ming, et al. Compound support structurefor large aperture mirror of space remote sensor[J]. Optics and Precision Engineering, 2016, 24(7): 1719-1730. (in Chinese)

[9] Wang Xin. Optimal research on 800 mm reflect mirror and its support structure of space camera [D]. Xi′an: University of Chinese Academy of Sciences, 2014. (in Chinese)

[10] Zhang Lei, Ding Yalin, Xu Zhengping, et al. Long type scanning mirror with flexible supporting[J]. Infrared and Laser Engineering, 2015, 44(12): 3678-3683. (in Chinese)

[11] Chen Hongda, Chen Yonghe, Shi Tingting, et al. Lightweight and mounting design for primary mirror in space camera[J]. Infrared and Laser Engineering, 2014, 43(2): 535-540. (in Chinese)

[12] Xu Hong, Guan Yingjun. Structural design of 1m diameter space mirror component of space camera. [J] Optics and Precision Engineering, 2013, 21(6): 1488-1495. (in Chinese)

[13] Li Xu, Sun Shijun, Tang Tianjin. Design of support structure for large mirror of space camera[J]. Spacecraft Recovery and Romote Sensing, 2016, 37(3): 91-99. (in Chinese)

[14] Cheng Zhifeng. Mechanical design of support structure of reflector in aerial camera [J]. Chinese Journal of Scientific Instrument, 2014, 35(6): 87-90. (in Chinese)

[15] Wu Qingwen, Yang Hongbo, Yang Jinsong, et al. Design and analysis for primary mirror and its support of space camera[J]. Optical Technique, 2004, 30(2): 152-156. (in Chinese)

[16] Zhu Nengbing. Research on the design of the supporting structure of lightweight mirror[D]. Chengdu: University of Chinese Academy of Sciences, 2016. (in Chinese)

[17] Wang Kejun, Dong Jibo, Li Wei, et al. Finite element analysis of overall structure of space camera[J]. OME Information, 2010, 17(12): 81-87. (in Chinese)

[18] Li Zongxuan. Analysis and test on the response of primary mirror flexure under random vibration [J]. Infrared and Laser Engineering, 2014, 43(s): 101-107. (in Chinese)

王克军, 董吉洪, 周平伟, 王晓宇, 姜萍. 空间遥感器反射镜背部支撑结构设计[J]. 红外与激光工程, 2019, 48(7): 0718004. Wang Kejun, Dong Jihong, Zhou Pingwei, Wang Xiaoyu, Jiang Ping. Back support structure design of mirror of space remote sensor[J]. Infrared and Laser Engineering, 2019, 48(7): 0718004.

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