Design of flexure support of space compact reflector subassembly and dynamic analysis

Liu Ming; Zhang Lizhong; Li Xiang; Li Xiaoming; Zhang Jiaqi; Meng Lixin; Liu Junjie

doi:10.12086/oee.2018.170686

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Liu Ming, Zhang Lizhong, Li Xiang, et al. Design of flexure support of space compact reflector subassembly and dynamic analysis[J]. Opto-Electronic Engineering, 2018, 45(5): 170686. doi: 10.12086/oee.2018.170686

Citation:

Liu Ming, Zhang Lizhong, Li Xiang, et al. Design of flexure support of space compact reflector subassembly and dynamic analysis[J]. Opto-Electronic Engineering, 2018, 45(5): 170686. doi: 10.12086/oee.2018.170686

Design of flexure support of space compact reflector subassembly and dynamic analysis

1.
National and Local Joint Engineering Research Center of Space Optoelectronics Technology, Changchun University of Science and Technology, Changchun, Jilin 130022, China
2.
School of Precision Instrument and Opto-Electronics Engineering, Tianjin University, Tianjin 300072, China
3.
Tianjin Jinhang Institute of Technical Physics, Tianjin 300308, China

Fund Project: Supported by National Natural Science Foundation of China(91338116)

More Information

Corresponding author: Liu Ming, liuming2525775@126.com

Received Date 13 December 2017

Revised Date 11 February 2018

Published Date 01 May 2018

Abstract

Abstract

The mirror assembly of an electro-optical tracking and pointing system for a space borne laser communication system is studied, three flexible supports are contrasted, according to practical applications of space load, the structural stiffness advantage and surface figure of the three flexible support scheme have been evaluated. The analysis results show that the surface figure RMS of neck side grooving flexible support scheme resisting microgravity and thermal environment change can reach 2.05 nm and 8.88 nm, the fundamental frequency mode is 926.1 Hz, in the balance between the surface figure RMS and the higher stiffness resisting hevibration damage, the flexible design is most reasonable. On this basis, the parameterized design of the flexible support structure of the reflector is completed and dynamic analysis have been done. The maximum stress of the frequency response is 96 Mpa, which is less than the material's tensile strength limit. The results of random vibration analysis show that root mean square of acceleration response is 11.14 g RMS, meeting 3σ law. Finally, a 0.2 g sine sweeptest proves that the relative error of the modal analysis is 2%, the experimental result show that the analysis results are basically accurate and reliable, that is, flexible support design is reliable to meet the requirements of use.
- compact reflector subassembly /
- flexure aupport /
- finite element analysis /
- dynamic stiffness /
- surface figure

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References

[1]	李行, 徐振邦, 李静秋.空间反射镜新型柔性支撑结构设计[J].电子测量技术, 2014, 37(8): 1-6. Google Scholar Li X, Xu Z B, Li J Q. Design of new flexure hinge support of space reflector subassembly[J]. Electronic Measurement Technology, 2014, 37(8): 1-6. Google Scholar
[2]	Schaffer C B, Jamison A O, Mazur E. Morphology of femtosecond laser-induced structural changes in bulk transparent materials[J]. Applied Physics Letters, 2004, 84(9): 1441-1443. doi: 10.1063/1.1650876 CrossRef Google Scholar
[3]	Liu M, Zhang X M, Fatikow S. Design and analysis of a multi-notched flexure hinge for compliant mechanisms[J]. Precision Engineering, 2017, 48: 292-304. doi: 10.1016/j.precisioneng.2016.12.012 CrossRef Google Scholar
[4]	Du Z J, Yang M, Dong W, et al. Static deformation modeling and analysis of flexure hinges made of a shape memory alloy[J]. Smart Materials and Structures, 2016, 25(11) : 158-163. Google Scholar
[5]	Paros J M, Weisbor L. How to design flexure hinges[J]. Machine Design, 1965, 37(27): 151-157. Google Scholar
[6]	Smith S T, Badami V G, Dale J S, et al. Elliptical flexure hinges[J]. Review of Scientific Instruments, 1997, 68(3): 1474-1483. doi: 10.1063/1.1147635 CrossRef Google Scholar
[7]	陈贵敏, 刘小院, 贾建援.椭圆柔性铰链的柔度计算[J].机械工程学报, 2006, 42(S1): 111-115. Google Scholar Chen G M, Liu X Y, Jia J Y. Compliance calculation of elliptical flexure hinge[J]. Chinese Journal of Mechanical Engineering, 2006, 42(S1): 111-115. Google Scholar
[8]	左行勇, 刘晓明.三种形状柔性铰链转动刚度的计算与分析[J].仪器仪表学报, 2006, 27(12): 1725-1728. Google Scholar Zuo X Y, Liu X M. Calculation and analysis of rotational stiffness for three types of flexure hinges[J]. Chinese Journal of Scientific Instrument, 2006, 27(12): 1725-1728. Google Scholar
[9]	李宗轩, 陈雪, 张雷, 等.大口径空间反射镜Cartwheel型柔性支撑设计[J].光学学报, 2014, 34(6): 210-218. Google Scholar Li Z X, Chen X, Zhang L, et al. Design of cartwheel flexural support for a large aperture space mirror[J]. Acta Optica Sinica, 2014, 34(6): 210-218. Google Scholar
[10]	李晓峰, 汪波, 胡渝.在轨运行热环境下的天线镜面热变形对空地激光通信链路的影响[J].宇航学报, 2005, 26(5): 581-585. Google Scholar Li X F, Wang B, Hu Y. Influence of mirror thermal distortion in thermosphere to space-to-ground laser communication links[J]. Journal of Astronautics, 2005, 26(5): 581-585. Google Scholar
[11]	孙宝玉.基于CAE的光学反射镜柔性结构设计与分析[J].光电工程, 2009, 36(1): 103-106. Google Scholar Sun B Y. Design and analysis on the flexible structure of the optical reflector based on the computer aided engineering[J]. Opto-Electronic Engineering, 2009, 36(1): 103-106. Google Scholar
[12]	张银刚, 寇生, 余建军, 等.星敏感器主反射镜组件的设计与分析[J].航空精密制造技术, 2010, 46(5): 14-16. Google Scholar Zhang Y G, Kou S, Yu J J, et al. Design and analysis of the primary mirror subassembly in a star sensor[J]. Aviation Precision Manufacturing Technology, 2010, 46(5): 14-16. Google Scholar
[13]	张新建, 余建军, 郭旭红, 等.轻型空间CCD相机镜筒的动力学分析[J].机械设计与制造工程, 2008, 37(5): 27-30, 34. Google Scholar Zhang X J, Yu J J, Guo X H, et al. Dynamic analysis of CCD drawtube of the lightweight space camera[J]. Machine Design and Manufacturing Engineering, 2008, 37(5): 27-30, 34. Google Scholar
[14]	李浩, 余建军, 郭旭红, 等.航空光谱相机反射镜部件的有限元分析[J].光学技术, 2013, 39(3): 263-266. Google Scholar Li H, Yu J J, Guo X H, et al. Finite-element analysis of the reflect component of an aerial spectral camera[J]. Optical Technique, 2013, 39(3): 263-266. Google Scholar

Overview

Overview

Overview: The reflector assembly of a telescopic week scan electro-optical tracking and pointing system for a space borne laser communication system is studied. There are many reflection links in the electro-optical tracking and pointing system, so the requirements for the surface figure and dynamic stiffness of the reflector assembly under the operating conditions are high. The surface figure of neck side grooving flexible support, neck side ring grooving flexible support and underside grooving flexible support with the same grooving width resisting microgravity and thermal environment change are contrasted, and the modes of the three flexible support structures are also analyzed, According to practical applications of space load, the structural stiffness advantage and surface figure of the three flexible support scheme have been evaluated. The analysis results show that the surface figure RMS of neck side grooving flexible support scheme resisting microgravity and thermal environment change can reach 2.05 nm and 8.88 nm, the fundamental frequency mode is 926.1 Hz and there is no dense frequency phenomenon in all modes. In the balance between the surface figure RMS and the higher stiffness resisting he vibration damage, the flexible design is most reasonable. On this basis, the parameterized design of the flexible support structure of the reflector is completed. To further verification of the dynamic stiffness of neck side grooving flexible support structure in space vibration environment, frequency response analysis and random vibration analysis of neck side grooving flexible support are have been done. The frequency response analysis results show that the magnification of the acceleration response is 2.86 times, the maximum stress is 96 MPa under the resonance which is less than the tensile strength limit of the material, the safety factor is 5.35; The frequency response analysis results show that the root mean square of the acceleration response of the reflector assembly is 11.14 g RMS, and the RMS of acceleration response is less than 3 times the input satisfying the 3σ criterion. The mean stress response of the flexible support under random vibration is 191 MPa which is also less than the tensile strength limit of the material, and the safety factor is 2.83. Finally the reliability of the stiffness of the flexible support structure is verified by a 0.2 g sinusoidal sweep test. The experimental results show that the primary natural frequency of the reflector components is 904.3 Hz, and the relative error with the modal analysis results is 2.4%, that is, the analysis results are basically accurate and reliable. So the flexible support design of reflector assembly is reliable to meet the requirements of the use.