Thermal-structural coupled analysis and verification of 2-D mirror gimbal for lunar-based telescope

Ai-hong SHANGGUAN; Chen-jie WANG; Hao-su ZHANG; De-jin QIN; Zhao-hui LIU

doi:10.3788/OPE.20162408.1956

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Thermal-structural coupled analysis and verification of 2-D mirror gimbal for lunar-based telescope

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-07-07

- Thermal-structural coupled analysis and verification of 2-D mirror gimbal for lunar-based telescope
- Optics and Precision Engineering Vol. 24, Issue 8, Pages: 1956-1964(2016)
- 作者机构：
  
  1.中国科学院西安光学精密机械研究所, 陕西西安 710119
  2.中国科学院大学, 北京 100049
  3.西安交通大学热流科学与工程教育部重点实验室, 陕西西安 710049
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20162408.1956
  CLC： V476.3;TH133
- Received：05 January 2016，
  
  Accepted：11 February 2016，
  
  Published：25 August 2016
- 稿件说明：
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Ai-hong SHANGGUAN, Chen-jie WANG, Hao-su ZHANG, et al. Thermal-structural coupled analysis and verification of 2-D mirror gimbal for lunar-based telescope[J]. Optics and precision engineering, 2016, 24(8): 1956-1964.
DOI：

Ai-hong SHANGGUAN, Chen-jie WANG, Hao-su ZHANG, et al. Thermal-structural coupled analysis and verification of 2-D mirror gimbal for lunar-based telescope[J]. Optics and precision engineering, 2016, 24(8): 1956-1964. DOI： 10.3788/OPE.20162408.1956.

摘要

为了提高月基望远镜反射镜转台的工作性能，对反射镜转台进行了热-结构耦合分析以及试验验证和在轨验证。根据输入条件、热载荷、热边界等建立有限元模型对反射镜转台结构及主要发热部件进行了温度场计算。将温度载荷，预紧力载荷，边界条件输入结构有限元模型进行了热-结构耦合分析，得到了半封闭U型结构、高精密运动轴系、蜗轮蜗杆热变形和热应力。推导了轴系摩擦力矩的计算公式，将分析计算中的数据代入公式中获得了轴系的摩擦力矩，并根据摩擦力矩选取了合适力矩的电机。计算结果显示，左轴系在低温工况-25℃下摩擦力矩较大，达14.163 N·mm；高温工况下摩擦力矩较小，55℃时为4.796 N·mm。垂直轴轴系在低温工况-25 ℃时摩擦力矩为16.45 N·mm；高温工况下由于轴系卸载，摩擦力矩为零。结果表明反射镜转台可以在-25 ℃～+55 ℃下正常工作。文中还通过试验验证和在轨验证证明了反射镜转台热-结构耦合分析的有效性和合理性。

Abstract

To improve the work performance of a 2-D mirror gimbal for the lunar-based telescope

the thermal-structural coupled analysis was carried out

and the analysis results were verified by thermal and onboard tests. According to the given input conditions

thermal loads and the thermal boundary

the finite element model was established to calculate the temperature fields of the mirror gimbal and main heating components. Through inputting the temperature loads

preloads and the boundary conditions into the finite element model

the thermal deformation and stress of the U-shape structure

precision moving shafting systems and the worm gears were obtained. Then

the expressions of friction moment were derived

and analytical data were used to the expressions to achieve the friction moment of shafting systems. On the basis of the friction moment

a proper moment motor was chosen. After calculation

the results show that the left shafting system has a larger friction moment at the low temperature condition of -25 ℃

and the maximal one is up to 14.163 N·mm; While the friction moment is smaller under high temperature condition 55 ℃

and the maximal one is 4.796 N·mm. The results also show friction moment of the azimuth shafting systems at a low temperature condition of -25 ℃ is 16.45 N·mm. Moreover

the vertical shaft system shows its friction moment to be 16.45 N·mm at the low temperature condition of -25 ℃

while it is zero at the high temperature condition because of shafting system unloading. The results indicate the reflection mirror gimbal works well between -25 ℃ to 55 ℃. Finally

the thermal and onboard tests were carried out to demonstrate the rationality and validity of the analysis results.

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Keywords

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