Thermal deformation optimization method for optical satellite payload mounting surface based on honeycomb lamination technology

Lin YANG; Yan-song WANG; Lei WEI; Zi-qiang HU

doi:10.37188/OPE.20212905.1043

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Thermal deformation optimization method for optical satellite payload mounting surface based on honeycomb lamination technology

Micro/Nano Technology and Fine Mechanics | 更新时间：2021-07-08

- Thermal deformation optimization method for optical satellite payload mounting surface based on honeycomb lamination technology
- Optics and Precision Engineering Vol. 29, Issue 5, Pages: 1043-1051(2021)
- 作者机构：
  
  1.山东大学前沿交叉科学青岛研究院，山东青岛 266200
  2.山东大学空间科学研究院，山东威海 264209
- 作者简介：
- 基金信息：
- DOI：10.37188/OPE.20212905.1043
  CLC： V423
- Received：12 September 2020，
  
  Revised：09 November 2020，
  
  Published：15 May 2021
- 稿件说明：
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杨林,王岩松,魏磊等.基于蜂窝板铺层技术的某光学卫星有效载荷安装面的热变形优化[J].光学精密工程,2021,29(05):1043-1051.

YANG Lin,WANG Yan-song,WEI Lei,et al.Thermal deformation optimization method for optical satellite payload mounting surface based on honeycomb lamination technology[J].Optics and Precision Engineering,2021,29(05):1043-1051.
杨林,王岩松,魏磊等.基于蜂窝板铺层技术的某光学卫星有效载荷安装面的热变形优化[J].光学精密工程,2021,29(05):1043-1051. DOI： 10.37188/OPE.20212905.1043.

YANG Lin,WANG Yan-song,WEI Lei,et al.Thermal deformation optimization method for optical satellite payload mounting surface based on honeycomb lamination technology[J].Optics and Precision Engineering,2021,29(05):1043-1051. DOI： 10.37188/OPE.20212905.1043.

摘要

本文基于增强树脂碳纤维铺层优化设计的方法对某光学卫星的结构热变形进行了优化设计和试验验证。首先分析得到卫星所在太阳同步轨道的外热流数据，然后根据外热流数据及卫星热特性分析计算得到卫星各舱板的高温工况和低温工况的温度载荷分布情况。根据极端工况卫星平台的温度载荷，以铺层角度作为设计变量，分析求得卫星平台相机支腿安装平面的平面度、角度以及整星

3个方向一阶频率的变化情况。分析数据表明，当

=40°时相机安装板的蜂窝板面板铺层角度顺序为［90°，+40，0°，

40，

40，0°，+40，90°］，载荷安装面热变形最小，整星基频满足运载火箭要求。经过热试验和振动试验验证，该设计方案在热载荷影响下，有效载荷安装面的平面度优于0.05，变化角度优于60″，

方向的一阶基频分别为22，18，49.8 Hz，满足光学相机安装精度及运载火箭对卫星基频的相关要求。

Abstract

The structural thermal deformation of an optical satellite was optimized and verified using the optimal design of carbon fiber reinforced plastic lamination technology. The external heat flow data of a satellite in a sun-synchronous orbit was analyzed and the temperature load distribution of the satellite decks under high and low temperature conditions was calculated according to the external heat flow data and by analyzing the thermal characteristics of satellite. According to the temperature load of the satellite platform in extreme working conditions， the lamination angle was used as the optimization variable to analyze the changes in the flatness and angle of the mounting plane of the camera leg of the satellite platform and the first-order frequency in

directions. Analysis data shows that when

=40°， the camera mounting plate layers of the honeycomb panel is in the angle order of ［90°， +40，0°，

40，

40，0°， +40，90°］. Under this condition， the mounting surface thermal deformation is the smallest and the fundamental frequency of the satellite meets the requirements of the launcher. In thermal and vibration tests， using the design scheme under the heat load， it was observed that the payload mounting surface flatness is

0.05， changing angle is

60 "， and first-order fundamental frequency of

direction is 22， 18， 49.8 Hz， respectively. It can meet the required optical camera installation precision and launch vehicle constraints.

关键词

Keywords

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