一种兼顾不同轨道姿态的卫星热控优化设计方法

周砚耕

doi:10.11728/cjss2016.03.380

一种兼顾不同轨道姿态的卫星热控优化设计方法

doi: 10.11728/cjss2016.03.380

周砚耕

上海卫星工程研究所上海 201109

基金项目: 国家重大航天器工程基金项目资助

详细信息

作者简介:
周砚耕,E-mail:zyg_aska@sina.com.

中图分类号: V474;TK124
计量
- 文章访问数: 939
- HTML全文浏览量: 23
- PDF下载量: 919
- 被引次数: 0
出版历程
- 收稿日期: 2015-11-12
- 修回日期: 2016-03-02
- 刊出日期: 2016-05-15

A Balanced Satellite Thermal Control Optimization Method for Different Orbit and Attitude

ZHOU Yangeng

Shanghai Institute of Satellite Engineering, Shanghai 201109

摘要

摘要: 分析了传统卫星的热控设计方案,提出一种能够同时满足太阳同步轨道和倾斜轨道条件的卫星热设计优化方法.基于该优化方法对某卫星在两种轨道条件下进行了热仿真分析,并对太阳同步轨道条件下的卫星进行热平衡试验和在轨验证.研究结果表明,采用该优化方法可减少倾斜轨道条件下卫星热设计的地面试验验证,缩短卫星研制周期并显著节约成本.研究结果可为卫星热控设计优化提供参考.
- 热控设计 /
- 优化方法 /
- 热仿真 /
- 研制周期
Abstract: Based on analysis of the thermal control design of traditional satellites,an optimization method for satellite thermal design which is applicable to both Sun-synchronous orbit and lowinclination orbit is presented.Using this optimization method,thermal simulation analysis is made for a satellite under both orbit conditions,and the satellite thermal balance test and in-orbit validation are conducted for the Sun-synchronous orbit.Combined with thermal simulation results,it is shown that the thermal design of low-inclination orbit satellite conditions can reduce the ground test verification,shorten the satellite development cycle and save the costs significantly.This research work can provide reference for the design optimization of satellite thermal control.
- Thermal control design /
- Optimization methods /
- Thermal simulation /
- Development cycle

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参考文献(10)

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