星敏感器光学系统轨道空间外热流计算方法

王爽; 耿云海; 宋道喆; 赵志军

doi:10.3788/OPE.20162413.0468

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星敏感器光学系统轨道空间外热流计算方法

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- 星敏感器光学系统轨道空间外热流计算方法
- Computational method for external heat flux of trajectory space on optical system of star sensor
- 光学精密工程 2016年24卷第10s期页码：468-476
- 作者机构：
  
  1. 中国空间技术研究院北京,100094
  2. 哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目（No.61304237）();长江学者创新团队发展计划资助项目（No.IRT0520）()
- DOI：10.3788/OPE.20162413.0468
  中图分类号： TP394.1;TH691.9
- 收稿日期：2016-06-10，
  
  修回日期：2016-07-17，
  
  纸质出版日期：2016-11-14
- 稿件说明：
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王爽, 耿云海, 宋道喆等. 星敏感器光学系统轨道空间外热流计算方法[J]. 光学精密工程, 2016,24(10s): 468-476

WANG Shuang, GENG Yun-hai, SONG Dao-zhe etc. Computational method for external heat flux of trajectory space on optical system of star sensor[J]. Editorial Office of Optics and Precision Engineering, 2016,24(10s): 468-476
王爽, 耿云海, 宋道喆等. 星敏感器光学系统轨道空间外热流计算方法[J]. 光学精密工程, 2016,24(10s): 468-476 DOI： 10.3788/OPE.20162413.0468.

WANG Shuang, GENG Yun-hai, SONG Dao-zhe etc. Computational method for external heat flux of trajectory space on optical system of star sensor[J]. Editorial Office of Optics and Precision Engineering, 2016,24(10s): 468-476 DOI： 10.3788/OPE.20162413.0468.

摘要

提出了一种基于反向蒙特卡罗法（RMC法）计算星敏感器光学系统表面空间外热流的方法。首先，设计环境映射面对星敏感器光学系统进行包覆，根据给定的轨道参数，确定不同时刻映射面接受环境热流的方向；然后，利用RMC法反向跟踪-统计从星敏感器光学系统表面面元发出的热射线能束，求出光学系统表面与映射面间的辐射传递因子；最后，计算得到光学系统表面的空间外热流。该方法不需计算辐射换热角系数可直接获得外热流密度，处理热射线反射-传递过程更加方便，能够计算存在遮挡情况下的飞行器表面空间外热流问题。仿真过程中分别针对两种在轨运行方案，计算得到了星敏感器光学系统受到的太阳辐射热流、地球红外辐射热流、地球反照辐射热流的大小；其中，特征点1、2、3、在方案一中接受到的空间外热流最大值分别为：1 008.54 W/m

、956.95 W/m

、477.88 W/m

，方案二中接受到的空间外热流最大值分别为：1 177.69 W/m

、1 055.55 W/m

、678.40 W/m

；仿真结果与理论分析保持一致，同时验证了方法的正确性和有效性。

Abstract

A computational method which is on the basis of Reverse Monte Carlo method (RMC method) is put forward to calculate the external heat flux on the optical system of star sensor. Firstly

the environment mapping surface is designed to coat optical system of star sensor

and the direction of external heat flux where the environment mapping surface receives is confirmed according to the given orbital parameters in different time. Secondly

radiation transfer factor between the surface of optical system and the environment mapping surface is gained by tracking the heat rays which are transmitted from the optical system of star sensor with RMC method. Finally

the external heat flux on the optical system surface of star sensor is calculated and gained. The radiation coefficients do not need to be calculated in this method. And the density of external heat flux can be gained directly. It is more convenient to handle the reflection and transmission process of these heat rays. And especially

it is available to calculate the external heat flux on the shaded component. In the simulation

two kinds of on-orbit operation schemes are designed to simulate the solar radiation heat flux

the earth infrared radiation heat flux and the earth albedo radiation heat flux accepted by the optical system of star sensor

the maximum external heat flux accepted by feature point 1

2 and 3 in scheme one respectively are 1 008.55 W/m

、956.95 W/m

、477.88 W/m

. While in scheme two

the corresponding values are 1 177.69 W/m

、1 055.55 W/m

、678.40 W/m

. The simulation results conform to the theoretical analysis

and it verifies that the proposed method is correct and effective.

关键词

Keywords

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