航天器工程2019，Vol.28Issue(3)：56-63,8.DOI:10.3969/j.issn.1673﹣8748.2019.03.010
高轨卫星机热一体化星敏感器支架设计
Design of Mechanical and Thermal Intergrated Bracket for Star Sensor of High Orbit Satellite
WANG Zhiguo 1ZHANG Zonghua 1CHEN Shuangquan 1MAO Min1
作者信息
- 1. Shanghai Institute of Satellite Engineering,Shanghai 201109,China
- 折叠
摘要
Abstract
Traditional light alloy metal material star sensor’s bracket have a thermal expansion coefficient of 10－5/℃,in a space thermal environment,pointing thermal deformation of star sen﹣sor mounting surface is relatively large,it can’t meet the requirement of a high precision satellite.The article gives a design method of a high rigidity and high precision micro deformation hot integrated bracket of star sensor,the test results show that the first order natural frequency of star sensor and bracket assembly is 1 78?4Hz,has sufficient stiffness characteristics,the level of mechanical environment of the star senor mounting surface is much better than the allowable value,thus protects the star senor;and maximum thermal deformation of the star senor mount﹣ing surface is 6?41″,peak to peak value is 1?58″under extreme conditions,attitude determination accuracy of the satellite in orbit is better than 2?8″,the bracket meets requirements of high preci﹣sion attitude determination and image navigation registration for a high orbit satellite.关键词
高轨卫星/高精度/星敏感器/支架Key words
high orbit satellite/high﹣precision/star sensor/bracket分类
航空航天引用本文复制引用
WANG Zhiguo,ZHANG Zonghua,CHEN Shuangquan,MAO Min..高轨卫星机热一体化星敏感器支架设计[J].航天器工程,2019,28(3):56-63,8.
