航天器工程2017，Vol.26Issue(2)：77-83,7.DOI:10.3969/j.issn.1673-8748.2017.02.011
一种星敏感器支架热变形控制方法
A Method for Controlling Thermal Deformation of Star Sensor Bracket
摘要
Abstract
In the high precision earth remote sensing satellites,requirements for the pointing accuracy of satellite attitude are strict.Star sensor is the principal measure component of the satellite attitude,in order to reduce the thermal deformation of star sensor bracket for the influence of star sensor,therefore it is necessary to control the thermal deformation of star sensor bracket.In this paper a kind of connection is presented in which,titanium honeycomb sandwich structure is mounted between star sensor bracket and star sensor bracket mounting structure.The high heat resistance,low distortion and low stiffness properties of the titanium alloy honeycomb structure are used to control the thermal deformation of star sensor bracket.Under the premise that the stiffness reduction of star sensor bracket is less than 10％,the heat transmission from payload to star sensor is reduced by the reasonable selection in the titanium alloy honeycomb.Results of simulation and experiment show that titanium honeycomb sandwich structure has better control of the deformation effect.The thermal deformation of star sensor bracket is significantly reduced from 14" to 7",and the pointing accuracy of star sensor is improved.The method in this paper can be used as a reference for thermal deformation control of other equipment brackets and optical load mounting structures on spacecraft.关键词
星敏支架/热变形/钛合金蜂窝夹层结构/隔热材料Key words
star sensor bracket/thermal deformation/titanium alloy honeycomb structure/heat insulation material分类
航空航天引用本文复制引用
任友良,王志国,胡炳亭..一种星敏感器支架热变形控制方法[J].航天器工程,2017,26(2):77-83,7.
