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.%在高精度对地遥感卫星中,对卫星姿态指向精度有严格的要求.星敏感器是卫星姿态测量的主要部件,为减少星敏感器支架(以下简称星敏支架)的热变形对星敏感器指向的影响,需要对星敏支架的热变形进行控制.文章提出了一种在星敏支架与安装结构之间充填钛合金蜂窝夹层结构的方法,利用钛合金蜂窝夹层结构的高热阻、低变形和低刚度特性来控制星敏支架的热变形.通过合理地选择钛合金蜂窝夹层结构的蜂窝芯子的芯格尺寸,在星敏支架刚度下降小于10％的条件下,降低了有效载荷传递至星敏支架的热量.仿真和试验结果表明:钛合金蜂窝夹层结构具有较好的变形控制效果,可将星敏支架的热变形从14”降低至7",提高了星敏感器的指向精度.此方法可为航天器上其他单机支架和光学载荷安装结构的热变形控制提供参考.
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