地磁测量卫星光学平台结构热稳定性设计与校验  

Thermal Stability Design and Verification of Optical Bench Structure of Geomagnetic Survey Satellite

作　　者：张欢[1] 刘志全[1] 于春宇[1] 罗文波[1] 袁丁 ZHANG Huan;LIU Zhiquan;YU Chunyu;LUO Wenbo;YUAN Ding(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《宇航学报》2023年第10期1604-1612,共9页Journal of Astronautics

基　　金：国家自然科学基金项目(12172041)。

摘　　要：针对地磁测量卫星光学平台(OB)结构与伸杆弯曲、扭转等整体热变形解耦难,星敏支架材料各向异性且可设计性差和多项精度指标下热稳定性设计与校验缺失的问题,开展了光学平台结构热稳定性设计,实现了中部臂杆整体热变形解耦。基于有限元方法(FEM),选定综合性能最佳的材料组合,给出了材料匹配性规律。用热变形测试结果修正后的有限元模型分析校验了准运动学支撑的热变形解耦能力。开展了在轨全周期热变形分析,结果表明,光学平台星敏光轴间夹角峰-峰值最大为1.24″,星敏光轴与磁强计体轴间夹角峰-峰值最大为3.13″。在相似使用环境下,所设计的光学平台结构星敏光轴间夹角变化均方根值较SWARM卫星的对应值减小约82%,验证了光学平台结构热稳定性设计的有效性。To solve insufficiency of thermal deformation decoupling of optical bench(OB)structure on geomagnetic survey satellite,the anisotropy and low designability of star sensor cube material,and the lack of thermal stability design and verification of small dimension satellite-borne devices,high thermal stability design is developed,including configuration design,quasi-kinematic support design,star sensor-cube connection design,magnetometer-carbon fiber reinforced tube connection design,and material combination selection.The design realizes the deformation decoupling between middle tube and other parts of the structure when keeping the stiffness and strength of OB structure satisfied.The best material combination is selected using finite element method(FEM),and the influence of materials with different physical parameters is studied.Thermal deformation test is carried out to modify and verify the FEM model.Thermal deformation decoupling ability of the quasi-kinematic support is verified using FEM model,and full cycle deformation analysis is carried out and shows that the maximum value of 3 peak to peak values(Vp-p)of angles between star sensor optic axis is 1.24″,and the maximum value of 9 Vp-ps of angles between star sensor optic axis and magnetometer body axis is 3.13″(the 12 angles above are used as the OB structure thermal stability indexes),and the maximum root mean square(RMS)of angles between star sensor optic axis is decreased by 82%compared with the corresponding RMS of SWARM OB structure in similar orbit thermal environment.The thermal stability design is thus validated.

关 键 词：光学平台结构 准运动学支撑 热稳定性 有限元分析 热变形分析 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]