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针对微小卫星对星敏感器的特殊要求,结合星敏感器特殊的工作性能和环境,采用拓扑方法对星敏感器支撑结构进行多目标优化设计并进行有限元分析和试验。首先,对模态分析和随机振动响应的基本理论进行介绍,推导出多目标拓扑优化的表达公式;其次,以支撑结构的体积最小和星敏感器在支撑结构上的四个安装点RMS值最小为目标,以最低自振频率为约束,建立支撑结构的拓扑优化模型,利用Opti Struct软件对其进行拓扑优化设计;然后利用MSC.Patran&Nastran有限元分析软件对优化后的支撑结构进行模态分析和随机振动响应分析,得到基频为327 Hz,安装点RMS值的放大率最大为1.55;最后,对支撑结构进行振动试验,试验结果和有限元分析结果的相对误差最大为6.68%,二者吻合较好,该星敏感器支撑结构满足微小卫星对其性能指标的要求。
Aiming at the special requirements of small satellites to star sensors, combined with the special working performance and environment of star sensors, a multi-objective optimization design of the star sensor support structure is carried out by using the topological method and the finite element analysis and experiments are carried out. Firstly, the basic theory of modal analysis and stochastic vibration response are introduced, and the expressions of multi-objective topology optimization are deduced. Secondly, the minimum RMS value of the four mounting points on the support structure with the smallest volume of the support structure and the star sensor As the goal, the topology optimization model of the supporting structure is established with the lowest natural frequency as the constraint, and the topology optimization design of the supporting structure is carried out by using Opti Struct software. Then the modal analysis of the optimized supporting structure is carried out by MSC.Patran & Nastran finite element analysis software The results show that the fundamental frequency is 327 Hz, and the magnification of RMS value at the installation point is 1.55. Finally, the vibration test of the support structure is carried out. The relative error between the experimental result and the finite element analysis is up to 6.68% Preferably, the satellite sensor support structure meets the performance requirements of microsatellites.