裴彦伟, 谷松, 赵春娟, 等. 空间多载荷高精度拼接支撑结构的优化设计[J]. 航天器环境工程, 2022, 39(1): 76-82 DOI: 10.12126/see.2022.01.011
引用本文: 裴彦伟, 谷松, 赵春娟, 等. 空间多载荷高精度拼接支撑结构的优化设计[J]. 航天器环境工程, 2022, 39(1): 76-82 DOI: 10.12126/see.2022.01.011
PEI Y W, GU S, ZHAO C J, et al. Optimized design of support structure for space multi-load and high-precision splicing[J]. Spacecraft Environment Engineering, 2022, 39(1): 76-82 DOI: 10.12126/see.2022.01.011
Citation: PEI Y W, GU S, ZHAO C J, et al. Optimized design of support structure for space multi-load and high-precision splicing[J]. Spacecraft Environment Engineering, 2022, 39(1): 76-82 DOI: 10.12126/see.2022.01.011

空间多载荷高精度拼接支撑结构的优化设计

Optimized design of support structure for space multi-load and high-precision splicing

  • 摘要: 针对遥感卫星在多载荷高精度拼接扩大幅宽时需保证成像质量的要求,考虑多载荷之间的耦合,对支撑结构进行空间布局优化以及结构/热控一体化设计。应用改进的Heaviside密度滤波拓扑优化方法获取最优结构/热控的材料分布形式,结合多目标遗传算法进行详细优化设计,获取支撑结构质量、一阶固有频率和载荷安装面面形精度的Pareto前沿解集,优化所得支撑结构组件的一阶固有频率为384.8 Hz,质量为9.47 kg,安装面面形精度为0.004 0 mm。对该结构进行静力和热变形仿真分析,并开展振动和结构稳定性试验,结果显示其星敏感器指向精度优于9″,双相机光轴夹角变化满足指标要求,即结构具有较优的结构/热稳定性,满足遥感卫星对其高性能指标要求。

     

    Abstract: In order to ensure the imaging quality of the multi-load remote-sensing satellite for high-precision splicing with the expanded image width, the spatial layout of the multiple loads is optimized with consideration of the coupling between the multiple loads, and a thermo-structural integration design scheme is proposed. The improved Heaviside density filter topology optimization method is applied to obtain the optimal structure/thermal material distributions, the multi-objective genetic algorithm is used for the detailed optimization design, and the Pareto front solution groups of the mass of the support structure are used to obtain the first-order natural frequency and the RMS of the surface figure. The optimized parameters of the support structure are obtained: the first-order natural frequency is 384.8 Hz; the mass is 9.47 kg; the configuration accuracy of the installation face is 0.004 0 mm. Then, the static load and the thermal deformation analyses are carried out, together with the vibration and structural test validation. It is shown that the support structure enjoys a good balance between light weight and structural & thermal stability in that the pointing accuracy of the star sensor is better than 9″, and the angle change between the optical axes of dual cameras is acceptable. Therefore, the support structure can meet the requirements of the remote sensing satellite for high-quality imaging.

     

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