基于脉冲子结构的探测器结构动力学优化设计

针对传统结构优化设计中，精细化模型求解复杂结构动响应过于耗时的问题，引入保精度、高效的脉冲子结构方法，提出一种考虑结构动力学响应的优化设计流程，并对月球探测器太阳翼结构进行优化分析，获得了太阳翼结构设计参数，有效地提高了太阳翼动力学特性指标，改善了月球探测器关键位置处的动力学环境。结果表明，脉冲子结构方法可以有效应用于航天器结构动力学优化设计，提高优化设计效率，所得优化结果对实际结构设计具有一定指导意义。

Dynamic Optimum Design of Lunar Lander Based on Impulse Substructuring Technique

To overcome the shortcomings of using the time-consuming refined model in the dynamic optimum design of the complex structures, the efficient and accurate dynamic responses prediction method named the impulse based substructuring (IBS) method is introduced. Meanwhile, a dynamic optimum design process considering the structural dynamic responses is proposed and the structure of the solar wings of a lunar lander is optimized. After the optimum design process, the structural design parameters of the solar wings are obtained. The dynamic performance of the solar wings and the dynamics environment of the critical locations of the lunar lander are improved. The results indicate that the IBS method can be applied in the optimum design of a spacecraft to improve the dynamic analysis efficiency. This research provides a theoretical basis and technical support for practical structural design.