腹板式航天器结构减振降噪的优化设计研究

针对腹板式航天器在轨运行过程中的结构减振降噪问题，利用FEM/IBEM法，提出了一种基于模态贡献度对流固耦合系统进行减振降噪的结构优化设计方法。先采用分块兰索斯法求解结构前20阶自由模态，获得固有振型。再利用间接边界元法，对姿控发动机激励下的整体结构进行模态贡献度分析，确定了对某灵敏仪器所处位置声学贡献最大的面板，以该面板为优化设计对象，一阶固有频率最大化为目标函数进行频率响应拓扑优化和形貌优化。优化结果表明，耦合系统在姿控发动机激励下，敏感仪器所处位置的峰值声压最大下降了21.27dB，总体质量减轻了6.83kg，获得了比较理想的减振降噪效果。

Research on design method for noise and vibration reduction

To solve the problem that noise and vibration reduction of ventral plate spacecraft structure in orbit, a structure optimal design method based on FEM/IBEM for fluid-solid coupling system was proposed. The front 20 orders free modal of object was solved by Block-Lanczos, and then makes modal contribution analysis for overall structure under attitude control engine with indirect boundary element method, and finally ascertain panel which made the greatest acoustics contribution for position of sensitive instrument. This panel is object of optimal design, topology optimization and shape optimization were performed to maximize the lowest frequency, optimization results show that the maximum peak sound pressure of sensitive instrument dropped 21.27dB and overall quality reduced 6.83kg, it get the ideal effects of vibration and noise reduction.