中国空间科学技术 ›› 2022, Vol. 42 ›› Issue (4): 27-35.doi: 10.16708/j.cnki.1000-758X.2022.0049

• 论文 • 上一篇    下一篇

航天器设备动力学分析模型简化方法与应用

李修峰*,白光明,高令飞,韩绍欢,周江   

  1. 中国空间技术研究院 通信与导航卫星总体部,北京100094
  • 出版日期:2022-08-25 发布日期:2022-08-09

Simplification method and application of dynamic analysis model for spacecraft equipment

LI Xiufeng*,BAI Guangming,GAO Lingfei,HAN Shaohuan,ZHOU Jiang   

  1. LI Xiufeng*,BAI Guangming,GAO Lingfei,HAN Shaohuan,ZHOU Jiang
  • Published:2022-08-25 Online:2022-08-09

摘要: 针对航天器设备因构成复杂引起的动力学分析模型建模困难问题,提出一种基于拓扑优化技术的有限元模型简化方法,以设备实测质量特性为约束条件,通过拓扑优化方法确定设备有限元模型可行设计空间中的材料分布,实现对结构刚度性能的模拟,获得满足动力学特性分析需要的简化的设备有限元模型。应用该方法创建了某星敏感器简化有限元模型,得到的星敏感器简化模型与产品实际质量、质心位置和转动惯量特性基本一致,并且前两阶频率分析值与试验值之间最大偏差约为30%。将该简化模型应用于其支撑结构的动态响应性能评估,两者组合体固有频率及加速度响应趋势的分析数据在450Hz以下的频率范围内与试验数据吻合较好,固有频率最大偏差约为39%。星敏感器简化模型的应用验证了基于拓扑优化技术的有限元模型简化建模方法的可行性,为航天器上复杂设备动力学分析有限元模型的简化建模提供了一种新的解决途径。

关键词: 航天器设备, 模型简化, 拓扑优化, 有限元, 动力学特性

Abstract: Aiming at the difficult modeling problem of dynamic analysis model caused by complex composition of spacecraft equipment, a method of finite element model simplification based on topology optimization was proposed.In this method, the measured mass characteristics of the spacecraft equipment were taken as the constraint condition, and the material distribution in the feasible design space of the finite element model of the equipment was determined by the topology optimization method.Then the stiffness performance of the structure was simulated, and finally the simplified finite element model of the equipment was obtained to meet the needs of dynamic characteristics analysis.A simplified finite element model of a star sensor was established by using this method.This obtained model is basically consistent with the actual mass, centroid position and moment of inertia of the product, and the maximum frequency deviation of the first two orders between the analysis values and the experimental values is less than 30%.Then, the simplified model was applied to the dynamic response performance evaluation of the support structure.The analysis data of natural frequency and acceleration response trend of the assembly are in line with the test data under the frequency range below 450Hz, and the maximum deviation of natural frequency is about 39%.The application results verify the rationality of the simplified finite element modeling method based on topology optimization technology, which provides a new solution for simplified finite element modeling of complex spacecraft equipment dynamics analysis.

Key words: spacecraft equipment, model simplification, topology optimization, finite element, dynamic characteristics