宇航学报 ›› 2022, Vol. 43 ›› Issue (7): 946-956.doi: 10.3873/j.issn.1000-1328.2022.07.011

• 材料、结构与制造 • 上一篇    下一篇

星箭分离减冲击环结构优化设计

朱璐,李响,胡迪科,周政言   

  1. 1.北京理工大学宇航学院,北京 100081; 2. 上海宇航系统工程研究所,上海 201109
  • 收稿日期:2021-10-16 修回日期:2022-02-14 出版日期:2022-07-15 发布日期:2022-07-15

Structural Optimization Design of Shock Isolation Ring for Satellite Rocket Separation

ZHU Lu, LI Xiang, HU Dike, ZHOU Zhengyan   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2. Shanghai Institute of Aerospace System Engineering, Shanghai 201109, China
  • Received:2021-10-16 Revised:2022-02-14 Online:2022-07-15 Published:2022-07-15

摘要: 针对星箭分离过程,建立了减冲击环结构模型,并分析了该结构的减冲原理。利用冲击响应谱的时域合成算法计算获得符合冲击谱规范的时域载荷,并以此作为结构优化设计中动力学模型的输入载荷工况。以减冲击环的连续层数、单层支撑块数、连续层厚度、支撑块层高度以及环的外半径和内半径6个结构参数为设计变量,以减冲效果和结构强度、刚度为约束,以质量最轻为目标,建立减冲击环的结构优化设计模型,这是一包含离散变量和连续变量的混合优化问题。为了在跨平台下求解该混合优化问题,采用代理模型策略和自适应模拟退火算法求解,并在最优点处开展结构性能对设计变量的敏度计算,对计算结果进行了分析评估。本研究对强冲击动力学环境下的航天器结构分析与设计有一定的指导意义。

关键词: 星箭分离, 减冲击环, 结构优化, 冲击响应谱, 时域合成

Abstract: In view of the process of satellite rocket separation, a structural model of shock isolation ring is established, and its working principle is analyzed. By using the time domain synthesis algorithm of the shock response spectrum, the frequency domain shock load is converted into time domain shock load, which is then used as the input load condition of the dynamic model in the structural optimization design. The structural optimization design model of the shock isolation ring is established with six structural parameters, namely, the number of the continuous layers, the number of single layer support blocks, the height of the continuous layers, the height of the support blocks, the inner and outer radius of the ring as design variables, the shock isolation effect, structural strength and stiffness as constraints, and the lightest mass as the goal. This is a hybrid optimization problem involving discrete and continuous design variables. In order to solve the hybrid optimization problem under cross platform, the surrogate model strategy and adaptive simulated annealing algorithm are used to solve the problem. The sensitivity calculation of structural performance to design variables is carried out at the optimal point, and the calculation results are analyzed and evaluated. The proposed design has certain guiding significance for the analysis and design of spacecraft structure under strong shock dynamics environment.

Key words: Satellite rocket separation, Shock isolation ring, Structural optimization, Shock response spectrum, Time domain synthesis

中图分类号: