卫星结构飞行动力稳定性优化设计  

Flight Dynamic Stability Optimization Design of Satellite Structure

作　　者：程龙[1,2] 王栋[1,3] 谷松[1,3] 张道威 

机构地区：[1]中国科学院长春光学精密机械与物理研究所,吉林长春130033 [2]中国科学院大学,北京100039 [3]长光卫星技术有限公司,吉林长春130033

出　　处：《计算机仿真》2017年第5期96-102,共7页Computer Simulation

基　　金：国家自然科学基金项目(41501383)

摘　　要：以动力稳定性为目标对卫星结构进行优化设计,可以使卫星结构满足安全性能要求的同时,还能够对外部激励具有良好的响应特性。卫星属于复杂的多自由度系统,影响力学性能的参数较多,另外卫星在发射过程中需要承受各种载荷的综合扰动,经历复杂的动力学环境,卫星动态响应的分析计算受到限制。对系统的模态特性、简谐激励响应、随机激励响应进行分析,结合有限单元法对结构动力稳定性进行多目标优化设计,优化结果表明卫星结构的动态力学性能指标达到要求,飞行动力稳定性较好。通过试验证明有限元仿真分析的准确性,进而证明上述优化方法可行有效。Take dynamic stability as the goal of optimal design, the satellite structure can not only satisfy the re- quirement of safety performance, but also have a good response characteristic to external incentives. Satellite is a complex system with multiple-degree-of-freedom, which leads many parameters affecting its mechanical properties. In addition, during the process of launching, satellite needs to withstand the integrated disturbance of multiple loads and undergo complex dynamic environment, which limits the analysis and calculation of satellite dynamic response. Modal characteristics analysis, harmonic incentive response analysis and random exciting response analysis of the sys- tem were carried out. Combined with the finite element method, a multi-objective optimal design of structural dynam- ic stability was implemented. Optimal results show that the dynamic mechanics performance indicators of satellite structure meet the requirement well, and the flight dynamic stability has a high performance. The accuracy of the fi- nite element simulation analysis is proved by the experiment, and then the feasibility and effectiveness of the optimal method are proved.

关 键 词：动力稳定性 优化设计 有限元分析 模态特性 简谐振动响应 随机振动响应 

分 类 号：V423.41[航空宇航科学与技术—飞行器设计]