新型整星隔振平台的被动隔振性能及星箭耦合特性分析

针对卫星的隔振要求,提出一种新型半主动整星隔振平台,采用磁流变(MR)阻尼器作为半主动作动器。为增加平台的横向转动刚度,提出一种套筒式防摇结构。建立新型整星隔振系统的详细有限元(FE)模型,对隔振系统进行基础随机激励下的响应分析和隔振平台的振级落差分析,并建立星箭系统的详细有限元模型,分析星箭结合后对整星隔振性能的影响情况,以及加入新型隔振平台后对火箭动态特性的影响。结果表明:新型整星隔振平台具有优良的被动隔振性能;火箭的动态特性对新型隔振系统的性能有一定影响,但当火箭和隔振平台结合处的刚度较大时,影响较小;加入新型隔振平台后,在火箭点火时到一级分离时,火箭整体的动态特性无明显变化。

Research on Passive Isolation Characteristics and Rocket-spacecraft Coupling of a New Whole-spacecraft Isolation Platform

To satisfy the requirements of whole-spacecraft isolation, a new semi-active isolation platform is presented using a magneto-rheological (MR) damper as the semi-active actuator. A sleeve anti-shaking structure is designed to increase the transverse and bending stiffness. The finite element (FE) model of the platform is presented, followed by a study of the response of the isolation system to base excitation. Then, the detailed FE model of the whole-spacecraft isolation system is presented, and the impact of the new platform on the dynamic characteristics of the rocket is studied. The results show that the new platform is able to satisfy the requirements of whole-spacecraft isolation. Its isolation performance is affected by the dynamic characteristics of the rocket, but the influence is comparatively small when there exists high connecting stiffness between the rocket and the payload. When replacing the adopter with the new platform, the dynamic characteristics of the rocket show little change from firing to the first separation of the rocket and spacecraft.