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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。
Aiming at the requirement of satellite isolation, a new type of semi-active whole-satellite isolation platform is proposed. The MR damper is used as a semi-active actuator. In order to increase the lateral rotation stiffness of the platform, a sleeve anti-sway structure is proposed. The FE model of a new type of whole-body vibration isolation system is established. The response analysis of the vibration isolation system under fundamental random excitation and the analysis of the vibration level of the vibration isolation platform are carried out. The detailed finite element model The impact of satellite-arrow combination on the vibration isolation performance of the whole satellite and the impact on the dynamic characteristics of the rocket after adding a new type of vibration isolation platform. The results show that the new monopole vibration isolation platform has excellent passive vibration isolation performance. The dynamic characteristics of the rocket have a certain impact on the performance of the new vibration isolation system. However, when the stiffness of the combination of the rocket and vibration isolation platform is relatively small, After adding a new type of vibration isolation platform, the overall dynamic characteristics of the rocket did not change significantly when the rocket ignited to a level of separation.