新型整星隔振系统动力学分析

在卫星的服役周期中,发射阶段的动力学环境最为恶劣,期间受到多种复杂载荷的作用。传统的星箭连接适配器由于刚度较大,给航天器的参数设计及生产带来了极大的困难。为了达到多轴隔振的目的,基于粘弹性材料受到剪切力作用时产生较大阻尼损耗的原理设计了一种新型整星隔振器。针对该隔振系统进行了简化,以质量刚度阻尼耦合的形式来模拟卫星和隔振器之间的关系,对其进行了隔振效果的分析。其中,重点对仿真中出现的隔振系统的一阶模态结构阻尼系数的饱和现象提供了详尽的理论和数值分析。最后,针对新型整星隔振器的工程具体应用提出了两点参考准则。

Analysis of dynamics for the new whole-spacecraft vibration isolator

In the service term of the satellites,the dynamics environment of launch phase is the worst one because of the variety of complex loads.The stiffness of traditional connection machine between satellite and rocket are so large that the difficulties will be brought into the spacecraft during designing and manufacturing.With the aid of multi-axis vibration isolation,one kind of whole-spacecraft vibration isolator based on the character of viscoelastic material is designed.The influence of the whole spacecraft vibration isolators’ quality,rigidity and damping on the vibration isolation performance of the whole spacecraft vibration isolation system was discussed.The simulated data show that the transmissibility,which is coupled with stiffness,can be reduced by attaching the vibration isolator between the spacecraft and the launch vehicle.At last,two reference criteria are induced when the new whole-spacecraft vibration isolator is applied in the actual application.And they also could be expanded to other actual design of the whole-spacecraft vibration isolator.