卫星减振的试验研究

根据某卫星发射对减振性能的要求,本文提出在适配器与星箭界面之间安装整星隔振器并且在适配器表面粘贴约束阻尼层的减振方案。并且利用振动台分别对卫星减振系统施加垂向和横向的基础激励,测量卫星上关键位置处的加速度响应,比较减振前后其频率响应特性的变化,以验证卫星减振方案的减振性能。试验结果的对比分析验证了此卫星减振系统能够隔离卫星高频段的横向和垂向振动,降低卫星结构频率响应的幅值,能够减小运载火箭发射时传递给卫星的环境载荷,提高卫星发射的可靠性。本文对于相关的航天器的减振设计具有实用的参考价值。

Experimental Research on Whole-Spacecraft Vibration Suppression

The experimental research on the whole-spacecraft vibration suppression,is carried out,where a series of isolator elements are interposed between the adapter and the launch vehicle,and a constrained damping layer is attached to the adapter surface.The acceleration responses of the concerned locations are measured as the whole-spacecraft vibration suppression system is under axial and lateral base excitation,the frequency responses with and without vibration suppression system are compared to verify the efficacy.According to the experimental results,it indicates that the whole-spacecraft vibration suppression system can effectively isolate the spacecraft axial / lateral vibration due to the broadband structure-born launch environment,reduce the launch-induced dynamic loads to the satellite to enhance the launch reliability.