摘要
研究离散型整星隔振系统的动力学参数设计问题。通过建立整星隔振系统的动力学模型,得到从隔振器底端到卫星质心的振动传递率。用理论和仿真方法对此动力学模型进行有效验证,表明该动力学模型能较好地体现离散型整星隔振系统前两阶的振动传递规律。通过衰减不同的共振峰值的内在规律,讨论该隔振系统动力学参数对振动传递特性的影响,提出离散型整星隔振系统的动力学参数设计原则,为整星隔振器的结构参数设计提供理论指导。利用振动台对离散型整星隔振系统进行振动试验,表明该隔振器具有很好的隔振性能,验证了动力学参数设计的正确性。
The problem of the dynamical parameter design of discrete whole-spacecraft vibration isolators is studied.By establishing the dynamical model of the whole-spacecraft vibration isolation system,the vibration transmissibility from the bottom of the vibration isolator to the mass center of the spacecraft is obtained,and the first two-order vibration transmissibility can be determined by this model.The inherent laws of the different attenuation of the resonance peak are proposed,and the design principle of the dynamic parameters for the discrete whole-spacecraft vibration isolator is discussed.The discrete whole-spacecraft vibration isolation system is tested on a vibration table,and the experiment results show that the discrete vibration isolator has good vibration isolation performance.
出处
《机械强度》
CAS
CSCD
北大核心
2012年第1期25-30,共6页
Journal of Mechanical Strength
基金
国防科技工业民用专项科研技术研究项目(C4120062301)~~
关键词
卫星
整星隔振
参数设计
振动试验
Spacecraft
Whole-spacecraft vibration isolation
Parameter design
Vibration test
