摘要
考虑具有端部附加质量的柔性附件及其和舱体的耦合效应,本文系统地推导出了一个带柔性附件的航天器热颤振准则,并用有限元程序进行了模拟校验.该准则揭示了柔性附件和舱体的质量特性和系统热诱发振动稳定性之间的关系.当舱体的质量特性远大于柔性附件的质量特性时,该准则就退化为悬臂柔性附件的热颤振准则.
A thermal flutter criterion is developed in this paper for a space structure with flexible appendages, considering the coupling between the hub and the appendage with a tip mass. The validity of this criterion is dem- onstrated by finite element simulations. This criterion clarifies the impact of the mass characteristics of the flexible appendage and the hub on the stability of the thermally induced vibration. In addition, this criterion can degener- ate to the existing criterion with cantilever flexible appendages when the mass characteristics of the hub are much larger than those of the flexible appendage.
出处
《动力学与控制学报》
2017年第6期563-568,共6页
Journal of Dynamics and Control
关键词
热诱发振动
热颤振
航天结构
稳定性分析
傅里叶温度单元
thermally induced vibration, thermal flutter, space structure, stability analysis, Fourier fi-nite element
