刚体-附件耦合系统热-动力学稳定性分析

Thermal-dynamic stability analysis of structural appendages attached to satellite

根据卫星的结构特点将之简化为刚体-附件耦合系统.在突加热流作用下,该系统存在两重耦合影响:附件结构的非线性瞬态温度场与舱体刚体转动和附件结构变形之间的相互耦合影响;卫星舱体刚体运动和附件振动之间的相互耦合影响,因此该系统具有高度非线性.针对该耦合系统,以有限元法为研究手段,分析了系统的热诱发振动响应和运动稳定性问题,发展了一套高效、可靠和实用的分析方法.所提出方法的可靠性得到了简单系统理论解的验证,可为卫星系统的设计提供有益的参考.

The satellite was simplified as a coupled system composed of a flexible appendage attached to a rigid body. Under the suddenly applied thermal loading, the system contained two coupling effects, i. e. , the coupling effect among the nonlinear transient temperature, the rigid body motion of the hub and the structural deformation of the appendage, and the coupling effect between the motions of the hub and the appendage. So it was a highly nonlinear system. Based on finite element methods （FEM）, some efficient, reliable and practical methods were developed to conduct the thermal-dynamic analysis and the correspond- ing stability analysis for the hub-appendage coupling system. The validity of the presented methods was verified by the existent theoretical solutions. The proposed method can provide beneficial references for the design of satellites.