航天器刚柔耦合动力学建模及热诱发动力学响应分析

摘要

A rigid-flexible coupling dynamic model for a flexible spacecraft with large solar panels represented by honeycomb panels was established by using the Hamiltonian principle.The effects of rigid-flexible coupling nonlinear terms on the dynamic model and the parameters of the flexible spacecraft on the natural characteristics and thermally induced vibration of the system were investigated.The numeric simulation results show that the frequencies of the system increase with decreased inertia of the rigid hub of the flexible spacecraft,and there is a particular honeycomb core height to solar panel thickness ratio which corresponds to the maximum system frequency.The rigid-flexible coupling nonlinear terms do not affect the quasi-static part of the thermally induced response of the flexible spacecraft;however,they increase the amplitude of vibration part and change the system frequency.When the reciprocal of the thermal time constant of the system is close to the fundamental frequency,the amplitude of thermally induced vibration reaches maximum.The conclusions provided theoretical guidance for spacecraft design.%针对带大型太阳能帆板的航天器，使用蜂窝板对太阳能帆板进行建模，利用哈密顿原理建立了航天器刚柔耦合动力学方程，分析了刚柔耦合非线性项及系统参数对航天器固有特性和热诱发动力学响应的影响。结果表明，系统频率随中心刚体转动惯量减小而升高，存在特定的蜂窝芯层与蜂窝板厚度比值，使系统频率最高；系统刚柔耦合非线性项不影响热诱发动力学响应中的准静态位移分量，但会使热诱发振动分量的振幅增大，振动频率发生偏移；当系统热特征时间常数的倒数和系统基频接近时，热诱发振动幅值最大。研究结果对航天器参数设计提供了理论指导。