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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。
For the spacecraft with large solar panels, honeycomb panels are used to model the solar panels. The rigid-flexible coupled dynamics equations of the spacecraft are established based on the Hamilton principle. The effects of rigid-flexible coupled nonlinearities and system parameters on spacecraft Intrinsic properties and effects of heat-induced kinetic responses. The results show that the system frequency increases with the decrease of the moment of inertia of the center rigid body, and there is a certain ratio of honeycomb core to honeycomb thickness, which results in the highest system frequency. The rigid-flexible coupling nonlinearity does not affect the thermal induced kinetic response However, the amplitude of heat-induced vibration component increases and the vibration frequency shifts. When the reciprocal of the thermal characteristic time constant of the system approaches the fundamental frequency of the system, the heat-induced vibration amplitude is the largest. The results provide theoretical guidance for spacecraft parameter design.