论文部分内容阅读
本文以含有挠性太阳能帆板的卫星为研究对象,建立了考虑动力刚化效应的刚柔耦合动力学模型,并与传统的线性模型进行了对比。首先,通过Hamilton变分原理建立了考虑动力刚化效应的挠性卫星的姿态运动和结构振动的偏微分方程;之后,通过假设模态法对偏微分方程进行离散,得到离散化后的线性模型和动力刚化模型;最后,给出了某些特定外界激励下两种模型动力学响应的数值仿真结果。仿真结果表明,动力刚化效应将对卫星的柔性结构振动产生较大影响;在一定的外界激励下,采用线型模型的计算结果与动力刚化模型的计算结果之间存在较大偏差。
In this paper, a flexible rigid-flexible coupled dynamic model considering the effect of stiffening is established by taking a satellite with a flexible solar panel as the research object, and compared with the traditional linear model. First, the partial differential equations of attitude and vibration of flexible satellites considering dynamic stiffening effect are established by Hamilton variational principle. After that, by the assumption of modal method, the partial differential equations are discretized to obtain the discrete linear model Finally, the numerical simulation results of the dynamic responses of two models under certain external stimuli are given. The simulation results show that the stiffening effect will have a great influence on the vibration of the flexible structure of the satellite. Under certain external stimuli, there is a big deviation between the linear model and the rigid model.