航天器帆板展开过程动力学建模与仿真

阐述了应用柔性多体动力学和Kane方程进行航天器帆板展开过程建模的方法，将帆板视为柔性体并进行模态分析，采用有限元法与模态缩聚技术建立了帆板的离散化模型．以国产某型号航天器为例，同时考虑4块帆板的柔性，应用ADAMS软件对帆板的展开过程进行了建模与仿真，得到了帆板的变形、大范围运动等动力学参量，为航天器帆板的设计提供了一定的依据．

Dynamics Modeling and Simulation of Spacecraft Solar Array

Flexible multibody system dynamics and Kane's equation are introduced to establish the dynamic model of a spacecraft solar array. The panels are regarded as flexible bodies and modal analysis is made. Finite element method and modal condensation technique are adopted to discretize the panels. A model of solar array with four panels is analyzed as an illustrative example, all the four panels are considered as flexible bodies. Geometric modeling and deploying simulation of the array are carried out with ANSYS and ADAMS software. Simulation results such as the panels' deformation, angular displacement and angular velocity are got and the results are useful for the design and test of spacecraft solar array.