基于ADAMS航天器太阳帆板展开与锁定动力学仿真

Dynamics simulation of deployment and locking of spacecraft solar panel using ADAMS

太阳帆板展开与锁定是航天器入轨后的重要操作之一,正确分析和预测柔性太阳帆板在展开与锁定过程对航天器本体姿态运动的影响是十分必要的。首先利用ANSYS有限元软件建立太阳帆板的有限元模型作为ADAMS中的柔性体,然后基于ADAMS建立了柔性太阳帆板在两种典型常见展开方式下的动力学仿真系统,一种展开方式为两侧太阳帆板同时展开;另一种展开方式为先展开一侧太阳帆板,经过一段时间稳定后再展开另一侧,分别仿真分析了这两种展开方式下太阳帆板展开与锁定过程的动力学性能以及航天器本体的姿态变化;设计了一种太阳帆板锁定机构,仿真结果表明这种锁定机构满足功能设计要求,对工程设计有一定的参考意义。

It is one of the most important operation for solar panels deployment and locking after spacecrafi flying into orbit. So it is necessary to analyze and forecast the attitude effects in the process of the flexible solar panel deployment and locking. First, using the finite element analysis software ANSYS establish the finite model of the flexible solar panel as the flexible body in ADAMS; second, establishing two dynamics simulation systems of flexible solar panels in two typical deployment modes using ADAMS, one is the panels on both side deployment at the same time; the other is the panels on one side deployment first and deploy the other side after a while; finally, making simulation and analyzing the attitude motion of spacecraft undergo the flexible solar panel deployment and locking; Further more designing a solar panel locking structure and the result of the simulation shows it satisfies the locking demand, which has some reference meaning to engineering design.