摘要
姿态角的准确控制是太阳帆航天器能够成功应用的关键,具有十分重要的研究意义。旋转式太阳帆航天器由于没有支撑结构而表现出柔性特征,因此在对其进行姿态动力学建模及控制时,不能使用传统的刚性建模及姿态控制方法。针对在轨航行的旋转式太阳帆航天器,在物理模型的基础上利用混合坐标法建立其姿态动力学刚柔耦合模型。针对该模型,设计能够跟踪最优姿态角且同时抑制帆面柔性振动的控制器,并分析采用4个反作用喷气装置作为执行机构时的实现情况。仿真结果表明,设计的LQR控制器能够使旋转式太阳帆跟踪到最优目标姿态角并且有效抑制了柔性帆面的振动,旋转式太阳帆在轨航行过程中利用反作用喷气力矩来对其姿态角进行控制是可行的。
Accurately control of the attitude angle for solar sail spacecraft is the key to successful application, which has very important research significance. As the spinning type solar sail does not have any rigid structure , it has significant flexible features. And The tra- ditional rigid modeling or the attitude control method cannot be used again. In consideration of the spinning solar sailing in orbit, a rig- id-flexible coupling dynamic model is presented. And a controller which can track the optimal attitude angle and simultaneously suppress the vibration of flexible sails is designed for the system. Besides, using four reaction when jet apparatus as executing agency achieve- ment is analyzed in the paper. Simulation results show that the LQR controller designed in this paper can reach the requirements above and using reaction jets torque to control the attitude angle is feasible.
出处
《控制工程》
CSCD
北大核心
2014年第5期700-704,共5页
Control Engineering of China
基金
国家863计划资助项目(2011AA7034056C)
关键词
旋转式太阳帆
刚柔耦合
姿态角
LQR控制器
spinning solar sail
rigid-flexible coupling
attitude angle
LQR controller
