摘要
基于航天器姿态动力学模型,对三轴稳定飞轮姿控微小卫星控制方法进行研究。不考虑解耦运算,采用改进的PD控制,以期望目标姿态角和角速度函数作为输入,飞轮角加速度作为输出,在每个通道上分别加入该控制器,实现对小卫星姿态的有效控制。仿真结果表明:该法对干扰抑制明显、对系统误差不敏感,响应过程快速,稳态精度较高(可达1×10-4 rad),应用时便于星载计算机处理,简单高效。
Based on spacecraft attitude dynamics equation, control algorithm for micro-satellite of three-axis stabilization via reaction-wheel was studied. With improved PD control algorithm, in which anticipant target angle and angle rate function was served as input, the acceleration of reaction- wheel was served as output, effective control for micro-satellite was realized, in which decouple-operation to the dynamics equation was avoided. The results showed that the method issued was effective in repressing disturbance and not sensitive to system error, which had high steady accuracy（ 1 × 10-4 rad）. The method was simple and efficient,which is convenient for computer on the satellite to disposal in application.
出处
《舰船电子工程》
2013年第1期61-63,共3页
Ship Electronic Engineering
关键词
微小卫星
姿态动力学模型
飞轮
三轴稳定
控制算法
期望目标姿态角
micro-satdlite, attitude dynamics equation, reaction-wheel, three-axis stabilization, control algorithm, anticipant target annie
