摘要
针对组合式航天器分离后惯量矩阵会产生较大变化的特点,提出了一种自适应控制律。利用姿态四元数建立航天器运动学模型,基于Lyapunov稳定理论,用退步控制方法设计了控制律。理论分析表明该控制律可保证系统渐近稳定,仿真结果验证了该控制律的有效性。
Based on varieties of the inertia matrix for a combined spacecraft after separation, this paper proposes a adaptive control algorithm. Attitude quaternion is adopted to establish the model of the kind of spacecraft, and based on the Lyapunov stability theory, the algorithm is designed by the backstepping control method. Theoretical analysis proves the algorithm to be stable, and the simulation results confirm the effectiveness of the algorithm.
出处
《空间控制技术与应用》
2009年第2期35-37,45,共4页
Aerospace Control and Application
关键词
组合式航天器
姿态控制器
设计
combined spacecraft
attitude controller
design
