摘要
研究了空间飞行器大角度机动飞行的变结构姿态控制。应用四元数来描述姿态运动,以消除大角度机动飞行时欧拉角描述所存在的奇异性。基于Lyapunov方法设计了变结构控制的切换函数,以保证系统的滑动模态,亦即四元数偏差的稳定性。基于所给切换函数,设计了变结构控制器。数值仿真的结果说明了设计方法的有效性。
Variable structure attitude control of spacecraft large angle maneuver flight is studied. The attitude dynamics is described by quaternion to eliminate singularity of Euler angle description. Based on the Lyapunov stability theory, switching functions of the variable structure controllers are designed to ensure the stability of the sliding modes, quaternion error dynamics. Based on the given switching functions, the variable structure controllers are designed. Numerical simulation results justify the feasibility of the proposed design method.
出处
《飞行力学》
CSCD
2004年第2期45-48,共4页
Flight Dynamics
关键词
空间飞行器
姿态控制
变结构控制
四元数
spacecraft
attitude control
variable structure control
quaternion
