摘要
研究了姿态跟踪机动问题⒀通过引入视线坐标系⑿将时变终端条件的控制问题转化为定边界的控制问题⒀建立了飞行器相对于视线坐标系的四元数姿态运动学模型⑿提供了由已知信息计算姿态四元数的函数关系⒀引入了拟欧拉角变换⑿基于拟欧拉角信号设计了跟踪机动控制律⒀通过对空间预警卫星监视低轨道飞行器问题的仿真⑿验证了设计方法的正确性⒀
Maneuver of a spacecraft tracking a moving target is studied. The time variable boundary value is transferred into a fixed boundary value by introducing the view of sight coordinate. Attitude model is described with four dimensions. Quasi Euler angle is introduced to change the three axis coupling attitude control system into three perturbed double integrated control systems. A variable structure control law is designed based on quasi Euler angle and its rate. The method is verified to be correct by the simulation for the task that a forewarning satellite monitors a low orbital spacecraft.
出处
《飞行力学》
CSCD
北大核心
1999年第3期86-91,共6页
Flight Dynamics
基金
国家自然科学基金
关键词
姿态跟踪
大角度机动
非线性控制
航天器
Attitude tracking High attitude maneuver Nonlinear control Quasi Euler angle
