摘要
本文采用欧拉四元数、姿态角速度和振型模态坐标、建立了具有角动量存贮挠性飞行器姿态动力学的奇异摄动非线性模型。讨论了系统的慢流形降阶和校正控制方法,给出了非线性退化系统的全局线性化公式。文中还介绍了数字仿真实例和结果。
In this paper, a singularly perturbed nonlinear model of flexible spacecraft dynamics are represented using the angular velocity, Euler quaternion, and flexible modes. The reduced system and corrective control are described on the slow manifold Me. The corrective control is expressed by the rigid-body control and rigid modes. The reduced system is transformed into an global equivalent linear system with controllable canonical form. The control torque commands of the actuators are designed. Numerical results are presented for a three-axis stabilized satellite with flexible solar arrays.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1989年第2期10-18,共9页
Journal of Astronautics
关键词
飞行器
姿态控制
非线性控制
Spacecraft, Attitude Control, Nonlinear control, Linearization.
