摘要
针对刚体卫星转速和控制力矩受限的情况,提出了避免敏感器及执行器饱和的大角度特征轴机动控制律,并用李雅普诺夫稳定性理论证明其稳定性。控制律以修正罗德里格参数表征姿态,采用特征轴机动作为拟最小时间机动策略,通过姿态误差的切换阈值将机动过程分为两个阶段。给出了控制参数的整定方法和选择范围。最后进行了控制律算法的数值仿真,仿真结果表明控制律能够在卫星进行大角度姿态机动过程中有效地避免敏感器及执行器饱和。
The problem of spacecraft large angle maneuver control under the saturation limit of sensor and actuator is investigated.The nonlinear feedback control logic with MRP as the representation of the attitude is introduced,avoiding the saturation of the sensor and the actuator during the maneuver.The maneuver is divided into two phases by a threshold determined by the error of the attitude.The setting way and scope of the control parameters are given and the stability of the system is proved by Lyapunov theory.A near-minimum-time eigenaxis rotation is used to improve the speed of the maneuver.Finally,the simulation of the control law is provided,the result of which proves the control law to be effective and reliable.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2010年第4期1036-1042,共7页
Journal of Astronautics
