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针对刚体航天器在参数不确定及环境扰动情况下的大角度姿态机动问题,提出一种自适应离散变结构姿态控制算法.建立包含航天器姿态运动学及动力学的仿射模型,并精确反馈线性化解耦;对得到的各线性动态方程离散化处理,由离散指数趋近律推导了参数化的离散变结构姿态控制律.最后基于Lyapunov稳定性理论设计了控制参数的自适应更新律,有效克服了模型中的各时变项及干扰项影响.仿真结果表明,该算法可有效减小干扰引起的姿态指令角跟踪偏差,确保了大角度姿态机动控制的精确性与鲁棒性,并且消除了常规变结构控制的抖振现象.
Aiming at the large-angle attitude maneuver problem of rigid spacecraft with uncertain parameters and environmental disturbances, an adaptive discrete variable structure attitude control algorithm is proposed, and affine models including attitude kinematics and dynamics of the spacecraft are established and accurately fed back The linearized decoupling method is used to discretize the obtained linear dynamic equations and the parameterized discrete variable structure attitude control law is deduced by the discrete index approach. Finally, an adaptive updating law of control parameters is designed based on the Lyapunov stability theory, Which can effectively overcome the influence of each time-varying and disturbing term in the model.The simulation results show that the proposed algorithm can effectively reduce the tracking error caused by disturbance and ensure the accuracy and robustness of maneuvering control in large-angle attitude Eliminating the chattering of conventional variable structure control.