基于滑模方法的挠性航天器姿态稳定控制(英文)

Sliding mode based controller design for flexible spacecraft attitude stabilization

针对复杂的非线性航天器轨道及姿态模型,考虑了存在外部扰动力矩及轨道机动引起航天器挠性附件振动的挠性航天器姿态稳定的问题,设计了基于滑模算法的挠性航天器姿态控制器,优点是设计的控制器仅需要航天器姿态角信息不需要姿态角速度信息。滑模算法表现出了对外部扰动及轨道机动过程对挠性航天器姿态影响的鲁棒性,可以使处于轨道机动过程中的挠性航天器姿态控制系统稳定。给出了基于Lyapunov稳定性理论的姿态控制闭环系统稳定性证明。仿真结果表明:本挠性航天器姿态控制系统在外部扰动及轨道机动控制力的影响下稳定。

Attitude stabilization for complex nonlinear spacecraft with flexible appendages is re-searched at the presence of external disturbances and orbital maneuver.A flexible spacecraft at-titude control er based on sliding mode algorithm is proposed,which only needs the information of attitude angular without the knowledge of the attitude angular velocity and exhibit excel ent robust performance.The paper demonstrates the close loop system stability employing the Lyapunov stability theory.The simulation results il ustrate this flexible spacecraft attitude control system maintain stable in spite of external disturbance and orbit control force.