CAJ | 학술논문

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。
침대복잡적비선성항천기궤도급자태모형，고필료존재외부우동력구급궤도궤동인기항천기뇨성부건진동적뇨성항천기자태은정적문제，설계료기우활모산법적뇨성항천기자태공제기，우점시설계적공제기부수요항천기자태각신식불수요자태각속도신식。활모산법표현출료대외부우동급궤도궤동과정대뇨성항천기자태영향적로봉성，가이사처우궤도궤동과정중적뇨성항천기자태공제계통은정。급출료기우Lyapunov은정성이론적자태공제폐배계통은정성증명。방진결과표명：본뇨성항천기자태공제계통재외부우동급궤도궤동공제력적영향하은정。
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.