摘要
大气层内直接力与气动力复合控制导弹具有响应快速、可用过载大等优点,可以拦截高速、高机动性目标。研究制导末端轨控直接力与气动力复合系统姿态稳定问题。首先分析了复合系统的特点和控制问题,建立了控制模型。然后应用扩张状态观测器观测对象模型内扰和外扰的实时作用量,进行反馈补偿,实现了动态线性化。最后设计了非平滑反馈控制律,从而实现了复合系统的姿态控制设计。仿真结果表明,系统具有良好的动态性能和稳态性能,控制器具有很强的鲁棒性。
Missile with lateral thrust and aerodynamics blended have the merits of rapid response and big available overload, so it can intercept missile of high speed and high maneuverability. This paper studies attitude stabilization problem for trajectorycontrol blended system at the end of guidance. At first, the characteristics and the main control problem for blended system are analyzed, and the blended control model is established. Then the extended state observer is applied to observe the internal disturbance and the external disturbance of control model for blended system, further the feedback compensation is performed, thus the dynamic linearization is implemented. At last the non-smooth feedback control law is designed for the linearized system, thus the attitude controller for blended system is achieved. The simulation results show that the closed loop system attains high dynamic performance and steady-state performance and the controller has excellent robustness performance. Ext
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第4期840-844,共5页
Journal of Astronautics
关键词
扩张状态观测器
非平滑反馈
复合控制
自抗扰控制器
姿态稳定
ended state observer （ESO）
Non-smooth feedback
Blended control
Active disturbance rejection controller （ADRC）
Attitude stabilization
