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针对飞行器在大姿态角飞行时系统存在的非线性、耦合和不确定性因素,提出了自适应模糊滑模的控制方法来设计飞行器的姿态控制系统。采用模糊逼近的方法对姿态控制系统的不确定性进行补偿,并在此基础上设计了自适应模糊滑模解耦控制器。推导了系统的控制律和参数自适应律,并基于李亚普诺夫函数证明了该控制方法可保证闭环系统的全局稳定,最后通过数值仿真验证了本文提出方法的有效性。
Aiming at the nonlinearity, coupling and uncertainty of the aircraft during large attitude angle flight, an adaptive fuzzy sliding mode control method is proposed to design the attitude control system of the aircraft. The method of fuzzy approximation is used to compensate the uncertainty of the attitude control system. On this basis, an adaptive fuzzy sliding mode controller is designed. The control law and parameter adaptive law of the system are deduced. Based on the Lyapunov function, the control method can be used to ensure the global stability of the closed-loop system. Finally, numerical simulation shows the effectiveness of the proposed method.