基于自抗扰的地效飞行器俯仰控制系统设计

Design of ground effect aircraft pitch control system based on auto disturbance rejection

针对地效飞行器在低空巡航阶段,纵向气动参数的非线性和大气扰动对纵向飞行姿态的影响,采用二阶自抗扰控制器进行飞行器的纵向俯仰姿态控制,通过MATLAB仿真验证当俯仰角输入分别为阶跃和正弦波下所设计的控制器的响应能力,并针对包线范围内不同状态点、参数扰动和大气扰动,分析所设计的自抗扰俯仰角控制器的控制效果。仿真结果表明,所设计的自抗扰俯仰角控制器是有效的,超调量和调节时间均满足系统要求,超调均小于5%,调节时间均小于10 s,且系统具有强的鲁棒性和抗干扰性。

Aiming at the low-altitude cruising stage of the ground-effect aircraft,the nonlinearity of the longitudinal aerodynamic parameters and the influence of atmospheric disturbances on the longitudinal flight attitude,a second-order ADRC controller was used to control the longitudinal pitch attitude of the aircraft.MATLAB simulation was used to verify when the pitch angle inputs were The response capability of the controller designed for step and sine waves,and the analysis of the control effect of the designed active disturbance-resistant pitch angle controller for different state points,parameter disturbances and atmospheric disturbances within the envelope.The simulation results show that the designed ADRC pitch angle controller is effective.Both the overshoot and the adjustment time meet the system requirements,the overshoot is less than,the adjustment time is less than,and the system has strong robustness and anti-interference.