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针对高超声速飞行器具有强耦合、控制器设计困难的问题,主要分析了飞行器的气动耦合特性,并在其基础上进行了耦合补偿控制器的设计。首先建立了高超声速飞行器的运动模型,并对气动模型进行了初步分析;然后利用对角优势阵理论对飞行器的气动耦合特性进行了详细分析,得到了稳定力矩耦合、阻尼力矩耦合以及操纵力矩耦合特性随马赫数、攻角及舵偏角的变化规律;最后,结合气动耦合特性设计了耦合补偿控制器,并进行了仿真验证。仿真结果表明,耦合补偿控制器的设计能有效降低飞行器三通道之间的气动耦合,提高了控制系统的动态响应能力和控制精度。
In order to solve the problem that the hypersonic vehicle has strong coupling and the controller is difficult to design, the aerodynamic coupling characteristics of the aircraft are mainly analyzed and the coupling compensation controller is designed. Firstly, the kinetic model of the hypersonic vehicle is established and the aerodynamic model is analyzed. Then, the aerodynamic coupling characteristics of the aircraft are analyzed in detail by using the diagonal dominant array theory. The coupling of the steady torque, the damping torque and the steering torque are obtained The characteristics of which are changed with Mach number, angle of attack and rudder angle. Finally, a coupled compensation controller is designed based on the aerodynamic coupling characteristics, and the simulation is verified. The simulation results show that the design of the coupling compensation controller can effectively reduce the aerodynamic coupling between the three channels of the aircraft and improve the dynamic response capability and control accuracy of the control system.