基于LQR的倾转旋翼机过渡段控制律设计

Design of Transition Control Law of Tilt-Rotor Aircraft Based on LQR

倾转旋翼机具有直升机模态、过渡段模态和定翼机模态,既有直升机的悬停和垂直起降性能,又有定翼机的高速巡航飞行能力,在过渡段模态,气动干扰严重且稳定性较差,因此,设计过渡段的控制律具有一定意义。以XV-15倾转旋翼机作为原型,首先用MATLAB建立飞机的气动模型,然后基于LQR最优控制算法对过渡段的纵垂向飞行姿态进行控制律的设计,最后进行模拟仿真。结果表明,LQR控制器对倾转旋翼机的飞行姿态具有较好的控制效果。

Tiltrotor aircraft have helicopter mode,transition mode,and fixed wing mode,which not only have the hovering and vertical takeoff and landing performance of helicopters,but also the high-speed cruise flight capability of fixed wing aircraft.In the transition mode,aerodynamic interference is severe and stability is poor.Therefore,designing control laws for the transition stage is of certain significance.Taking the XV-15 tiltrotor aircraft as a prototype,the aerodynamic model of the aircraft was first established using MATLAB.Then,based on the LQR optimal control algorithm,the control law for the longitudinal and vertical flight attitude of the transition section was designed.Finally,simulation was conducted,and the results showed that the LQR controller had a good control effect on the flight attitude of the tiltrotor aircraft.