倾转旋翼飞机直升机模态短舱倾转飞行控制

为了研究倾转旋翼飞机短舱倾转过程中的飞行控制问题,提出了一种基于线性规划的动态逆方法,以实现直升机模态下短舱小角度倾转时的姿态和速度控制。建立了倾转旋翼飞机简化的纵向非线性模型,以短舱角、旋翼纵向周期变距和总距作为控制输入,使用基于线性规划控制分配的动态逆方法设计了控制器。仿真结果表明:飞机在执行姿态或速度指令时,在无输入饱和和输入速率饱和的情况下能以最快速度完成倾转。该方法能完成要求的控制任务,闭环系统稳定,稳态性能好,有一定的鲁棒性。

Flight control of tiltrotor aircraft in helicopter mode with nacelle tilting

A linear programming-based dynamic inverse attitude and velocity control method was developed for tiltrotor aircraft operating in helicopter mode with a small degree of nacelle tilting.A simplified longitudinal nonlinear model was used which approximated the asymmetric aerodynamic force on the fuselage caused by the rotor induced velocity.The control inputs were the nacelle angle,the collective pitch and the longitudinal cyclic pitch.The controller uses a linear programming control allocation-based dynamic inverse method.Simulations show that the controller can rapidly tilt the nacelle without control input or input rate saturation when executing attitude or velocity commands.The results indicate that the controller provides good stability,stable performance and robustness.