Tilt rotor unmanned helicopter flight control method for the transition period

One kind of tilting rotor unmanned helicopter flight control method of the transition section, wherein the optimal preview control method using the equations of motion restraint system through fusion, predictable performance over the state of the restriction information and most of tiltrotor helicopter flight control transition section; specific methods: Firstly tiltrotor unmanned helicopter model the nonlinear transition section, and the nacelle angle at different linear trim obtained state-space description of linear equations; secondly, based on linear model, design optimal preview controller that controls the transition flight speed, altitude and attitude angle; finally forming a smooth transition of formula Fader design inertial delay between the different inclination of the nacelle tiltrotor unmanned helicopter. Object of the present invention is a method of flight control unmanned helicopter rotor to provide a transition section tilting, fusion predictable desired speed, altitude and attitude angle information, the switching between the secure complete tilting rotors unmanned helicopter mode.