Flying Wing Uav Control Law Design

As Unmanned Aerial Vehicle(UAV) has taken more important part in both military and civil field, more attentions are paid to the development of UAV in many countries. Flying-wing layout has some unique technique advantages, which makes many advanced aircrafts are designed with flying-wing layout. However, the exclusive pneumatic layout and structure peculiarity also brings it some disadvantages. In order to design a satisfactory flight control system to improve the flight quality of flying-wing UAV, this thesis is concentrated on the preliminary research of flight control laws design of one high altitude and long endurance flying-wing reconnaissance UAV.The take-off and landing stages of UAV are introduced in detail and the take-off and landing characteristics of flying-wing UAV are firstly studied in this paper. According to the comparison between two design schemes, a scheme is chosen to design a suitable automatic landing system. Then the math model is built using flight dynamics theory and the flight quality of flying-wing UAV is analyzed. According to the standard of flying-wing UAV's flight quality and control performance, the augment stability control laws and control laws of basical flight models are designed. And the longitudinal and lateral control laws of automatic landing are designed in detail by adopting glide beam guiding system, auto leveling control system and lateral beam guiding system. Nonlinear emulational program is developed in Matlab Simulink environment to test the laws' validity and they should be adjusted if necessary. And the robustness of the designed control system to the atmospheric turbulence is verified by simulation. Finally, main methods and characteristics of flying-wing UAV's control system design are analyzed based on nonlinear simulation results and some advice for improvement is presented.