Flight Control System Design And Simulation For A Certain Fixed-wing UAV

Nowadays, unmanned aerial vehicle(UAV) is widely used in military and civilian fieldsbecause of its convenience、safety and low-cost during performing tasks. The flight controlsystem (FCS) is the core of a UAV and the key for a UAV to complete the mission efficiently.More and more attention has also been paid to the study of FCS among some scientificresearch institutes, universities and companies.Traditional PID controller is widely utilized in the flight control system and has beenapplied to practical flight situations successfully. The flight system and controller design aredescribed by taking an aeromagnetic detecting UAV as an example. A flight control methodbased on multi-model control is proposed. Contributions of the work are as follows:Firstly, the development of UAV and its flight control system is outlined. Methodsemployed in flight control system are compared and analyzed, and the establishment ofmathematical models of UAV is introduced as well as the method of linearization.Secondly, based on the analysis of a flight control system of an aeromagnetic probe UAV，the thesis introduces composition of the fixed-wing UAV flight control system and doesanalysis to the ground control station and the airborne control system. Then, the design of thecontrol law and the navigation strategy for a general layout UAV are highlighted. Altitude,speed and heading control loop are designed by introducing angular rate feedback as the innercontrol loop, which facilitates to complete missions according the pre-set instructions. Apractical flight test is carried out to verify the performance of the flight control system basedon PID control. Results show that the designed system can meet the requirements of thesubject tasks.Aiming at some deficiencies of PID control, multi-model control technique is proposed.Furthermore, due to lack of aerodynamic parameters of UAV in the laboratory, F-16is takenas the control plan. Then multiple aircraft models are established as well as the correspondingcontrollers for fixed-wing aircrafts. In addition, the controller is applied to the flight controlsystem and the simulation validates efficiency of the proposed method, which provides areference for the later study about the application of multi-model technique for UAVs.Finally, summary and analysis of all work have been done. Future focus and direction of thework are put forward according to the subject and the practical debugging experience.