Research On Modeling And Control Of Fan-wing Aircraft

In recent years, Fan-wing aircraft has been developed as a new low-speed, large-load vehicle. The Fan-wing has many advantages such as short-distance take-off, landing/vertical take-off,landing, large angle of attack without stalling, significant stability and safety of low-speed, large payload and so on. Owing to these advantages, it becomes a hot-spot in unmanned aerial vehicle and it has a broad application in both military and civilian field. Since the invention was put forward for no long time, the research needs many improvements and a large number of important theories need to be studied and presented. For the unique flying principle, this paper has designed and given the mathematical model and the flight control system of the Fan-wing aircraft.The main contributions of this thesis can be illustrated as follows:Firstly, the thesis introduces the structure and composition of the Fan-wing aircraft, analyzes the flying principle and characteristics briefly. Then the mathematical model based on the flight dynamics will be established and the stability of this aircraft will be discussed. According to the small perturbation principle, the linear model can be obtained and analysis of the aerodynamic characteristics can be discussed, which will be the foundation for the design of the control law in the following context.Secondly, according to the different flight modes, this thesis designs the longitudinal and lateral control law by resorting to the classical control theory.Finally, the thesis can realize the Fan-wing’s whole process of digital simulation. The simulation results show that the mathematical model of the Fan-wing is available, the flight control system achieves good effect, and the autonomous and safe flight can be realized.