Research On Flight Control System 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 and landing, large angle of attack without stalling, simple control, low noise, good stability and safety of low-speed and so on. The performance of the fan-wing aircraft is between fixed-wing and helicopter. Having these advantages, it recently becomes a hot-spot in unmanned aerial vehicle and it has a broad application in both military and civilian field. Due to the invention, the research is in it’s fancy and many related theories in which should be studied. Therefore establishing mathematical model and the corresponding control law design have important significance for the improvement and development of fan-wing.Firstly, the thesis analysts the structure composition and lift principal of the Fan-wing aircraft, then estimates the performance of Fan-wing aircraft under given conditions based on the aerodynamic data and the thrust data of fan.Secondly, the thesis establishes a mathematical model of six-freedom under the MATLAB/Simulink environment, according to the relevant assumptions of rigid aircraft. Then it has been transformed into the C language to satisfy the computing needs of real-time simulation. Nonlinear equations are simplified to linear equations by balancing calculation and linear perturbation theory. Based on the linear model, the feature analyses are carried out and lay a foundation for the design of the control law.Thirdly, according to the characteristics of the fan-wing aircraft and the improvement of the flight quality, the control law of longitudinal and lateral-directional is designed by the classical control theory with the root locus method control parameters. And the major control parameters are also been described.Finally, the thesis has validated the rationality of the control law through the whole process of simulation. And to ensure that the control law are still valid under uncertainty environment, the thesis uses the Monte Carlo method to verify the robustness of the control law.