Study On Flight Mechanics Performance And Autonomous Control Technology Of A Canard-configuration UAV

With the development of modern technology, the frequency of the usage of UAV becomes higher and the application of UAV becomes widespread either in range of military and civilian. The coming problem is how to improve the control performance of UAV in autonomous flight.The flight control system of UAV belongs to the nonlinear control category. Dynamic inversion method, which is a good method, since it owns a lot of flexibility to adapt to the change of the model of aircraft and can satisfy the unconventional control requirement such as high attack angle control and super maneuver control, is one of so many methods which can transfer nonlinear systems to linear systems with the development of modern control technology. This paper takes a certain type of canard-configuration UAV as the research object. Firstly, three dimension model of UAV is established and then the UAV aerodynamic performance is analyzed and the kinematic and dynamic equations are built up based on the pneumatic model. Secondly, the nonlinear control system is transferred to the linear control system using dynamic inversion method based on dynamic inversion system theory. And the study on the operation of UAV and flight dynamics characteristics depended on the transformation. Then a kind of method used to control the flight trajectory based on direct coordinate is proposed and the autonomous flight control law of UAV is designed. Lastly, the software MATLAB is used to simulate the processes of autonomous flight of UAV. The simulation consequences imply that the two inner loops of the control law of UAV designed by the method dynamic inversion are stable, with less overshoot and no vibration and reasonable response time. The outer loop can maintain the accuracy of trajectory tracking.