Research On Control Laws For A Tailless Flying Wing UAV With Low Aspect-ratio And Simulation

A plenty of advanced unmanned combat aerial vehicle(UCAV) at present are designed with flying wing layout. Flying wing UCAV has excellent performance in endurance, structure and stealth capability, with the shortcomings of poor stability and low handling efficiency. In this article, a flying wing UAV with low aspect-ratio is researched. The flight control system is designed by two control methods after its characteristics analyzed. By the simulation, the reliability of the design is verified while the advantages and disadvantages of two methods compared.Firstly, the UAV in this paper is introduced in general. The nonlinear equation which is established under the basic hypothesis is linearized and decoupled. After that, based on the aerodynamics data calculated by CFD and wind turner data, stability and control characteristics and main aerodynamics peculiarity are analyzed. The influence of yawing control devices Spoiler/Slot Deflector on the UAV with low aspect-ratio is discussed.Secondly, the classical control and the robust servo LQR are briefly introduced. After that, the control law and the flight control system are designed while airplane mode is set up by MATLAB/SIMULINK. Simulating the impact of sensor noise and environmental factors as authentic as really as possible, the whole flying process is simulated successfully while three-dimensional animation is displayed. By the step response curve in typical position on routes, the two control methods are compared. And then the simulation with Monte-Carlo method verifies the feasibility and the robustness of the control system.Finally, the conclusions to the whole article and the prospects to some deficiencies and direction which could be improved and studied further have been done.