Abstract
As the flying wing layout unmanned aerial vehicle (uav) extensive research and task environment increasingly complex, Yu Feiyi layout unmanned aerial vehicle (uav) for fault tolerant control gradually become the main technical means of the flight control, using the established mathematical model of the flying wing uav longitudinal layout setting the actuator failure effect, is in the nature of adaptive control allocation fault-tolerant algorithm is given, and MATLAB/simulink simulation is carried out for uav longitudinal motion, realize the rapid and stable, the control command and response to complete the nonlinear fault-tolerant control of flying wing uavs.
Highlights
In consideration of the changing aerodynamic configuration, the flying-wing UAV is equipped with the structure of multiple rudder surfaces, which gives rise to a variety of combinations of various rudder surfaces
If the torque and the angular acceleration are respectively projected into the three axes of the airframe structure’s axle system, and the control allocation algorithm is used to process the effective and rational allocation of multiple rudder surfaces in performance control, the UAV can be allowed to adapt to different flight conditions, and loss in various aspects can be reduced, which will significantly increase the control efficiency and the fault-tolerance performance of the UAV with the structure of multiple rudder surfaces
In terms of the flying-wing UAV studied in this chapter, the steerage of the four rudder surfaces in pitch control is the same, so it is required that the sum of the deflection angles of the four rudder surfaces is equal to the expected deflection angle of the elevator ue0c ; 2) The sum of the rolling moment caused by the deflection angles of the four rudder surfaces is zero
Summary
In consideration of the changing aerodynamic configuration, the flying-wing UAV (unmanned aerial vehicle) is equipped with the structure of multiple rudder surfaces, which gives rise to a variety of combinations of various rudder surfaces. If the torque and the angular acceleration are respectively projected into the three axes of the airframe structure’s axle system, and the control allocation algorithm is used to process the effective and rational allocation of multiple rudder surfaces in performance control, the UAV can be allowed to adapt to different flight conditions, and loss in various aspects can be reduced, which will significantly increase the control efficiency and the fault-tolerance performance of the UAV with the structure of multiple rudder surfaces. The comprehensive utilization and combined control of the rudder surface can fully explore the potential of each rudder surface and the airframe structure, and at the same time reduce the cost and price, it can still greatly improve the flight performance of the UAV
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