Resrarch On Maneuver Flight Control Technology For Flying-Wing Unmanned Aerial Vehichle

The maneuvering capability of flying wing unmanned aerial vehicle(UAV)is particularly important in close-in air combat.With the increasing challenge of the task to be carried out by the UAV,higher requirements have been put forward for the maneuverability of the aircraft.During the process of maneuvering,the perturbations of parameters and the nonlinear characteristics are obvious.In this paper,the problem of maneuvering flight is analyzed,and the maneuvering control of the flying wing UAV is realized.The main contents of the design include:Firstly,aiming at the flight process such as rapid acceleration / deceleration,jumping / diving,rapid turning and snake-like maneuvering,the kinematics and dynamics are analyzed.Based on the limitation of time and the maximum performance,the maneuvering flight control instructions are designed by using the method of piecewise linear function.Secondly,according to the neural network of Levenberg-Marquardt algorithm,the angular acceleration command allocation mechanism is designed to solve the problem of control assignment in flying wing UAV.Thirdly,according to the demand of maneuvering control,using sideslip angle and angular velocity feedback solves the unstability in lateral-direction.For the nonlinear coupling in the process of maneuvering,the feedforward Cross Coupling Method is used to decouple the nonlinear coupling.Based on the adaptive control of robust servo and model reference,the dynamic control law of the main-auxiliary architecture based on acceleration and angular rate is designed to realize the fast,stable and precise control of overload and track during maneuvering.Finally,a numerical simulation environment is built under MATLAB.The four kinds of maneuver commands and flight control law are verified.The results show that the proposed maneuvering control law can track the maneuver instruction quickly and effectively with good robustness and stability under the bounded perturbation and parameter perturbation,and satisfies the requirements of maneuver flight control.