Research On The Control Algorithms And The Modeling Of Flying Wing UAV

As the application area of Unmanned Aerial Vehicle (UAV) is more widely, thedevelopment of UAV technology is also getting more and more attention all over the word.Due to the flying wing layout has a lot of dynamic advantages and good stealth performance,it becomes the best choice of the aerodynamic shape of UAV. But such specific pneumaticstructure will decrease the static stability, reduce the operating efficiency and make theaircraft be vulnerable to outside interference. In allusion to the problems mentioned above,this paper puts forward some new control methods based on the study of flying wing UAV. Itprovides detailed design of the corresponding flight control law and carries out simulation test,the flying wing UAV can achieve a stable flight.Firstly, the model of six degrees of freedom of UAV is modeled according to theaerodynamics and Newtonian mechanics theory. The principle of small perturbation is used toprocess the longitudinal and lateral decomposition and linearization of typical flight state ofthe UAV. At the same time, it makes a detailed analysis on the longitudinal and lateral staticand dynamic stability of flying wing UAV in open-loop state. Then according to the standardflight quality and control performance of flying wing UAV, it completes the augmentationcontrol of the UAV with the design of the longitudinal and lateral augment stability controllaws based on conventional Linear Quadratic Regulator (LQR) and the output feedback linearquadratic regulator method. Finally, aiming at the problem that the flying wing UAV isvulnerable to outside interference, the paper gets two kinds of augmented LQR controlalgorithm by combing the conventional LQR regulator with special control systems, anddesigns longitudinal and lateral attitude control law of the UAV based on these two controlalgorithms.The emulational model of the flying wing UAV is established in Matlab/Simulinkenvironment to test the effectiveness of above control laws. Simulation results show that thecontrol law of augment stability and attitude has good control performance, and it can satisfy the flight quality requirements of flying wing UAV.