Matrix Theory And Control Design For A Kind Of Aircrafts

In recent years, High Altitude and Long Endurance Unmanned Aerial Vehicle (HALE UAV) as a new kind of UAVS has drawn extensive attention. They play important and special roles in strategic reconnaissance and up air soundings. The flying-wing configuration HALE UAV has features of high ratio of lift and drag, low level of detective, and technical advantages such as good load carrying properties, etc., which make it become research focus of aerospace industry. However, the special configuration of flying-wing aircraft also brings about some inherent deficiency, and its flight envelope is very broad. These characteristics make it become a more complex controlled object. Therefore, In order to design a satisfactory flight control system to improve the flight quality of flying-wing UAV, the design of flight control laws is rather critical.Now, there are many kinds of methods for robust control system design of wide-flight envelope, but each of them has its own defects. Especially, they lack developed theoretical argument in aspect of multi-objectives optimization.In this paper, we propose to apply the robust parametric method based on matrix algebra theory to control system design for flying-wing UVA, and represent the particular advantages of the method by comparing with traditional method. Also, some modification is made to improve the theory in aspect of multi-objectives optimization of the robust parametric method. For testing the validity of the proposed method, the method combining with the modified performance index are used in this thesis to design robust controller for one flying-wing UVA. First, nonlinear kinetic equations are built for one flying-wing aircraft and the mathematical form of the state-space model of the kinetic equations is given by using the small deviation linearized principle for nonlinear differential equations. Further, parameterized methods developed in this paper are applied to the preliminary design of control systems according to the flying qualities of flying-wing UAV combined with the control performance for the above model, state feedback control laws are derived of three characteristic state. Simulation results presented in this paper show that the control laws designed can successfully lead the closed loop system to achieve expected flight qualities, and with good dynamic response characteristic and stronger robustness.