High Viability Of Uav Control Law Reconfiguration,

High-altitude Long endurance(HALE) Unmanned Aerial Vehicles(UAV) have important effect in wars. But the probability of control system failure increased highly. In the process of flight control system development overseas, the reliability and survivability of HALE UAV are enhanced, to ensure safety of plane and equipment, carry out high reconnaissance and head off missiles possibly. When HALE UAV is suffered damage and failure, it needs high survivability flight control system (FCS). So this paper introduces reconfigurable flight control system, and reconfigure control law for HALE UAV when it is in some typical failures.The work mainly includes the following parts:1. The UAV linear model is built by small disturbance equation with aerodynamic parameters. Control law is designed for plane in given situation for flight qualities. And control law is revised in nonlinear model.2. The conception of failure detectability and reconfiguration are discussed for reconfigurable control system. Control redundancy and reconfiguration condition of nonlinear system are given. HALE UAV control law for typical single failure situation is designed in classical method, and simulated by matlab.3. Digital simulation model in a tri-redundancy half physics simulation system is built for HALE UAV. It is linked with external physics equipment, and verified in closed loop experiment.4. Some control law reconfiguration project is discussed for situation of more particular aerodynamic data. Reconfiguration for failure surface by Pseudo-inverse Method (PIM) is researched. And some other methods are introduced , such as Mode Following Method, Artificial Intelligence Method ,ect.