Flying Wing UAV Reconfigurable Flight Control Using Sliding Mode
A reconfigurable flight control design technique on the basis of sliding mode control for flying wing UAV is developed in this work. On-line damage (parameter) estimation is not required .the fault of actuators and damage of aerodynamic surfaces are considered as a disturbance or unexpected parameter change which degrades the system performance or may destabilized the system, for the system on the sliding mode surface is robust to the matched unmolded dynamics and matched disturbance, so the flight control system is reconfigured automatically when some fault of actuators and damage of control surfaces arise. A Modular structure of the system is proposed. An optimal control allocation algorithm is employed for the redundant control effectors of UAV. For the obvious differences in time scales of the control variables, the two closed-loops sliding mode control is applied to this system, the outer loop is the angular loop and the inner loop is the angular rate loop. A mathematical model of the flying wing UAV is used to demonstrate the abilities of the sliding mode control to address aerodynamic surface failures and actuator fault during execution of flight maneuvers. The results of simulation show that it has excellent tracking and high accuracy reconfiguring performance ．
sliding mode control flying wing UAV flight control control allocation
LI Hongzeng ZHANG Yuzhuo
Department of Automatic Control, Northwestern Polytechnical University, Xian, China, 710072
国际会议
北京
英文
2007-08-05（万方平台首次上网日期，不代表论文的发表时间）