点击次数：

所属单位：自动化学院

发表刊物：Guid. Navig. Control Conf.

摘要：In this paper, the design of a constrained adaptive backstepping flight control law based on prescribed performance bound is discussed for a flying wing aircraft longitudinal control with actuator stuckness or failures, saturation nonlinearity of actuators considered. By prescribed performance, the tracking errors are restrained within prespecified envelope curves so that the maximum overshoot and convergence rate are within designated values. Faults of actuators are handled by online update laws which can estimate the fault parameters, thus reducing the effect of faults on control accuracy. Second-order low-pass command filters are introduced to limit the deflection angles of elevators and throttle levels, therefore avoiding saturation of actuators and the complex derivative computation in the backstepping process. In addition, control allocation strategy is designed to reduce the effect of faults on the lateral motion. The stability of the closed-loop system and the convergence of parameters are proved. Computer simulation shows that the closed-loop system is stable, the control law tracks reference trajectories well, and the actuators are within their physical limits in the presence of actuator faults. © 2017, American Institute of Aeronautics and Astronautics. All rights reserved.

是否译文：否

发表时间：2017-01-01

合写作者：Shuang, Weifang,Wu, Xue,van Kampen, Erik-Jan,Chu, Qiping

通讯作者：张绍杰