Finite-time adaptive sliding mode control for heavyweight airdrop operations  

作　　者：Ri Liu Xiuxia Sun Wenhan Dong Dong Wang 

机构地区：[1]Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi’an 710038, China

出　　处：《Journal of Systems Engineering and Electronics》2017年第2期338-346,共9页系统工程与电子技术（英文版）

基　　金：supported by the National Natural Science Foundation of China(61273141);Aviation Science Foundation of China(20141396012)

摘　　要：This paper investigates the problem of designing a fast convergent sliding mode flight controller of a transport aircraft for heavyweight airdrop operations in the presence of bounded uncertainties without the prior knowledge of the bounds. On the basis of feedback linearization of the aircraft-cargo motion system, a novel integral sliding mode flight control law with gains adaptation is proposed. It contains a nominal control law used to achieve finite-time stabilization performance and a compensated control law used to reject the uncertainties. The switching gains of the compensated control law are tuned using adaptation algorithms, and the knowledge of the bounds of the uncertainties is not required to be known in advance. Meanwhile, the severe chattering of the sliding mode control that caused by high switching gains is effectively reduced. The controller and its performance are evaluated on a transport aircraft performing a maximum load airdrop task in a number of simulation scenarios.This paper investigates the problem of designing a fast convergent sliding mode flight controller of a transport aircraft for heavyweight airdrop operations in the presence of bounded uncertainties without the prior knowledge of the bounds. On the basis of feedback linearization of the aircraft-cargo motion system, a novel integral sliding mode flight control law with gains adaptation is proposed. It contains a nominal control law used to achieve finite-time stabilization performance and a compensated control law used to reject the uncertainties. The switching gains of the compensated control law are tuned using adaptation algorithms, and the knowledge of the bounds of the uncertainties is not required to be known in advance. Meanwhile, the severe chattering of the sliding mode control that caused by high switching gains is effectively reduced. The controller and its performance are evaluated on a transport aircraft performing a maximum load airdrop task in a number of simulation scenarios.

关 键 词：flight control nonlinear system sliding mode control adaptive control finite-time stability 

分 类 号：V249[航空宇航科学与技术—飞行器设计]