Backstepping design of missile guidance and control based on adaptive fuzzy sliding mode control

作     者：Ran Maopeng Wang Qing Hou Delong Dong Chaoyang 

作者机构：School of Automation Science and Electrical Engineering Beihang University School of Aeronautic Science and Engineering Beihang University 

基　　金：co-supported by the National Natural Science Foundation of China (No. 61074027) the National Defense Pre-research Foundation of China (No. 9140C48020212HK0101) 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2014年第27卷第3期

页      码：634-642页

摘      要：This paper presents an integrated missile guidance and control law based on adaptive fuzzy sliding mode control. The integrated model is formulated as a block-strict-feedback nonlinear system, in which modeling errors, unmodeled nonlinearities, target maneuvers, etc. are viewed as unknown uncertainties. The adaptive nonlinear control law is designed based on backstepping and sliding mode control techniques. An adaptive fuzzy system is adopted to approximate the coupling nonlinear functions of the system, and for the uncertainties, we utilize an online-adaptive control law to estimate the unknown parameters. The stability analysis of the closed-loop system is also conducted. Simulation results show that, with the application of the adaptive fuzzy sliding mode control, small miss distances and smooth missile trajectories are achieved, and the system is robust against system uncertainties and external disturbances.

主 题 词：Adaptive fuzzy system Backstepping Integrated guidance and control Nonlinear Sliding mode control 

学科分类：08[工学] 081105[081105] 0804[工学-材料学] 0811[工学-水利类] 

核心收录：

D　O　I：10.1016/j.cja.2014.04.007

馆 藏 号：203307685...