Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

作     者：Ahmed Awad Wang Haoping 

作者机构：Sino-French International Joint Laboratory of Automatic Control and Signal Processing (LaFCAS) School of AutomationNanjing University of Science & Technology 

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

年 卷 期：2016年第29卷第5期

页      面：1302-1312页

核心收录：

学科分类：08[工学] 081105[工学-导航、制导与控制] 0804[工学-仪器科学与技术] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0811[工学-控制科学与工程] 0801[工学-力学（可授工学、理学学位）] 

基　　金：co-supported by the National Natural Science Foundation of China (No.61304077) International Science & Technology Cooperation Program of China (No.2015DFA01710) the Natural Science Foundation of Jiangsu Province of China (No.BK20130765) the Chinese Ministry of Education Project of Humanities and Social Sciences (No.13YJCZH171) the 11th Jiangsu Province Six Talent Peaks of High Level Talents Project of China (No.2014_ZBZZ_005) the Jiangsu Province Project Blue: Young Academic Leaders Project 

主　　题：Flight control system Global fast terminal slidingmode control Integrated autopilot Nonlinear state observer Skid-to-turn missile 

摘      要：The acceleration autopilot design for skid-to-turn （STT） missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of integrated roll-pitch-yaw autopilot based on global fast terminal sliding mode control （GFTSMC） with a partial state nonlinear observer （PSNLO） for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The proposed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters＇ variation. Furthermore, the environmental conditions＇ dynamics are mod- eled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simulation is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature.