Practical Finite-Time Control of Missiles-A Terminal Sliding Mode Approach

被引：0

作者：

Hou, Mingzhe ^{[1
]}

Wang, Shitao ^{[1
]}

Duan, Guangren ^{[1
]}

Tan, Feng ^{[1
]}

Liu, Yang ^{[1
]}

机构：

[1] Harbin Inst Technol, Harbin 150001, Heilongjiang, Peoples R China

来源：

PROCEEDINGS OF THE 36TH CHINESE CONTROL CONFERENCE (CCC 2017) | 2017年

基金：

中国博士后科学基金; 中国国家自然科学基金; 国家自然科学基金重大项目;

关键词：

missile control; terminal sliding mode; finite-time; robust control; TO-TURN MISSILES; AUTOPILOT DESIGN; NONLINEAR CONTROL; NEURAL NETWORKS; CONTROL-SYSTEMS; FLIGHT CONTROL; AGILE MISSILE; VEHICLE;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error can be driven into a given small neighborhood of the origin in the pre-specified time. The simulation results show the effectiveness of the proposed results.

引用

页码：1238 / 1242

页数：5

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