Robust terminal guidance law design for missiles against maneuvering targets

被引:10
作者
Chen, Yung-Yue [1 ]
机构
[1] Natl Cheng Kung Univ, Dept Syst & Navel Mechatron Engn, 1 Univ Rd, Tainan 701, Taiwan
关键词
Terminal guidance law; Missiles; Feedback linearization control; Optimal robust control; Maneuvering targets; Terminal phase;
D O I
10.1016/j.ast.2016.03.028
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
This paper describes an application of a new terminal guidance law for missiles against maneuvering targets in three-dimensional (3D) environment during the terminal phase. This novel approach is suitable for practical implementation of the guidance law under the circumstance of a guided missile against a maneuvering target. The design procedure is divided into two steps. First, a feedback linearization control scheme is designed to approximately achieve desired tracking of the uncertain missile-target system. Next, a combined optimal robust control scheme is employed to minimize the worst-case effect arising from external disturbances (target's maneuvers) in improving the tracking performance. Simulation examples are presented to illustrate engagement performance of the proposed approach. (C) 2016 Elsevier Masson SAS. All rights reserved.
引用
收藏
页码:198 / 207
页数:10
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