Robust terminal guidance law design for missiles against maneuvering targets

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7 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)198-207
Number of pages10
JournalAerospace Science and Technology
Volume54
DOIs
Publication statusPublished - 2016 Jul 1

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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