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Biased optimal guidance law with specified velocity rendezvous angle constraint

Published online by Cambridge University Press:  27 January 2016

X. Xu  and
Y. Liang
X. Xu*
Affiliation:
Information Engineering School, Henan University of Science and Technology, Luoyang, China China Airborne Missile Academy, Luoyang, China Department of Automatic Control, Xi’an Jiao Tong University, Xi’an, China
Y. Liang
Affiliation:
Information Engineering School, Henan University of Science and Technology, Luoyang, China
*
xuxingyuan2003@126.com
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Abstract

In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1220 , October 2015 , pp. 1287 - 1299
Copyright
Copyright © Royal Aeronautical Society 2015

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