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Adaptive terminal guidance law with impact-angle constraint

Published online by Cambridge University Press:  29 November 2017

C. Gao ,
J. Li ,
T. Feng  and
W. Jing
C. Gao*
Affiliation:
Department of Aerospace Engineering, Harbin Institute of Technology, Harbin, People's Republic of China
J. Li*
Affiliation:
Department of Aerospace Engineering, Harbin Institute of Technology, Harbin, People's Republic of China
T. Feng*
Affiliation:
Department of Aerospace Engineering, Harbin Institute of Technology, Harbin, People's Republic of China
W. Jing*
Affiliation:
Department of Aerospace Engineering, Harbin Institute of Technology, Harbin, People's Republic of China
*
corturb@126.com
ljq18@hit.edu.cn
fengtianming@hit.edu.cn
jingwuxing@hit.edu.cn
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Abstract

This paper proposes an adaptive guidance law for attacking a ground target based on motion camouflage strategy. The coefficients of normal and bi-normal feedback guidance law are given according to the relative motion relationship under Frenet frame. Utilizing the coefficients, the motion camouflage proportional guidance law is derived. In order to improve the initial overload characteristic of the missile, an adaptive feedback coefficient is introduced. Then, the adaptive guidance law is applied to a longitudinal plane interception problem with impact-angle constraint. Finally, the validity of this guidance law for air-to-ground missiles is proved by simulations.

Keywords

terminal guidance lawimpact-angle constraintmotion camouflage
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1249 , March 2018 , pp. 369 - 389
Copyright
Copyright © Royal Aeronautical Society 2017 

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References

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