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Discrete Dynamics in Nature and Society
Volume 2016, Article ID 6219609, 10 pages
http://dx.doi.org/10.1155/2016/6219609
Research Article

Guidance Law and Neural Control for Hypersonic Missile to Track Targets

School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China

Received 17 October 2015; Revised 22 December 2015; Accepted 14 January 2016

Academic Editor: Filippo Cacace

Copyright © 2016 Wenxing Fu et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.