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International Journal of Aerospace Engineering
Volume 2018, Article ID 3968242, 10 pages
Research Article

New Integrated Guidance and Control of Homing Missiles with an Impact Angle against a Ground Target

1Institute of Precision Guidance and Control, Northwestern Polytechnical University, Shaanxi 710072, China
2Beijing Aerospace Technology Institute, Beijing 100074, China

Correspondence should be addressed to Jianguo Guo; nc.ude.upwn@ougnaijoug

Received 4 February 2018; Revised 25 May 2018; Accepted 9 July 2018; Published 5 August 2018

Academic Editor: Giovanni Palmerini

Copyright © 2018 Shengjiang Yang 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.


A new integrated guidance and control (IGC) law is investigated for a homing missile with an impact angle against a ground target. Firstly, a control-oriented model with impact angle error of the IGC system in the pitch plane is formulated by linear coordinate transformation according to the motion kinematics and missile dynamics model. Secondly, an IGC law is proposed to satisfy the impact angle constraint and to improve the rapidity of the guidance and control system by combining the sliding mode control method and nonlinear extended disturbance observer technique. Thirdly, stability of the closed-loop guidance and control system is proven based on the Lyapunov stability theory, and the relationship between the accuracy of the impact angle and the estimate errors of nonlinear disturbances is derived from stability of the sliding mode. Finally, simulation results confirm that the proposed IGC law can improve the performance of the missile guidance and control system against a ground target.