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International Journal of Automation and Computing 2018, Vol. 15 Issue (2) :218-227    DOI: 10.1007/s11633-016-0953-y
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Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints
Hui-Bo Zhou1,2, Jun-Hong Song2, Shen-Min Song2
1 School of Mathematical Sciences, Harbin Normal University, Harbin 150009, China;
2 Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin 150001, China
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Abstract In order to improve the precision of guidance for the missile intercepting maneuvering targets, this paper proposes a sliding mode guidance law with impact angle constraints based on the equation of the relative motion of the missile and the target in a 2D plane. Two finite-time convergent guidance laws are proposed based on the nonsingular terminal sliding mode, while, two exponential convergent guidance laws involving dynamic delay are developed through applying the higher-order nonsingular terminal sliding mode. The simulations denote that, in all the four scenarios of the target s maneuvering, the guidance laws are able to inhibit the chattering phenomenon of the sliding modes effectively; and from an expected aspect angle, the missiles could attack the targets with high precision and fast speed.
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KeywordsAutopilot   impact angle   nonsingular terminal sliding mode   finite-time convergent   guidance     
Received: 2014-05-29; Revised: 2015-04-08; published: 2015-04-08

This work was supported by National Natural Science Foundation of China (No. 61021002).

Corresponding Authors: Hui-Bo Zhou     Email: zhouhb0306@sina.com
About author: Hui-Bo Zhou received the B. Sc. degree in College of Mathematics and Systems Science from Shenyang Normal University in 2006. E-mail:zhouhb0306@sina.com;Jun-Hong Song received the B.S. degree in Applied Mathematics from Liaocheng University in 2010 and M.S. degree in Applied Mathematics from Harbin Institute of Technology in 2012. E-mail:songjunhong111@163.com;Shen-Min Song received the Ph.D. degree in Control Theory and Application from Harbin Institute of Technology in 1996. E-mail:songshenmin@hit.edu.cn
Cite this article:   
Hui-Bo Zhou, Jun-Hong Song, Shen-Min Song. Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints[J]. International Journal of Automation and Computing , vol. 15, no. 2, pp. 218-227, 2018.
http://www.ijac.net/EN/10.1007/s11633-016-0953-y      或     http://www.ijac.net/EN/Y2018/V15/I2/218
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