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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This work was supported by National Natural Science Foundation of China (No. 61021002).
Recommended by Associate Editor Yuan-Qing Xia
Hui-Bo Zhou received the B. Sc. degree in College of Mathematics and Systems Science from Shenyang Normal University in 2006. Now she is a teacher in the School of Mathematical Science at Harbin Normal University, and at the same time she is Ph.D. candidate in the Center for Control Theory and Guidance Technology at Harbin Institute of Technology.
Her main research interests include vehicle guidance and control.
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. She is Ph.D. candidate at the School of Astronautics, Harbin Institute of Technology.
Her main research interests include vehicle guidance and control.
Shen-Min Song received the Ph.D. degree in Control Theory and Application from Harbin Institute of Technology in 1996. He carried out postdoctoral research at Tokyo University from 2000 to 2002. He is currently a professor at the School of Astronautics, Harbin Institute of Technology.
His main research interests include spacecraft guidance and control, intelligent control, and nonlinear theory and application.
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Zhou, HB., Song, JH. & Song, SM. Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints. Int. J. Autom. Comput. 15, 218–227 (2018). https://doi.org/10.1007/s11633-016-0953-y
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DOI: https://doi.org/10.1007/s11633-016-0953-y