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Design of sliding mode guidance law with dynamic delay and impact angle constraint

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  • Control Theory and Applications
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Abstract

A sliding mode guidance law with dynamic delay and impact angle constraints is designed for the relative motion between the missile and the target in the intercepting plane. First of all, the missile’s first order dynamic delay is involved into the system model to design the guidance law based on sliding mode variable dynamic method. Secondly, the target’s maneuvering is taken as the system disturbance, and a non-homogeneous disturbance observer is applied to estimate such maneuvering in finite time rapidly, which, through dynamic compensation, realizes the missiles precision attack to targets of different maneuvering at a desired line-of-sight (LOS) angle. Finally, numerical simulations are performed to demonstrate the effectiveness of the designed guidance law.

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Author information

Authors and Affiliations

  1. School of Mathematical Sciences, Harbin Normal University, Harbin, 150009, China

    Hui-Bo Zhou

  2. Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Yi Kuang Street, Nan Gang District, Harbin, 150001, China

    Shen-Min Song & Jun-Hong Song

Authors
  1. Hui-Bo Zhou
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  2. Shen-Min Song
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  3. Jun-Hong Song
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Corresponding author

Correspondence to Hui-Bo Zhou.

Additional information

Recommended by Associate Editor Juhoon Back under the direction of Editor Myo Taeg Lim. This work supported by the National Natural Science Foundation for Innovation Group of China( No. 61021002).

Hui-Bo Zhou was born in Heilongjiang, China in 1977. She received her M.S. degree in College of Mathematics and Systems Science from Shenyang Normal University in 2006 and Ph.D. degree in Control Theory and Application from Harbin Institute of Technology in 2015. Now she is an associate professor at the School of Mathematical Science in Harbin Normal University.Her main research interests include vehicle guidance and control.

Shen-Min Song received his 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 in the School of Astronautics at Harbin Institute of Technology. His main research interests include spacecraft guidance and control, intelligent control, and nonlinear theory and application.

Jun-Hong Song was born in Shandong, China in 1984. She received her 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 pursuing her Ph.D. degree at the School of Astronautics, Harbin Institute of Technology. Her main research interests include vehicle guidance and control.

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Zhou, HB., Song, SM. & Song, JH. Design of sliding mode guidance law with dynamic delay and impact angle constraint. Int. J. Control Autom. Syst. 15, 239–247 (2017). https://doi.org/10.1007/s12555-015-0186-9

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  • DOI: https://doi.org/10.1007/s12555-015-0186-9

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