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.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
References
M. Kim and K. V. Grider, “Terminal guidance for impact attitude angle constrained flight trajectories,” IEEE Transactions on Aerospace and Electronic Systems, vol. 9, no. 6, pp. 852–859, 1973.
J. I. Lee, I. S. Jeon, and M. J. Tahk, “Guidance law to control impact time and angle,” IEEE Transactions on Aerospace and Electronic Systems, vol. 43, no. 1, pp. 301–310, 2007.
N. Harl and S. N. Balakrishnan, “Impact time and angle guidance with sliding mode control,” IEEE Transactions on Control Systems Technology, vol. 20, no. 6, pp. 1436–1449, 2012.
T. Shima, “Intercept-angle guidance,” Journal of Guidance, Control, and Dynamics, vol. 34, no. 2, pp. 484–492, 2011.
Y. Zhang, M. Sun, and Z. Chen, “Finite-time convergent guidance law with impact angle constraint based on sliding-mode control,” Nonlinear Dynamics, vol. 70, no. 1, pp. 619–625, 2012.
S. R. Kumar, S. Rao, and D. Ghose, “Sliding-mode guidance and control for all-aspect interceptors with terminal angle constraints,” Journal of Guidance, Control, and Dynamics, vol. 35, no. 4, pp. 1230–1246, 2012.
S. Rao and D. Ghose, “Terminal impact angle constrained guidance laws using variable structure systems theory,” IEEE Transactions on Control Systems Technology, vol. 21, no. 6, pp. 2350–2359, 2013.
Z. Zhang, S. Li, and S. Luo, “Composite guidance laws based on sliding mode control with impact angle constraint and autopilot lag,” Transactions of the Institute of Measurement and Control, vol. 35, no. 6, pp. 764–776, 2013.
Z. Zhang, S. Li, and S. Luo, “Terminal guidance laws of missile based on ISMC and NDOB with impact angle constraint,” Aerospace Science and Technology, vol. 31, no. 1, pp. 30–41, 2013.
P. P. Qu. and D. Zhou, “A dimension reduction observerbased guidance law accounting for dynamics of missile autopilot,” Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 227, no. 7, pp. 1114–1121, 2012.
S. Sun, M. H. Zhang, and D. Zhou, “Sliding mode guidance law with autopilot lag for terminal angle constrained trajectories,” Journal of Astrinautics, vol. 34, no. 1, pp. 69–78, 2013.
S. Sun, D. Zhou, and W. T. Hou, “A guidance law with finite time convergence accounting for autopilot lag,” Aerospace Science and Technology, vol. 25, no. 1, pp. 132–137, 2013.
Y. B. Shtessel, I. A. Shkolnikov, and A. Levant, “Smooth second-order sliding modes: Missile guidance application,” Automatica, vol. 43, no. 8, pp. 1470–1476, 2007.
D. Zhou, S. Sun, and K. L. Teo, “Guidance laws with finite time convergence,” Journal of Guidance, Control, and Dynamics, vol. 32, no. 6, pp. 1838–1846, 2009.
K. M. Ma, H. K. Khalil, and Y. Yao, “Guidance law implementation with performance recovery using an extended high-gain observer,” Aerospace Science and Technology, vol. 24, no. 1, pp. 177–186, 2013.
Y. G. Hong, “Finite-time stabilization and stabilizability of a class of controllable systems,” Systems & Control Letters, vol. 46, no. 4, pp. 231–236, 2002.
H. K. Khalil and J. Grizzle, Nonlinear Systems, vol. 3, Prentice hall, Upper Saddle River, 2002.
A. Levant, “Non-homogeneous finite-time-convergent differentiator,” Proceedings of the 48th IEEE Conference on Decision and Control held jointly with the 28th Chinese Control Conference, pp. 8399–8404, 2009.
P. Li, X. P. Feng, and J. J. Meng, “Non-homogeneous disturbance observer-based second order sliding mode control for a tailless aircraft,” Proc. of Chinese Automation Congress (CAC), pp. 120–125, 2013.
Author information
Authors and Affiliations
Corresponding author
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.
Rights and permissions
About this article
Cite this article
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
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s12555-015-0186-9