Guidance and control of the Pitch channel of an interceptor missile using neural sliding mode control

Authors

1 Khawaja Nasir Faculty of Mechanics

2 Member of the academic staff of Khwaja Nasiruddin Toosi University of Technology

Abstract

The integrated design method for a missile guidance and control system is such that all the limitations of the subsystems are taken into account during the design in a bid to increase the accuracy and overall performance of the system in the final phase. This will improve efficiency, save time and implementation cost, and as a result, system performance will improve. This article describes the process of designing and simulating the performance of the neural sliding model controller, which was created to guide the missile in a two-dimensional engagement in minimizing the collision time and the miss distance to the target. In the design of the controller, a PID is first considered to evaluate the proposed controller, followed by the design of the neural sliding model controller discussed using neural networks. According to the simulations, it can be shown that the use of this proposed controller and the application of the integrated guidance and control model will reduce the final miss distance and the collision time compared to the PID controller.

Keywords

Main Subjects

References

[1] P. Zarchan (2012), Tactical and strategic missile guidance. American Institute of Aeronautics and Astronautics
[2] Neil F Palumbo, Ross A Blauwkamp, and Justin M Lloyd (2010) Basic principles of homing guidance. Johns Hopkins APL Technical Digest.
[3] Ching-Fang Lin, John Bibel, Ernest J Ohlmeyer, and Steve Malyevac(1998). Optimal design of integrated missile guidance and control. In Al A A and SAE, World Conference, page 5519.
[4] James R Cloutier, Christopher N D’Souza, and Curtis P Mracek(1996). Nonlinear regulation and nonlinear H infinity control via the state-dependent Riccati equation technique: Part 1, theory. In Proceedings of the First International Conference on Nonlinear Problems in Aviation and Aerospace, pages 117-130.
[5] James R Cloutier(1994). Adaptive matched augmented proportional navigation.
[6] Mracek, C. P. , & Cloutier, J. R. (1996). Missile longitudinal autopilot design using the state-dependent Riccati equation method. In Proceedings of the International Conference on Nonlinear Problems in Aviation and Aerospace (pp. 387-396).
[7] P K Menon and Ernest J Ohlmeyer(1999). Integrated design of agile missile guidance and autopilot systems. Control Engineering Practice, 9(10): 1095-1106.
[8] Neil F Palumbo and Todd D Jackson(1999). Integrated missile guidance and control: A state dependent Riccati differential equation approach. In Control Applications, 1999. Proceedings of the 1999 IEEE International Conference on, volume 1, pages 243-248. IEEE.
[9] Menon, P. K. , Sweriduk, G. D. , Ohlmeyer, E. J. , & Malyevac, D. S. (2004). Integrated guidance and control of moving-mass actuated kinetic warheads.  J. Guid., cntrl, Dyn., 27(1), 118-126.
[10] Menon, P. , Vaddi, S. , & Ohlmeyer, E. (2006). Finite-horizon robust integrated guidance-control of a moving-mass actuated kinetic warhead. In AIAA guidance, navigation, and control conference and exhibit (p. 6787).
[11] Hwang, T. W. , & Tahk, M. J. (2006). Integrated backstepping design of missile guidance and control with robust disturbance observer. In 2006 SICE-ICASE International Joint Conference (pp. 4911-4915). IEEE.
[12] Harl, N. , Balakrishnan, S. , & Phillips, C. (2010). Sliding mode integrated missile guidance and control. In AIAA guidance, navigation, and control conference (p. 7741).
[13] Harl, N. , & Balakrishnan, S. N. (2010). Reentry terminal guidance through sliding mode control.  J. guid., control, dyn., 33(1), 186-199.
[14] Wang, X. H. , Tan, C. P. , & Cheng, L. P. (2020). Impact time and angle constrained integrated guidance and control with application to salvo attack.  Asian J. Cntrl., 22(3), 1211-1220.
[15] He, S. , Song, T. , & Lin, D. (2017). Impact angle constrained integrated guidance and control for maneuvering target interception.  J. Guid., Cntrl, Dyn., 40(10), 2653-2661.
 [16] Ma, J. , Guo, H. , Li, P. , & Geng, L. (2013). Adaptive integrated guidance and control design for a missile with input constraints.  IFAC Proceedings Volumes, 46(20), 206-211.
[17] Cross, M. (2020).  Missile Interceptor Integrated Guidance and Control: Single-Loop Higher-Order Sliding Mode Approach. The University of Alabama in Huntsville.
[18] Lee, K. W. , & Singh, S. N. (2018). Longitudinal nonlinear adaptive autopilot design for missiles with control constraint.  Proceedings of the Institution of Mechanical Engineers, Part G: J. Aerospace Eng., 232(9), 1655-1670.
[19] Ma, M. C. , Zhao, K. , & Song, S. M. (2020). Adaptive sliding mode guidance law with prescribed performance for intercepting maneuvering target.  Int. J. Innov. Comput. , Inform. Control, 16(2), 631-648.
[20] Mingzhe, H. , & Guangren, D. (2008). Integrated guidance and control of homing missiles against ground fixed targets.  Chinese J. aeronautics, 21(2), 162-168.
 
[21] Cross, M. A. , & Shtessel, Y. B. (2020). Single-loop integrated guidance and control using high-order sliding-mode control.  Variable-Structure Systems and Sliding-Mode Control: From Theory to Practice, 433-462.
[22] Cross, M. , & Shtessel, Y. B. (2018). Integrated guidance navigation and control using high-order sliding mode control for a missile interceptor. In 2018 AIAA Guidance, Navigation, and Control Conference (p. 1121).
[23] Luan, F. , Na, J. , Huang, Y. , & Gao, G. (2019). Adaptive neural network control for robotic manipulators with guaranteed finite-time convergence.  Neurocomputing, 337, 153-164.
[24] Ogata, K. (2010).  Modern control engineering fifth edition.
Journal of Solid and Fluid Mechanics
Volume 13, Issue 6
January and February 2024
Pages 59-73

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