A New Proportional - Pursuit Coupled Guidance Law with Actuator Delay Compensation

Authors: Chien-Chun Kung, Feng-Lung Chiang, Kuei-Yi Chen, Hsien-Wen Wei, Ming-Yi Huang, Cai-Ming Huang, Sheng-Kai Wang

Abstract:

The aim of this paper is to present a new three-dimensional proportional-pursuit coupled (PP) guidance law to track highly maneuverable aircraft. Utilizing a 3-D polar coordinate frame, the PP guidance law is formed by collecting proportional navigation guidance in Z-R plane and pursuit guidance in X-Y plane. Feedback linearization control method to solve the guidance accelerations is used to implement PP guidance. In order to compensate the actuator time delay, the time delay compensated version of PP guidance law (CPP) was derived and proved the effectiveness of modifying the problem of high acceleration in the final phase of pursuit guidance and improving the weak robustness of proportional navigation. The simulation results for intercepting Max G turn situation show that the proposed proportional-pursuit coupled guidance law guidance law with actuator delay compensation (CPP) possesses satisfactory robustness and performance.

Keywords: Feedback linearization control, time delay, guidance law, robustness, proportional navigation guidance, pursuit guidance.

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1085469

References:

[1] Richard DeMeis, Fire-and-Forget Tactical Missiles, Aerospace America, 22(8), August 1984, pp. 62-65.
[2] Tian-Guang Jhang, New Combat Techniques for Fighters, Aerospace science Techniques, 2002, pp. 27-29.
[3] John Harris, Nathan Slegers, Performance of a Fire-and-Forget Anti-Tank Missile with a Damaged Wing, Mathematical and Computer Modelling, 50(1-2), July 2009, pp. 292-305.
[4] J. V. Breakwell, A. Davidovitz, J. Shinar, Two-Target Game Model of an Air Combat with Fire-and-Forget All-Aspect Missiles, Jornal of Optimization Theory and Applications, 63(2), November 1989, pp. 133-165.
[5] Fen Wu, Andy Packard, Gary Balas, Systematic Gain-Scheduling Control Design: A Missile Autopilot Example, Asian Journal of Control, 4(3), September 2002, pp. 341-347.
[6] F. Imado and S. Miwa, Fighter Evasive Boundaries against Missiles, Computers & Mathematics with Applications, 18(1-3), 1989, pp. 1-14.
[7] F. Imado, Some Aspects of a Realistic Three-Dimensional Pursuit-Evasion Game, Journal of Guidance, Control, and Dynamics, 16(2), March-April 1993, pp. 1-14.
[8] Ciann-Dong Yang, Fei-Bin Hsiao, and Fang-Bo Yeh, Generalized Guidance Law for Homing Missiles, IEEE Transactions on Aerospace and Electronic Systems, 25(2), 1989, pp. 197-212.
[9] Fu-KuangYeh, Design of Nonlinear Terminal Guidance/Autopilot Controller for Missiles with Pulse Type Input Devices, Asian Journal of Control, 12(3), May 2010, pp. 399-412.
[10] George M. Siouris, Missile Guidance and Control Systems, first ed., Springer Press, New York, 2004.
[11] Erik Berglund, Guidance and Control Technology, Technologies for Future Precision Strike Missile Systems, June 2001, pp. 3-1 ¶Çé▒ 3-15.
[12] Chih-Min Lin, Chun-Fei Hsu, Shing-Kuo Chang, Rong-Jong Wai, Guidance Law Evaluation for Missile Guidance Systems, Asian Journal of Control, 2(4), December 2000, pp. 243-250.
[13] Chao-Yong Li, Wu-Xing Jing, Geometric Approach to Capture Analysis of PN Guidance Law, Aerospace Science and Technology, 12, 2008, pp. 177-183.
[14] Chun-Liang Lin, Rei-Min Lai, Parameter Design for a Guidance and Control System Using Genetic Approach, Aerospace Science and Technology, 5, 2001, pp. 425-434.
[15] Lu-Ping Tsao, Ching-Jar Ji, and Ching-Show Lin, A Study on the Evasive Tactics of a Fighter against a Missile, Transactions of the Aeronautics and Astronautics Society of the Republic of China, 29(40), 1997, pp. 329-335.