A FULL MISSILE HOMING SYSTEM DESIGN BASED ON PROPORTIONAL NAVIGATION GUIDANCE LAW AND ELECTRO-OPTICAL TRACKING SYSTEM
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Abstract
Generally, the homing systems are majorly constructing from three components: the guidance law, the target tracking system, and the missile flight control system. Therefore, in this paper, we construct our homing system from the following components: the proportional navigation guidance law which is considered as the guidance scheme for most homing missile systems, the
electro-optical tracking system, and a tail controlled missile. And subsequently complete mathematical derivations and the demand transfer function formulations of all these three components have been introduced. The proposed homing system is capable to pursuit and hit any target just by specifying the required missile flight time. A SIMULINK software program has been built mainly from four subsystems to simulate the operation of this homing system, and the simulation results show clearly the efficient performance of the proposed homing system under any probable disturbance
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Alamir M. (2001). Nonlinear receding horizon sub-optimal guidance law for the minimum Interception time problem. Control Engineering Practice, 9, 107–116.
Babu K. R., Sarma I. G., & Swamy K. N. (1994). Two robust homing missile guidance laws based on sliding mode control theory. IEEE National Aerospace and Electronics Conference (pp. 540–547). Dayton, OH, USA.
Ben-Asher J., and Ben Yaesh I. (1991), “Advance in Missile Guidance Theory”, Vol.180; 1998.
Lin, C. Modern navigation, guidance, and control processing (pp. 353–359). Upper Saddle River, NJ: Prentice-Hall Ben-Asher J. & Yaesh I. (1997). Optimal guidance with reduced sensitivity to time-to-go estimation errors. Journal of Guidance, Control, and Dynamics, 20(1), 158–163.
Cho H., Ryoo C., & Tahk M. (1999). Implementation of optimal guidance laws using predicted missile velocity profiles. Journal of Guidance, Control, and Dynamics, 22(4), 579–588.
Finny and Thomas. (1989). "Calculus" Vol. published by Addison-Wesley Company, Inc.
Gurfil P. (2001). Synthesis of zero miss distance missile guidance via solution of an optimal tuning problem. Control Engineering Practice, 9, 1117–1130
Gurfil P, (2002), Zero-miss-distance guidance law based on line-of-sight rate measurement only 0967-0661/02/$ - see front matter r 2002 Elsevier Science Ltd.(pp. 820-832)
Ha I., Hur J., Ko M., & Song T. (1990). Performance analysis of PNG laws for randomly maneuvering targets. IEEE Transactions on Aerospace and Electronic Systems, 26(5), 713–719.
Lin, J., & Mon, Y. (2001). Fuzzy logic-based CLOS guidance law353–359). Upper Saddle River, NJ: Prentice-Hall. design. IEEE Transactions on Aerospace and Electronic Systems, 37(2), 719 – 727.
Moon J., Kim K., & Kim Y. (2001). Design of missile guidance law via variable structure control. Journal of Guidance, Control, and Dynamics, 24(4), 659–664.
Nesline F. W., & Nesline M. L. (1984). Homing missile autopilot response sensitivity to stability derivative variations. In Proceedings of the 23rd IEEE conference on decision and control, Las Vegas, December 1984.
Rajasekhar V., & Sreenatha A. G. (2000). Fuzzy logic implementation of proportional navigation guidance. Acta Astronautica, 46(1), 17–24.
Song J., & Ha I. (1994). A Lyapunov-like approach to performance analysis of 3-dimensional pure PNG laws. IEEE Transactions on Aerospace and Electronic Systems, 30(1), 238–248
Shinar J., & Steinberg D. (1977). Analysis of optimal evasive maneuvers based on a linearized twodimensional kinematics model. Journal of Aircraft, 14(8), 795–802.
Shneydor N. A. (1998). Missile guidance and pursuit: Kinematics, dynamics and control. Horwood Publishing, Chapter 5, (pp. 125–148)
Zarchan P. (1990) “Tactical and Strategic Missile Guidance”, Vol.124