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Guidance and Control Synthesis for a Short-range Homing Surface-to-air Missile

Agus Budiyono


This paper presents a high-performance and simple guidance method for a short-range missile. Missile control systems are designed along the estimated flight envelope of the missile based on classical control theory. The LTI models are obtained by linearizing missile nonlinear model at specific operating points. The governing equations of motion are accurately modeled by taking into account the effect of the mass rate and the center of gravity shift. The result of control synthesis is a velocity-scheduled gain in the form of look-up table. Proportional navigation law is considered as the guidance method. Various engagement scenarios are studied and the missile  performance is evaluated based on simulation.

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. Ki-Seok Kim, Youdan Kim, Design of generalized conceptual guidance law using aim angle, Control Engineering Practice 12 (2004) 291–298

. P.K. Menona and E.J. Ohlmeyer, Integrated design of agile missile guidance and autopilot systems, Control Engineering Practice 9 (2001) 1095–1106

. Gerard Leng, Missile guidance algorithm design using inverse kinematics and fuzzy logic, Fuzzy Sets and Systems 79 (1996) 287-295

. V. Rajasekhar and a. G. Sreenatha, Fuzzy logic implementation of proportional navigation guidance, Acta Astronautica Vol. 46, No. 1, pp. 17-24, 2000

. Y. Z. Elhalwagy and M. Tarbouchi, Fuzzy logic sliding mode control for command guidance law design, ISA Transactions 43 (2004) 231–242

. Hungu Lee et al. , Missile guidance using neural networks, Control Eng. Practice, Vol. 5, No. 6, pp. 753-762, 1997

. Han-Lim Choi, Min-Jea Tahk and Hyochoong Bang, Neural network guidance based on pursuit-evasion games with enhanced performance,

Control Engineering Practice 14 (2006) 735–742

. Eun-Jung Song and Min-Jea Tahk, Real-time midcourse missile guidance robust against launch conditions, Control Engineering Practice 7

(1999) 507-515

. Chun-Liang Lin and Rei-Min Lai, Parameter design for a guidance and control system using genetic approach, Aerosp. Sci. Technol. 5 (2001)


. Mazen Alamir, Nonlinear Receding horizon sub-optimal guidance law for the minimum interception time problem, Control Engineering Practice

(2001) 107-116

. Mario Innocenti, Nonlinear Guidance techniques for agile missiles, Control Engineering Practice 9 (2001) 1131–1144

. Harapan Rachman, Design Synthesis of Surface-to-air Missile Guidance and Control System –A case study of Hypothetical Missile Based on LAPAN RKX-10C18, ITB Undergraduate Thesis, Bandung, 2008.

. George M. Siouris, Missile Guidance and Control System, Springer-Verlag New York, Ohio, 2003.

. W.A. Kaufmann, Flight Control Design Issues in Bank-To-Turn Missiles, AGARD Lecture Series No. 173, California, 1990.

. E.J. Ohlmeyer, Application of Optimal Estimation and Control Concepts to a Bank-To-Turn Missile, AGARD Conference Proceedings No.411, Virginia, 1986.

. Ulrich Hartmann, Midcourse Guidance Techniques for Advanced Tactical Missile Systems, AGARD Lecture Series No. 173, Germany, 1990.

. Frederick W. Riedel, Bank-To-Turn Technology Survey for Homing Missiles, NASA Contractor Report 3325, Maryland, 1980.

. Thomas J. Urban, Synthesis of Missile Autopilots Robust to the Presence of Parametric Variations, MIT Master Thesis, Massachusetts, 1991.

. John H. Blakelock, Automatic Control of Aircraft and Missiles, John Wiley & Sons, 1965.



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