Proportional Guidance and CDM Control Synthesis for a Short-Range Homing Surface-to-Air Missile
Publication: Journal of Aerospace Engineering
Volume 25, Issue 2
Abstract
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 coefficient diagram method. The linear time invariant (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. A novel algebraic approach called coefficient diagram method (CDM) is used to design normal acceleration and roll angle control systems. The proportional navigation law is considered as the guidance law. One case of engagement scenarios is studied and the missile performance is evaluated. The robustness of the proposed controller is tested against parameter uncertainties and wind disturbance.
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References
Alamir, M. (2001). “Nonlinear Receding horizon sub-optimal guidance law for the minimum interception time problem.” Control Eng. Pract.COEPEL, 9, 107–116.
Blakelock, J. (1965). “Automatic control of aircraft and missiles,” John Wiley & Sons, Hoboken, NJ.
Budiyono, A., and Rachman, H. (2009). “Guidance and control synthesis for a short-range homing surface-to-air missile.” Proc. Int. Sym. on Intelligent Unmanned Systems (ISIUS), Konkuk Univ., Korea.
Choi, H-L., Tahk, M-J., and Bang, H. (2006). “Neural network guidance based on pursuit-evasion games with enhanced performance.” Control Eng. Pract.COEPEL, 14, 735–742.
Elhalwagy, Y. Z., and Tarbouchi, M. (2004). “Fuzzy logic sliding mode control for command guidance law design.” ISA Trans.ISATAZ, 43(2), 231–242.
Hartmann, U. (1990). “Midcourse guidance techniques for advanced tactical missile systems.” AGARD Lecture Series No. 173, North Atlantic Treaty Organization (NATO), Brussels, Belgium.
Innocenti, M. (2001). “Nonlinear guidance techniques for agile missiles.” Control Eng. Pract.COEPEL, 9(10), 1131–1144.
Kaufmann, W. A. (1990). “Flight control design issues in bank-to-turn missiles.” AGARD Lecture Series No. 173, North Atlantic Treaty Organization (NATO), Brussels, Belgium.
Kim, K-S., and Kim, Y. (2004). “Design of generalized conceptual guidance law using aim angle.” Control Eng. Pract.COEPEL, 12(3), 291–298.
Lee, H., Lee, Y-I., Song, E-J., Sun, B-C., and Tahk, M-J. (1997). “Missile guidance using neural networks.” Control Eng. Pract.COEPEL, 5(6), 753–762.
Leng, G. (1996). “Missile guidance algorithm design using inverse kinematics and fuzzy logic.” Fuzzy Sets Syst., 79(3), 287–295.FSSYD8
Lin, C-L., and Lai, R-M. (2001). “Parameter designs for a guidance and control system using genetic approach.” Aerosp. Sci. Technol., 5(6), 425–434.
Manabe, S. (1998). “Coefficient diagram method.” Proc., 14th IFAC Symposium on Automatic Control in Aerospace, IFAC.
Manabe, S. (2001). “Application of coefficient diagram method to dual-control surface missile.” Proc., 15th IFAC Symposium on Automatic Control in Aerospace, IFAC International Federation of Automatic Control (IFAC), Austria.
Menona, P. K., and Ohlmeyer, E. J. (2001). “Integrated design of agile missile guidance and autopilot systems.” Control Eng. Pract.COEPEL, 9(10), 1095–1106.
Ohlmeyer, E. J. (1986). “Application of optimal estimation and control concepts to a bank-to-turn missile.” AGARD Conference Proceedings No. 411, North Atlantic Treaty Organization (NATO), Brussels, Belgium.
Pradana, W. A., Joelianto, E., Budiyono, A., and Adiprawita, W. (2011). “Robust MIMO integral-backstepping PID controller for hovering control of unmanned model helicopter.” J. Aerosp. Eng.JAEEEZ, 24(4), 454–462.
Rachman, H. (2008). “Design synthesis of surface-to-air missile guidance and control system –a case study of hypothetical missile based on LAPAN RKX-10C18.” B.S. thesis, Institut Teknologi Bandung (ITB), Bandung, Indonesia.
Rajasekhar, V., and Sreenatha, A. G. (2000). “Fuzzy logic implementation of proportional navigation guidance.” Acta Astronaut.AASTCF, 46(1), 17–24.
Riedel, F. (1980). “Bank-to-turn technology survey for homing missiles.” NASA Contractor Report 3325, Scientific and Technical Information Branch, Washington, DC, Maryland.
Siouris, G. (2003). Missile guidance and control system, Springer-Verlag, New York.
Song, E-J. and Tahk, M-J. (1999). “Real-time midcourse missile guidance robust against launch conditions.” Control Eng. Pract.COEPEL, 7(4), 507–515.
Urban, T., (1991). “Synthesis of missile autopilots robust to the presence of parametric variations.” Master thesis, MIT, Cambridge, MA.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 25 • Issue 2 • April 2012
Pages: 168 - 177
Copyright
© 2012. American Society of Civil Engineers.
History
Received: Oct 1, 2009
Accepted: Jan 12, 2011
Published online: Jan 15, 2011
Published in print: Apr 1, 2012
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