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

Agus Budiyono

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 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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References


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DOI: http://dx.doi.org/10.21535%2FProICIUS.2009.v5.563

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