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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© 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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