Abstract
This paper presents a control structure that integrates guidance and control loops for tail-controlled missile systems. Motivated by the fact that common tail-controlled missiles involve non-minimum phase dynamics, the proposed controller is designed to aim at preventing the zero dynamics from diverging as well as achieving homing against the intended target. Since the derived controller has a similar structure of the conventional three-loop topology that has been utilized for various tail-controlled flight systems, it is also expected that the proposed method can easily be applicable to the actual system from a practical point of view.
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