H∞ Design of Missile Control Systems for PN Guidance Laws

S. Park, J. Song, S.-H. Song, J.-W. Hong, and I.-J. Ha (Korea)

Keywords

H∞ control, Missile systems, Proportional Navigation Guidance, Linear matrix inequality

Abstract

This note presents a design method for missile systems with linear time-invariant autopilot systems and propor tional navigation guidance(PNG) laws. In the design of missile control systems, the nonlinear planar pursuit situ ation is fully considered and using the well-known small gain theorem, a sufficient condition is obtained which guar antees a desired final miss distance and L2 stability of the closed-loop system. H∞ and LMI approach are employed to design a linear missile control system satisfying the gen erated sufficient condition.

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• DOI:
• From Proceeding (536) Intelligent Systems and Control - 2006

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