Abstract
This paper presents a performance analysis of missile control systems considering nonlinear pursuit dynamics and proportional navigation guidance (PNG) laws. In order to analyze the system stability, missile dynamics are simplified as a linearized model which is often considered in missile autopilot design and the well-known $${{{H}}}_{\boldsymbol{\infty }}$$ approach is employed. A sufficient condition guaranteeing miss distance and the closed loop stability is proposed. The provided condition of missile system stability can be numerically easily verified by a linear matrix inequality (LMI).
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