Abstract
Most modern missiles implement some variant of proportional navigation (PN) guidance law. In order to implement this form of navigation, the missile has to measure line of sight (LOS) rate. Devices capable to measure LOS rate are referred to as the seekers. This article aims to present analysis of a missile seeker mathematical models with purpose to obtain LOS rate estimation used for implementation of PN in three dimensions. This paper includes MATLAB simulations of developed seeker with 6-DOF nonlinear missile mathematical model and autopilot presented in earlier works by the authors.
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