This document provides a detailed description of the optimal control theory employed to establish the lower bound performance accuracy limits for air-to-surface missile systems. Techniques from optimal control theory are used to separate the contribution of sensor error to mean square miss distance from the total missile system mean square miss distance. The guidance sensor measurements are operated on by a Kalman filter which provides optimal estimates of the measured state variables. Employing these optimal estimates to steer an ideal missile, the lower bound performance accuracy is established. Two general types of guidance measurements are considered; Line of Sight Angle Tracking and Direct Distance Measurement.


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    A Probabilistic Method to Estimate a Missile Target

    Duflos, E. / Vanheeghe, P. / Penel, P. et al. | British Library Conference Proceedings | 1999