Abstract
The dominant effects of small seeker scale-factor uncertainty on optimal guidance are determined under certain limitations for a homing missile that uses a strapdown seeker to intercept a randomly maneuvering target. These effects are a change in a feedback gain and the addition of a rapidly fluctuating acceleration component. The latter mainly serves to refine the scale-factor estimate, even though uncertainty in this parameter is not explicitly penalized in the performance criterion for which the guidance law is optimized. This criterion is a standard quadratic one, which essentially maximizes a weighted average of the missile's terminal speed and its probability of intercept, and for which proportional navigation would be the optimal guidance law in the absence of scale-factor uncertainty. The numerical significance of these results is shown for a specific example.
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