Swamy, KN and Sarma, IG (1989) Performance Of APN Guidance Law In A Two Dimensional Aerial Engagement Scenario. In: IEEE 1989 National Aerospace and Electronics Conference, 1989. NAECON 1989, 22-26 May, Dayton,OH, Vol.1, 209-215.
In the available literature, the main advantage claimed for APN is that it demands a progressively decreasing missile acceleration in the constant target maneuver situation, as opposed to an increasing missile acceleration for the more conventional PN guidance. This inference is mainly based on studies with one dimensional models. The present study, based on a two dimensional model, not only incorporates a more realistic target maneuver, but also considers the effect of target glint characterized by correlated noise. The missile acceleration and the miss-distance induced by target maneuver and glint are the two features of performance investigated in this study. In the deterministic study, with target maneuver initiation occuring at various points in time, the acceleration profiles resemble the ones obtained from a linear quadratic tracking formulation of the guidance problem. The results indicate that there is a considerable improvement in the miss distance performance over PN, for maneuvers which are initiated when the relative seperation is small.
|Item Type:||Conference Paper|
|Additional Information:||Copyright 1989 IEEE. Personal use of this material is permitted. However, permission to reprint/republish this material for advertising or promotional purposes or for creating new collective works for resale or redistribution to servers or lists, or to reuse any copyrighted component of this work in other works must be obtained from the IEEE.|
|Department/Centre:||Division of Electrical Sciences > Computer Science & Automation (Formerly, School of Automation)|
|Date Deposited:||01 Jun 2006|
|Last Modified:||19 Sep 2010 04:28|
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