An Analysis of Optimal Command Guidance vs. Optimal Semi-Active Homing Missile Guidance

An optimal command guidance system and an optimal semi-active homing missile guidance system are analyzed using adjoint theory. Both systems contain a Kalman filter to estimate the states and an optimal full state guidance law to generate the acceleration commands. The dynamics and error inputs of b...

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Bibliographic Details

Published in:	1986 American Control Conference pp. 1103 - 1111
Main Authors:	Nesline, F. William, Nesline, Mark L.
Format:	Conference Proceeding
Language:	English
Published:	IEEE 01.06.1986
Subjects:	Acceleration Apertures Costs Missiles Noise measurement Radar measurements Radar tracking State estimation Target tracking Transmitters
Online Access:	Get full text
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