A study into the effects of Kalman filtered noise in advanced guidance laws of missile navigation
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Authors
Osborn, Adam M.
Subjects
Missile guidance
proportional navigation guidance law
differential geometry guidance law
Kalman filtering
Kalman filtered noise
proportional navigation guidance law
differential geometry guidance law
Kalman filtering
Kalman filtered noise
Advisors
Hutchins, Robert G.
Date of Issue
2014-03
Date
Mar-14
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Advanced missile guidance laws may provide an air-to-air combat tactical advantage by increasing effective missile range. The current standard in missile guidance, proportional navigation (PN), is only optimal against a non-maneuvering target. Differential geometry (DG) guidance is optimized for a maneuvering target. Analysis of the DG guidance equation indicates noise degrades DG performance more than PN. This thesis evaluates the effect of Kalman filtered noise on PN and DG performance. A simplified three degree of freedom (DOF) discrete time version of previous researchers' six DOF continuous time model is generated. Zero mean Gaussian white noise is inserted into simulated line-of-sight angle and range sensor measurements. Discrete time Kalman filters utilize these two noisy simulated sensor measurements to generate all guidance law inputs, including portions of the target state for DG. Simulations with Kalman filtered noise are conducted with both PN and DG guidance laws against maneuvering targets. Kinematic boundaries are used to evaluate a possible tactical advantage of DG over PN guidance in the presence of Kalman filtered noise.
Type
Thesis
Description
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Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.