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.
Hutchins, Robert G.
Naval Postgraduate School
Master Of Science In Electrical Engineering
Electrical And Computer Engineering
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