Accession Number:

ADA220419

Title:

A Passive Homing Missile Guidance Law Based on New Target Maneuver Models

Descriptive Note:

Interim rept.

Corporate Author:

TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS

Report Date:

1990-01-30

Pagination or Media Count:

13.0

Abstract:

A new stochastic dynamic target model is proposed on the assumption that certain targets execute evasive maneuvers orthogonal to their velocity vector. Along with this new acceleration dynamic model, the orthogonality is also enforced by the addition of a fictitious auxilliary measurement. The target states are estimated by the modified gain extended Kalman filter, and the angular target maneuver rate is constructed on-line. A guidance law that minimizes a quadratic performance index subject to the assumed stochastic engagement dynamics that includes state dependent noise is derived. This guidance law is determined in closed form where the gains are an explicit function of the estimated target maneuver rate as well as time to go. The numerical simulation for the two-dimensional angle-only measurement case indicates that the proposed target model leads to significant improvement in the estimation of the target states. Furthermore, the effect on terminal miss distance using this new guidance scheme is given and compared to the Gauss- Markov model. Keywords Guided missile targets Kalman filter Target estimation Linear quadratic guidance law Guidance laws.

Subject Categories:

  • Navigation and Guidance

Distribution Statement:

APPROVED FOR PUBLIC RELEASE