Date of Award

12-1992

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Electrical and Computer Engineering

First Advisor

Robert Riggins, PhD

Abstract

The Air Force has equipped its aircraft with avionic systems such as Global Positioning System (GPS) and Inertial Guidance Systems (INS) capable of providing accurate navigation solutions. The aircrews flying these aircraft require a system that can either survive the hostile environments encountered in combat or notify the aircrew that their performance has been significantly degraded. This research focuses on failure detection and isolation techniques using an extended Kalman filter and generalized likelihood ratios using matched filters. Analysis is conducted using a Kalman filter development package known as the Multimode Simulation for Optimal Filter Evaluation (MSOFE). Both a large order truth model for the navigation system (in which a full 24 satellite constellations is modeled) and a reduced-order Kalman filter are developed. Results suggest that failures within the GPS can be detected, isolated, and in some cases compensated through feedback.

AFIT Designator

AFIT-GE-ENG-92D-37

DTIC Accession Number

ADA259023

Comments

The author's Vita page is omitted.

Download

Share

COinS