Investigation of a Failure Detection/Identification System for a Tactical Aircraft Navigation System
Abstract
The purpose of this thesis was to develop a suitable filter model and failure detection/identification (FDI) processor as a basis for a fully simulated adaptive tactical navigation (ATN) system. A 52-state truth error model was developed from which a 26-state filter error model was derived. The measurement process uses a six measurement satellite positioning system (three velocity measurements and three position measurements), a three measurement Doppler radar, and a terrain correlation system. The filter residuals for the different measurement processes are then used in N-step likelihood function computations to observe the residual behavior. Two different testing criteria have been developed for failure declaration. Simple threshold establishment and the tracking of the likelihood function N-step characteristics are used for this purpose. Based on the statistics of the observed failure characteristics, an isolation processor isolates the fault and makes the correct identification. Originator-Supplied Keywords include: Detection, Detectors, Kalman Filtering, Isolation, Filters, and Failure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1984
- Accession Number
- ADA151846
Entities
People
- G. R. Johnston
Organizations
- Air Force Institute of Technology