The system design described in this paper obtains for the worst case failure pattern a fail-operate, fail-operate and fail-safe (FO-FO-FS) capability both as a flight control reference and navigation system. The paper first discusses highly-efficient algorithms for rapid detection and isolation of failed or degraded instruments for a system of two identical inertial measurement units each with redundant gyros and accelerometers. A spcecific relative orientation between these two inertial measurement units is assumed in the derivation. The paper then discusses the second type of alagorithm which utilizes the non-degraded sensor outputs to construct the optimal permissible solutions for both the flight control system reference inputs and the navigation function. The specific configuration that is selected by these latter design equations is identified for both of these functions for each possible failure detection and isolation condition up to that for FO-FO-FS.
Sensor management for a fault tolerant integrated inertial flight control reference and navigation system
Sensormanagement fuer ein fehlertolerantes, integriertes, Traegheits-Flugregelungs-Referenzsystem und Navigationssystem
1986
11 Seiten, 15 Bilder, 6 Quellen
Aufsatz (Konferenz)
Englisch
Fault tolerant inertial navigation system
AIAA | 1988
|Flight-control/navigation inertial reference system
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|Flight-control/navigation inertial reference system
NTRS | 1977
|Integrated inertial reference systems for flight-control and navigation
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