A system known as Global Positioning System (GPS) Integrated Navigation (INAV), under development and test at Texas Instruments, has now progressed from laboratory test to a flight-test phase on a company-owned aircraft. This paper describes the results of these flight tests at the GPS test range at the Yuma Proving Ground (YGP). The tightly coupled INAV approach supports the traditional alignment of an inertial set with GPS and, in addition, provides a real-time calibration of the basic inertial sensor errors, compensating for day-to-day drift of the instruments. Effective sensor drift rates are improved by a factor of 3. The GPS tracking loops incorporate carrier loop-aiding from the inertial process, allowing the receiver to operate through high dynamic maneuvers and extensive periods of signal outage arising from antenna shading or jamming. The performance of this single-channel multiplex GPS receiver against dynamics or jamming exceeds that achieved with many multichannel sets to date. Although the system is configured for use with low-cost inertial systems, it is readily adapted to higher quality inertial instruments.
YUMA flight-test validation of an integrated GPS/inertial navigation system
Auswertung der YUMA Flugtests mit einem integrierten GPS/Traegheitsnavigations-System
1987
8 Seiten, 20 Bilder, 3 Quellen
Aufsatz (Konferenz)
Englisch
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