Integrity monitoring method and apparatus for GPS and DGPS recei

Communications: directive radio wave systems and devices (e.g. – Directive – Including a satellite

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340979, 701213, G01S 502, G01C 2100, G06F 770

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active

056637322

ABSTRACT:
A fail safe GPS system for an aircraft moving along a desired trajectory within vertical and horizontal limits using first and second redundant GPS receivers a first of which is connected to the avionics equipment of the aircraft and to an alarm and the second of which is connected only to the alarm so that if a malfunction in the flight management system occurs both GPS's will cause the alarm and if a malfunction in the first GPS system occurs, so that the aircraft exceeds the vertical or horizontal limits, the second GPS system will cause the alarm.

REFERENCES:
patent: 4567483 (1986-01-01), Bateman et al.
patent: 5461388 (1995-10-01), Applegate et al.
patent: 5488559 (1996-01-01), Seymour
Vallot et al, "Design and Flight Test for a Differential GPS/Inertial Navigation System for Approaching/Landing Guidance", Navigation: Journal of the Inst. of Nav., vol. 38, #2, Summer 1991.
Matts Brenner application entitled "Differential Satellite Positioning System Ground Station With Integrity Monitoring," Ser. No. 08/497,995 file date Jun. 30, 1995.

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