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Differential GPS/inertial navigation approach/landing flight test resultsResults of a joint Honeywell/NASA-Langley differential GPS/inertial flight test conducted in November 1990 are discussed focusing on postflight data analysis. The test was aimed at acquiring a system performance database and demonstrating automatic landing based on an integrated differential GPS/INS with barometric and radar altimeters. Particular attention is given to characteristics of DGPS/inertial error and the magnitude of the differential corrections and vertical channel performance with and without altimeter augmentation. It is shown that DGPS/inertial integrated with a radar altimeter is capable of providing a precision approach and autoland guidance of manned return space vehicles within the Space Shuttle accuracy requirements.
Document ID
19920068385
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Snyder, Scott
(NASA Langley Research Center Hampton, VA, United States)
Schipper, Brian
(NASA Langley Research Center Hampton, VA, United States)
Vallot, Larry
(Honeywell Systems and Research Center Minneapolis, MN, United States)
Parker, Nigel
(Honeywell, Inc. Clearwater, FL, United States)
Spitzer, Cary
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
May 1, 1992
Publication Information
Publication: IEEE Aerospace and Electronic Systems Magazine
Volume: 7
Issue: 5, Ma
ISSN: 0885-8985
Subject Category
Aircraft Communications And Navigation
Accession Number
92A51009
Distribution Limits
Public
Copyright
Other

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