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Flight test results of a tightly integrated RLG-based Global Positioning System/inertial navigation system

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2 Author(s)
Lynch, M.F. ; Kearfott Guidance & Navigation Corp., Wayne, NJ, USA ; Weber, D.J.

Development of a tightly integrated Global Positioning System/inertial navigation system (GPS/INS) is being pursued following the development of a miniaturized GPS receiver and a compact multiaxis ring laser gyro. The flight test program is reviewed, and the results are discussed in detail. The flight test results showed the excellent performance capabilities of the GPS/INS integrated configuration. In a region of nonoptimum satellite geometry, the unit performed very close to the planned accuracy levels. It is noted that, for both test flights, satellite geometry was, at best, not optimum and the aircraft landed in a period of very poor satellite geometry. However, the terminal performance of the integrated system was not degraded and demonstrated GPS-quality performance, with INS and air data computer providing the altitude information unavailable due to poor satellite geometry. Evaluation of the integrated GPS/INS by independent agencies and further planned enhancements to the system's performance are presented

Published in:

Position Location and Navigation Symposium, 1990. Record. The 1990's - A Decade of Excellence in the Navigation Sciences. IEEE PLANS '90., IEEE

Date of Conference:

20-23 Mar 1990

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