DESIGN AND FLIGHT TEST OF A DIFFERENTIAL GPS/INERTIAL NAVIGATION SYSTEM FOR APPROACH/LANDING GUIDANCE

Lawrence Vallot, Scott Snyder, Brian Schipper, Nigel Parker, and Cary Spitzer

Peer Reviewed

Abstract: A flight test project evaluating an integrated differential GPS (DGPWinertial navigation system as an approach/landing aid has recently been completed. The test objectives were to acquire a system performance database, and to demonstrate automatic landings using the integrated DGPSinertial system augmented with barometric and radar altimeters. The airborne and ground components of the DGPS/inertial system are built around standard transport aircraft avionics: a global positioning/inertial reference unit and two GPS sensor units. Flight tests were conducted using a specially modified Boeing 737-100. Performance of the DGPSinertial system was evaluated in real time by comparison against Microwave Landing System (MLS) position. DGPSinertial, MLS, and laser tracking system position data were recorded during the tests for postflight analysis. Over 120 landings were flown during the project, 36 of which were fully automatic DGPSinertial landings. The paper describes the objectives of the project, the system implementation, and the flight tests conducted. Laboratory test results and preliminary flight test results are also presented.
Published in: NAVIGATION, Journal of the Institute of Navigation, Volume 38, Number 2
Pages: 103 - 122
Cite this article: Vallot, Lawrence, Snyder, Scott, Schipper, Brian, Parker, Nigel, Spitzer, Cary, "DESIGN AND FLIGHT TEST OF A DIFFERENTIAL GPS/INERTIAL NAVIGATION SYSTEM FOR APPROACH/LANDING GUIDANCE", NAVIGATION, Journal of The Institute of Navigation, Vol. 38, No. 2, Summer 1991, pp. 103-122.
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