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Design and Flight Test of a Differential GPS/Inertial Navigation System for Approach/Landing Guidance

1991; Wiley; Volume: 38; Issue: 2 Linguagem: Inglês

10.1002/j.2161-4296.1991.tb01719.x

2161-4296

L. Vallot, S. Snyder, Brian Schipper, N. Parker, Cary R. Spitzer,

Inertial Sensor and Navigation

A flight test project evaluating an integrated differential GPS (DGPS)/inertial 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 DGPS/inertial 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 DGPS/inertial system was evaluated in real time by comparison against Microwave Landing System (MLS) position. DGPS/inertial, 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 DGPS/inertial 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.