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Aircraft Automatic Landing Systems Using GPS

Published online by Cambridge University Press:  21 October 2009

B. W. Parkinson  and
K. T. Fitzgibbon
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Abstract

This paper is based on a presentation made at the IAIN International Navigation Congress held in Sydney, Australia, in February 1988.

The global positioning system (GPS) offers a new opportunity for the automation of aircraft landing systems. The position and velocity measurements provided by a state-of-the-art GPS receiver using the C/A code and working in a normal or differential mode (D-GPS) and aided by one or two ground-based PseudoLites (PLS), may be able to satisfy the landing accuracy requirements of the FA A.

This paper describes the design and simulation of an aircraft automatic landing system. Aircraft position and velocity are assumed to be measured using a (carrier-tracking) GPS receiver. The hypothesized capability is based on measurements taken at Stanford and elsewhere, using the Trimble 4000SX, five-channel receiver in an integrated-doppler-aiding mode. For some of the autopilot designs, either ground-based GPS transmitters (pseudolites) or a radar altimeter have also been incorporated.

Included in the landing simulations are wind shears and a gust model, creating realistic landing situations. The performances of the lateral and vertical displacements are presented with their 1σ r.m.s. estimation errors during the glide-slope and flare phases. Included are different wind conditions, GPS configurations and controllers. The results are compared with the FAA requirements for various categories of automatic landing systems.

Type
Research Article
Information
The Journal of Navigation , Volume 42 , Issue 1 , January 1989 , pp. 47 - 59
Copyright
Copyright © The Royal Institute of Navigation 1989

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References

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