SINGLE-ANTENNA GPS-BASED AIRCRAFT ATTITUDE DETERMINATION

Richard P. Kornfeld, R. John Hansman, and John J. Deyst

Peer Reviewed

Abstract: A method for synthesizing aircraft attitude information from single-antenna GPS velocity measurements is described. The attitude information consists of flight path angle and roll angle about the aircraft velocity vector axis. This ‘pseudo-attitude’ is compared with the conventional attitude consisting of pitch and roll angle about the body axis. Zn addition, a pseudo-attitude display is presented that shows fZight path angle and roll angle instead of the traditional pitch and roll information, thus yielding direct indications of the actual fZight path state. Flight tests in a Piper Arrow aircraft demonstrated that pseudo-attitude is equivalent in performance to conventional attitude, with no subjective or objective differences between the two. The results show that a single-antenna GPS receiver provides a useful source of attitude information and consequently may be used as a backup attitude system or for fault diagnostics in redundant systems.
Published in: NAVIGATION, Journal of the Institute of Navigation, Volume 45, Number 1
Pages: 51 - 60
Cite this article: Kornfeld, Richard P., Hansman, R. John, Deyst, John J., "SINGLE-ANTENNA GPS-BASED AIRCRAFT ATTITUDE DETERMINATION", NAVIGATION, Journal of The Institute of Navigation, Vol. 45, No. 1, Spring 1998, pp. 51-60.
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