Significant position errors develop in an unaided GPS navigator if tracking of two of the four satellites is interrupted during aircraft maneuvers. Inertial aiding is known to overcome this performance problem, but utilizing a full three axis inertial measurement unit is not a low cost solution. This paper shows that partial inertial aiding, using only one rate gyro, also overcomes the performance problem and is of much lower cost. Another partial aiding design employs one rate gyro plus two accelerometers and gives somewhat better performance than the single gyro design. Both partial inertial aiding designs give performance comparable to a barometric altimeter aided GPS navigator during short interruptions. The performances of the various designs are compared using a simulation of an aircraft approach and landing.
Partial inertial aiding for low cost aircraft GPS navigators
Partielle, inertiale Unterstuetzung fuer preiswerte GPS Flugzeugnavigatoren
1986
8 Seiten, 11 Bilder, 3 Quellen
Conference paper
English
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