An aircraft receives pseudorange input from a plurality of satellites of an augmentation system. Each pseudorange input includes a precise position solution and error data. The aircraft receives a high frequency measurement from an inertial navigation system. The aircraft applies the precise position solution, error data, and high frequency measurement to a set of parallel Schmidt extended Kalman filters to produce a corrected position solution and integrity data. The aircraft applies the integrity data to a receiver autonomous integrity monitoring system to produce a protection level for the corrected position solution. The aircraft performs an aircraft operation using the corrected position solution and protection level.
Radar altimeter augmented receiver autonomous integrity monitoring in aircraft
2024-11-26
Patent
Electronic Resource
English
RADAR ALTIMETER AUGMENTED RECEIVER AUTONOMOUS INTEGRITY MONITORING IN AIRCRAFT
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