Honeywell International Inc.

John Savoy

Alfonso Malaga

Anthony H Luk

Barry D Webb

Sidney Richard Strong

Hui Zhao

Systems and methods for the selection of antennas in aircraft navigation systems are provided. In one embodiment, a navigation receiver system for an aircraft comprises: a first aircraft antenna that receives transmitter signals from fixed-location ground transmitters and a second aircraft antenna that receives transmitter signals from the fixed-location ground transmitters, wherein the first aircraft antenna has a first gain pattern that is different from a second gain pattern of the second aircraft antenna; a switch coupled to a first receiver and the first and second aircraft antenna; and a switch controller coupled to the switch. The switch controller operates the switch to electrically couple the first receiver to either the first or second aircraft antenna based on a determination of whether the first gain pattern or the second gain pattern provides higher gain in a direction of a first fixed-location ground transmitter of the fixed-location ground transmitters.

Systems and methods for the selection of antennas in aircraft navigation systems

Systems and methods for reporting position and associated integrity during times when extrapolation is not taking place as accurately as possible. In one example, a processing device deactivates extrapolation of global positioning system (GPS) position information based on a predefined condition, receives ground speed information, and HFOM and HIL values from a global position system (GPS); calculates inflated HFOM and HIL values based on the received HFOM and HIL values and the ground speed and generates an automatic dependent surveillance-broadcast (ADS-B) OUT signal based on the calculated inflated HFOM and HIL values. A transmitter coupled to the processing device transmits the generated ADS-B OUT signal.

Systems and methods for updating HIL and HFOM integrity components when not extrapolating position data

In one embodiment, a method for ionospheric delay compensation is provided. The method includes determining an ionospheric delay based on a signal having propagated from the navigation satellite to a location below the ionosphere. A scale factor can be applied to the ionospheric delay, wherein the scale factor corresponds to a ratio of an ionospheric delay in the vertical direction based on an altitude of the satellite navigation system receiver. Compensation can be applied based on the ionospheric delay.

Ionospheric delay compensation using a scale factor based on an altitude of a receiver

Example embodiments disclosed herein provide for a method for detecting a fault in a receiver for a satellite navigation system. The method includes calculating a plurality of measurement residuals corresponding to a position solution and combining the plurality of measurement residuals to form a test statistic. The method also includes calculating a threshold corresponding to the test statistic, wherein calculating the threshold includes selecting the threshold to be a value from a non-central chi squared distribution of possible test statistics that corresponds to a desired probability of false alarm. The test statistic is compared to the threshold and if the test statistic is larger than the threshold, performing at least one of: outputting an alarm indicative of a fault in the position solution and discarding the position solution.

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Olathe, KS, United States of America

John Savoy