Abstract: A method of using space based augmentation system (SBAS) ephemeris data in conjunction with a ground based augmentation systems (GBAS) station is provided. The method includes integrating a space based augmentation system (SBAS) receiver in the GBAS station; receiving an industry-standard message type via the SBAS receiver at the GBAS station; consuming, at the GBAS station, the SBAS ephemeris data from the industry-standard message type associated with satellites in view of the GBAS station. The industry-standard message type includes SBAS ephemeris data associated with satellites in a global navigation satellite system (GNSS). The method further includes, based on the consuming, improving error bounds to GBAS broadcast ephemeris decorellation parameters broadcast from the GBAS station and reducing time to reintroduce a satellite in the GNSS.

Abstract: Systems and methods for a code carrier divergence (CCD) high-pass filter monitor are provided.

Abstract: A system to mitigate errors in GPS corrections and ephemeris uncertainty data broadcast to a vehicle is presented. The system includes reference receivers in a first ground subsystem and a processor. The processor: receives, from reference receivers in a wide area network of reference receivers, satellite measurement data for a first plurality of satellites and receives, from the reference receivers in the first ground subsystem, satellite measurement data and ephemeris data from a second plurality of satellites; evaluate the satellite measurement data to determine if the GPS corrections are degraded by a current ionosphere disturbance activity; determine a current quality metric of the ionosphere; adjust a Vertical Ionosphere Gradient standard deviation sigma-vig; evaluate the ephemeris data to determine if the GPS corrections provided to the vehicle are degraded by ephemeris errors; and establish ephemeris uncertainty to protect integrity based on the evaluation of the ephemeris data.

Abstract: A method of implementing a real-time screening process for phase scintillation is presented. The method includes detecting a phase scintillation event during a sample time period at a phase scintillation monitor; excluding associated satellite measurement data from further use based on the detection of the phase scintillation event at the phase scintillation monitor; detecting an end to the phase scintillation event at the phase scintillation monitor; and readmitting associated satellite measurement data collected after the end of the phase scintillation event as detected by the phase scintillation monitor.

Abstract: GBAS includes reference receivers, processing module, and communication device. Processing module checks GNSS satellite measurements to determine proximity of GNSS satellite measurement's IPP to IGPs derived from SBAS geostationary satellites. Processing module determines that GNSS satellite measurement is safe for mitigation using overbounded Vertical Ionosphere Gradient standard deviation sigma-vig (?vig) when IGPs possess acceptable GIVE values. Processing module determines whether number of GNSS satellite measurements determined safe for mitigation using ?vig are able to produce VPL that meets VAL required for precision approach.

Abstract: A system to mitigate errors in GPS corrections and ephemeris uncertainty data broadcast to a vehicle is presented. The system includes reference receivers in a first ground subsystem and a processor. The processor: receives, from reference receivers in a wide area network of reference receivers, satellite measurement data for a first plurality of satellites and receives, from the reference receivers in the first ground subsystem, satellite measurement data and ephemeris data from a second plurality of satellites; evaluate the satellite measurement data to determine if the GPS corrections are degraded by a current ionosphere disturbance activity; determine a current quality metric of the ionosphere; adjust a Vertical Ionosphere Gradient standard deviation sigma-vig; evaluate the ephemeris data to determine if the GPS corrections provided to the vehicle are degraded by ephemeris errors; and establish ephemeris uncertainty to protect integrity based on the evaluation of the ephemeris data.

Abstract: A method of using space based augmentation system (SBAS) ephemeris data in conjunction with a ground based augmentation systems (GBAS) station is provided. The method includes integrating a space based augmentation system (SBAS) receiver in the GBAS station; receiving an industry-standard message type via the SBAS receiver at the GBAS station; consuming, at the GBAS station, the SBAS ephemeris data from the industry-standard message type associated with satellites in view of the GBAS station. The industry-standard message type includes SBAS ephemeris data associated with satellites in a global navigation satellite system (GNSS). The method further includes, based on the consuming, improving error bounds to GBAS broadcast ephemeris decorellation parameters broadcast from the GBAS station and reducing time to reintroduce a satellite in the GNSS.

Abstract: A method of implementing a real-time screening process for amplitude scintillation is presented. The method includes detecting an amplitude scintillation event during a sample time period at an amplitude scintillation monitor; excluding associated satellite measurement data from further use based on the detection of the amplitude scintillation event at the amplitude scintillation monitor; detecting an end to the amplitude scintillation event at the amplitude scintillation monitor; and readmitting associated satellite measurement data collected after the end of the amplitude scintillation event as determined by the amplitude scintillation monitor.

Abstract: GBAS includes reference receivers, processing module, and communication device. Processing module checks GNSS satellite measurements to determine proximity of GNSS satellite measurement's IPP to IGPs derived from SBAS geostationary satellites. Processing module determines that GNSS satellite measurement is safe for mitigation using overbounded Vertical Ionosphere Gradient standard deviation sigma-vig (?vig) when IGPs possess acceptable GIVE values. Processing module determines whether number of GNSS satellite measurements determined safe for mitigation using ?vig are able to produce VPL that meets VAL required for precision approach.

Abstract: Systems and methods for monitoring broadband radio frequency interference are provided. In certain embodiments, a method comprises calculating a smoothed carrier to noise value for a received signal on a processing unit, wherein the received signal is associated with a receiver and at least one satellite; calculating an average jammer power to noise power value for the receiver; calculating an instantaneous carrier to noise value for the received signal based on the average jammer power to noise power value and the smoothed carrier to noise value; comparing the instantaneous carrier to noise value to an exclusion threshold, and determining whether to exclude the received signal from calculations of global positioning data based on the comparison of the instantaneous carrier to noise value to the exclusion threshold; and when the received signal is excluded, monitoring the received signal for readmittance to the calculation of global positioning data.

Abstract: Systems and methods for a code carrier divergence (CCD) high-pass filter monitor are provided.

Abstract: A method of implementing a real-time screening process for phase scintillation is presented. The method includes detecting a phase scintillation event during a sample time period at a phase scintillation monitor; excluding associated satellite measurement data from further use based on the detection of the phase scintillation event at the phase scintillation monitor; detecting an end to the phase scintillation event at the phase scintillation monitor; and readmitting associated satellite measurement data collected after the end of the phase scintillation event as detected by the phase scintillation monitor.

Abstract: A method of implementing a real-time screening process for amplitude scintillation is presented. The method includes detecting an amplitude scintillation event during a sample time period at an amplitude scintillation monitor; excluding associated satellite measurement data from further use based on the detection of the amplitude scintillation event at the amplitude scintillation monitor; detecting an end to the amplitude scintillation event at the amplitude scintillation monitor; and readmitting associated satellite measurement data collected after the end of the amplitude scintillation event as determined by the amplitude scintillation monitor.

Abstract: Systems and methods for using SBAS delay measurements to mitigate ionospheric error are provided. In an embodiment, an array of ionospheric delay measurements of a GNSS is provided, wherein a pierce point is associated with each delay measurement in the array. Further, at least one first element in the array and at least one second element in the array that has a different pierce point than the at least one first element are selected and it's determined whether the difference between the delay measurement of the at least one first element and the delay measurement of the at least one second element is less than a threshold. A level of inflation of error due to geometric screening techniques is adjusted if the difference between the delay measurement of the at least one first element and the delay measurement of the at least one second element is less than the threshold.

Abstract: Systems and methods for monitoring broadband radio frequency interference are provided. In certain embodiments, a method comprises calculating a smoothed carrier to noise value for a received signal on a processing unit, wherein the received signal is associated with a receiver and at least one satellite; calculating an average jammer power to noise power value for the receiver; calculating an instantaneous carrier to noise value for the received signal based on the average jammer power to noise power value and the smoothed carrier to noise value; comparing the instantaneous carrier to noise value to an exclusion threshold, and determining whether to exclude the received signal from calculations of global positioning data based on the comparison of the instantaneous carrier to noise value to the exclusion threshold; and when the received signal is excluded, monitoring the received signal for readmittance to the calculation of global positioning data.

Abstract: A method and apparatus are provided for predicting the position error bound in a satellite positioning system at a future time. The future position of each satellite at the future time is calculated from the trajectory data obtained from each satellite. The predicted position for each satellite and the estimated position of the satellite positioning system receiver is then used to generate a line of sight matrix at the future time from which a position error bound is determined.

Abstract: A method and apparatus are provided for predicting the position error bound in a satellite positioning system at a future time. The future position of each satellite at the future time is predicted from the trajectory data obtained from each satellite. The predicted position for each satellite and the estimated position of the satellite positioning system receiver is then used to generate a line of sight matrix at a future time, from which a position error bound value determined.

Abstract: An aircraft landing system is disclosed in which a differential GPS global positioning system is employed. A ground station, located in the vicinity of one or more landing strips, includes a GPS receiver and a data link transmitter for transmitting GPS correction data and also the global position of two points which define a desired aircraft glide path associated with a particular landing strip. The system further includes aircraft equipment comprising a receiver for receiving the correction data and the global position of the two glide path points, and a GPS receiver. The aircraft equipment further includes a computer for determining a corrected global position of the aircraft as a function of the aircraft GPS range data and the correction data, and subsequently determines the lateral deviation and vertical deviation from the glide path defined by the two glide path points.