An apparatus and a method for providing a global localization output are provided. When the apparatus receives navigation signals, the apparatus processes the signals to determine, based on a fixed earth-centered, earth-fixed (ECEF) reference pose of a reference point in an ECEF coordinate, a new ECEF pose, and to convert the fixed ECEF reference pose to an east-north-up (ENU) reference pose in an ENU coordinate. When the apparatus determines that a jump occurs in the new ECEF pose based on a pose change between the new ECEF pose and a previous ECEF pose, the apparatus calculates a reference shift of the ENU reference pose based on the pose change to absorb the jump in the ENU coordinate, and updates the ENU reference pose based on the reference shift. Thus, a new ENU local pose may be obtained using the ENU reference pose.

An apparatus and a method for providing a global localization output are provided. When the apparatus receives navigation signals, the apparatus processes the signals to determine, based on a fixed earth-centered, earth-fixed (ECEF) reference pose of a reference point in an ECEF coordinate, a new ECEF pose, and to convert the fixed ECEF reference pose to an east-north-up (ENU) reference pose in an ENU coordinate. When the apparatus determines that a jump occurs in the new ECEF pose based on a pose change between the new ECEF pose and a previous ECEF pose, the apparatus calculates a reference shift of the ENU reference pose based on the pose change to absorb the jump in the ENU coordinate, and updates the ENU reference pose based on the reference shift. Thus, a new ENU local pose may be obtained using the ENU reference pose.

A system and method for determining attitude of an end point equipment (EPE) using a global navigation satellite system (GNSS) receiver. The method includes collecting signals and radio frequency (RF) switch states, wherein the signals are GNSS signals received by at least one GNSS antenna of an end point equipment (EPE), wherein the signals are associated with the respective RF switch states; generating differencing data of the signals with respect to reference measurements, wherein the reference measurements are collected from a GNSS receiver at a reference station in a predetermined distance from the EPE; determining an attitude of the EPE based on the generated differencing data; and causing reorientation of the EPE based on the determined attitude.

Systems and methods of heading determination with global navigation satellite system (GNSS) signal measurements are provided herein. A pair of antennas may be separated by a known baseline length and mounted on a vehicle. A GNSS receiver may obtain pseudorange and carrier phase measurements for GNSS satellites within view. An LRU may estimate carrier phase ambiguities and a two-dimensional vector, using the known baseline length and a linearized measurement model. The LRU may determine integer ambiguities using the estimated carrier phase ambiguities. The LRU may determine assumed wrong fixes of the integer ambiguities and a probability of almost fixed value. The LRU may store the set of integer ambiguities. The LRU may determine, from accumulated data over measurement epochs, updated integer ambiguities. The LRU may correct the carrier phase measurements using the updated integer ambiguities. The LRU may compute the heading using the corrected carrier phase measurements.

Systems and methods of heading determination with global navigation satellite system (GNSS) signal measurements are provided herein. A pair of antennas may be separated by a known baseline length and mounted on a vehicle. A GNSS receiver may obtain pseudorange and carrier phase measurements for GNSS satellites within view. An LRU may estimate carrier phase ambiguities and a two-dimensional vector, using the known baseline length and a linearized measurement model. The LRU may determine integer ambiguities using the estimated carrier phase ambiguities. The LRU may determine assumed wrong fixes of the integer ambiguities and a probability of almost fixed value. The LRU may store the set of integer ambiguities. The LRU may determine, from accumulated data over measurement epochs, updated integer ambiguities. The LRU may correct the carrier phase measurements using the updated integer ambiguities. The LRU may compute the heading using the corrected carrier phase measurements.

Systems and methods for use in navigating aircraft are provided. The systems can use Geometry Redundant Almost Fixed Solutions (GRAFS) or Geometry Extra Redundant Almost Fixed Solutions (GERAFS) to compute high confidence error bounds for a heading angle estimate or pitch angle derived using signals received on at least two antennas.

A method, apparatus and computer program product provide one or more of navigation-data parameters or correction-model parameters for one or more navigation satellites. In the context of a method, the method includes receiving (i) navigation data regarding one or more of a position of a respective navigation satellite or a clock offset of a clock of the respective navigation satellite and (ii) correction data regarding corrections to one or more of the position or the clock offset of the respective navigation satellite. The method also includes predicting an orbit and the clock of the respective navigation satellite based on the navigation data and the correction data. The method further includes fitting at least one of the navigation-data parameters or the correction-model parameters to the predicted data and, following the fitting, providing the at least one of the navigation-data parameters or the correction-model parameters to one or more navigation devices.

A method, apparatus and computer program product provide one or more of navigation-data parameters or correction-model parameters for one or more navigation satellites. In the context of a method, the method includes receiving (i) navigation data regarding one or more of a position of a respective navigation satellite or a clock offset of a clock of the respective navigation satellite and (ii) correction data regarding corrections to one or more of the position or the clock offset of the respective navigation satellite. The method also includes predicting an orbit and the clock of the respective navigation satellite based on the navigation data and the correction data. The method further includes fitting at least one of the navigation-data parameters or the correction-model parameters to the predicted data and, following the fitting, providing the at least one of the navigation-data parameters or the correction-model parameters to one or more navigation devices.

A relative angle acquisition unit (110) acquires a relative angle (31) between each base station of a plurality of base stations and a communication device. A provisional position calculation unit (120) calculates a position of the communication device as a provisional position (32), using the relative angle (31) and a position of each base station. A weight calculation unit (130) calculates a distance between each base station and the communication device, using the position of each base station and the provisional position, and calculates a weighting coefficient (33) for correcting the provisional position (32) for each base station, based on the distance between each base station and the communication device. A device position calculation unit (140) calculates the position of the communication device as a device position (34), using the relative angle (31), the position of each base station, and the weighting coefficient (33).

A relative angle acquisition unit (110) acquires a relative angle (31) between each base station of a plurality of base stations and a communication device. A provisional position calculation unit (120) calculates a position of the communication device as a provisional position (32), using the relative angle (31) and a position of each base station. A weight calculation unit (130) calculates a distance between each base station and the communication device, using the position of each base station and the provisional position, and calculates a weighting coefficient (33) for correcting the provisional position (32) for each base station, based on the distance between each base station and the communication device. A device position calculation unit (140) calculates the position of the communication device as a device position (34), using the relative angle (31), the position of each base station, and the weighting coefficient (33).