A positioning signal from a satellite positioning system is received at a mobile station, correction information from a reference station is used, a pseudo distance observation formula using a code and a phase distance observation formula using a carrier wave are used to perform positioning using single frequency at the mobile station, and these observation formulas are expressed by a satellite clock error, clock errors at the reference station and the mobile station, a ionospheric delay and a tropospheric delay, and a code bias and a phase bias of single frequency at the reference station, the mobile station and a satellite.

A method of calculating ionospheric scintillation includes calculating a motion-corrected perturbation of a GNSS radio signal received by a monitoring device deployed in an oceanic environment. The method includes calculating the σφ using the high rate phase of the GNSS signal adjusted by removing the change in distance between the monitoring device and the GNSS satellite. The calculating the σo may further include passing the adjusted high rate phase through a high pass filter to remove a drift motion of the monitoring device. The method further includes calculating the S4 through calculating a tilt angle between the antenna of the monitoring device with the GNSS satellite and adjusting the antenna gain through known gain pattern of the antenna. The wave height of the oceanic environment may be calculated by detrending the antenna height to remove low frequency motion when a high rate position of the monitoring device is calculated.

A wide-lane ambiguity and a respective satellite wide-lane bias are determined for the collected phase measurements for each satellite for assistance in narrow-lane ambiguity resolution. Satellite correction data is determined for each satellite in an orbit solution based on the collected raw phase and code measurements and determined orbital narrow-lane ambiguity and respective orbital satellite narrow-lane bias. A slow satellite clock correction is determined based on the satellite orbital correction data, the collected raw phase and code measurements, and clock narrow-lane ambiguity and respective satellite narrow-lane bias. A low latency clock module or data processor determines lower-latency satellite clock correction data or delta clock adjustment to the slow satellite clock based on freshly or recently updated measurements of the collected raw phase measurements that are more current than a plurality of previous measurements of the collected raw phase measurements used for the slow satellite clock correction to provide lower-latency clock correction data.

A satellite corrections generation system receives reference receiver measurement information from a plurality of reference receivers at established locations. In accordance with the received reference receiver measurement information, and established locations of the reference receivers, the system determines narrow-lane navigation solutions for the plurality of reference receivers. The system also determines clusters of single-difference (SD) narrow-lane floating ambiguities, each cluster comprising pairs of SD narrow-lane floating ambiguities for respective pairs of satellites. A satellite narrow-lane bias value for each satellite of a plurality of satellites is initially determined in accordance with fractional portions of the SD narrow-lane floating ambiguities in the clusters, and then periodically updated by a Kalman filter. A set of navigation satellite corrections for each satellite, including the satellite narrow-lane bias value for each satellite, is generated and transmitted to navigation receivers for use in determining locations of the navigation receivers.

A satellite corrections generation system receives reference receiver measurement information from a plurality of reference receivers at established locations. In accordance with the received reference receiver measurement information, and established locations of the reference receivers, the system determines narrow-lane navigation solutions for the plurality of reference receivers. The system also determines, in accordance with the narrow-lane navigation solutions, at a first update rate, an orbit correction for each satellite of a plurality of satellites; at a second update rate, a clock correction for each such satellite; and at a third update rate that is faster than the second update rate, an update to the clock correction for each such satellite. Further, the system generates navigation satellite corrections for each such satellite, including the orbit correction updated at the first update rate, and the clock correction that is updated at the third update rate.

A satellite corrections generation system receives reference receiver measurement information from a plurality of reference receivers at established locations. In accordance with the received reference receiver measurement information, and established locations of the reference receivers, the system determines wide-lane navigation solutions for the plurality of reference receivers. The system also determines clusters of single-difference (SD) wide-lane floating ambiguities. A satellite wide-lane bias value for each satellite of a plurality of satellites is initially determined in accordance with fractional portions of the SD wide-lane floating ambiguities in the clusters and over-range adjustment criteria. A set of navigation satellite corrections for each satellite, including the satellite wide-lane bias value for each satellite, is generated and transmitted to navigation receivers for use in determining locations of the navigation receivers.

An error correcting location system includes a ground station with fixed reference coordinates. The ground station may receive satellite broadcast messages from a plurality of location system satellites. Further, the ground station may determine location coordinates based on the satellite broadcast messages, and compare the location coordinates to the fixed reference coordinates to determine a compensation value. In addition, the ground station may send the compensation value to location system devices. Upon receipt of the compensation value, the location system devices may utilize the compensation value to generate highly accurate location coordinates.

A method for determining a model of an electron distribution in the Earth's atmosphere in order to correct time-of-flight measurements of signals that are transmitted by earth satellites for position determinations with signal receivers includes determining local electron density data of provision sites and determining a local resolution accuracy as a function of the electron density data of the provision sites. The method further includes determining functions for interpolation of a distribution of the determined electron density data of the provision sites as a function of the determined resolution accuracy and compiling the model of the electron density distribution with the determined electron density data of the provision sites and the determined functions for interpolation.

The disclosed technology includes a computerized ionospheric tomography method based on vertical boundary truncation rays, which relates to the technical field of computerized ionospheric tomography (CIT). The method includes: obtaining an initial ionospheric electron density (IED) of each voxel in a target region and an ionospheric total electron content (TEC) value along a propagation path from a global navigation satellite system (GNSS) satellite; extending the target region so that GNSS stations within a certain range beyond the target region are encompassed within the target region; for GNSS stations within a certain range in the target region, calculating a vertical boundary truncation TEC value; for the GNSS stations within the target region, calculating a vertical boundary truncation TEC value; and building a three-dimensional CIT model based on the vertical boundary truncation TEC values P.sub.rTEC and P.sub.sTEC.

A method for providing raw correction data for correcting atmospheric disturbances for satellite navigation includes checking whether a mobile satellite receiver for satellite navigation is in an immobile state using at least one sensor signal. The sensor signal represents a measurement variable dependent on a state of movement of the mobile satellite receiver. The method further includes evaluating at least one satellite signal transmitted between at least one satellite and the mobile satellite receiver in the immobile state with regard to a signal property dependent on atmospheric disturbances in order to generate the raw correction data. The raw correction data represents an item of information regarding the atmospheric disturbances.