Abstract: In the invention, a rover receiver first utilizes data from a base Receiver, a DGNSS reference network, or other differential source to compute a differentially corrected location. Then, using this location and data observed only at the rover, the rover computes an internal set of differential corrections that are stored in computer memory, updated as necessary, and applied in future times to correct observations taken by the rover. The possibly mobile rover receiver, therefore, corrects its own observations with differential corrections computed from its own past observations; relying on external differential for the sole purpose of establishing a reference location, and this is unlike prior art.

Abstract: Various methods, apparatuses, and systems for providing a delayed geotag using GPS devices are described. The GPS device includes a wireless receiver configured to receive satellite state data and satellite range measurements from a plurality of satellites, a communications interface in communication with a media device, and a position engine configured to calculate a geotag. The GPS device can be configured to receive satellite range measurements from one or more satellites at a first point in time when the satellite state data for a minimum number of the satellites is unavailable, and to calculate the satellite state data at that time using satellite state data received at a second, later point in time. The satellite state information at the first point in time is calculated using an algorithm to extrapolate the satellite state data back to the first point in time when the satellite range measurements were made.

Abstract: A method is provided for automatically locating a container in a stowage location of a container ship for loading and unloading of the container ship in container terminals. The method includes the following steps: obtaining the position information of the container ship from container ship positioning units, obtaining the position information of the container from container positioning units when the container is in its stowage location, and determining the stowage location of the container in the container ship by first computing a relative position of the container in the container ship based on both the position information of the container ship and the position information of the container and then correlating the relative position with a stowage plan of the container ship.

Abstract: An interface between an RF processing section and a baseband processing section supports general purpose message transmission as well as satellite positioning system signal sample transmission between the RF processing section and the baseband processing section. The interface includes a bi-directional message serial interface and a data serial interface. The complexity of the data serial interface may be minimized by using a single data bit signal line in the data serial interface.

Abstract: A method and system for delivery of location-dependent time-specific corrections. In one embodiment, a first extended-lifetime correction for a first region is generated. A distribution timetable is used to determine a first time interval for transmitting the first extended-lifetime correction to the first region. The first extended-lifetime correction is then transmitted via a wireless communication network to said first region in accordance with said distribution timetable.

Abstract: A system and method of calculating corrections to a navigation solution based on accurate data are provided. GNSS ephemeris, clock models and other navigation information are received from at least three GNSS satellites and pseudo-ranging to the GNSS satellites is performed. A PVT solution is resolved from the GNSS ephemeris, clock models, and other navigation information and the pseudo range measurements. The PVT solution includes a statistical measure. Differential GNSS data for calculating the corrections to the PVT solution is received and a corrected PVT solution is calculated based upon the differential GNSS data. The corrected PVT solution is compared to a region defined by the statistical measure and the corrected PVT solution is rejected when the corrected PVT solution is not within the region.

Abstract: The satellites of a constellation of satellites each transmit, on distinct frequencies, a first and a second radionavigation signal, respectively. Each station of a reference network from which a satellite is visible performs non-differentiated measurements of code and phase for each of the two signals originating from the satellite and deduces therefrom a raw value of the widelane ambiguity. An internal delay of the satellite and a whole value of the widelane ambiguity are determined, in the network, on the basis of this raw value.

Abstract: A method for mitigating atmospheric errors in code and carrier phase measurements based on signals received from a plurality of satellites in a global navigation satellite system is disclosed. A residual tropospheric delay and a plurality of residual ionospheric delays are modeled as states in a Kalman filter. The state update functions of the Kalman filter include at least one baseline distance dependant factor, wherein the baseline distance is the distance between a reference receiver and a mobile receiver. A plurality of ambiguity values are modeled as states in the Kalman filter. The state update function of the Kalman filter for the ambiguity states includes a dynamic noise factor. An estimated position of mobile receiver is updated in accordance with the residual tropospheric delay, the plurality of residual ionospheric delays and/or the plurality of ambiguity values.

Abstract: A method of locating a first GPS receiver relative to a second GPS receiver. The method includes the steps of: providing a first and second GPS receiver, the first and second GPS receiver spaced apart by a distance D along a baseline; receiving a finite number of observables from a plurality of GPS satellites in a finite period of time; performing in a batch mode the following series of calculations on the finite number of observables: calculating a least squares estimate position for each of the first GPS receiver and the second GPS receiver; calculating a plurality of single difference residuals; calculating a plurality of double difference residuals; calculating an estimate of a geometry free solution; applying geometric annihilation to the geometry free solution; and calculating a least squares solution to provide a measurement of the distance D. A batch processing mode differential GPS apparatus is also described.

Abstract: Methods and apparatuses for processing correction messages in a GNSS receiver are provided. One of the proposed methods includes providing a first storage unit; receiving a plurality of correction messages from at least one data sources, wherein a plurality of assistance data are carried by the plurality of correction messages; and storing a portion of the assistance data in the first storage unit without storing remaining assistance data in the GNSS receiver.

Abstract: Provided is a method and apparatus for a pseudo range verification of a global navigation satellite system (GNSS) receiver, more particularly, a method and apparatus for the pseudo range verification of the GNSS receiver by comparing the pseudo range for a measurement calculated in the GNSS receiver and the pseudo range for a verification generated depending on a position of the GNSS receiver.

Abstract: A processing function to monitor a horizontal delay gradient in satellite signals is provided. The processing function includes a satellite differencing module, a double differencing module, and a gradient estimator module. The satellite differencing module receives carrier phase measurements for at least two satellites from at least two reference receivers that have a known geometric relationship to each other. The satellites include a monitored satellite and at least one other satellite. The satellite differencing module determines differences in the carrier phase measurements between signals from the monitored satellite and at least one other satellite. The double differencing module forms double-differences between pairs of the at least two reference receivers; compensates the double-differences between the pairs for the known difference-in-position of the reference receivers; and averages the double differences.

Abstract: A satellite navigation system generates a smooth and flexible parameterization of satellite orbits and/or clock corrections. The satellite orbit(s) and/or the satellite clock corrections, are described by a first function system of advancing differentiable functions having a high approximation quality and long range of influence. Satellite orbits and/or clock corrections parameterized from the first function system are transmitted from a central ground processing unit to satellite(s) and then to a user device. (Alternatively, transmission may be effected via only a ground infrastructure.) In addition, a second advancing function system of at least continuous functions of moderate approximation quality and a very short range of influence may be provided, which permits a conversion to the first function system, particularly via the user terminal. Thus, the time required to determine the first navigation information (the time to the first fix) can be significantly shortened.

Abstract: Methods and apparatus for processing of data from GNSS receivers are presented. (1) A real-time GNSS rover-engine, a long distance multi baseline averaging (MBA) method, and a stochastic post-processed accuracy predictor are described. (2) The real-time GNSS rover-engine provides high accuracy position determination (decimeter-level) with short occupation time (2 Minutes) for GIS applications. The long distance multi baseline averaging (MBA) method improves differential-correction accuracy by averaging the position results from several different baselines. This technique provides a higher accuracy than any single baseline solution. It was found, that for long baselines (more than about 250 km), the usage of non-iono-free observables (e.g. L1-only or wide-lane) leads to a higher accuracy with MBA compared to the commonly used iono-free (LC) combination, because of the less noisy observables and the cancellation of the residual ionospheric errors.

Abstract: Methods and systems enhance the accuracy of the global positioning system (GPS) using a low earth orbiting (LEO) satellite constellation. According to embodiments described herein, GPS data is received from GPS satellites at a GPS control segment and is used to create GPS correction data to be utilized by user equipment to correct errors within the GPS data. The GPS correction data is transmitted from the GPS control segment to a LEO ground segment, where it is uplinked to the LEO satellite constellation. To account for bandwidth constraints and minimize any performance degradation of the LEO satellites, the GPS correction data is broadcast to earth on a subset of the total number of available spot beams. The subset of spot beams is selected in part according to satellite angular velocity, bandwidth constraints, and message latency estimates.

Abstract: A method and system for precise position determination of general Internet Protocol (IP) network-connected devices. A method enables use of remote intelligence located at strategic network points to distribute relevant assistance data to IP devices with embedded receivers. Assistance is tailored to provide physical timing, frequency and real time signal status data using general broad band communication protocols. Relevant assistance data enables several complementary forms of signal processing gain critical to acquire and measure weakened or distorted in-building Global Navigation Satellite Services (GNSS) signals and to ultimately extract corresponding pseudo-range time components. A method to assemble sets of GNSS measurements that are observed over long periods of time while using standard satellite navigation methods, and once compiled, convert using standard methods each pseudo-range into usable path distances used to calculate a precise geographic position to a known degree of accuracy.

Abstract: In a method of mitigating errors in satellite navigation measurements at a satellite navigation receiver, respective single-frequency signals are received from respective satellites in a plurality of satellites in a satellite navigation system. Pseudorange and carrier-phase measurements corresponding to respective received single-frequency signals are calculated. These calculations include filtering the pseudorange and carrier-phase measurements in a Kalman filter having a state vector comprising a plurality of states, including a position state, a receiver clock state, and a plurality of bias states. Each bias state corresponds to a respective satellite in the plurality of satellites. The filtering includes updating the state vector. An estimated position of the satellite navigation receiver is updated in accordance with an update to the state vector.

Abstract: A method and apparatus for calculating corrections to a navigation solution based on differential GPS data includes receiving GPS ephemeris from at least three GPS satellites. A PVT solution is resolved from the GPS ephemeris. The PVT solution includes a Circular Error Probable (CEP). Differential GPS data for calculating the corrections to the PVT solution is received. A corrected PVT solution is then based upon the differential GPS data. The corrected PVT solution is compared to an area defined by the CEP. Where the corrected PVT solution is not within the area, the corrected PVT solution is rejected in favor of the PVT solution for determining an accurate navigational solution.

Abstract: A positioning apparatus includes: a first positioning device for calculating a reception position of a GPS receiver with respect to each combination of satellites based on a pseudo distance from each positioning satellite to the reception position; a component error calculator for calculating an error of at least one component in a calculation result of the first positioning device; a pseudo distance error calculator for obtaining a relation equation between the error of the at least one component and an error of the pseudo distance, and for solving simultaneous equations comprising the relation equation so that the error of the pseudo distance with respect to each positioning satellite is calculated; and a second positioning device for correcting the reception position based on the error of the pseudo distance.

Abstract: In a system for determining the positions of multiple towed vehicles that are towed by a towing vehicle, a satellite antenna is provided on each towed vehicle and a high accuracy satellite receiver is placed on the towing vehicle, the positions of the towed vehicle of interest being determined by switching its antennae signal through to the satellite receiver.

Abstract: In the invention, a rover receiver first utilizes data from a base Receiver, a DGNSS reference network, or other differential source to compute a differentially corrected location. Then, using this location and data observed only at the rover, the rover computes an internal set of differential corrections that are stored in computer memory, updated as necessary, and applied in future times to correct observations taken by the rover. The possibly mobile rover receiver, therefore, corrects its own observations with differential corrections computed from its own past observations; relying on external differential for the sole purpose of establishing a reference location, and this is unlike prior art.

Abstract: A system determines and transmits correctional data of a global navigation satellite system (GNSS) which has a plurality of reference stations that can be used to determine the correction data by repeatedly measuring the position of the reference stations and comparing it to the previously determined exact position. The data determined in this manner are transmitted to a central station via a network and optionally processed in the central station. Such a system requires that every reference station be equipped with a GNSS receiver, but it is especially the connection to the central station that requires considerable financial resources for the establishment of the connection and both for the maintenance and operation of the network. An already existing network of the phasor measurement units of a power transmission network is therefore used.

Abstract: The present invention provides systems and methods for downloading navigation data to a satellite receiver under weak signal conditions. In an embodiment, the receiver uses a tracking algorithm to estimate the Doppler frequency and rate of change of the Doppler frequency to compensate the phases of the I/Q samples from the received signal to reduce the effect of the Doppler frequency. In an embodiment, differential detection based data bit decoding is provided. In another embodiment, phase compensation based data bit decoding is provided, in which the phase of samples are rotated to compensate for phase error. In an embodiment, a multiple frame strategy is provided to increase signal-to-noise ratio (SNR) and improve sensitivity, in which similar placed samples in consecutive frames are coherently summed over the consecutive frames. In an embodiment, the samples are weighted to reduce the impact of noise in the multiple frame strategy.

Abstract: A method and computer program for determining an error factor for a differential global positioning system is disclosed as well as a method of tracking a vehicle. In determining the error factor, estimated positional data is transmitted from a GPS via GPRS to a server. Since the GPS signals are being transmitted from a vehicle travelling along a known route, i.e. a road or rail track, the data can be matched to the route and a correction factor calculated. The error factor is then transmitted to differential GPS devices. For vehicle tracking a global positioning system sends, via GPRS, data a regular intervals relating only to its position.

Abstract: An unmanned vehicle is guided by selecting locations along a predetermined mute defining adjacent first, second and third linear portions. If an imaginary circle can be constructed that is mutually tangential to all three linear portions or to projections thereof, the vehicle is guided according to the circle intercept method until it reaches an imaginary point of contact (M) between the circle and the second linear portion or passes its traverse. If an imaginary circle cannot be constructed that is mutually tangential to all three linear portions or to projections thereof, an imaginary circle is constructed that is mutually tangential to the first and second linear portions; and the vehicle is guided along according to the leg intercept method until it reaches an imaginary point of contact (M) between the circle and the first linear portion or passes its traverse. The process is repeated iteratively in respect of successive locations.