Systems, methods, and non-transitory computer program products for mitigating global navigation satellite system spoofing (GNSS). Real-time correlation data derived from a GNSS signal is received from a tracking channel over a time period. The real-time correlation data includes one or more peaks. The one or more peaks of the real-time correlation data are monitored to determine a presence of at least two distinct peaks separated by at least a predetermined minimum amount of time. An authentic peak is identified within the at least two distinct peaks based on a comparison of predicted correlation data with the real-time correlation data. A tracking command is provided to the tracking channel to facilitate modifying tracking points to center on the authentic peak.

Systems, methods, and non-transitory computer program products for mitigating global navigation satellite system spoofing (GNSS). Real-time correlation data derived from a GNSS signal is received from a tracking channel over a time period. The real-time correlation data includes one or more peaks. The one or more peaks of the real-time correlation data are monitored to determine a presence of at least two distinct peaks separated by at least a predetermined minimum amount of time. An authentic peak is identified within the at least two distinct peaks based on a comparison of predicted correlation data with the real-time correlation data. A tracking command is provided to the tracking channel to facilitate modifying tracking points to center on the authentic peak.

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.

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.

A satellite positioning receiver includes a local oscillator, a front-end circuit with having an analog mixer, a number of signal processing channel circuits, and a processing circuit. The satellite positioning receiver performs a method that includes (i) acquiring a first satellite using a first frequency search space that spans both uncertainties due to the first satellite's orbit and uncertainties due to the clock bias or a time rate of change of the bias; and (ii) using the bias or the time derivative of the bias determined during the acquisition of the first satellite, acquiring a second satellite using a second frequency search space that spans substantially only uncertainties due to the second satellite's orbit.

A satellite positioning receiver includes a local oscillator, a front-end circuit with having an analog mixer, a number of signal processing channel circuits, and a processing circuit. The satellite positioning receiver performs a method that includes (i) acquiring a first satellite using a first frequency search space that spans both uncertainties due to the first satellite's orbit and uncertainties due to the clock bias or a time rate of change of the bias; and (ii) using the bias or the time derivative of the bias determined during the acquisition of the first satellite, acquiring a second satellite using a second frequency search space that spans substantially only uncertainties due to the second satellite's orbit.

A position detection method to be executed by a computer, the position detection method includes transmitting, by a sensor terminal, a signal obtained by performing capture processing on a satellite signal from a satellite of a search target according to an order of the satellites of the search targets; calculating, by a calculation device, a position of the sensor terminal based on a signal transmitted by the sensor terminal; and determining a satellite having a highest discovery probability based on a specific estimation method for second and subsequent search targets, using an index which is reflected larger as the discovery probability of other satellites is higher or lower, in a case where the first satellite is captured when a first search target is determined.

Techniques are provided for GNSS carrier phase multipath mitigation using a blanked correlator in conjunction with a full correlator. A tracking loop may track a carrier of the GNSS signal utilizing the full correlator. A chip-edge accumulation (CEA) unit of the tracking loop may accumulate chip edges of a ranging code to generate CEA output. A blanked correlator may receive the CEA output to generate blanked correlator values. A running-sum filter may utilize the blanked correlator values to generate a running-sum value. A phase estimate may utilize the running-sum value to generate phase estimator output. In an exemplary embodiment, the blanked correlator operates as a monitoring correlator and the phases estimator output is the estimated carrier phase multipath error. In an exemplary embodiment, the blanked correlator provides input to the tracking loop and discriminator output is subtracted from the phase estimator output to generate the estimated carrier phase multipath error.

A method is provided for acquiring a signal from a satellite in a global navigation satellite system. The signal includes a pseudorandom code. The method includes, for each time period of a plurality of time periods: generating samples of the signal, segments of the samples of the signal are correlated with a local copy of the pseudorandom code, thereby producing correlation values for the time period. A discrete Fourier transform is performed using, as inputs, the correlation values for the respective time period, thereby producing a frequency representation of the correlation values for the time period. The frequency representations of the correlation values for the plurality of time periods are combined according to a data hypothesis. When a magnitude of the combined frequency representations meets predefined criteria, a frequency corresponding to the magnitude is selected as a tracking frequency for the satellite.

A method is provided for acquiring a signal from a satellite in a global navigation satellite system. The signal includes a pseudorandom code. The method includes, for each time period of a plurality of time periods: generating samples of the signal, segments of the samples of the signal are correlated with a local copy of the pseudorandom code, thereby producing correlation values for the time period. A discrete Fourier transform is performed using, as inputs, the correlation values for the respective time period, thereby producing a frequency representation of the correlation values for the time period. The frequency representations of the correlation values for the plurality of time periods are combined according to a data hypothesis. When a magnitude of the combined frequency representations meets predefined criteria, a frequency corresponding to the magnitude is selected as a tracking frequency for the satellite.