An information processing system includes a server and a first vehicle acquiring a combination of first and second position information of the first vehicle. The first position information is calculated using a positioning signal from the first satellite system. The second position information is obtained by correcting an error of the first position information using a positioning reinforcement signal from the second satellite system. The first vehicle or the server calculates difference information between the first and second position information for each combination thereof. The server estimates a calculation accuracy for the first position information in a road section on a road map based on one or more pieces of difference information in which one or more positions indicated by the second position information corresponding to the difference information are within the road section and to output the calculation accuracy for the first position information in the road section.

Methods and systems are provided for navigating a mobile platform in an environment. A processor obtains information about an object in the environment, obtains information about a first satellite, and estimates a probability indicator for a non-line of sight signal transmission between a current satellite location of the first satellite and a current location of the mobile platform using the information about the first satellite and the information about the object. The processor further determines a discrepancy indicator using a movement information of the mobile platform and a movement information of the first satellite such that a weighting indicator can be determined using the estimated probability indicator and the determined discrepancy indicator. The processor then assigns a weighting indicator to a satellite signal transmitted from the first satellite in order to provide a first weighted signal for navigating the mobile platform.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

A wearable training computer comprising a processing circuitry configured to determine a location of the wearable training computer based on received location information. Based on the location of the wearable training computer, the processing circuitry is further configured to select a satellite positioning system configuration used for determining the location of the wearable training computer during a physical exercise.

Significant, cost-effective improvement is introduced for Position, Navigation, and Timing (PNT) on a global basis, particularly enhancing the performance of Global Navigation Satellite Systems (GNSS), an example of which is the Global Positioning System (GPS). The solution significantly improves performance metrics including the accuracy, integrity, time to acquire, interference rejection, and spoofing protection. A constellation of small satellites employing a low-cost architecture combined with improved signal processing yields an affordable enabler for spectrum-efficient transportation mobility. As air traffic management modernization transitions to a greater dependence on satellite positioning, the solution provides aviation users new protections from both intentional and unintentional interference to navigation and surveillance. And in response to an era in which intelligent transportation is under development for automobiles, reliable where-in-lane positioning enables new applications in connected and autonomous vehicles. New military capability increases PNT availability.

A precise point position and real-time kinematic (PPP-RTK) positioning method, including: when direct emission signals broadcast by a multi-system navigation satellite and a low-earth-orbit constellation are detected, determining raw observation data (S11); receiving navigation satellite augmentation information broadcast by the low-earth-orbit constellation, and a low-earth-orbit satellite precise orbit and precise clock difference (S12); using the navigation satellite augmentation information, the low-earth-orbit satellite precise orbit and precise clock difference and the raw observation data for precise point positioning (S13); or when comprehensive ground-based augmentation error correction information is received, using the navigation satellite augmentation information, the low-earth-orbit satellite precise orbit and precise clock difference, the raw observation data and the comprehensive ground-based augmentation error correction information for precise point positioning of ground-based augmentation (S13′). The present application further relates to a precise point position and real-time kinematic (PPP-RTK) positioning device, a computer-readable storage medium and a processor.

A signal generation system for signal simulation includes at least one data input, a pulse description word generator, a multi-frequency signal generator, and at least one radio frequency output. The multi-frequency signal generator is configured to simulate a multi-frequency global navigation satellite system signal. The pulse description word generator and the multi-frequency signal generator are assigned to the data input in order to process data received via the data input. The pulse description word generator and the multi-frequency signal generator are configured to generate an output signal based on at least one instruction for a certain generator behavior of the pulse description word generator and/or the multi-frequency signal generator. The at least one instruction is encompassed in the data received. Further, a method of signal generation is described.

An illustrative example embodiment of a system for determining heading direction information includes a plurality of detectors in a predetermined detector arrangement. The detectors are respectively configured to detect at least one satellite. At least one processor is configured to determine a spatial relationship between at least one characteristic of the detector arrangement and a single satellite detected by each of the detectors. The processor is configured to determine the spatial relationship at each of a plurality of times when each of the detectors detects the single satellite. The processor is configured to determine heading direction information based on a difference between the determined spatial relationships.

A system and method for determining the location of a vehicle when GNSS signals are not available use triangulation between one or two radio transmitters and, respectively, two or one radio receivers mounted on the vehicle. The distance between each radio transmitter and/or each radio receiver can be determined according a phase difference between received radio signals. The radio signals can have the geographical location of the radio transmitter included therein. Utilizing the demodulated geographical location of each radio transmitter and the distance between the radio transmitter and each radio receiver, triangulation can be used to determine the geographical location of the vehicle.

Methods of checking the integrity of the estimation of the position of a mobile carrier are provided, the position being established by a satellite-based positioning measurement system, the estimation being obtained by the so-called “real time kinematic” procedures. The method verifies that the carrier phase measurement is consistent with the code pseudo-distance measurement. The method comprises a step of calculating the velocity of the carrier, at each observation instant, a step of verifying that at each of the observation instants, the short-term evolution of the carrier phase of the signals received on each of the satellite sight axes is consistent with the calculated velocity and a step of verifying that at each of the observation instants, the filtered position obtained on the basis of the long-term filtered measurements of pseudo-distance through the carrier phase is dependable.