A method of enhancing the accuracy of a navigation system which includes a GNSS receiver. The method includes receiving navigation signals from at least one GNSS constellation and a LEO constellation. Position estimates will be made through implementation of a filter using successive readings of pseudoranges and carrier-phase measurements from the GNSS constellation and carrier-phase measurements from the LEO constellation.

A satellite signal receiving device includes a sampling clock outputting circuit that receives a reference clock and outputs a sampling clock, a first RF receiving circuit that is capable of performing intermittent driving in which an on operation and an off operation, and, during the on operation, down-converts a first satellite signal received by a first receiving antenna and outputs a first intermediate signal, a first baseband processing circuit that processes the first intermediate signal in accordance with the reference clock, a second RF receiving circuit that is capable of performing intermittent driving, and, during the on operation, down-converts a second satellite signal received by a second receiving antenna and outputs a second intermediate signal, and a second baseband processing circuit that processes the second intermediate signal in accordance with the sampling clock.

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 satellite signal processing method and a satellite positioning apparatus are disclosed, and relate to the field of communication technologies, to improve system performance and user experience when an RNSS is integrated with an RDSS. The satellite positioning apparatus includes: an RNSS radio frequency channel, configured to receive an RNSS received signal; an RNSS baseband processor, coupled to the RNSS radio frequency channel, and configured to perform position, velocity, and time PVT computation on the RNSS received signal to obtain PVT information; an RDSS baseband processor, configured to determine a carrier frequency of an RDSS received signal based on a carrier frequency offset value, where the carrier frequency offset value is generated based on the PVT information; and an RDSS radio frequency channel, coupled to the RDSS baseband processor, and configured to receive the RDSS received signal based on the carrier frequency of the RDSS received signal.

Examples for enhancing sensitivity to reflected GNSS signals are presented herein. An example may involve identifying, by a receiver, a particular positioning signal that reflected off a reflecting plane prior to reaching the receiver. The receiver may be in motion. The example may also involve determining a reflected satellite position for a satellite that transmitted the particular positioning signal based on identifying the particular positioning signal. The reflected satellite position may be determined by reflecting a position of the satellite about the reflecting plane. The example may also involve determining a direction vector to the reflected satellite position for the satellite and performing coherent integration over a threshold duration of time to increase a signal to noise ratio for the particular positioning signal based on the direction vector to the reflected satellite position.

A method, apparatus, and computer-readable medium are provided for wireless communication at a Road Side Synchronization Device (RSSD). The RSSD receives, from a first neighbor device, a first Sidelink Synchronization Signal (SLSS). The RSSD synchronizes in time/frequency with the first neighbor device, and transmits a second SLSS. The second SLSS is based on a synchronized timing and a synchronized frequency with the first neighbor device.

A method of enhancing the accuracy of a navigation system which includes a GNSS receiver. The method includes receiving navigation signals from at least one GNSS constellation and a LEO constellation. Position estimates will be made through implementation of a filter using successive readings of pseudoranges and carrier-phase measurements from the GNSS constellation and carrier-phase measurements from the LEO constellation.

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.

An aircraft receives pseudorange input from a plurality of satellites of an augmentation system. Each pseudorange input includes a precise position solution and error data. The aircraft receives a high frequency measurement from an inertial navigation system. The aircraft applies the precise position solution, error data, and high frequency measurement to a set of parallel Schmidt extended Kalman filters to produce a corrected position solution and integrity data. The aircraft applies the integrity data to a receiver autonomous integrity monitoring system to produce a protection level for the corrected position solution. The aircraft performs an aircraft operation using the corrected position solution and protection level.

A tightly combined GPS/BDS carrier differential positioning method is provided. The method comprises: using a GPS as a reference system to construct a GPS intra-system double-difference ionosphere-free combination model and a GPS/BDS inter-system double-difference ionosphere-free combination model; selecting a BDS reference satellite to re-parameterize an ambiguity of a GPS/BDS inter-system double-difference ionosphere-free combination and perform parameter decorrelation, estimating an ionosphere-free combination carrier differential inter-system bias in real time, and performing reference conversion on the ionosphere-free carrier inter-system bias to realize a continuous estimability of the ionosphere-free carrier differential inter-system bias in necessary; and finally, using ambiguity-fixed base carrier observations to form the ionosphere-free combination and performing tightly combined positioning on the inter-system double-difference ionosphere-free combination based on the estimated ionosphere-free carrier difference inter-system bias.