An ephemeris data processing method, electronic device and storage medium are disclosed, which relate to the fields of satellite communication, positioning, and navigation. The ephemeris data processing method includes: receiving raw ephemeris data from a plurality of user devices; analyzing the raw ephemeris data according to an analysis mode of each user device and a satellite ephemeris protocol of each galaxy. According to embodiments of the present disclosure, ephemeris data of a plurality of user devices can be centrally processed and stored, thereby storing more complete ephemeris data and then providing more abundant ephemeris data.

A signal receiver method to achieve satellite position fix by improving satellite orbit prediction includes: acquiring satellite signals and navigation data and calculating a position solution, which includes predicting the state or orbit of one or more satellites. The prediction includes using a model of the solar radiation pressure operating on a selected satellite. The method includes: expressing the model of the solar radiation pressure operating on the satellite as a Fourier series having a frequency function of the satellite-Earth-Sun angle and having respective Fourier coefficients, calculating position approximation errors comparing true satellite positions at given time points against predicted satellite positions at corresponding time points, estimating said Fourier coefficients as a function of the position approximation errors, and using the estimated Fourier coefficients in the model of the solar radiation pressure operating on the satellites as a Fourier series used in the model to predict the state or orbit of the satellite.

A signal receiver method to achieve satellite position fix by improving satellite orbit prediction includes: acquiring satellite signals and navigation data and calculating a position solution, which includes predicting the state or orbit of one or more satellites. The prediction includes using a model of the solar radiation pressure operating on a selected satellite. The method includes: expressing the model of the solar radiation pressure operating on the satellite as a Fourier series having a frequency function of the satellite-Earth-Sun angle and having respective Fourier coefficients, calculating position approximation errors comparing true satellite positions at given time points against predicted satellite positions at corresponding time points, estimating said Fourier coefficients as a function of the position approximation errors, and using the estimated Fourier coefficients in the model of the solar radiation pressure operating on the satellites as a Fourier series used in the model to predict the state or orbit of the satellite.

A positioning control apparatus is provided, which includes: an acquisition unit that acquires predictive ephemeris data from outside of the positioning control apparatus; a setup unit that sets up, based on a predetermined condition different from an expiration date that has been set up in the predictive ephemeris data, a switching condition as to whether the predictive ephemeris data acquired by way of the acquisition unit should be used for positioning calculation to calculate location information that indicates a current location of the positioning control apparatus; and a control unit that switches, based on the switching condition that has been set up by way of the setup unit, whether the predictive ephemeris data should be used for the positioning calculation.

A positioning control apparatus is provided, which includes: an acquisition unit that acquires predictive ephemeris data from outside of the positioning control apparatus; a setup unit that sets up, based on a predetermined condition different from an expiration date that has been set up in the predictive ephemeris data, a switching condition as to whether the predictive ephemeris data acquired by way of the acquisition unit should be used for positioning calculation to calculate location information that indicates a current location of the positioning control apparatus; and a control unit that switches, based on the switching condition that has been set up by way of the setup unit, whether the predictive ephemeris data should be used for the positioning calculation.

An apparatus computes first locations of a satellite for several points in time based on a first set of parameters values broadcast by the satellite for a first validity period and second locations of the satellite for these points in time based on a second set of parameter values with associated second validity period. The first or second validity period is extended by an equation of motion, which includes forces acting on the satellite. The apparatus computes a value of an error component for points in time by comparing first with second locations and fits parameter values of a model to the values of the error component to obtain a model of a time-evolution of values of the error component. The apparatus provides the model of the time-evolution as a basis for a correction of locations of the satellite that are computed based on the first set of parameter values.

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.

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.

The present invention provides a method and apparatus for supporting estimation of inter-satellite link acquisition times in a satellite constellation. The method includes computing or generating an indication of a statistical model based on observations for prior link acquisition times. The method further includes communicating an indication such as a statistical model for link acquisition times or related parameters through a communication network, or a combination thereof. The indication may be communicated using one or more transmission techniques or protocols, such as flooding, a link state protocol or gossip protocol. Based on the disseminated indication, future link acquisition times can be predicted by satellites in the satellite constellation. Embodiments of the invention use a statistical-based computation approach, such as regression modelling or random variable modelling, to estimate link acquisition times or associated estimation parameters. The estimates or associated estimation parameters may then be disseminated through the constellation.

A method for providing integrity information for checking atmospheric correction parameters for the correction of atmospheric disturbances for satellite navigation for a vehicle includes reading state signals relating to a state of an atmosphere between at least one satellite receiver and at least one satellite of the at least one satellite receiver. Each state signal represents certain state data that are transmitted between a satellite and a satellite receiver. The method further includes using at least one satellite signal and that are dependent on a state of the atmosphere between the satellite and the satellite receiver. The method further includes determining the integrity information using the state data. A variation of the state data against time is analyzed.