34 results about "Satellite broadcasting" patented technology

The invention relates to a remote sensing satellite broadcast data processing method and system, and belongs to the technical field of satellite remote sensing data processing, and the method comprises the steps: S1, receiving remote sensing satellite broadcast data, and verifying and storing a data packet; s2, the data packet is analyzed, a remote sensing image is generated, and the remote sensing image comprises a single slice or an area image formed by splicing a plurality of sub-images; s3, generating a unique orbit number for each orbit remote sensing image; s4, when packet loss occurs in the data transmission process, automatically identifying lost data blocks, and blackening lost parts in the remote sensing image; and S5, distributing the processed remote sensing image and related data to a target user. According to the method, intelligent packet loss processing and a unique track number generation mechanism are introduced into a data processing flow, so that the integrity of the remote sensing image and the convenience of data management are remarkably improved.

This invention relates to a method and system for broadcasting PPP-RTK corrections. The method includes acquiring grid point information; determining correction information according to a dynamic partitioning method based on the satellite's orbital direction, satellite signal coverage area, and the grid point information; the correction information includes a header file, the grid point information, tropospheric corrections, and oblique ionospheric corrections; and uploading the correction information to an uplink station to control satellite broadcasting of the correction information. This invention solves the problems of satellite bandwidth allocation, correction area division, and correction data format encoding for PPP-RTK atmospheric delay corrections broadcast in low-Earth orbit satellite broadcasting areas.

The application discloses a satellite broadcast simulation method, device and equipment and a readable storage medium, and relates to the technical field of satellite communication. The satellite broadcast simulation method comprises the following steps: acquiring navigation message data and enhanced message data; framing the navigation message data and the enhanced message data respectively to obtain navigation signal frames and enhanced signal frames; and modulating the navigation signal frames and the enhanced signal frames simultaneously in response to a timing control signal, and transmitting the modulated navigation signal frames and enhanced signal frames. The application simulates the process of broadcasting navigation signals and enhanced signals by real low-orbit satellites, thereby improving the authenticity of the test environment for the receiving terminal of the low-orbit satellite communication system, and simultaneously modulating based on the timing control signal, thereby avoiding the delay error in the early receiving and framing process and reducing the probability of timing error.

The invention relates to the technical field of satellite communication, in particular to a low-orbit satellite beam self-adaptive acquisition method based on fused double architectures, which comprises the following steps: realizing local clock calibration by locking a high-orbit satellite broadcast channel and acquiring a target low-orbit satellite almanac; a terminal pose and an array surface temperature gradient are acquired in real time by using an inertial measurement unit and a temperature sensor network, and a multi-dimensional physical characteristic tensor is constructed. Then, inputting the feature tensor into a nonlinear compensation model integrating multi-scale cavity convolution and a spatial self-attention mechanism, and reasoning and outputting a phase pre-distortion matrix; and by executing channel-level Hadamard product operation of the pre-distortion matrix and the theoretical pointing matrix, generating a wave control driving matrix and synthesizing a physical receiving wave beam. After a downlink signal is captured, a real Doppler frequency shift residual error is extracted, an error autocorrelation matrix is constructed, and an almanac compensation weight is reversely corrected. According to the invention, through multi-dimensional feature perception and algorithm logic closed loop, robust beam capture is realized.

Embodiments of the present invention relate to a method, computing device, and medium for solar outage prediction and avoidance. The solar outage prediction method includes obtaining the sun's position vector based on satellite broadcasts from the local satellite; obtaining multiple transformation matrices based on the satellite's position, velocity, attitude, and laser payload installation location information, including at least: a first transformation matrix from the inertial frame to the center-of-mass orbital coordinate system, a second transformation matrix from the center-of-mass orbital coordinate system to the satellite's coordinate system, and a third transformation matrix from the satellite's coordinate system to the laser payload's coordinate system, wherein the third transformation matrix is ​​calculated at least based on the laser payload's installation orientation and installation error angle along the three axes of the satellite; and calculating the field-of-view angle between the sun's position vector and the laser payload's line of sight from the local satellite based on the multiple transformation matrices; to determine whether the local satellite has entered the solar outage region. This improves the accuracy of solar outage prediction and enhances the efficiency of inter-satellite communication link recovery after a solar outage.

The application relates to a self-adaptive split federated learning method in an air-ground integrated network, comprising the following steps: a hierarchical training network environment is constructed, and a hierarchical agent and related parameters are initialized; at the beginning of each long cycle, a long cycle agent determines a model split action of each device, and splits a global model into a device end submodel and a server end submodel; model parameters and split instructions are distributed through high-orbit satellite broadcasting, and each device loads a corresponding submodel with a ground station; in each short cycle, a short cycle agent generates a resource scheduling decision, realizes multi-device parallel split training, and updates the short cycle agent; at the end of the long cycle, a new global model is generated through weighted aggregation and the long cycle agent is updated through a high-orbit satellite. By adopting the technical scheme, the conflict between limited device computing power and large model training can be solved, training delay can be reduced, transmission reliability can be improved, and self-adaptive optimization of a training strategy and system scalability in a dynamic network can be realized.

Embodiments of the application disclose a paging method and related device, storage medium and computer program product. A first network element is co-located with a satellite gateway station. The paging method applied to the first network element comprises: receiving system messages broadcast by each satellite of N satellites; wherein N is a positive integer, and the N satellites are over-the-top satellites connected with the satellite gateway station; for each satellite of the N satellites, a corresponding set of satellite ephemeris parameters is parsed from the respective system message, and N sets of satellite ephemeris parameters are obtained; in response to a reporting instruction sent by a first core network, M sets of satellite ephemeris parameters currently effective in the N sets of satellite ephemeris parameters are reported to the first core network, so that the first core network determines a first satellite providing services for a non-terrestrial network (NTN) terminal from M satellites corresponding to the M sets of satellite ephemeris parameters, and pages the NTN terminal; wherein M is a positive integer, the first core network is a core network to which the NTN terminal belongs, and the NTN terminal is a call object of a ground cellular terminal.

The embodiment of the invention provides a synchronization method and device for an inbound reference time mark of an RDSS receiver, the receiver and a storage medium. The method comprises the following steps: determining a timing interruption time difference by acquiring tracking channel observed quantity data, correcting a timing interruption triggering moment to be aligned with an outbound reference time mark, acquiring an outbound frame number in satellite broadcast, and maintaining outbound frame time count and an inbound reference time mark in each timing interruption; therefore, the inbound response time can be accurately determined, the transmitting module is controlled to transmit the inbound signal on time, and the technical problem that the inbound response transmitting time sequence is inaccurate due to the fact that timing interruption and outbound reference time marks are difficult to align and intra-frame time maintenance is easy to drift in existing counting is solved.

The invention discloses an AEB control method based on cooperation of a low-orbit satellite and the Internet of Vehicles, and relates to the technical field of intelligent traffic and vehicle safety control, and the method comprises the steps: enabling an intelligent vehicle to collect the state data of the vehicle and the information of surrounding vehicles through a low-orbit satellite communication module, and uploading the data to the low-orbit satellite; the low-orbit satellites group and summarize vehicle data in a similar geographic area, construct a dynamic map of vehicles in the area, screen vehicle clusters needing information intercommunication, generate scheduling information and issue the scheduling information to the vehicles, and the edge calculation unit sends a brake triggering instruction to the AEB control unit when judging that the risk reaches a preset safety threshold. According to the AEB system, beyond-visual-range data intercommunication is achieved through the low-orbit satellites, sight shielding and distance limitation of traditional vehicle-mounted sensing are broken through, and the risk identification precision and response timeliness of the AEB system are improved.

The invention discloses a coding time slot random access method based on a rate division multiple access transmission technology, which solves the problems of low resource utilization rate and low system throughput under high load in the prior art, realizes terminal adaptive transmission, remarkably improves the system resource utilization rate, optimizes the throughput performance, and improves the system performance. A stable and reliable communication effect is kept in a high-load scene; the method comprises the following steps that: a terminal preprocesses a data packet according to an optimal strategy of satellite broadcast to form a plurality of data packet groups, and randomly selects a transmission power level and a segmentation time slot through a power hierarchical distribution mode to send the data packet groups to a satellite; and the gateway performs iterative interference elimination decoding on the received signal, analyzes the information of each terminal, calculates the estimated throughput of different transmission strategies based on the real-time load, and dynamically selects and broadcasts a new optimal strategy. And the terminal updates the transmission parameters according to the data and periodically executes the process until all the data are transmitted.

A pay television satellite broadcast includes validation data that can be used to validate authenticity of live global positioning system (GPS) data. The validation data may be included within entitlement messages and encrypted for security and selective reception by authorized receivers. A navigation system may compute checksums of received live GPS data and compare with the validation data for a match. A decision about whether or not to use the live GPS data may be taken based on whether or not the computed checksums match the validation data received via the pay television satellite broadcast signals.

The embodiment of the invention provides a satellite switching method, a communication system, terminal equipment, a satellite and a related device, and relates to the technical field of communication. The method includes a source satellite broadcasting a first signal. A terminal device receives a first signal from a source satellite. The first signal comprises beam range information of the source satellite and target satellite information. And the terminal equipment sends a first scheduling request (SR) to the target satellite. The SR is used for satellite switching. The first compensation parameter for time-frequency pre-compensation of the first SR is determined based on the first position of the terminal device and the target satellite information. The first position relates to beam range information, height, and synchronization parameters of the source satellite, irrespective of GNSS positioning and SSB of the target satellite. In a terminal equipment hard handover scene or a scene in which the terminal equipment cannot perform GNSS positioning (such as a GNSS stop scene), the success rate of satellite handover of the terminal equipment can be improved.

The application provides a target monitoring method, system and medium, wherein the method comprises: after a second satellite receives a remote sensing imaging task broadcast by a first satellite, determining whether an attitude condition corresponding to the remote sensing imaging task is met, the attitude condition being used to indicate that a position attitude of the second satellite can execute the remote sensing imaging task earliest among m satellites; when it is determined that the attitude condition is met, executing the remote sensing imaging task to obtain a remote sensing image of a target area, and performing on-orbit identification on the remote sensing image to obtain corresponding identification information; when the identification information meets a preset alarm condition, generating a corresponding early warning message and broadcasting the early warning message to the space-based system, so as to send the early warning message to a ground station in the territory for processing by a third satellite in the space-based system. In this way, technical problems in the prior art, such as the need for occupying more transmission arc segment resources for a remote sensing image, long transmission time consumption and reduced timeliness of target monitoring, can be solved.

The application provides a low-orbit satellite broadcast ephemeris parameter robust determination method and system. It relates to the field of satellite navigation technology. The method comprises: performing multiple collinearity analysis on the designed broadcast ephemeris model in the satellite precise ephemeris data to be fitted to determine whether there is a multiple collinearity relationship; when the multiple collinearity relationship exists, determining the generalized ridge estimation step diagonal matrix prior value according to the satellite precise ephemeris data and the designed broadcast ephemeris parameter; setting a search interval and fitting the broadcast ephemeris parameter by generalized ridge estimation step by step according to the generalized ridge estimation step diagonal matrix prior value, calculating the fitting residual, obtaining the generalized ridge parameter value corresponding to the optimal residual after the search in the search interval is completed, and fitting the broadcast ephemeris parameter according to the generalized ridge parameter value. The application solves the problem that the least square equation is seriously ill due to improper design of the broadcast ephemeris model, which further leads to fitting failure.

The invention relates to a digital regeneration-based static orbit satellite broadcast forwarding system, which is characterized in that a demodulation receiver receives uplink data of a ground station through a receiving antenna, completes data demodulation and transmits the data to a rear-end data processor; the data processor judges whether the uplink data needs to be fused with the real-time remote sensing data or not according to the identifier of the uplink data, and if the uplink data is the data needing to be fused, fusion processing of the uplink data and the remote sensing data is completed in the data processor; if the uplink data does not need to be fused, directly storing the uplink data into the solid-state memory; reading broadcast distribution data from the solid-state memory, and forwarding the broadcast distribution data to the broadcast modulator through the data processor; the broadcast modulator encodes and modulates broadcast downlink data into a radio frequency signal, and the radio frequency signal is broadcast and distributed to a designated area through the transmitting antenna after being subjected to filtering and power amplification. And the use efficiency of broadcast distribution of the geostationary orbit remote sensing satellite is effectively expanded.

The embodiment of the invention provides a positioning method and device based on an unmanned aerial vehicle, equipment and a storage medium. The method comprises the following steps: acquiring ephemeris information, correction information, first observation information and second observation information of a preset satellite; the ephemeris information represents ephemeris parameters of preset satellite broadcast; the correction information represents deviation data broadcasted by the preset satellite-based enhancement system and used for correcting ephemeris parameters of the preset satellite; the first observation information represents a carrier phase observation value of a preset satellite acquired by a preset base station; the second observation information represents a carrier phase observation value of a preset satellite acquired by the unmanned aerial vehicle; determining coordinate information of the preset satellite according to ephemeris information and correction information of the preset satellite; the coordinate information represents the position, collected by the unmanned aerial vehicle, of a preset satellite in a three-dimensional space; and determining the position information of the unmanned aerial vehicle according to the coordinate information of each preset satellite, the first observation information and the second observation information. The method is used for improving the positioning accuracy of the unmanned aerial vehicle.

The present application provides a communication method, which can be applied to satellite communication. The method comprises: a first communication device sending a first ephemeris, wherein the first ephemeris is an ephemeris broadcast by at least one satellite and received by the first communication device; then receiving a constellation ephemeris from a second communication device, the constellation ephemeris comprising a second ephemeris of each satellite among a plurality of satellites, wherein the second ephemeris of a first satellite is determined by the second communication device on the basis of at least one first ephemeris of the first satellite; and then, selecting a satellite suitable for access, reselection, or handover on the basis of the constellation ephemeris. In the solution provided by the present application, because the constellation ephemeris comprises the second ephemerides of a large number of satellites, the accuracy of satellite selection by the second communication device can be improved.

The application provides a BDS-3 three-frequency pseudorange single-point positioning method based on DCB correction, which comprises the following steps: obtaining an original observation data file, a satellite broadcast ephemeris file and a differential code bias correction file; performing smoothing filtering inspection and gross error elimination processing on the original observation data to obtain processed satellite observation values; performing three-frequency ionosphere elimination combination on the Beidou B1I / B2a / B3I and B1C / B2a / B3I satellite observation values, and performing three-frequency differential code bias correction to obtain modified three-frequency combined observation values; calculating satellite clock difference correction, troposphere error correction, earth rotation correction and relativistic effect correction; using various error correction values and the modified three-frequency combined observation values to construct a three-frequency ionosphere-eliminated combined pseudorange observation equation, and then obtaining a user final spatial rectangular coordinate system positioning result, so that the multi-frequency pseudorange single-point positioning precision of the user end is improved.

The embodiment of the invention relates to a method, computing equipment and a medium for predicting and avoiding solar radiation. The sunshine prediction method comprises the following steps: acquiring a position vector of the sun based on satellite broadcast of a satellite; the method is based on position information, speed information, satellite attitude information and laser load installation position information of a satellite body. The obtained multiple conversion matrixes at least comprise a first conversion matrix from an inertial system to a centroid orbit coordinate system, a second conversion matrix from the centroid orbit coordinate system to a satellite body coordinate system and a third conversion matrix from the satellite body coordinate system to a laser load coordinate system; the third conversion matrix is calculated at least based on the installation direction and the installation error angle of the laser load on the three axes of the satellite body; calculating a view field included angle between the position vector of the sun and the laser load visual axis of the satellite based on the plurality of conversion matrixes; and determining whether the satellite enters the sunshine area or not. Therefore, the method can improve the precision of the sun-on prediction, and improves the recovery efficiency of the inter-satellite communication link after the sun-on is finished.

This application provides a method, apparatus, receiver, and storage medium for synchronizing the incoming reference time standard of an RDSS receiver. The method includes: determining the timing interrupt time difference by acquiring tracking channel observation data and correcting the alignment of the timing interrupt trigger time with the outgoing reference time standard; simultaneously acquiring the outgoing frame number from the satellite broadcast and maintaining the outgoing frame time count and the incoming reference time standard during each timing interrupt; ensuring that the incoming response time can be accurately determined and controlling the transmission module to send the incoming signal on time; and solving the technical problems of inaccurate incoming response transmission timing caused by difficulty in aligning the timing interrupt with the outgoing reference time standard and easy drift in intra-frame time maintenance in existing counting methods.

The application provides an early warning customized service system based on cloud and local end cooperation, the system comprises: a basic resource layer for integrating cloud computing resources and local hardware resources; a data exchange layer for accessing multi-source heterogeneous meteorological data of satellite broadcast, international meteorological exchange system and local observation system; a digital base layer for cleaning, fusing, storing and managing the gathered data; an algorithm processing layer for identifying meteorological risks and generating early warning decision results; an integrated platform layer for encapsulating computing, data and algorithm capabilities as unified services; a business application layer for realizing comprehensive monitoring, forecast analysis and early warning information release based on the services. The application has the beneficial effects that through the cooperation and deep customization design of the cloud and the edge, the data transmission minimization, the on-demand utilization of computing resources and the efficient, flexible and accurate improvement of early warning capability are realized while ensuring the business continuity in extreme scenarios.

The application discloses a kind of based on low inclination low-orbit satellite constellation's internet of things terminal direct connection satellite communication method and system, belong to satellite communication technical field, including: according to the orbit height of low-orbit satellite and inclination division ground coverage area, and determine terminal attribution.Satellite broadcast ephemeris, terminal receives after combining own position carries out orbit prediction, generates and corrects coverage prediction time series, according to this in window outside hibernation, window before wake up.According to service type and electric quantity after wake up, execute hierarchical wake-up timing.In wake-up period, calculate Doppler shift, and according to coverage area type selection compensation strategy to complete frequency synchronization.Meanwhile, satellite determines beam pointing angle according to subsatellite point latitude table, so that beam center points to target grid.After completing frequency synchronization and beam covers terminal, terminal executes data transmission.The application realizes low-power consumption, high reliability, low-cost low-orbit satellite internet of things terminal direct connection satellite communication.

The application provides a satellite broadcast audio clock synchronization method, device, medium and product, relates to the technical field of digital clock synchronization, and the method comprises the steps of extracting a PCR time stamp from a satellite TS stream and decoding PCM audio data; calculating the difference between the PCR time stamp and a local numerical control oscillator counter as a time error value; inputting the time error value into a PI controller for proportional integral operation, and performing smoothing processing on the output of the PI controller through an IIR low-pass filter to obtain a frequency adjustment amount; writing the frequency adjustment amount into the local numerical control oscillator to adjust the frequency, so that the restored PCR clock signal is obtained through convergence; phase-locked frequency division of the restored PCR clock signal to generate an audio output clock signal, and synchronization output of the PCM audio data is realized based on the audio output clock signal. The problem that loud noise and broken noise are prone to occurring during master-backup switching due to large clock restoration jitter when the existing satellite broadcast receiving device operates independently without external synchronization source is solved.

The invention discloses a low-orbit satellite communication method based on information on demand, which comprises the following steps: S1, a low-orbit satellite dynamically pre-judges an effective on-demand service window according to an orbit ephemeris of the low-orbit satellite and a preset communication duration threshold value, and pre-configures a communication link parameter of each window, the method has the beneficial effects that through a three-in-one mechanism of dynamic window activation, on-satellite intelligent scheduling and satellite-ground cooperative transmission, the defects (short overhead time and discontinuous link) of the low-orbit satellite are converted into controllable resources; valuable time windows are intelligently selected for service so as to save energy, and reliable transmission of large files can be completed through multiple transit opportunities like a relay match. The problems that a traditional satellite broadcast mode is one-way and fixed in content, and a traditional satellite communication mode is high in resource occupation and difficult to support mass non-real-time big data transmission are solved, and a satellite can concurrently provide personalized and on-demand data services for mass users like ground internet services.

This application provides a satellite handover method, communication system, terminal device, satellite, and related apparatus, relating to the field of communication technology. The method includes a source satellite broadcasting a first signal. The terminal device receives the first signal from the source satellite. The first signal includes beam range information of the source satellite and target satellite information. The terminal device sends a first scheduling request (SR) to the target satellite. The SR is used for satellite handover. The first compensation parameter for time-frequency pre-compensation used in the first SR is determined based on the first location of the terminal device and the target satellite information. The first location is related to the beam range information, altitude, and synchronization parameters of the source satellite, but is independent of GNSS positioning and the target satellite's SSB. This method can improve the success rate of satellite handover for the terminal device in hard handover scenarios or in scenarios where the terminal device cannot perform GNSS positioning (such as GNSS-inaccessible scenarios).

The invention discloses a credit-based random access method in a satellite network, solves the problem of contradiction between time-sensitive service guarantee and system efficiency, and belongs to the technical field of data communication transmission. The random access method comprises the following steps: S1, determining a signaling structure which comprises a BCH broadcast message and a preemption request signal; s2, a satellite initializes system parameters, and broadcasts the parameters and the current frame structure to all terminals; s3, the satellite periodically and dynamically adjusts the size proportion of the CR area and the GR area through the real-time network load and the time-sensitive service volume, and notifies the terminal through broadcast signaling; s4, each terminal maintains a credit counter in a local memory, and credit value updating is driven by a terminal local clock and the received satellite broadcast parameters; before a terminal sends, a physical layer continuously monitors and preempts a channel; and S5, when the terminal has data to be sent, a corresponding service process is adopted according to the service type.

The application discloses a Beidou-3 space signal ranging precision improvement method and device based on an Informer model, and belongs to the technical fields of satellite navigation, deep learning and satellite positioning and orbit determination. The method acquires orbit error and clock error history data of broadcast ephemeris of Beidou-3 satellites and external physical characteristic data; performs feature importance sorting and correlation analysis, and screens physical characteristics strongly correlated with the orbit error and the clock error; a multivariate time series prediction model fusing the error history data and the external physical characteristics is constructed based on the Informer model, long sequence error prediction is realized through a ProbSparse Attention mechanism and a generative decoder; a self-defined loss function considering a coupling relationship between the orbit error and the clock error is used for model training; and the predicted error is compensated to original broadcast ephemeris to generate high-precision ephemeris products. The application can significantly improve space signal ranging precision and improve satellite positioning performance.

The application belongs to the technical field of satellite navigation and positioning, and provides a navigation and positioning method based on a lunar orbit receiver, so as to solve problems such as time synchronization error and positioning accuracy of the lunar orbit receiver in the positioning process. The application introduces a method for bidirectional time synchronization with ground communication equipment, so that the lunar orbit receiver can accurately calculate the clock difference with the GPS system, thereby overcoming the time synchronization error caused by signal delay in the prior art, and effectively improving the positioning accuracy. Meanwhile, the lunar orbit receiver also receives the GPS satellite broadcast signal, and combines the clock difference to perform real-time positioning calculation, so as to ensure accurate positioning in the lunar orbit.

This invention discloses a satellite IoT terminal control method and system based on GNSS-free Doppler positioning and dynamic hibernation. The method includes: determining the terminal's operating mode based on original geographic location coordinate data and original satellite ephemeris data stored in the terminal's local memory; when any data is missing or invalid, the control terminal enters a satellite scanning mode, intermittently capturing satellite broadcast frames within a receiving window, and sending uplink signals after successful capture; obtaining geographic location coordinates and ephemeris data based on the Doppler frequency shift calculation feedback from the satellite system using the uplink signals; when all data is valid, the control terminal enters a satellite tracking mode, calculating the satellite transit time based on the original geographic location coordinate data and original satellite ephemeris data, and entering a deep hibernation state during non-transit periods, waking up before the transit time arrives to perform data communication. This invention is suitable for application scenarios with low operating frequency and limited power consumption.

The invention belongs to the technical field of satellite navigation and positioning, and provides a navigation and positioning method based on a lunar orbit receiver, so as to solve the problems of time synchronization error, positioning precision and the like of the lunar orbit receiver in the positioning process. And the lunar orbit receiver can accurately calculate the clock error with the GPS system, so that the time synchronization error caused by signal delay in the existing method is overcome, and the positioning accuracy is effectively improved. Meanwhile, the lunar orbit receiver can also receive GPS satellite broadcast signals, real-time positioning calculation is carried out in combination with clock correction, and it is ensured that the accurate position is obtained in the lunar orbit.