438 results about "Low earth orbit" patented technology

The invention belongs to the technical field of satellite orbit prediction, and provides a low-orbit satellite orbit state prediction method based on artificial intelligence, which comprises the following steps of: dividing step lengths of a predicted orbit according to a time window, calculating a resultant acceleration of each step length, performing stress input on an initial position and speed, and obtaining a nominal orbit state sequence; forming an augmented state vector with aerodynamic synthesis parameters; inputting a time sequence neural network model, and performing rolling updating on the augmented state according to the output; obtaining an original standard deviation through mapping by using uncertainty measurement, calculating a standardized residual error, solving a right side weighted quantile according to a normalized time weight, comparing the right side weighted quantile with a preset threshold value, and carrying out adaptive deviation adjustment; and calculating risk measurement by using the acquired data, comparing the risk measurement with a set threshold value and a priority rule, automatically executing a judgment action on the risk measurement, recording a trigger reason and the judgment action, and updating parameters in the time sequence neural network model.

The invention provides a low-orbit satellite communication terminal network performance dynamic tuning method and system, and relates to the technical field of low-orbit satellite communication. Comprehensive data such as relative movement of a satellite and a terminal and signal transmission loss are acquired; preprocessing the integrated data, inputting the preprocessed integrated data into a time sequence prediction model containing LSTM and Transform, generating a signal quality and intensity index sequence and a link stability level in a future preset time window, and carrying out dynamic optimization based on the generated indexes, including adjusting a terminal modulation mode according to the signal quality; combining the link stability and the signal strength to aggregate the link, and optimizing the switching opportunity and path; allocating resources according to the signal strength and the service characteristics; and optimizing the energy consumption according to the relative motion and the business characteristics. Through accurate prediction and multi-dimensional adjustment and optimization, the communication efficiency and reliability of the low-orbit satellite communication terminal network are improved, energy consumption and delay are reduced, and good communication quality is guaranteed.

The invention discloses a double-layer ionosphere modeling method fusing low-orbit satellite data, which comprises the following steps of: preprocessing ground-based GNSS (Global Navigation Satellite System) data to obtain an STEC expression of a ground-based GNSS; preprocessing the precise orbit determination data of the low-orbit satellite to obtain a VTEC expression of the precise orbit determination data; obtaining an electron density profile product of the radio occultation of the low-orbit satellite, and obtaining VTEC of the radio occultation through profile integration; using two groups of spherical harmonic coefficients to express global VTEC distribution, and constructing an observation equation; and determining weights of different types of data by using Helmert variance component estimation, and finally solving to obtain two groups of spherical harmonic coefficients to generate an ionized layer grid product. Projection errors caused by vertical layering in a traditional single-layer model are weakened, meanwhile, precise orbit determination data and radio occultation data of a low-orbit satellite are combined, the problem that ionosphere TEC cannot be correctly layered in a double-layer model is solved, data of areas where GNSS tracking stations are sparsely distributed are supplemented, and the reliability of the GNSS tracking stations is improved. Therefore, a global ionosphere model with higher precision is obtained.

The invention provides a low-earth-orbit satellite global beam position distribution and scheduling system based on deep reinforcement learning, and the system comprises a low-earth-orbit satellite scene modeling beam position distribution module which is used for constructing a low-earth-orbit satellite communication scene and completing the global beam position division. A satellite constellation configuration and orbit parameters are set, global beam positions are divided based on a spherical network, a beam ground projection model and a user system model are established, and a scene basis and a beam position division basis are provided for beam resource scheduling; the deep reinforcement learning beam resource scheduling module is used for realizing intelligent allocation scheduling of beam resources, establishing a decision system based on a Markov decision process by constructing a beam resource allocation model, extracting features through a state space model, performing time sequence modeling, and optimizing a scheduling strategy based on deep reinforcement learning. And dynamically matching the user demand and the beam resource. Therefore, dynamic optimization of low-orbit satellite beam resources is realized, the resource utilization rate is improved, and the communication requirements of users are efficiently met.

The invention discloses an urban canyon positioning method and system fusing GNSS, vision and low orbit satellites, GNSS signals and images near a visual sign are collected in an urban canyon to serve as mapping points, and sign angular point coordinates are recorded; and analyzing to obtain a GNSS latitude and longitude list corresponding to each mark, and extracting LoFTR feature descriptors and storing the LoFTR feature descriptors in a map database. During positioning, firstly performing rough matching with the current position through the KNN, and then realizing fine positioning in the candidate area through LoFTR feature matching and homography matrix calculation; and if the matching fails, calculating a joint confidence coefficient based on the satellite PDOP / number, and estimating the current position through dynamic weighting by fusing Kalman filtering with a visual odometer. According to the method, a two-stage positioning strategy is adopted, GNSS and visual information are preferentially used for high-precision matching positioning, a fusion positioning mechanism based on low-orbit satellite joint confidence is started after failure, and the matching success rate and the positioning precision under the complex visual condition are improved.

The invention discloses a service scheduling method and system for a photoelectric hybrid low earth orbit satellite network, and relates to the technical field of satellite communication and network resource management.The method comprises the steps that the photoelectric hybrid low earth orbit satellite network is constructed, and topological information, node information and a to-be-scheduled service set of the photoelectric hybrid low earth orbit satellite network are obtained; establishing a mixed integer linear programming model containing node selection constraint, service scheduling sequence constraint and routing constraint by taking the minimum weighted sum of the total service completion energy consumption and the total service completion time as a target; in order to solve the problem of high model complexity, a heuristic algorithm based on simulated annealing is designed, and efficient solution is carried out by iteratively optimizing a scheduling sequence and a routing path of a service; and finally, implementing service scheduling according to the obtained optimal scheduling scheme. According to the method, heterogeneous characteristics of the photoelectric nodes and link resource conflicts are fully considered, dynamic balance of energy consumption and time delay is achieved, network energy efficiency and business service quality are remarkably improved, and the method is suitable for efficient operation of large-scale low-orbit satellite constellations.

The invention discloses a frequency offset estimation method and device, electronic equipment and a storage medium, and relates to the technical field of communication. The method comprises the following steps: receiving a baseband spread spectrum signal from a low earth orbit satellite to obtain a received signal; performing segmented sweep frequency compensation on the received signal to obtain a compensated measured signal; despreading and descrambling the compensated measured signal by using prior information determined from the received signal, and completing coarse frequency offset estimation on the measured signal despread and descrambled for the first time; and de-spreading and descrambling the signal data after the coarse frequency offset estimation again, and finishing fine frequency offset estimation on the signal data after the second time of de-spreading and descrambling. According to the invention, prior information is introduced to directly lock and track a specified target beam signal, so that the directionality and efficiency of measurement are remarkably improved; by designing a low-complexity signal processing flow, the algorithm burden can be remarkably reduced, it is ensured that adjacent satellite beam frequency offset estimation is rapidly completed in service proceeding, and the real-time requirement of seamless switching is met.

A method and system for low Earth orbit (LEO) satellite multiple access and communication using grating lobes is disclosed. The method may include: acquiring ephemeris data for a plurality of LEO satellites; predicting an orbital trajectory for each of the plurality of LEO satellites based on the ephemeris data; selecting target satellites using the predicted orbital trajectories; adjusting an antenna array to form grating lobes in the directions of the selected target satellites; and transmitting and receiving data with the target satellites using the adjusted antenna array.

The invention provides an integrated antenna integrating Beidou, low-orbit and Tiantong satellite communication and high-precision navigation positioning. A low-orbit satellite microstrip antenna, a GNSS high-precision microstrip antenna, a Tiantong microstrip antenna and a Beidou short message microstrip antenna are sequentially stacked on the upper surface of a PCB in a conical mode. A shielding cover is arranged on the lower side of the PCB; antenna radiation patches of the low-orbit satellite microstrip antenna are arranged on the outer edges of the upper surface and the lower surface of the low-orbit satellite antenna substrate and are not covered by the GNSS high-precision microstrip antenna; circuits of the low-orbit satellite microstrip antenna and the sky-pass microstrip antenna are arranged on the upper surface of the PCB circuit substrate. And circuits of the GNSS high-precision microstrip antenna and the Beidou short message microstrip antenna are arranged on the lower surface of the PCB. According to the invention, the four-in-one combined design of the antenna, the low-orbit satellite antenna, the Beidou short message antenna and the high-precision navigation antenna is adopted, so that the problem of performance insufficiency when each antenna is used independently is solved, complementation among the antenna, the low-orbit satellite antenna, the Beidou short message antenna and the high-precision navigation antenna is realized, and the cost is reduced; the electromagnetic compatibility between the antennas is improved through frequency band and polarization isolation design, and the stability of a communication link is guaranteed through interference resistance of the peripheral low-orbit satellite antenna.

The invention provides a low-orbit satellite planning method which can be applied to the technical field of satellite observation task planning. The method comprises the following steps: predicting a potential activity area of a target in a planning time interval based on multi-satellite collaborative observation information; mesh generation is carried out on the potential activity area, and a target motion potential area mesh set is constructed; calculating the existence probability of the target in each grid; selecting satellite resources meeting conditions, and determining available satellites in combination with the observation time interval and the potential activity area; determining an intersection part of a satellite observable area and a potential activity area, and constructing a satellite candidate observation area set; calculating a profit value of each candidate observation area based on the existence probability of the target in each grid and the coverage condition of the satellite candidate observation area; selecting the satellite observation area strip with the maximum profit value through iterative calculation, and obtaining the optimal solution of the multi-satellite observation profit; and generating a multi-satellite collaborative observation planning scheme according to all the determined satellite observation areas.

The invention relates to an unmanned aerial vehicle high-precision positioning method based on micro-centimeter space low-orbit constellation and Beidou PPP-B2b fusion enhancement, and the method comprises the steps: obtaining a precise orbit correction number and a precise clock correction number of a GPS and a BDS system based on a Beidou PPP-B2b signal; calculating a precise orbit and a precise clock error of the GNSS satellite based on the precise orbit correction and the precise clock error correction; on the basis of the precise orbit and the precise clock error of the GNSS satellite, an observation value of a micro-centispace low-orbit satellite is fused, and a GNSS / LEO combined PPP observation model is constructed; and based on extended Kalman filtering, precise point positioning calculation is carried out on the GNSS / LEO combined PPP observation model, and the real-time high-precision position of the unmanned aerial vehicle is obtained. According to the invention, the real-time high-precision position of the unmanned aerial vehicle can be rapidly and stably obtained, and a reliable position reference is provided for autonomous operation of the unmanned aerial vehicle in a network-free environment.

The present invention relates to the technical field of communications, and provides a 6G space-air-ground-sea integrated fusion architecture based on software-defined cloud-edge collaboration, comprising: three tiers of cloud nodes from low to high: an edge cloud, a space-based cloud, and a core cloud; the edge cloud comprises 6G-enabled ships based on software-defined networking and mobile edge computing technologies; the space-based cloud comprises low earth orbit satellites based on software-defined satellite technology and low earth orbit satellite constellations connected by means of an inter-satellite link; the core cloud comprises a space-based 6G core network; the edge cloud, the space-based cloud, and the core cloud follow a task offloading mechanism and an information feedback mechanism; the task offloading mechanism is configured to select, on the basis of characteristics of a task, a cloud node of a target tier for task processing; and the information feedback mechanism is configured such that the cloud node of the upper tier sends feedback information to a cloud node of the lower tier, so as to optimize task processing of the lower tier. The present invention achieves fast and flexible networking for a 6G space-air-ground-sea integrated fusion network, thereby realizing efficient utilization and collaborative management and control of resources.

The invention provides a routing method for a space-ground collaborative low-orbit satellite network, which comprises the following steps that: a space-ground collaborative routing system is established, the space-ground collaborative routing system comprises a ground management and control center and satellite nodes, the ground management and control center is deployed with an experience pool and a joint training engine, and each satellite node is deployed with a local inference engine; before a satellite network is started, a ground management and control center obtains empirical data through self-simulation and stores the empirical data in an empirical pool, and the empirical data comprises original local sub-graph data and interactive experience; the ground management and control center carries out sampling to obtain an experience sample and carries out training on the joint training engine; model parameters obtained through training are compressed and uploaded to all satellite nodes, so that the satellite nodes update a local inference engine; enabling a satellite network, and making a local routing decision by a satellite node to obtain empirical data; and issuing the experience data to the ground management and control center at regular intervals so as to store the data into an experience pool, and returning to the step of training the joint training engine. The method provided by the invention solves the problems of high network dynamics and limited on-satellite resources.

The invention discloses a switching judgment method and device for a low-orbit satellite communication coverage area, and relates to the technical field of satellite communication. The method comprises the following steps: determining a first scanning wave position set of each wave beam of a low-orbit satellite in a current coverage area; determining a second scanning wave position set of each wave beam when the low-orbit satellite migrates to the next coverage area; according to the first scanning beam position set and the second scanning beam position set of each beam, determining a virtual beam position scanning scheme of each beam in a next-hop beam period by using a genetic algorithm; judging whether each beam is subjected to beam migration in a next-hop beam period or not; and migrating the communication coverage range of the low-orbit satellite to the next coverage area in the next-hop beam period under the condition that the number of the beams subjected to beam migration is judged to reach the preset threshold value. Therefore, the method can adapt to the scanning characteristics and coverage requirements of different beams of the multi-beam low-orbit satellite based on the independent judgment logic of each beam.

The invention provides a terminal for low-orbit communication and a signal processing method, which are applied to the technical field of low-orbit communication, and the terminal comprises a terminal antenna, a radio frequency front end, a radio frequency transceiving unit and a baseband signal processing unit. The terminal antenna is responsible for receiving and sending radio frequency signals of an SS frequency band; the radio frequency front end carries out low-noise amplification and filtering on the received signal and carries out power amplification on the sent signal; the radio frequency transceiving unit is used for performing frequency conversion, filtering and analog-to-digital / digital-to-analog conversion on signals; and the baseband signal processing unit performs physical layer and high layer protocol stack processing to demodulate and decode service data and generate a sending signal. Through the integrated design, the terminal can efficiently process radio frequency signals and baseband data in low earth orbit satellite communication, low noise amplification, accurate filtering, efficient frequency conversion and baseband processing of the signals are ensured, and therefore reliable service data transmission is achieved.

The invention relates to the technical field of satellite communication, in particular to a high-gain phased array receiving antenna system for low-orbit satellite communication, which comprises a radiation feed integration module, a beam phase mapping module, a digital beam forming module, a signal amplification module, a protection packaging module and a performance verification module. Stacking strip line feed networks and performing electromagnetic coupling to obtain an initial radiation channel; receiving and analyzing a beam control instruction through an embedded circuit, extracting a target beam pointing angle and mapping the target beam pointing angle into a phase offset; generating a digital phase control word according to the phase offset, and applying the digital phase control word to the radio frequency signal to complete phase calibration; a transistor with a low-noise amplification structure is used for enhancing the calibrated signal energy; the wave-transparent front cover covers the radiator, and the electromagnetic shielding rear cover wraps the internal components to form an assembly in a sealing manner; and verifying the gain and beam switching rate of the assembly in the typical frequency band of the low-orbit satellite. According to the invention, the low-orbit satellite communication signal receiving efficiency can be improved.

In some embodiments, a communications system can include a plurality of low earth orbit (LEO) satellites deployed at different altitudes and configured to communicate with one or more terrestrial devices and with one another. The communications system may further include a plurality of geosynchronous (GEO) satellites deployed above the plurality of LEO satellites. The plurality of LEO satellites may cooperate with one another and with the plurality of GEO satellites to provide a global communication network having redundant point-to-point communication.

The invention discloses a low-orbit satellite Internet of Things terminal baseband communication system, and relates to the technical field of Internet of Things communication. The system comprises a data frame construction unit, a channel regulation and control unit, a bandwidth tracking unit and a decoding correction unit, wherein the data frame construction unit generates an initial frame according to an Internet of Things protocol and dynamically adjusts a frame structure in combination with channel characteristic parameters to complete data packing; and the channel regulation and control unit judges a coding modulation mode according to real-time channel quality and satellite motion parameters, processes a transmitting link, dynamically adjusts the transmitting power of the high-frequency analog signal based on path loss estimation, and finally transmits the high-frequency analog signal through an antenna. At a receiving end, a bandwidth tracking unit adaptively adjusts the loop bandwidth according to the switching characteristic parameter, and dynamically filters the received signal; and the decoding correction unit performs adaptive early stop correction of iterative decoding according to the decoding convergence rate, and finally completes data analysis.

The invention relates to the technical field of spacecraft satellite-ground communication, and provides a low-earth-orbit satellite communication time delay optimization method and system aiming at the defects that a traditional low-earth-orbit satellite communication satellite system and a satellite communication frame have high time delay and poor real-time communication function. The core of the invention comprises three parts: firstly, an efficient receiving and transmitting end coding and decoding technology: a transmitting end adopts a subblock coding technology of a Turbo code; and a receiving end uses an MAX-Log-MAP algorithm to carry out rapid iterative decoding on the word block code of the Turbo code. And secondly, compressing the user data: carrying out lossless compression on the user data and a satellite communication frame header by using Huffman coding, reducing the transmission data volume, improving the data processing speed, and thus reducing the processing time delay. And finally, simplifying the frame header design: optimizing the frame header of the communication frame so as to reduce the total length of each frame. The method is particularly suitable for communication satellites (the orbit height is less than or equal to 1500km) in a low earth orbit.

The invention discloses a port risk management and control system and method based on a low-orbit satellite, and relates to the technical field of port management and control, and the system comprises a stacking estimation module which is used for carrying out the detection region division, shadow recognition and container cell and shadow cell configuration of a high-resolution satellite image of a port container yard, the vertical stacking layer number and the corresponding reliability of each cell are estimated in sequence, and the container occupancy rate and the congestion level of each detection area are calculated after the low-reliability cells are manually corrected so as to generate storage yard congestion training data; and the congestion level identification module is used for constructing a convolutional neural network model based on the congestion training data output by the stacking estimation module, training by taking the cut image of the detection area as input and the congestion level as output, executing end-to-end reasoning on a new satellite image after the model training is completed, outputting the congestion level of each detection area, and outputting the congestion level of each detection area. The method has the characteristic of quantitative analysis.

The invention discloses an LDPC (Low Density Parity Check) code check matrix construction method, which is used for processing a low earth orbit satellite ground foundation zone, and comprises the following steps of: A1, determining degree distribution of a basis matrix under a high code rate by adopting an extrinsic information transfer graph EXIT, and realizing construction of the basis matrix under the constraint of optimal degree distribution through extrinsic information transfer P-EXIT based on a basic model graph; a2, based on the code length and the code rate of FEC coding of the DVB-S2 protocol, determining the size and the expansion factor of a basis matrix corresponding to each code rate; a3, determining a finite field and a generator based on an expansion factor, and constructing a linearly independent shift value row vector and cycle coefficient table; a4, selecting row vectors from the cyclic coefficient table to construct a cyclic shift matrix, and performing short ring identification and elimination on the cyclic shift matrix; and A5, performing matrix hashing on the basis of the basis matrix and the cyclic shift matrix to obtain an LDPC check matrix.

An adaptive satellite routing orchestration system and an adaptive satellite routing orchestration method are provided. Under the low earth orbit satellite network architecture, by the determination of the connection status of the external submarine cable at the location where the ground network access point and the mobile core network are connected to the mobile network, the traffic of the mobile network is guided to the mobile core network via the submarine cable or the traffic of the mobile network is guided to the mobile core network via the low earth orbit satellite network. A computer-readable medium for executing the adaptive satellite routing orchestration method is further provided.

Mitigation of erosive effects of atomic oxygen encountered by telescope systems deployed in low earth orbit (LEO is effected by providing an array of multiple very small projections on the interior surface of an open-ended tubular metering shell extending forwardly from a mirror to be protected. The projections are made of material that is geometrically configured to deflect AO atoms one or more times within the shell at angles that ultimately direct the atoms away from the mirror surface and back out through the forward end of the shell.

This invention discloses a heterojunction low-temperature curing silver paste suitable for space HJT battery applications, its preparation, and its application. The heterojunction low-temperature curing silver paste comprises the following components in parts by weight: 75-92 parts of a first conductive powder, 0.5-5 parts of a second conductive powder, 2.25-9.5 parts of a composite resin system, 0.5-4.8 parts of a blocked isocyanate curing agent, 0.05-0.5 parts of a latent accelerator, 0.2-1.8 parts of a coupling agent, 0.3-1.5 parts of a dispersant, and 1.5-6.4 parts of a solvent; the composite resin system comprises epoxy resin and cyanate ester resin, with a mass ratio of epoxy resin to cyanate ester resin of (2-8):1. The silver paste of this invention can form a dense cross-linked network after curing at 150-250℃, while meeting the low outgassing requirements of materials for spacecraft. It can withstand extreme temperature difference cycles from -196℃ to +150℃ and high-energy particle irradiation environments in space, and is suitable for the preparation of metallized electrodes for HJT solar cells in low Earth orbit and medium-high Earth orbit.

We present a ground-based laser system for searching, ranging, and tracking that actively illuminates small resident space objects (RSOs) in low Earth orbit (LEO) and observes position and transit-time of reflections, enabling orbital custody of most one-to-few centimeter-sized objects. A diode-pumped alkali laser (DPAL) augmented with mode-locking and Q-switching serves as an illuminator and offers exceptionally high spectral brightness due to its output beam's sub-nanosecond pulse duration and picometer-level spectral linewidth. Kilohertz fast-rastering enables interrogations of distinct few-meter-sized sky-patches at megahertz rates. Paired on the observation side with one or more telescopes outfitted with Faraday anomalous dispersion optical filters (FADOFs), image intensifiers, multi-pixel arrays, and nanosecond timing, the combined system could offer nearly background-free discoveries of RSOs every hour, even during daytime. Periodically re-flashing previously discovered objects to maintain orbit custody expends only a small fraction of total observing time.

The invention relates to a low-orbit star network target prediction method based on transfer learning, and belongs to the technical field of detection and tracking. A real target simulation flight path is generated, and spatial position information of the target at each moment is accurately obtained; an observation error conforming to normal distribution is introduced into the simulation data so as to simulate an observation value of a satellite when the target flies, namely, the spatial position information of the observed target at each moment is obtained; a prediction model based on a self-attention mechanism and a feedforward network is constructed, training is carried out, and spatial position information of the target at each moment is predicted; comparing the predicted value with a real track to obtain a compensation value; through iterative correction, a predicted value is gradually close to a real value; outputting target high-precision indication data; the trajectory prediction process is repeatedly executed, and low-orbit star network target prediction is completed; the problems that real satellite trajectory data is difficult to obtain and a corresponding verification method is lacked for trajectory prediction capability simulation verification of a low-orbit star network detection target are solved.

The invention provides a low earth orbit satellite network video code rate determination method and device and electronic equipment. The method comprises the following steps: acquiring link state information of a low earth orbit satellite network link; predicting whether a link reconstruction event occurs at the next moment based on the link state information; and under the condition of predicting that a link reconstruction event occurs in the low earth orbit satellite network link at the next moment, dividing a time domain into independent control intervals, and independently determining the video block code rate at the next moment based on the network state of the independent control interval in each independent control interval. According to the method, the satellite network reconstruction event is predicted, and the video code rate is independently determined in the interval mode in the reconstruction event period, so that the video live broadcast experience quality in the low-orbit satellite network environment is improved.

The invention relates to a dynamic self-adaptive communication, sensing and calculation integrated method for an air-space-ground integrated network. The method comprises the following steps: S1, constructing an air-space-ground integrated network model fusing a low earth orbit satellite, an unmanned aerial vehicle and ground users / edge nodes; s2, establishing a cross-layer communication-perception-calculation integrated joint optimization model, and respectively forming two modes of binary unloading and partial unloading according to whether a task can be segmented or not; s3, for a binary unloading mode, realizing distributed solution and generating an unloading decision and a beam / power / bandwidth / computing resource scheme by using a dynamic adaptive prediction alternating direction multiplier (DAP-ADMM); and S4, aiming at a partial unloading mode, adopting a weighted minimum mean square error alternative optimization method, introducing a receiving equalizer, error weight and other auxiliary variables, executing block coordinate descent iteration, and outputting an unloading proportion, power distribution and a beam forming result. According to the DA-ISCC architecture and the optimization algorithm thereof provided by the invention, cross-domain calculation unloading with low time delay, high throughput and low overhead can be realized in a high-dynamic space-air-ground integrated network environment, and the DA-ISCC architecture and the optimization algorithm thereof can be widely applied to emergency communication, low-altitude logistics, ocean monitoring and other scenes.

The application belongs to the technical field of low-orbit satellite wireless communication, and particularly relates to a terminal grouping switching method in a low-orbit satellite Internet of Things scene, comprising the following steps: constructing a multi-satellite coverage communication system model, which comprises a plurality of user terminals and a plurality of low-orbit satellites; calculating a similarity matrix based on bandwidth demand, service priority and position coordinates; performing initial division on the user terminals according to the similarity matrix to obtain a plurality of initial groups; constructing a utility function of each user terminal according to a predicted switching success rate, a predicted satellite load, a predicted switching delay and an actual service priority; performing in-group optimization and inter-group optimization switching based on the initial groups according to the utility function to obtain a final grouping switching result; and the application can better adapt to various satellite communication scenes, reduce the signaling overhead of the system and improve the switching success rate of the user terminals.