81 results about "Satellite technology" patented technology

The embodiment of the invention provides a bridge monitoring satellite data quality control method based on signal-to-noise ratio grid comparison, and belongs to the technical field of satellites. The method comprises the following steps: carrying out pseudo-range single-point positioning calculation according to an observation value file and a broadcast ephemeris file to obtain observation data of each satellite; performing grid division on the satellite sky map according to a preset elevation angle interval and an azimuth angle interval to obtain a standard grid; on the basis of a standard grid, independently stacking observation data of each observation station to obtain a signal-to-noise ratio grid model corresponding to each observation station; performing preferential fusion according to the signal-to-noise ratio grid models of all the observation stations to obtain a high-quality grid model; performing data comparison on the signal-to-noise ratio grid model of each observation station and the high-quality grid model to obtain an available data area of each observation station; and performing quality control on the current observation data according to the available data area to obtain high-quality data. According to the invention, the observation area which is not subjected to interspersed shielding interference can be identified, and data quality control is realized.

The invention relates to the technical field of satellites, in particular to a three-super platform actuator eddy current sensor fault autonomous reconstruction method. Comprising the following steps: according to a parallel mechanism kinematics relationship of each actuator, determining a first relationship between axial displacement measured by an actuator eddy current sensor and a load relative to a six-degree-of-freedom pose of a satellite platform; determining a parallel mechanism kinematics relationship of the fault-free eddy current sensor, and determining a second relationship between the axial displacement and the load measured by the fault-free eddy current sensor and the six-degree-of-freedom pose of the satellite platform; according to the first relation and the second relation, matrix reconstruction is carried out on the remaining fault-free actuator eddy current sensors, and an autonomous reconstruction matrix is obtained; and according to the autonomous reconstruction matrix and the measurement of the fault-free actuator eddy current sensor, obtaining all actuator eddy current measurement values of the actuator where the fault eddy current sensor is located. According to the method, when the eddy current sensor has a fault, the eddy current sensor distribution array is reconstructed, and three-super control is recovered.

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 an adjacent satellite adjusting method and device based on satellite damage reconstruction, and relates to the technical field of satellites, whether a target satellite is damaged or not is judged according to telemetry data of the target satellite, and if it is judged that the target satellite is damaged, the adjacent satellite is adjusted according to a preset double-row element and an orbit model. Determining the real-time position data of the target satellite and the real-time position data of the adjacent satellites of the target satellite according to the real-time position data of the target satellite, the double-row element number of the target satellite and the double-row element number of the adjacent satellites of the target satellite; determining a mean anomaly change value required by the adjacent satellite to move from the current position to the target position, updating the number of double rows of the adjacent satellite according to the mean anomaly change value, and adjusting the orbit position of the adjacent satellite based on the updated number of double rows; according to the method, satellite damage reconstruction can be quickly realized at low cost through adjacent satellite adjustment.

A user equipment (UE) performs a public land mobile network (PLMN) scan for a higher priority PLMN, and reports a list of candidates PLMNs based on the scan. An identity of a first one of the candidate PLMNs includes a shared mobile country code (MCC). The shared MCC has a value between 900 and 999 and is also used for performing access with satellite technology. The UE selects the first one of the candidate PLMNs from among the list of candidate PLMNs. Each of the candidate PLMNs has either a mobile country code (MCC) the same as an identity of a serving PLMN or the shared MCC, when the identity of the serving PLMN does not comprise the shared MCC. The selecting is based on the first one of the candidate PLMNs having a higher priority than the serving PLMN.

The embodiment of the invention provides a data processing method and device and electronic equipment, and relates to the technical field of satellites.The method comprises the steps that star sensor data obtained by collecting spacecraft attitude information through a star sensor and gyroscope data obtained by collecting spacecraft attitude information through a gyroscope are obtained and comprise data from the k-n moment to the k moment; carrying out fusion and linear interference filtering processing on the data of the star sensor and the gyroscope at each moment by using Kalman filtering to obtain preliminary prediction data of attitude information, and calculating a first residual value of the data of the star sensor; the star sensor data, the gyroscope data and the first residual value from the k-n moment to the k moment are input into the trained LSTM network, a second residual value of the preliminary prediction data at the k moment is predicted, and the second residual value represents an error of nonlinear interference; and compensating the second residual value to the preliminary prediction data to obtain attitude information of the spacecraft at the moment k. According to the embodiment of the invention, the error of spacecraft attitude information acquisition is reduced.

The application provides a satellite splicing imaging posture maneuver angle error correction method and related device, and relates to the technical field of satellites. A plurality of ground imaging points are acquired, and then actual posture angles of the satellite pointing to each ground imaging point are obtained respectively; and simulation posture angles of the satellite pointing to each ground imaging point obtained by using a satellite simulation tool are obtained respectively. Finally, based on the actual posture angles and the simulation posture angles of each ground imaging point, a posture angle deviation mean value is obtained. In this way, the posture angle error of the collected remote sensing image can be corrected based on the real-time flight state of the satellite using the posture angle deviation mean value, so that deviation of the collected remote sensing image is avoided.

The present invention discloses a method, device, medium, and system for autonomous power consumption optimization of a transit satellite payload. These methods, which pertain to the field of satellite technology, include an autonomous entry / exit decision process, which rapidly determines the entry / exit status of a satellite payload by calculating distance. This process adapts to the impact of changes in orbital altitude after a satellite orbit change. The transit payload autonomously calculates the satellite's exit and entry delays, and, in conjunction with the satellite's energy management unit, enables autonomous shutdown of the transit payload while it is operating outside the country and autonomous startup before entering the country, thus saving energy consumed by the transit payload during standby operation outside the country. The present invention can address the issue of satellite energy shortages and promote satellite development and application.

The invention provides a terminal equipment positioning method and device based on a satellite direct connection network, and relates to the technical field of satellites. The terminal equipment positioning method based on the satellite direct connection network comprises the following steps: acquiring target communication signaling at a plurality of moments from the satellite direct connection network; according to the target communication signaling at the multiple moments, extracting position clues of the terminal equipment at the multiple moments; acquiring track point information of satellites which correspond to the multiple moments and provide satellite direct connection network services; and determining the position information of the terminal equipment according to the position clues at the multiple moments and the track point information of the satellite at the multiple moments. The satellite network can be directly connected through the terminal device, and a terminal device positioning function is provided for a user.

The application discloses a stackable aluminum extrusion profile frame satellite structure, and relates to the technical field of aerospace satellites, comprising: at least one stackable sub-frame; each stackable sub-frame comprises: a plurality of L-shaped extrusion forming structures, a plurality of outer wall plates and an inner partition plate; wherein each outer wall plate is composed of a plurality of I-shaped extrusion forming structures; the inner partition plate is composed of a plurality of I-shaped extrusion forming structures; when the stackable sub-frames are multiple, two adjacent stackable sub-frames are modularly stacked by aligning and splicing the upper end and the lower end of the L-shaped extrusion forming structures at the corresponding positions, and the lower end of the L-shaped extrusion forming structure of the upper stackable sub-frame is adaptively connected with the upper end of the L-shaped extrusion forming structure of the lower stackable sub-frame. The application can improve the mechanical bearing performance of the satellite structure, effectively improve the space utilization rate of the launch vehicle fairing, and realize the mixed stacking of satellite structures of different models, thereby meeting the installation requirements of equipment of different sizes.

The utility model discloses a sliding unfolding device for a micro-nano satellite, and relates to the technical field of satellites. According to the technical key points, the satellite comprises a satellite main body, solar wing plates are hinged to the opposite sides of the satellite main body respectively, and elastic driving pieces are arranged at the joints of the solar wing plates and the satellite main body; a telescopic supporting unit is installed in a shell of the satellite body, the top of the supporting unit is connected with a horizontal linkage rod, and the two ends of the horizontal linkage rod are slidably connected with the shell of the satellite body in the vertical direction. The two ends of the horizontal linkage rod are each provided with a clamping head, and the two solar wing plates are each provided with a clamping groove. An adjusting unit capable of controlling the position of the horizontal linkage rod at the top of the supporting unit in the vertical direction is arranged on the upper side of the middle position of the horizontal linkage rod. According to the unfolding device, the solar wing plate can be rapidly unfolded according to needs, and components in a satellite can be effectively prevented from being damaged by high temperature when the unfolding device is used.

The present application relates to the technical field of satellite, in particular to a kind of solar elevation angle calculation method of multi-view axis reference.The view axis is executed for each view axis, and reference coordinate system of view axis is constructed;According to the current attitude of the satellite carrying the view axis and the reference coordinate system of the view axis, the attitude of the view axis under the reference coordinate system is calculated;According to the scaling matrix of the earth ellipsoid under the inertial system, the satellite position vector under the inertial system, the attitude of the view axis under the reference coordinate system, the conversion matrix from the inertial system to the orbital system and the earth radius, the distance vector from the center of the earth to the view axis pointing point in the inertial system is determined;According to the distance vector from the center of the earth to the view axis pointing point in the inertial system, the scaled vector from the center of the earth to the view axis under the inertial system and the unit vector of the sun under the inertial system, the solar elevation angle of the view axis pointing point is determined.The present application can simultaneously accurately calculate the solar elevation angle for multi-view axis reference.

The invention relates to the technical field of satellites, and provides a task planning method and device for networking of a satellite and a ground station, an Internet of Things system, a storage medium and a computer program product, and the method comprises the steps: obtaining a task planning time period when the satellite and the ground station need to be networked, and obtaining ephemeris orbit prediction information of the task planning time period; according to ephemeris orbit forecast information, based on a genetic algorithm, designing a task planning algorithm for coverage optimization of an Internet of Things system for networking of satellites and ground stations; and the designed task planning algorithm is utilized to perform coverage optimization on the Internet of Things system with the networked satellite and ground station so as to improve the duration of the Internet of Things system capable of being connected with the satellite in the target area of the ground station. According to the scheme, a task planning algorithm oriented to coverage optimization of the satellite Internet of Things can be designed, coverage optimization is carried out on the satellite Internet of Things by using the task planning algorithm, the time length of the Internet of Things system capable of being connected with the satellite in the target area is prolonged, the accuracy of task planning is improved, and the coverage range is expanded.

The invention discloses a satellite low-brightness design and analysis method based on a satellite thermal control model, and belongs to the technical field of satellites. The method comprises the steps of task analysis, star catalogue thermal control low-brightness design, satellite thermal control-brightness analysis integrated modeling, thermal control feasibility analysis, satellite brightness analysis based on a thermal control model, index satisfaction degree analysis and the like. At present, a theoretical calculation method of a simplified model is generally used for brightness analysis of a satellite, and can not be effectively iterated and updated in time according to a thermal control star catalogue design condition of the satellite. According to the design and analysis method, the thermal control design and the brightness design and analysis of the satellite are integrated, and the low-brightness design is realized while the thermal control design is performed; and establishing an analysis model with unified thermal control and brightness analysis, and carrying out statistical analysis of the satellite brightness based on thermal analysis model data. According to the method, the satellite low-brightness design and the thermal design are organically combined, and the efficiency and the accuracy of the brightness design are improved.

The application relates to a high-reliability cryocooler micro-vibration insulation system and belongs to the technical field of satellites; a support Dewar is installed on the upper surface of a cold finger flange; a coupling substrate is placed on the top of the support Dewar; the top end of a support column is connected with the coupling substrate, and the bottom end is connected with the cold finger flange; a pyrotechnic cutter and a conductive sensor are arranged on the support column; a detector Dewar cover is installed on the coupling substrate; a splicing substrate is installed on the coupling substrate; a detector device is installed on the splicing substrate; a cryocooler cold head extends into the inner cavity of the support Dewar from the bottom of the cold finger flange; a flexible cold chain is arranged on the top of the cryocooler cold head and is connected with the coupling substrate; a vacuum pump is in communication with the detector Dewar; a water cooler is in communication with the cold finger flange; the application can not only guarantee that the launch section effectively supports the detector assembly but also guarantee that the support end and the detector assembly are physically isolated during the in-orbit period, so that the micro-vibration generated by the cryocooler during in-orbit work is insulated from the detector.

The invention discloses a satellite-borne computer device based on a D2000V processor, and belongs to the technical field of satellites. Comprising a processor module, a control module, a storage module, a power module and an external interface module. The processor module adopts a Feiteng D2000V processor to form a minimum hardware system for CPU (Central Processing Unit) operation of the processor; the control module adopts an anti-fuse type or Flash type FPGA (Field Programmable Gate Array) to realize a control management function, and mainly comprises health management functions such as remote control and telemetering information processing, program reconstruction management function, storage channel selection, CPU (Central Processing Unit) start control, CPU on-orbit operation state management, fault diagnosis and the like; the storage module realizes a program storage function of the processor and adopts a multi-redundancy physical backup form, the power supply module realizes input power supply conversion and provides a basic power supply function for the spaceborne computer device, and the external interface module realizes external information interaction of the spaceborne computer device. The reconstruction scheme is flexible, the integration level is high, external interfaces are rich, the space environment adaptability is high, and various satellite processing load requirements are met.

The invention provides a remote sensing satellite observation parameter pre-analysis method, calling method, system and equipment, and relates to the technical field of remote sensing satellites. Known remote sensing satellite ephemeris data, gridding coding is carried out on a remote sensing satellite sub-satellite point through an earth space grid coding rule, a remote sensing satellite sub-satellite point grid is taken as a center, and a remote sensing satellite imaging point moves east or west along a latitude line by taking the grid as a step length; under the condition of considering a remote sensing satellite imaging point grid, a satellite position, a satellite breadth and constraints, a satellite side-sway angle observation parameter and a coverage grid are calculated and stored in a database so as to be conveniently called at any time when a remote sensing task is executed, a task of observation parameter analysis is completed in advance, the time spent on executing the remote sensing task is shortened, and the remote sensing task execution efficiency is improved. The occupation of computing resources is reduced, and the response speed is improved.

The present invention provides a space-based, sensorless harassment device and method, relating to the field of microsatellite technology. The space-based, sensorless harassment device includes a micro-carrier satellite and a force-current multi-field coupling actuator mounted on the micro-carrier satellite. The micro-carrier satellite is used to drive the force-current multi-field coupling actuator toward a target satellite and, by adjusting its attitude, align its jet nozzle with the target satellite's reconnaissance lens. The force-current multi-field coupling actuator is used to spray a harassing liquid from the jet nozzle toward the target satellite's reconnaissance lens under electrostatic pressure, thereby achieving a "blinding" effect on the target satellite's reconnaissance lens. Compared to existing directed energy anti-satellite technologies or parasitic soft-kill methods, the device not only has the advantages of simple structure, low manufacturing cost, and low energy consumption, but can also achieve long-term effective harassment by spraying the harassing liquid toward the target satellite's reconnaissance lens.

The present application relates to the technical field of satellite, in particular to a RDSS system frequency offset compensation method and RDSS system, the present application embodiment provides a kind of frequency offset compensation method of RDSS system, comprising: determining target Beidou satellite;Wherein, the target Beidou satellite is the nearest Beidou satellite of remote sensing satellite or the normal of the antenna of the RDSS system and the angle formed when the straight line connecting the RDSS system and Beidou satellite is at the minimum time corresponding Beidou satellite;According to the speed of remote sensing satellite and the speed of target Beidou satellite, the relative speed between remote sensing satellite and target Beidou satellite is determined;According to the relative speed, frequency offset value is obtained;The sending frequency of the RDSS system is compensated using the frequency offset value.The present application embodiment provides a kind of frequency offset compensation method of RDSS system, and makes remote sensing satellite and Beidou satellite again communicate between disconnection.

The invention relates to a method and a system for forecasting the position of a medium-high orbit equatorial orbit satellite, and belongs to the technical field of satellites, the method for forecasting the position of the medium-high orbit equatorial orbit satellite comprises the following steps: preprocessing multi-source observation data, determining initial orbit parameters, constructing an equatorial orbit adaptive orbit dynamics model, and determining the position of the medium-high orbit equatorial orbit satellite; and orbit forecasting calculation based on adaptive numerical integration, dynamic error compensation and multi-source data fusion optimization, forecasting result output and precision verification. The core innovation of the invention focuses on deep adaptation of orbit characteristics of medium-high orbit equatorial orbit satellites, and the precision bottleneck of the existing method in equatorial orbit application is solved through the full-process technical innovation of model optimization, integral improvement, error compensation and data fusion.

Embodiments of the present application are applicable to the technical field of satellites, and provide a positioning and orientation integrated method and device, a terminal device and a storage medium. The method comprises: obtaining first satellite observation data, second satellite observation data and third satellite observation data obtained by a main antenna and slave antennas of a base station and a terminal device when observing multiple satellites at the same time; determining a target position of the terminal device according to the first satellite observation data and the second satellite observation data, and simultaneously orienting the terminal device according to the second satellite observation data and the third satellite observation data. The above method can ensure the accuracy of positioning and orientation, and reduce the hardware cost required by the terminal device.

The application provides a satellite damage reconstruction-based neighboring satellite adjustment method and device, and relates to the technical field of satellites. According to telemetry data of a target satellite, whether the target satellite is damaged is judged. If it is judged that the target satellite is damaged, according to a preset two-line element and an orbit model, and a two-line element of the target satellite and a two-line element of a neighboring satellite of the target satellite, real-time position data of the target satellite and real-time position data of the neighboring satellite of the target satellite are determined. According to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, a mean anomaly change value required for the neighboring satellite to move from a current position to a target position is determined. According to the mean anomaly change value, the two-line element of the neighboring satellite is updated, and the orbit position of the neighboring satellite is adjusted based on the updated two-line element. The application can quickly and at low cost realize satellite damage reconstruction through neighboring satellite adjustment.

The invention provides a modularized large-folding-unfolding-ratio solar cell variable structure system and a satellite, and relates to the technical field of satellites. The modularized solar cell variable structure system with the large folding-unfolding ratio is arranged to be a paper folding structure with a folded state and an unfolded state and comprises a driving hinge made of a shape memory material, and the driving hinge comprises two first connecting parts and a first arc-shaped part connected between the two first connecting parts; the elastic hinge comprises two second connecting parts and a second arc-shaped part connected between the two second connecting parts; the battery panels are arranged in two rows on the two sides of the calibration direction, in the same row, the battery panels are arranged at intervals in the calibration direction, every two adjacent battery panels are connected with the two second connecting parts of the elastic hinge respectively, and in the calibration direction, the two adjacent battery panels are connected with the two second connecting parts of the elastic hinge respectively. And the bending directions of the second arc-shaped parts of the elastic hinges are alternately distributed forwards and backwards.

The invention discloses a method, a device and equipment for judging the application technology maturity of an ocean microwave product, relates to the technical field of ocean microwave remote sensing satellites, and is used for solving the problem that the application technology maturity of the ocean microwave product cannot be accurately and effectively judged in the prior art. Comprising the following steps: establishing a plurality of application technology maturity levels of the marine microwave product; setting inspection elements and weight factors of each maturity level in the plurality of maturity levels; calculating an application technology maturity index based on the inspection elements and the weight factors, and calculating to obtain a target maturity index through a weighted summation mode; and determining the target application technology maturity of the marine microwave product according to a comparison result of the target maturity index and a preset threshold value, and judging the development level of the application technology by using a dynamic threshold value. According to the technical scheme provided by the invention, the application technology maturity of the marine microwave product can be accurately and effectively judged, and a basis is provided for design and index optimization of a satellite payload.

The application provides a high-compatibility remote sensing satellite commonality application support platform and a layout method thereof, and belongs to the technical field of satellites. The problems that the satellite support platform in the prior art cannot be applied to different loads and different types of carrier rockets are solved. The camera mounting plate, the satellite-rocket separation mechanism support, the carried load mounting plate, two solar cell array assemblies and a flywheel support assembly are all mounted on an optical load light shield. Multiple carried loads are mounted on the carried load mounting plate. One end of a satellite-rocket separation mechanism is connected with the optical load light shield through two mass center adjusting structures, and the other end is connected with the satellite-rocket separation mechanism support through another two mass center adjusting structures. The mass center adjusting structure comprises a mass center adjusting moving block, a mass center adjusting support and an adjusting bolt. The mass center adjusting support is connected with the satellite-rocket separation mechanism, and the adjusting bolt connects the mass center adjusting moving block with the optical load light shield or the satellite-rocket separation mechanism support. The application has the characteristics of high compatibility of carried loads and carrier rockets.

This application relates to a stacked satellite mass launch system, belonging to the field of satellite technology. It includes a mounting base pressure rod and multiple satellites stacked on a mounting base. A positioning assembly is provided between adjacent satellites. The positioning assembly includes a positioning post and a sleeve. The positioning post is fixedly disposed on the bottom wall of the satellite, and the sleeve is fixedly disposed on the top wall of the satellite, for inserting the positioning post to define the position of adjacent satellites. A first elastic element is provided inside the sleeve for driving the positioning post out of the sleeve. The pressure rod is hinged to the mounting base and has a clamping assembly for applying clamping force to the satellites. When the satellites separate, the clamping assembly unlocks, and under the action of the first elastic element, the upper-layer satellite is pushed, causing the positioning post to disengage from the sleeve, at which point the upper-layer satellite can be unlocked and separated.

The invention relates to the technical field of satellites, and discloses a space situation awareness strong cursor calibration satellite. The satellite comprises a calibration satellite body, and a power supply subsystem, a calibration light source subsystem, a GNSS navigation system, an energy storage system, a telemetering and remote control subsystem, a monocular / multi-view space optical camera system and the like which are integrated on the calibration satellite body. Through a multi-stage linkage mechanism, multi-directional adjustment of a camera system can be realized, images of other satellites or fragments can be accurately captured, target errors are updated by combining image processing, star map matching and GNSS orbit data, and high-precision space situation awareness is realized. The satellites can work independently or a plurality of satellites are distributed on different orbits to form constellations for cooperative work; the calibration light source provides standardized strong light, ensures accurate coverage of an imaging view field, and improves the calibration reliability. The structural design gives consideration to the on-orbit stability and the assembly and maintenance convenience, and the adaptability and practicability are outstanding.

The application provides a positioning method and device and a computer readable storage medium, relates to the technical field of positioning satellites, and can improve the accuracy of determining the position of a receiver. The method comprises the following steps: S1: acquiring a signal quality index of each initial positioning satellite in an initial positioning satellite set and a signal quality index of each non-initial positioning satellite in a non-initial positioning satellite set; S2: eliminating a target non-initial positioning satellite in the current non-initial positioning satellite set, and determining a test result of W test of the signal quality index of each positioning satellite in the current target positioning satellite set; S3: in the case where the test result indicates that the test fails, determining a signal anomaly index of each positioning satellite and a contribution index of a geometric dilution of precision of each positioning satellite; and S4: in the case where the contribution index of a first positioning satellite in the current target positioning satellite set is the maximum value of the plurality of contribution indexes, eliminating a second positioning satellite in the current target positioning satellite set.

The application relates to the technical field of satellites, in particular to a micro-satellite release device which comprises a shell, a micro-satellite, a rotating piece, a release device, the micro-satellite is located in the inside of a storage groove of the shell, one side of the storage groove is provided with a push plate one, the push plate one is connected in the inside of the storage groove through an elastic rod one, the inside of the shell is provided with a limiting groove one, the inside of the shell is provided with an elastic buckle one, the inside of the shell is provided with a waste groove, one side of the release device is provided with a detection piece, the detection piece is connected with a detection head through a detection rod, the lower portion of the detection head is provided with a push plate, one side of the detection head is provided with a connecting head, the micro-satellite can be released in two opposite directions at the same time, the angle adjustment of the device when the micro-satellite is released in the opposite direction can be avoided, and the micro-satellite can be efficiently released.

A method for multi-beam resource management and control of communication satellites based on deep reinforcement learning belongs to the field of satellite technology. This method utilizes a multi-agent reinforcement learning algorithm to dynamically adjust and optimize beam resource allocation strategies. By utilizing satellite antenna hopping technology and time-division multiplexing, it flexibly responds to changes in ground user demand and communication traffic, significantly improving the overall throughput of the onboard link. This dynamic optimization mechanism ensures efficient resource utilization and enhances the transmission rate and quality of the communication system.