38 results about "Satellite technology" patented technology

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 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 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 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.

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.

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 satellite cluster precise orbit determination method based on multi-source data fusion, and belongs to the technical field of satellites. Basic parameters are set, a dynamic model and a state transition equation of a satellite are established, absolute positions and velocities of the satellite cluster are taken as observation quantities, an observation equation of the absolute state of the satellite is established, inter-satellite relative positions and velocities of the satellite cluster are taken as observation quantities, an observation model of the relative state of the satellite is established, a state quantity optimal estimation value is obtained by solving a cluster positioning state updating equation by using a Newton method, and the spatial position and velocity of the satellite cluster are calibrated. The method fuses the absolute state observation and the inter-satellite relative state observation of the satellite cluster, overcomes the limitation of a single measurement method in measurement accuracy, has expansibility, can fuse various observation methods, and further improves the orbit determination accuracy of the satellite cluster.

The application relates to the technical field of satellites and provides a constraint design method and device in satellite networking task planning, an Internet of Things system, a storage medium and a computer program product, the method comprising the following steps: acquiring a task planning period required for networking of a satellite and a ground station, and acquiring ephemeris orbit prediction information of the task planning period; designing a task planning algorithm for coverage optimization of the Internet of Things system facing the networking of the satellite and the ground station based on a genetic algorithm according to the ephemeris orbit prediction information; performing constraint design on the designed task planning algorithm to obtain a task planning algorithm after constraint design; and performing coverage optimization on the Internet of Things system for the networking of the satellite and the ground station by using the task planning algorithm after constraint design, so that the time length during which the Internet of Things system in a target area of the ground station can connect the satellite is improved. The scheme can perform coverage optimization on the satellite Internet of Things by using the task planning algorithm after constraint design, and improve the communication service stability of the satellite Internet of Things.

The application provides a shape memory material-based metamorphic satellite structure and relates to the technical field of space satellites. The metamorphic satellite structure comprises a variable-configuration regular pentagon module and a variable-configuration regular hexagon module made of shape memory material, the variable-configuration regular pentagon module is connected with the variable-configuration regular hexagon module to form a spherical polyhedral structure, and the variable-configuration regular pentagon module and the variable-configuration regular hexagon module are both used for synchronous contraction or synchronous expansion by temperature change. The structure is optimized through material-structure collaborative design, the characteristics of the multi-stable structure that can still maintain a stable geometric configuration after load removal are utilized, the configuration stability of the system is fundamentally improved, and the dependence on single material characteristics is reduced; even when the shape memory polymer and the composite material thereof cause incomplete phase change due to temperature fluctuation, the system can still maintain a target configuration, and the reliability in an extreme space environment is significantly improved.

The application relates to the technical field of satellites and discloses a common carrier satellite with interstellar interconnection and storage processing functions, which comprises a satellite common body and an interface unit; the common body comprises an interstellar communication module, a satellite-ground communication module, a solar photovoltaic panel, an energy storage unit, a satellite maneuvering unit, a data processing unit and a data storage unit; the interface unit is provided with slots loaded with different loads or a plurality of equidistantly-distributed integrated wire harnesses; each integrated wire harness is sealed and penetrates through the base, and the tail end of the integrated wire harness is provided with an aviation data plug. The application actually separates the original common part of the satellite, loads the same into a plurality of different loads in a mode, and endows the common part with different functions, so that the production efficiency of the satellite is greatly improved and the satellite manufacturing cost is reduced.

The invention discloses a Beidou global short message communication bidirectional authentication method, which enables a satellite and a user terminal to be mutually authenticated, ensures the legality of the satellite and the terminal participating in communication, and belongs to the technical field of navigation satellites. The method provided by the invention is divided into a first access authentication process and an authentication process after switching the visible relationship between the satellite and the user, the Beidou No.3 global short message service is fully utilized, the security is higher, and the authentication after switching is realized through cooperation among satellites, so that the problems of high protocol overhead and increased delay caused by visible switching are avoided.

The utility model relates to the technical field of satellites, and particularly provides a floor GNSS antenna camouflage device. The device comprises a customized antenna protection cover, a miniaturized GNSS choking coil antenna, an antenna holding pole, a bolt, a grounding grid and a lightning rod. Wherein the customized antenna protection cover is in an appearance shape coordinated with the surrounding environment; the customized antenna protection cover is buckled on the miniaturized GNSS choking coil antenna and is screwed and connected with the miniaturized GNSS choking coil antenna; the miniaturized GNSS choking coil antenna is connected with the antenna holding pole; the antenna holding pole is fixed on a wall through a bolt; the lightning rod is placed on the top of the customized antenna protection cover, the vertical part is located on one side close to the wall, and the tail end is connected with the grounding grid. According to the invention, the antenna protection cover is customized to be in the appearance shape coordinated with the surrounding environment, and the lightning rod is hidden on the wall side, so that the overall shape adapts to the surrounding environment. Meanwhile, the size of the GNSS antenna is miniaturized, the signal receiving and transmitting function is guaranteed, meanwhile, the occupied area is reduced, the number of derricks is reduced, and the construction cost is saved.

The invention discloses a satellite oblique path troposphere delay calculation method and device, and belongs to the technical field of satellites, and the method comprises the steps: obtaining a real-time geographic position of a target observation point, a real-time satellite observation elevation angle, a current visible satellite, and historical satellite observation data of the current visible satellite; solving historical oblique path troposphere delay of the current visible satellite based on historical GNSS satellite observation data in the historical satellite observation data; fitting an inclined path troposphere delay calculation model according to the historical inclined path troposphere delay corresponding to each historical satellite observation data, the historical observation point geographic position and the historical observation point satellite observation elevation angle to obtain a model solving coefficient of the inclined path troposphere delay calculation model; and calculating the troposphere delay of the current inclined path based on the real-time geographic position of the target observation point, the real-time satellite observation elevation angle and the model solving coefficient. Therefore, by implementing the method, the problem of low delay accuracy of the inclined path troposphere in the prior art can be solved.

The invention provides a flexible cable network expansibility design method for a flat satellite and a flexible cable network, and belongs to the technical field of spaceflight satellites in order to solve the problem that a traditional wire type cable network cannot be suitable for the flat satellite due to the fact that the expansibility design of the traditional wire type cable network is insufficient. The flexible cable network is provided with a rigid area used for installing a telemetry signal connector of the butt joint integrated electronics, and is provided with a capacitor array connected in series; a transfer rigid area is arranged in the middle of the whole satellite structure, and a transfer auxiliary connector and a universal resistance-capacitance bonding pad are arranged, so that the anti-interference design is realized; a rigid area is arranged at a CAN communication connector, and a matched resistance bonding pad is arranged; cAN connection of the upper bin and the lower bin is achieved through an adapter connector. The rigid area is arranged at the connector end of the flexible cable, the universal resistance-capacitance bonding pad is arranged, and the resistance-capacitance of the rigid area is connected into the flexible cable by adopting scattered wires, so that the emergency handling capacity of abnormal conditions in the whole satellite stage is improved. The method is suitable for cable network development of flat satellites.

The invention relates to the technical field of elevator safety protection, and discloses an elevator power-off multistage safety protection system based on a PLC (Programmable Logic Controller) and a star sealing technology, which comprises the following steps: collecting elevator operation key data, analyzing the overlapping degree of a hot area and a door body track, judging the elevator operation state, and carrying out preventive maintenance and fault self-diagnosis; constructing an impedance dynamics response model library to maintain state balance; calculating a membership adaptive protection strategy, and calculating a dynamic deviation to perform preview and verification on a door body recovery operation; whether the superconducting module is quenched or not is judged according to the change of fault accumulated energy, if yes, fault current is guided into the super capacitor set, and a fault isolation relay is synchronously controlled to disconnect a main loop; if the pulling force of the door body is continuously increased, double protection is formed through the mechanical ejector rod and the electromagnetic resistance of the star sealing loop; constructing star sealing contactor group redundancy, and if the contactors fail, automatically switching residual combinations to maintain a basic star sealing function; the PLC adopts double-circuit power supply, and impedance verification is carried out on the safety circuit.

This application discloses an on-board remote sensing data management method, apparatus, device, and medium, relating to the field of remote sensing satellite technology. The method includes: dividing a ground area into grids based on the satellite's real-time position and the terrain of the area to be observed, and generating an ID code for each grid; acquiring remote sensing data blocks, determining the data block ID of each data block, determining the feature hash value of each data block, and determining an association table and a search directory corresponding to each remote sensing data block based on the ID code, data block ID, and feature hash value; determining the IDs of each target data block corresponding to a ground search request based on the search directory, generating a data block ID list, reading the original remote sensing data blocks according to the data block ID list, and determining valid data based on the original remote sensing data blocks; packaging the valid data according to network bandwidth to obtain packaged data, and transmitting the packaged data to the ground. This achieves unified organization and efficient management of massive, multi-source remote sensing data in orbit.

The application relates to the technical field of satellites, and discloses a satellite communication and navigation signal forwarding system supporting multi-user sharing, which comprises a satellite communication forwarding subsystem, a satellite navigation signal forwarding subsystem, and a control and interface subsystem; the satellite communication forwarding subsystem is used for receiving and processing all signals of the uplink and downlink forwarding channels of satellite communication signals; the satellite navigation signal forwarding subsystem is used for receiving and processing all signals of the uplink and downlink forwarding channels of satellite navigation signals; the control and interface subsystem is used for receiving forwarding data and completing the scheduling, control and interaction of signals; the receiving and transmitting links of the satellite communication forwarding subsystem and the satellite navigation signal forwarding subsystem are independent of each other and do not interfere with each other, satellite communication signals and satellite navigation signals can be simultaneously forwarded, and multi-user multiplexing expansion modules are arranged in the satellite communication forwarding subsystem and the satellite navigation signal forwarding subsystem to realize that a set of forwarding systems can be simultaneously shared by multiple users. The application realizes integrated forwarding of satellite communication signals and satellite navigation signals, and can simultaneously complete satellite communication link data transmission and satellite navigation link positioning signal forwarding.

The invention provides a two-line orbit element acquisition method and a related device, and relates to the technical field of satellites. The two-row orbit element acquisition method comprises the following steps: acquiring position information and speed information of a target satellite at a target moment; converting the position information and the speed information into six instantaneous Kepler elements as initial values of the two rows of orbits; according to a preset correction strategy, correcting the initial value of the number of the two lines of orbits to obtain a corrected value of the number of the two lines of orbits; wherein the preset correction strategy comprises that at least one of an area integral constant, an orbit eccentricity rate and an orbit semi-major axis is used as a parameter correction convergence condition in the correction process. According to the technical scheme, the problem that in the prior art, the number of two lines of tracks is difficult to obtain can be solved.

This invention relates to the field of satellite technology, and particularly to a static polarity verification method and system for a fire detection system. The static polarity verification method for a fire detection system includes: establishing a reference mirror coordinate system based on the probe reference mirror of the fire detector; using a fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, observing the vector information of the fire point in the reference mirror coordinate system to determine whether the polarity of the fire detector is correct; installing the fire detector with correct polarity on the satellite; simulating satellite operation under a satellite dynamics model, using the fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, and comparing the latitude and longitude information of the fire point with the latitude and longitude information of the nadir point when the satellite is ascending and descending, respectively, to determine whether the polarity of the fire detection system is correct. This invention provides a static polarity verification method and system for a fire detection system, capable of verifying the correctness of the polarity of the fire detection system.

This application relates to the field of satellite technology, specifically disclosing a panoramic beam antenna device and a satellite system. The device includes: multiple waveguide horn antennas, each including an interconnected radiating horn and a signal transmission interface; the multiple waveguide horn antennas are divided into n groups, with each waveguide horn antenna in the same group being non-connected; an antenna support, to which each of the waveguide horn antennas is detachably connected; and a signal transmission substrate, to which each of the signal transmission interfaces is connected, the signal transmission substrate including n sets of connection terminals. Each signal transmission interface of a waveguide horn antenna in the same group is connected to the same set of connection terminals via different signal transmission traces in the signal transmission substrate, and different groups of waveguide horn antennas correspond to different sets of connection terminals. This simplifies the antenna structure and reduces technical complexity.

This invention provides a method, apparatus, electronic device, and computer-readable storage medium for precision control of satellite antenna profiles, relating to the field of spaceborne satellite technology. The precision control method includes: acquiring the array strain and key coordinates of the satellite antenna profile; inputting the array strain and key coordinates into the array structural mechanical model of the satellite antenna to evaluate the profile deviation coordinates; and performing profile precision control of the satellite antenna based on the profile deviation coordinates. This addresses at least the problems of low efficiency, poor consistency, and lag in precision adjustment in related technologies. It is suitable for antenna offset prediction and control scenarios.

The invention discloses a direct memory access (DMA) engine system for satellite-borne synthetic aperture radar (SAR) in-orbit imaging processing based on an instruction set, relates to the technical field of remote sensing satellites, and solves the technical problems of overuse of DMA resources and low data access efficiency caused by repeated configuration and execution of a large number of transmission commands and address increase commands in the prior art. The AXIS bus module is used for configuring a register related to transmission in the register-level instruction processing module; after the configuration of the register is completed, writing a data access operation instruction into the instruction memory read-write module through the AXIS bus module; the instruction set read-write analysis module reads the instruction data from the instruction memory read-write module and analyzes the instruction data to obtain a control instruction; controlling the state machine to jump through the control instruction, and outputting a control signal; a control signal enters the one-dimensional instruction analysis module after passing through the one-dimensional read-write instruction module; and the one-dimensional instruction analysis module is controlled by the control signal to perform read-write operation on the data.

This application relates to the field of meteorological satellite technology and provides a meteorological satellite Earth operational service system, comprising: a data acquisition module for acquiring basic data; a data processing module for preprocessing the basic data; and a data product service module for publishing and providing data product services to users. The data processing module includes a data preprocessing unit, which further includes: a multi-resolution cloud image time-density encryption component for generating time-encrypted multi-resolution cloud image data; a high-resolution cloud image data reconstruction component for generating spatial high-resolution cloud image data; and a visible light cloud image generation component for generating visible light cloud image data using infrared cloud image data. This application implements functions such as encrypting low-resolution time-density cloud image data, reconstructing low-resolution cloud image data to high resolution, and automatically generating visible light cloud image data using infrared cloud image data.

Decentralized blockchain enabled mobile communications on a secure, open and distributed network and that is network agnostic. Networks of future will be based on cellular, Wi-Fi, and / or satellite technology, may be private or public, will be decentralized and will provide a variable network capacity, latency and bandwidth. The endpoints for networks will vary but increasingly include several Internet-Of-Things (IOT) endpoints. Peer-to-peer connections traverse many of these networks. As of today, communications networks will continue to exist in secure and not secure embodiments.

The application relates to the technical field of cable detection, and discloses an outdoor high-altitude cable detection device with a Tianhong data transmission network. The detection device comprises a UAV main body of an airborne Tianhong satellite communication system, lateral overturning assembly grooves are formed in the two side walls of the UAV main body, an electric control overturning type adjusting mechanism is movably assembled in the lateral overturning assembly grooves, an electric control lifting arm is movably assembled in the electric control overturning type adjusting mechanism, an electric control top driving wheel is movably assembled on the inner top surface of the electric control lifting arm, and a visual sensing probe, an optical distance measuring probe and an optical detection unit are assembled on the upper surface of the UAV main body. The detection device directly transmits information by adopting the Tianhong satellite technology, is not affected by land base stations, and is more convenient in information communication; the UAV main body is adopted as a carrier for control, manual conveying is not needed, and the cost of reloading is saved; the lateral overturning mode is adopted to hoist the cable, the UAV main body is not needed to drive in the detection process, and the endurance is good.

The invention discloses an FPGA (Field Programmable Gate Array) software rapid reconstruction and loading / refreshing system, which belongs to the technical field of satellites and mainly comprises a storage management board card, a single-machine internal interconnection and a service function board card. Wherein the storage management board card mainly comprises a processor, a plurality of groups of storage particles and a control FPGA (Field Programmable Gate Array), and is mainly used for realizing data uploading receiving, analysis, verification, caching and rapid reconstruction functions of software such as the FPGA, and the plurality of groups of storage particles are used for storing program data of the FPGA. A shared centralized storage architecture is adopted, centralized storage management of multiple FPGA program data is achieved, the total storage capacity of the system is reduced, and the system cost is reduced; a rapid reconstruction method is adopted, the FPGA program reconstruction time of the system is shortened, and the reconstruction efficiency is improved; parallel loading and refreshing of the FPGA are realized, and the refreshing period is shortened; according to the method, the single event upset resistance in the FPGA program running process is effectively improved, and the stability of the on-orbit running function of the FPGA is improved.