3577 results about "Satellite" patented technology

The invention discloses a method for judging an RTK abnormal value in an automatic driving integrated navigation system, and relates to the technical field of automatic driving high-precision integrated navigation, and the method comprises the steps: collecting RTK observation data, inertial measurement unit data, a wheel speed pulse signal and LiDAR point cloud data, carrying out timestamp alignment and coordinate system unification, and generating a fusion data value; calculating a carrier-to-noise ratio weight signal quality index of the satellite through the fused data value, and generating a signal quality report; and combining the signal quality report, the current satellite geometric accuracy factor and the vehicle motion acceleration, calculating a residual threshold, constructing a coriolis force compensated double-integral prediction model by using inertial measurement unit data, and predicting the position of the vehicle at the current moment. According to the method, multi-dimensional features such as satellite signal quality, vehicle motion state and residual analysis are fused through multi-source decision, and the anomaly detection capability of complex scenes such as urban canyons is effectively improved.

The invention relates to a multi-source data fusion rainfall revision model construction method based on dynamic physical constraints, and belongs to the technical field of artificial intelligence and meteorology and hydrology crossing. The method comprises the steps that multi-source heterogeneous data such as satellites, reanalysis, sites and terrains are acquired and fused, and a standardized space-time sample set is constructed; constructing a special deep learning network comprising a double-flow encoder, a cross-scale physical attention fusion module and a decoder; constructing a composite loss function fusing data fidelity, terrain uplift constraint and wind field advection constraint; designing a dynamic constraint gating mechanism, and adaptively adjusting a physical constraint weight according to a real-time atmospheric state; and a high-precision precipitation revision model is obtained by optimizing the composite loss function training network. According to the method, the key physical process is embedded into the model in a dynamic adjustable mode, the problems that a traditional method is poor in physical consistency and generalization ability are solved, and a revised precipitation field which is physically reasonable and higher in precision can be generated under complex terrains and changeable weather.

The invention discloses a low earth orbit satellite network digital twin drive switching optimization method and system, and relates to the technical field of inter-satellite communication, and the method comprises the steps: building a digital twin system which is synchronously evolved with a physical LEO satellite network; predicting the link quality between each candidate satellite and the user terminal in a future time window based on a digital twin system; dividing a time window into a plurality of continuous time slices, constructing a directed weighted dynamic graph model which takes a satellite-time slice as a node and takes link comprehensive utility cost as an edge weight, and searching an optimal path in the directed weighted dynamic graph model by utilizing a shortest path algorithm so as to determine an optimal switching opportunity and a target satellite sequence; the optimal switching strategy is issued to a user terminal to be executed, and a link quality prediction result is corrected in real time through a feedback mechanism of the digital twin system to form closed-loop optimization; the method can effectively meet differentiated service quality requirements in a multi-service scene, and is suitable for a high-dynamic LEO satellite communication system.

The invention discloses a multi-mode fusion time service method and system based on dynamic calibration of DCP equipment. The method comprises the following steps: completing initial time reference data acquisition based on a multi-mode satellite signal; meanwhile, time data of a ground time service network are collected, and motion parameters of DCP equipment are monitored in real time through an inertial navigation unit; establishing a correlation model of the motion parameter and the time service error; quantitative analysis of error sources is completed based on the correlation model; fusing the multi-source time data; dynamically adjusting the fusion weight of each data source according to the real-time motion state of the DCP equipment; redundant time slots are automatically distributed to high-error equipment; outputting the calibrated time signal to DCP equipment through an interface to complete clock synchronization; and continuously monitoring the time deviation of the DCP equipment, and dynamically updating the calibration parameters to form closed-loop optimization. And the environmental adaptability and the precision stability of the timing system are improved.

The invention discloses a power distribution network fault positioning method and device based on a satellite time service inverter, and belongs to the technical field of power system fault diagnosis, and the method comprises the steps: obtaining a time service signal of a satellite navigation system, decoding the time service signal to generate a unified space-time reference, distributing the unified space-time reference to a plurality of inverter nodes in a power distribution network, and forming a cooperative measurement network; a coding sequence current signal is injected into a power distribution network line through a master control inverter node; synchronously acquiring response voltage traveling wave data by each inverter node, performing cross-correlation analysis on the response voltage traveling wave data and the coded sequence current signal, and extracting propagation time delay of each inverter node; and correcting the reference line wave velocity by using the current line parameters and the current meteorological data, and calculating fault point position data in combination with propagation time delay. According to the method, an inverter cooperative measurement network is constructed by using satellite time service, a coding sequence current signal is actively injected, and a real-time wave velocity is corrected by combining an intelligent model, so that rapid, accurate and high-reliability positioning of a power distribution network fault can be realized.

The invention provides a wireless resource scheduling method and device used in a scene in which a mobile phone is directly connected with a satellite, and relates to the technical field of satellite communication, and the method comprises the steps: constructing an electromagnetic map which represents the corresponding relation of a geographic position, a physical resource block and ground interference power in a satellite beam coverage area; link budgeting is carried out on the multiple user terminals in combination with the real-time orbit geometric parameters of the satellite and the electromagnetic map, and the signal to interference plus noise ratio of each user terminal on each physical resource block is predicted; based on the predicted signal to interference plus noise ratio, adopting a proportional fair marginal gain greedy algorithm to allocate an optimal continuous spectrum resource block for each user terminal; on the allocated spectrum resources, optimizing and reallocating the total transmitting power of the satellites by adopting a water injection algorithm; and a final spectrum-power joint scheduling scheme is generated, and subsequent link self-adaption and data transmission are guided. According to the invention, the spectrum efficiency, throughput and connection stability of the system are obviously improved.

The invention discloses a safe operation system and a safe operation method of a space-ground integrated rescue vehicle, which are used for the rescue vehicle working in a complex disaster environment and ensure stable and reliable two-way communication connection between the rescue vehicle and a command center by establishing an intelligent switching mechanism of a low-orbit satellite main link and a ground network standby link. Real-time transmission of key instructions and field information is guaranteed, and a foundation is laid for safe operation. Advanced risk early warning is achieved through a space-ground cooperation mechanism, dynamic decision making and path planning are carried out by integrating satellite information and local sensor data, and the global adaptive capacity of the rescue vehicle to the complex disaster environment is improved. Satellite pre-sensing information is combined with a local decision, and a pre-control instruction is generated to act on a drive-by-wire chassis, so that the rescue vehicle can smoothly deal with hidden or developmental risks in advance, and the driving safety and stability are improved.

A routing method for supporting differential service requirements in a satellite internet comprises the following steps: step 1, constructing multi-dimensional network state perception as a base layer which is responsible for collecting and quantifying physical states and logic states of a satellite network in real time, and obtaining objective network states and subjective QoS (Quality of Service) requirements of services; 2, generating a nonlinear adaptive weight driven by a service as a strategy layer, mapping an objective network state and a subjective QoS (Quality of Service) demand of the service, dynamically adjusting the value orientation of routing judgment, and generating a dynamic weight; and step 3, taking the dynamic cost routing decision as an execution layer, calculating the comprehensive cost based on the dynamic weight, and executing next hop selection and path maintenance, and through cooperative work of the dynamic cost routing decision, the comprehensive cost and the next hop selection and path maintenance, realizing intelligent path selection and high-reliability transmission for different service flows in a high-dynamic and resource-limited environment of the low-orbit satellite. According to the invention, while the routing computation overhead is effectively reduced, multiple requirements of differentiated services on low time delay and high reliability can be considered.

The invention discloses an aeronautical ice accretion identification method based on multi-source data, which solves the coverage blind area of a single data source (mode / satellite) through multi-source data fusion processing, improves the integrity of a three-dimensional space, and further establishes a scene classification foundation through cloud layer structure identification and accurate division of a cloud area / a precipitation area. Through membership function construction processing, a nonlinear relation between meteorological elements and icing is quantified, and a traditional threshold value method is replaced; furthermore, through physical scene classification processing, single-layer cloud / multi-layer cloud / freezing water freezing mechanisms are distinguished, and misjudgment is avoided; through initial index calculation, CTTmap is dynamically adjusted according to different scenes, and satellite detection deviation is corrected; finally, through dynamic index correction processing, vertical motion, supercooled water and a real-time report are introduced, and result self-adaptive optimization is achieved.

The invention discloses a causal reasoning-based satellite-ground collaborative remote sensing image interpretation method and device, relates to the technical field of remote sensing image processing, and mainly aims to solve the problem that the inference requirement of environmental causes in a remote sensing image cannot be met in the prior art. Comprising the following steps: a ground end obtains initial interpretation features obtained by performing initial interpretation on multi-modal remote sensing data by a satellite-borne end, and interprets the initial interpretation features based on a first interpretation model of which model training is completed to obtain core interpretation features; determining causal variables based on the core interpretation features, and constructing a causal variable graph based on the causal variables; determining a cause label and an interpretation result of the label area according to the causal variable graph, and obtaining a verification result corresponding to the cause label and the interpretation result; and based on the knowledge distillation and the verification result, determining learning core features of the first interpretation model for updating training, so that a second interpretation model in the satellite-borne end coordinates the learning core features fed back based on the ground end.

The invention provides an offshore ship suspicious navigation behavior identification method and system, and the method comprises the steps: collecting AIS, radar, satellite and other multi-source data of a ship in a target sea area, and carrying out the data cleaning, fusion and standardization preprocessing; extracting navigation features, staying features, mode features and interaction features of the ship, constructing a behavior recognition model based on a neural network, inputting ship features, and then outputting a recognition result and confidence; and judging result validity through a confidence coefficient threshold value of dynamic calculation, triggering artificial review or multi-source data secondary verification through an invalid result, generating early warning information when a valid suspicious behavior is identified, calculating a risk value in combination with a ship type, a behavior severity degree and an environmental impact factor, and matching a pre-constructed decision library to generate a decision suggestion. According to the method, the recognition precision is improved through multi-source data fusion and an intelligent model, and real-time and efficient monitoring and response to suspicious navigation behaviors are realized in combination with a confidence coefficient mechanism and risk decision support.

The invention relates to the technical field of forest fire prevention, in particular to an infrared image forest fire point early recognition method based on space-time analysis, which comprises four steps of infrared image sequence continuous acquisition, moving target detection, moving target feature analysis and fire point judgment and result generation. Acquiring an infrared image sequence of the forest area by using an infrared sensor carried by an unmanned aerial vehicle or a satellite; differential processing is carried out through a frame difference method, and a moving target is extracted in combination with morphological operation; calculating the distinction degree of the moving target and the background based on the gray features, and screening possible fire point targets; the fire point is regarded as a singular attractor in a dynamic system, a space-time state space is constructed, dynamic characteristics of the space-time state space are analyzed for discrimination, a dynamic system theory and a multi-time-scale analysis framework are innovatively introduced, the early fire point can be accurately recognized, the development trend of the early fire point can be predicted, the recognition accuracy is remarkably improved, and the method is suitable for popularization and application. And a scientific basis is provided for timely intervention.

The invention discloses a satellite-ground cooperative processing method and system based on edge computing, and the method comprises the steps: constructing a satellite-ground integrated cloud edge-end cooperative architecture which comprises a satellite terminal layer, a ground edge layer and a cloud computing layer, connecting a satellite end with a ground cloud center through a distributed foundation edge service station, and achieving the unified scheduling of satellite-ground resources and task cooperation; establishing a task processing position decision model based on task data volume, link bandwidth and computing power, dynamically selecting a satellite end, an edge station or a cloud center for processing in combination with response time constraint and energy consumption cost, and optimizing time delay and energy consumption; the method comprises the following steps: constructing a geoscience sky intelligent learning framework, performing ground center offline training to optimize a deep learning model, performing pruning quantification to generate a lightweight model, issuing the lightweight model to a satellite end, performing on-line reasoning by the satellite end, and collecting and returning data to form a closed-loop learning process; an offline-online cooperation mode is introduced, high-real-time tasks are preferentially processed online, non-real-time tasks are cached and downloaded in batches, and a strategy is dynamically adjusted to improve the system efficiency and the resource utilization rate.

The invention discloses a satellite beam scanning scheduling method and device for preventing same-frequency interference and a storage medium. The method belongs to the field of satellite communication, and comprises the following steps: determining sub-bands respectively adapted to a plurality of beams of a satellite; initializing a particle swarm, wherein each element of a particle vector of the particle swarm indicates a beam position scanned by each beam of the satellite in each beam hopping time slot of a beam hopping period through different numerical intervals; a fitness function is constructed, and the function value of the fitness function is related to the severity of the same-frequency interference in the satellite coverage area; performing iterative optimization on the particle swarm according to a particle swarm optimization algorithm, and determining an optimal particle vector; and according to the optimal particle vector, determining the beam position scanned by each beam in each beam hopping time slot of the beam hopping period. According to the invention, by optimizing the beam position scanning scheduling scheme of the beam in the beam hopping period, the coverage overlapping and signal cross interference of adjacent same-frequency sub-beams are effectively avoided.

The invention belongs to the technical field of fault positioning, and discloses a Beidou satellite time service-based power distribution network fault section positioning method, which comprises the following steps of: acquiring three-phase current, and performing phase synchronization alignment on the three-phase current by using a Beidou satellite to obtain a three-phase current synchronization data sequence; performing modulus transformation on the three-phase current synchronous data sequence to obtain a zero-mode current component and a line-mode current component; performing adaptive waveform decomposition on the zero mode current component and the line mode current component to obtain an intrinsic mode component, and performing signal reconstruction on a target component to obtain an enhanced fault traveling wave signal; performing waveform curvature sudden change detection on the enhanced fault traveling wave signal to obtain a wave head arrival time and a time difference observation sequence; performing geometric analysis on the topological structure based on the time difference observation sequence and the traveling wave propagation speed to obtain a suspected fault section; and comprehensively studying and judging the suspected fault section to obtain an actual fault section. The power distribution network fault positioning efficiency can be improved.

The embodiment of the invention provides a satellite communication and navigation integrated system, which comprises a baseband subsystem and a processor subsystem, the baseband subsystem comprises a front-end processing module, a low-orbit communication module, a navigation processing module and a decoder module, the front-end processing module is configured to preprocess an acquired satellite signal and output a baseband signal, and the decoder module is configured to decode the baseband signal. The baseband signal comprises a navigation signal and a low-orbit communication signal; the navigation processing module is configured to process the navigation signal to obtain a first target signal; the low-orbit communication module is configured to perform signal processing on the low-orbit communication signal to obtain a second target signal; the decoder module is configured to decode the first target signal and the second target signal to obtain navigation data and communication data; and the processor subsystem is configured to perform resource scheduling on the front-end processing module, the navigation processing module, the low-orbit communication module and the decoder module based on the navigation data and the communication data. According to the invention, the integrated requirement of the navigation chip on navigation and communication can be realized.

The invention relates to the technical field of satellite attitude control, in particular to a satellite-borne laser semi-autonomous pointing control method, electronic equipment and a storage medium. The method is completed by cooperation of a ground system and an on-satellite system, the ground system calculates a top target passing moment T * in advance, generates a unified laser pointing control instruction and injects the instruction into a satellite; and the satellite-borne system receives and analyzes the instruction, obtains parameters such as T * and beam selection, and then autonomously controls a specified load for work preparation. And the satellite-borne system autonomously calculates the optimal moment T1 and the target attitude when passing through the calibration field through high-precision orbit extrapolation based on the latest navigation data, finally autonomously executes attitude maneuver and laser pointing tasks, and autonomously returns after the tasks are completed. Instructions in a uniform format are generated and injected from the ground, ground operation is greatly simplified, efficient cooperation of ground decision triggering and on-satellite autonomous execution is achieved, pointing errors caused by orbit extrapolation are greatly reduced, the pointing precision and the task success rate are improved, and universality is good.

The invention discloses a satellite attitude system anti-interference finite time control method under complex dynamic disturbance, and the method comprises the steps: building a rigid satellite attitude maneuver control model according to satellite attitude dynamics and kinematics equations; designing a self-adaptive fine disturbance observer to estimate the total disturbance of a satellite attitude system by combining the influence of the external disturbance variable on the rigid satellite attitude maneuver process, and outputting an estimated value of the external disturbance variable; a three-stage segmented sliding mode control method is designed, dynamic continuity of a three-stage sliding mode is ensured, and segmented sliding mode control output is obtained; and compensating the segmented sliding mode control output by using an estimated value of an external disturbance variable output by a self-adaptive fine disturbance observer to realize satellite attitude stable control. According to the method, the problem that the stability of the satellite is reduced in the attitude maneuvering performance process when external disturbance exists is solved, better observation performance and shorter attitude stabilization time are achieved, and the control precision of the satellite is effectively improved.

The invention relates to a hybrid task-driven satellite group autonomous task planning thermodynamic diagram generation and updating method, and relates to the field of multi-satellite task planning. The method comprises the following steps: inputting initial data containing a static task and a dynamic task and generating an initial thermodynamic diagram; periodically and autonomously updating the thermodynamic diagram by adopting a time-driven method according to the updating time period; a planning result is generated from the thermodynamic diagram through a task planning method and executed by a satellite; respectively inputting the static task execution result, the dynamic task execution result after target association fusion and the new task into an event-driven thermodynamic diagram updating method for updating; and finally, re-inputting an updating result into the task planning to form a closed loop. According to the method, a unified task driving input and decision reference model is provided for satellite-borne task collaborative decision through the thermodynamic diagram, time driving and event driving are combined, automation and intelligence of satellite group task planning are achieved, and the planning efficiency and the system self-adaptive capacity are remarkably improved.

The invention discloses a global ionosphere modeling method and device based on Beidou single-frequency ionosphere weighted PPP, and belongs to the technical field of GNSS navigation positioning and atmosphere modeling. The method comprises the following steps: acquiring real-time precise orbit and clock error information of a Beidou satellite and an initial ionospheric delay correction value; a single-frequency ionosphere weighted precision single point positioning (SF-IW-PPP) observation equation is constructed; establishing a space-time correlation constraint model of the ionized layer delay error and determining a prior variance; carrying out combined calculation by taking the previous variance as a constraint to obtain an ionosphere delay residual error, and further obtaining the total delay of the high-precision inclined ionosphere; and finally generating a global ionosphere grid model. According to the invention, high-precision and real-time global ionosphere modeling is realized by only needing a low-cost single-frequency receiver and combining Beidou real-time enhancement service, the hardware threshold and data processing delay are remarkably reduced, and the method is suitable for the fields of public navigation, intelligent transportation, space weather monitoring and the like.

The invention discloses a GNSS (Global Navigation Satellite System) signal spoofing detection method, device and equipment, a storage medium and a program product. The method comprises the following steps: tracking and monitoring a plurality of GNSS satellite signals, calling a tracking loop correlator to carry out autocorrelation operation to obtain the autocorrelation power of each satellite signal, constructing the AP detection quantity of each satellite signal based on the autocorrelation power, verifying the Gaussian property of the AP detection quantity, and carrying out moving average filtering processing on the AP detection quantity conforming to Gaussian distribution to obtain the AP detection quantity of each satellite signal. The method comprises the following steps: acquiring Gaussian distribution characteristic information of a GNSS satellite signal, constructing an AP-MA detection quantity, determining a detection threshold according to the Gaussian distribution characteristic information, detecting the AP-MA detection quantity based on the detection threshold, and judging whether the GNSS satellite signal has deception jamming or not; the AP detection quantity is constructed based on the self-correlation power to carry out signal spoofing detection, so that the detection range and the detection precision are effectively improved, and the timeliness and the stability of spoofing detection are ensured under the condition of not increasing additional equipment and algorithm complexity.

The invention relates to the technical field of airspace control, and discloses an AI-based low-altitude airspace information center collaborative control method, which comprises six core steps of multi-source sensing fusion, abnormal behavior discrimination, dynamic risk assessment, environmental constraint re-planning, communication collaborative optimization and collaborative execution decision-making to construct a closed-loop intelligent decision-making mechanism. Microsecond-level time synchronization is realized through a Beidou or GPS satellite time service system, and the target identification precision is improved in combination with a weighted evidence fusion theory; an R-tree and space-time bounding box dual rule engine is combined to accurately detect abnormal flight; the collision risk between the aircrafts is quantified by using a three-layer stacked multi-head map attention network, and trajectory re-planning under environmental constraints is realized through a multi-dimensional environment voxel model; a ground and satellite hybrid networking architecture is adopted for communication collaborative optimization, so that terrain shielding and electromagnetic interference are avoided in management and control communication, global coverage and accurate adjustment are realized, and the accuracy, real-time performance and safety of management and control are ensured.

The invention relates to the technical field of deep foundation pit monitoring, and discloses a deep foundation pit micro-deformation InSAR remote sensing method and system and a storage medium. The method comprises the following steps: synchronously acquiring data through a ground radar and an InSAR satellite, and obtaining a point target set and an original scattering characteristic sequence; obtaining a net deformation phase sequence without influence through registration residual correction, phase deduction and weighted fusion processing, and carrying out phase consistency quality control and unwrapping processing to obtain an accumulated deformation quantity sequence; constructing a deformation mechanism correlation characteristic matrix based on correlation analysis of the cumulative deformation quantity sequence and radar reflection intensity amplitude attenuation characteristics; and fusing the deformation mechanism correlation feature matrix and the real-time differential interference image group, extracting deformation rate and phase gradient change, and further generating a deep foundation pit local micro-deformation risk early warning index set. According to the invention, the tiny deformation of the surrounding area of the foundation pit can be effectively detected, potential risks are warned in advance, and the safety and monitoring efficiency in the construction process are improved.

The invention discloses a fire point detection device applied to a satellite, and belongs to the technical field of space remote sensing. The method comprises the steps that first detection equipment and second detection equipment are installed on a satellite; the first detection device is in communication connection with a control computer of a satellite, and the second detection device is in communication connection with a data management computer of the satellite; the first detection equipment has a first field angle and a first resolution ratio and is used for determining the position of a fire point and sending the position of the fire point to the control computer, so that the control computer determines a maneuvering target based on the position of the fire point and sends the maneuvering target to the data management computer; the data management computer is used for controlling the working state of the second detection equipment based on the maneuvering target; the second detection equipment has a second field angle and a second resolution ratio and is used for imaging the fire point under the control of the data management computer; wherein the first field angle is larger than the second field angle, and the first resolution ratio is lower than the second resolution ratio. According to the invention, through a cooperation mechanism of the first detection device and the second detection device, rapid discovery and accurate detailed investigation of global fire points by a satellite are realized, and the observation efficiency and the resource utilization rate are significantly improved.

The invention relates to the technical field of satellite power supplies, in particular to a weak light power-on control circuit and processing method for a satellite before satellite-rocket separation, and the circuit comprises a storage battery pack, an autonomous power-on unit, a forced shunting unit and a plurality of solar cell subarrays. The forced shunting unit comprises a forced shunting signal output module and a forced shunting power execution module, and the solar cell sub-array irradiated by weak light before satellite-rocket separation is a target solar cell sub-array; the forced shunting signal output module is arranged at two ends of the storage battery pack and is used for forming a driving voltage of a forced shunting signal through voltage division; and the forced shunting power execution modules are arranged at two ends of the target solar cell sub-array and are used for receiving the forced shunting signals to form a forced shunting loop, performing forced shunting on weak light current formed by the target solar cell sub-array before satellite-rocket separation, and pulling down the driving voltage to disconnect the forced shunting loop after satellite-rocket separation. According to the invention, the weak light current formed by the target solar cell subarray can be forcibly shunted before satellite-rocket separation.

The invention provides a satellite optical communication link switching method and system, electronic equipment and a storage medium, and relates to the technical field of communication, and the method comprises the steps: carrying out the analysis and processing of a first bit error rate and / or first signal intensity of a first satellite-ground link between a first satellite and a first ground gateway station, so as to obtain an average bit error rate and / or average signal intensity; the abnormal condition of the first satellite-ground link can be identified timely and accurately; according to the method, position information of satellites, service information of service data and performance parameters of a plurality of inter-satellite links are obtained, and link weights of the inter-satellite links are calculated based on the information to select a target inter-satellite link, so that an adaptive inter-satellite transmission path can be efficiently determined; and the service data is forwarded from the first satellite to the target satellite through the target inter-satellite link, and the service data is forwarded by means of the target satellite and the corresponding target ground gateway station, so that the continuity of satellite service transmission from space to the ground is ensured, and the service transmission blocking caused by link interruption is avoided.

The invention discloses a high-heat-flux heat dissipation system for an on-orbit computing power cluster, and belongs to the technical field of spacecraft heat control. The system is independent of a satellite conventional thermal control platform and is specially used for discharging waste heat of an AI calculation array. The system comprises a heat capture unit, a pumpless heat transfer unit and a foldable heat dissipation unit. The heat transmission unit comprises a micro-channel flexible pulsating heat pipe (such as a diamond film material), and the heat pipe spans a folding area and has the functions of structural connection and heat transmission, so that a thermal low-impedance independent channel relative to a satellite structure is formed. Through the design of removing a mechanical pump and removing a mechanical hinge, the problems of large weight, micro-vibration interference, high contact thermal resistance and the like of a heat dissipation system of the computing power satellite are solved, and preferential directional heat dissipation of high-flux heat is realized.

According to a communication method and related devices, first information received by a first communication device is used for indicating information of N satellite beams, and the first communication device can determine a target satellite beam communicating with a first terminal device based on the information of the N satellite beams. Wherein in each of the K time periods, a signal coverage area of at least one satellite beam in the N satellite beams comprises a first geographic area, and when the first communication device receives the first information, the terminal device located in the first geographic area comprises a first terminal device. In other words, any terminal device located in the first geographic area can determine the target satellite beam based on the information of the N satellite beams indicated by the first information. In this way, one or more terminal devices located in the same geographic area can determine the target satellite beam based on the first information, and the transmission overhead can be reduced.

The invention discloses a satellite-based routing decision making method and device and a storage medium. The method comprises the following steps: determining a plurality of reference curves in each first sampling period; determining a first distribution curve in the current time period, and broadcasting the reference curve of the current time period, the first distribution curve and the channel capacity of each area in the current time period to each satellite; determining a reference curve of the next time period, calculating a deformation relation between the reference curve of the second sampling time period and the reference curve of the third sampling time period, and performing deformation processing on the first distribution curve to obtain a plurality of second distribution curves of the next time period; predicting the satellite congestion degree of each region in the next time period according to the channel capacity of each region in the current time period on the basis of the plurality of second distribution curves; and based on each region, constructing a plurality of corresponding routing paths, and determining an optimal routing path in the plurality of routing paths by using a genetic algorithm. Therefore, the technical effect of reliably transmitting data is achieved.

The invention discloses a spaceborne high-performance calculation module and system based on a SpaceVPX standard and a control method. The calculation module comprises a board card following the SpaceVPX standard, and a core processor module, a storage module, a communication interface module, a monitoring module, a power management module and a VPX connector which are integrated on the board card. The core processor module adopts an anti-radiation reinforced high-performance processor; the storage module comprises a DDR4, a NORFLASH and an SSD (Solid State Disk); the communication interface module comprises an Ethernet, an SRIO high-speed interface and a debugging interface; the monitoring module collects state information through an I2C bus; the power management module provides stable power supply; the VPX connector leads out an SRIO bus, an ETH bus and an I2C bus, and star interconnection with other units on a satellite is achieved. Through standardized and modular design, the problems that an existing satellite-borne computing architecture is fixed, poor in expansibility and insufficient in reliability are solved, and high-performance, high-reliability and flexibly-combined satellite-borne data processing capacity is achieved.