58 results about "Satellite constellation" patented technology

The application discloses a satellite communication baseband processing method with flexible configuration function, relates to the technical field of satellite communication, and specifically a baseband processing method process is as follows: S1, interface adaptive adaptation scheduling; S2, downlink receiving scheduling; S3, uplink sending scheduling; S4, configurable hardware acceleration scheduling.The application can greatly improve the adaptive flexibility of baseband processing and the hardware multiplexing rate by executing four-step cooperative scheduling of downlink receiving scheduling, uplink sending scheduling, configurable hardware acceleration scheduling and interface adaptive adaptation scheduling, and all signal data are uniformly stored and scheduled with the memory as the core, compared with the fixed hardware pipeline architecture in the prior art, and therefore the technical problems of the prior satellite communication baseband processing, such as the need of modifying hardware circuits when switching satellite constellations or replacing radio frequency devices, high adaptation cost and low efficiency, can be solved.

The application provides a star group autonomous cooperative search and tracking method based on dynamic information gain, which comprises the following steps: acquiring satellite constellation parameters and target initial state information; long-time sequence tasks are decomposed into continuous short-time sequence decisions based on a closed-loop rolling horizon planning framework, the target state distribution is predicted to obtain the uncertainty degree and generate an atomic task candidate set in each rolling period; the tracking or search mode is adaptively selected according to the uncertainty degree and the value is evaluated; the optimal task scheme is generated based on a multi-objective evolutionary algorithm; and the observation is performed and the target state is updated according to the observation result to enter the next period. The application dynamically adapts to the target uncertainty evolution through the closed-loop rolling horizon planning, avoids tracking rupture, uniformly measures the value of search and tracking through adaptive dual-mode cooperative decision, solves the value conflict problem, realizes the space-time optimal configuration of star group resources through the multi-objective evolutionary algorithm, and improves the continuous tracking capability and resource utilization efficiency.

Systems, methods and devices to manage user orders for geospatial information and to perform an optimization scheme for satellite resources within a satellite constellation are provided. Embodiments include computer-implemented methods comprising receiving, from a user, an order for geospatial information, wherein the order comprises at least one attribute related to the ordered geospatial information; and querying a database to identify information about other orders received from the same or different users, with the same or different attributes; and at least one of: setting a price for the geospatial information ordered by the user based at least in part on the at least one attribute and the identified other orders, or performing an optimization scheme for determining whether the ordered geospatial information can be provided to the user and the other user orders can be satisfied, and targeting at least one sensor on board a manned or unmanned aerial vehicle configured to collect the geospatial information based on the determination.

A kind of distributed attack-resistant domain management and control method and system for giant constellation, the present application relates to satellite constellation management and control technical field, the present application aims at solving the problem of cooperative management and control and attack-resistant resilience maintenance of multi-layer heterogeneous giant constellation in dynamic topology environment.Technical points: the present application takes the management and control node satellite as core, combines with the cluster head satellite and ordinary satellite in domain, forms distributed management and control domain structure.The structure undertakes cross-orbit communication switching and distributed cooperative management and control function, effectively deals with the cooperative management and control challenge brought by the difference of multi-orbit satellite in operation cycle, communication topology and communication time delay;Introduce multi-element maximum entropy trust model: based on fuzzy C clustering algorithm and maximum entropy principle, construct dynamic trust evaluation system, and comprehensively quantitatively analyze the trust degree of distributed nodes.Through real-time identification of high-risk nodes and implementation of isolation measures, significantly reduce the interference of malicious satellite to inter-satellite data transmission, improve system security.The present application realizes the efficient cooperative management and control and attack-resistant ability enhancement of multi-layer heterogeneous giant constellation, provides key technical support for stable operation of giant constellation under complex threat environment.

This application provides a remote sensing data processing method and system, electronic device, and storage medium, relating to the technical field of remote sensing data processing. The remote sensing data processing method includes: acquiring target remote sensing data from a target satellite constellation based on received user data requests; parsing the sensor type corresponding to the target remote sensing data to determine at least one target type of remote sensing data; determining the metadata information of the target type remote sensing data; performing block processing on the target type remote sensing data based on the metadata information to obtain multiple sub-target type remote sensing data; and performing distributed parallel computation on the multiple sub-target type remote sensing data to obtain the target output result. This application enables online access and acquisition of remote sensing data by parsing user data requests online, avoiding local downloads and offline processing. By migrating remote sensing data and algorithms to the cloud, it solves problems such as long processing time, low processing efficiency, and high local resource consumption costs.

This invention provides a method for rapid perception of the topology status of a satellite constellation network. It deploys a multi-dimensional physical layer monitoring module, a dynamic adaptive BFD detection mechanism, the OSPF routing protocol, and a shared data exchange area between the BFD driver and the OSPF process on each satellite node. This invention utilizes physical layer signal status monitoring technology and the rapid link status detection capability of the BFD protocol to monitor the connectivity of inter-satellite links in real time. Upon detecting a fault, it immediately notifies relevant nodes via control messages. Simultaneously, it links the BFD detection results with the OSPF routing protocol, triggering immediate route recalculation, thereby shortening route convergence time. This invention constructs a cross-layer closed-loop linkage system, dynamically adjusting protocol layer detection parameters through physical layer perception data, and combining hardware acceleration to optimize the entire fault detection process. This not only accelerates fault detection and recovery but also improves the resource utilization efficiency and overall transmission efficiency of the inter-satellite network, ensuring high network reliability and stability.

This application provides a target detection method and system based on multi-satellite on-orbit scheduling to combat cloud interference. The method includes: deploying a satellite constellation architecture, which includes a central satellite and multiple edge satellites; capturing images of the area to be detected to obtain initial remote sensing images, and identifying and classifying cloud thickness in the initial remote sensing images to determine thin cloud regions and thick cloud regions; identifying at least one area to be captured from the thick cloud-covered areas corresponding to the thick cloud region images; generating a capture schedule table for the areas to be captured; capturing images of the areas to be captured using the target edge satellites according to the capture schedule table to obtain target images of the areas to be captured; performing target detection on the thin cloud region images and the target images to determine the targets in the areas to be detected. By optimizing the scheduling and cooperation between satellites, the method can effectively capture targets in the areas to be detected.

A satellite communication system which provides interference mitigation across multiple constellations. The satellite communication system provides interference mitigation when an in-line event occurs where a main lobe of a satellite of the first constellation and a main lobe of a user terminal communicating with the satellite of the second satellite constellation intersect sufficiently to cause significant interference on a common frequency band of the satellite and the user terminal.

This invention discloses a secure transmission method for satellite constellation communication based on post-quantum cryptography, relating to the fields of satellite communication and information security technology. The method includes: analyzing the satellite constellation topology to determine the latency sensitivity level of the secure handshake; pre-screening a set of candidate PQC algorithms based on the sensitivity level; sensing the channel and extracting non-stationary features such as fading depth, duration, and Doppler rate of change; constructing a multi-dimensional joint optimization model with algorithm identifier, fragmentation granularity, redundancy, and modulation and coding scheme as joint decision variables, aiming to maximize the handshake probability within the expected duration; solving the model to generate an adaptive transmission strategy, and performing adaptive non-uniform fragmentation and fountain code encoding on PQC protocol data units; predicting link trends based on Doppler rate of change and dynamically scheduling symbol transmission. This invention achieves deep coupling optimization of network topology, cryptographic algorithms, and channel characteristics, improving the transmission reliability of PQC in dynamic satellite networks.

This application provides a deformation monitoring method, device, medium, and program product based on satellite constellations, belonging to the field of Internet technology. The method includes: acquiring observation data of the monitored object from each satellite constellation in a satellite constellation platform based on the object's location information; correcting the coordinate data of the corresponding satellite constellation according to the target correction parameters of each satellite constellation to obtain corrected coordinate data; fusing the corrected coordinate data of the corresponding satellite constellation according to the fusion weight parameters of each satellite constellation to obtain target coordinate data; analyzing the reference coordinate data and target coordinate data to obtain analysis results; and if the analysis results determine that the target coordinate data is abnormal, then the monitoring result is determined to be abnormal deformation of the monitored object. Using the method provided in this application, multiple satellite constellations can be used to monitor the deformation of the monitored object, effectively improving the accuracy of deformation monitoring.

This invention discloses a post-quantum cryptographic encryption communication device for a satellite constellation communication network, belonging to the field of satellite communication security technology. It includes a constellation link management module, a post-quantum authentication module, a post-quantum key negotiation module, a data encryption processing module, a secure key storage module, and a hardware acceleration and power consumption control module. The constellation link management module is communicatively connected to the post-quantum key negotiation module, the post-quantum authentication module, and the data encryption processing module. The post-quantum authentication module is communicatively connected to the post-quantum key negotiation module and the secure key storage module. The post-quantum key negotiation module is communicatively connected to the data encryption processing module, the secure key storage module, and the hardware acceleration and power consumption control module. This invention uses the above device to achieve real-time perception of the satellite communication link status through the constellation link management module, enabling key negotiation to be dynamically triggered according to constellation topology changes, thereby improving communication security.

The application discloses a constellation health state diagnosis method based on multi-dimension performance index fusion, and has the characteristics that the steps are as follows: (1) based on the task implementation performance, resource occupation rate and timeliness of a satellite constellation when performing a task, the satellite constellation index and the satellite index of each satellite in the satellite constellation are calculated; (2) each constellation index and each satellite index are standardized to obtain the standardized constellation index corresponding to each constellation index and the standardized satellite index corresponding to each satellite index; (3) the standardized satellite indexes of the same category of all satellites are respectively grouped into a set of standardized satellite index sets; (4) based on the entropy weight method and the analytic hierarchy process, the fusion weight corresponding to each standardized constellation index and the standardized satellite index set is obtained; (5) based on the fusion weight of each standardized constellation index and the standardized satellite index set, the comprehensive performance evaluation value of the satellite constellation is obtained, and then whether the satellite constellation has a fault is evaluated.

A satellite constellation forming system (100) forms a satellite constellation which is composed of a satellite group and in which the satellite group cooperatively provides a service. The satellite constellation has a plurality of orbital planes in each of which a plurality of satellites fly at the same nominal orbital altitude. A satellite constellation forming unit (110) continues providing the service while avoiding a collision between satellites by both or one of control of an orbital altitude and control of a passage timing of a satellite group flying in a region where the plurality of orbital planes intersect.

This invention discloses a system and method for optimizing the configuration of a space target surveillance satellite constellation. The system includes: a constraint modeling and configuration module, which uniformly models the detection constraints and observation constraints in the space target surveillance process and constructs an observable judgment model; a surveillance performance evaluation index module, which constructs various surveillance performance evaluation indices; a multi-objective parallel optimization module based on a determinant-based point process, which, based on a non-dominated sorting genetic algorithm, introduces a determinant-based point process to model the diversity of the non-dominated solution set, optimizes the selection of individual quality and solution set diversity by maximizing the determinant of the subset of the kernel matrix, and completes efficient screening using a greedy approximate inference method; and a constellation configuration optimization solution module, which constructs a multi-objective optimization problem with the surveillance performance evaluation index as the optimization objective, calls the multi-objective parallel optimization module based on a determinant-based point process for joint optimization, and obtains the optimal or near-optimal constellation configuration scheme that satisfies multiple constraints.

The application provides a kind of low-orbit satellite constellation-oriented computing resource arrangement method, system and equipment, it is related to satellite communication technical field, including: low-orbit satellite receives remote sensing satellite in current time slot under the task set generated, and the computing resource arrangement problem of task set is decomposed into task scheduling subproblem and resource allocation subproblem;Low-orbit satellite models task scheduling subproblem as Markov decision process, utilizes the scheduling strategy network based on deep reinforcement learning to solve Markov decision process, to determine the target low-orbit satellite corresponding to task, and issues task to target low-orbit satellite;Low-orbit satellite models resource allocation subproblem as convex optimization process, utilizes Lagrange multiplier algorithm to solve convex optimization process, to allocate target computing resource for the task received by low-orbit satellite.The application can significantly improve the problem of task demand diversification, satellite resource limited heterogeneity and satellite load imbalance in low-orbit satellite constellation.

The application relates to a kind of optical satellite constellation comprehensive quality evaluation methods;Satellite constellation can effectively improve the overall performance of satellite through multi-satellite networking, and the comprehensive quality evaluation of satellite constellation is an important factor in satellite efficiency analysis, while the multi-satellite comprehensive quality evaluation process is affected by the inconsistency of geometric radiation, the application proposes an optical satellite constellation comprehensive quality evaluation system based on load observation ability and orbit coverage ability analysis, and the comprehensive quality evaluation of satellite constellation is realized by using multi-satellite quality consistency processing method, and the satellite constellation comprehensive quality evaluation result obtained by the method is more comprehensive and reliable, which can provide technical basis for subsequent domestic optical satellite constellation comprehensive quality evaluation.

This invention provides a method for accurately calculating the airspace coverage of a satellite constellation, including: delineation of the airspace responsibility area of ​​the satellite; tracking of coverage feature points and dynamic airspace segmentation; analytical expression of the segmented coverage area function; segmented integration and coverage volume calculation; and calculation of the total constellation coverage rate. This method forms a Voronoi diagram by subdividing a spherical triangular network composed of the satellite's nadir points and their neighboring points. Based on the varying number of coverage feature points on the spherical shell at different altitudes, a dynamic airspace segmentation strategy oriented towards spatial altitude is proposed. By dividing the satellite coverage area into three-dimensional primitives, and combining this with the dynamic airspace segmentation strategy, a method for accurately calculating the constellation airspace coverage rate based on an integral Voronoi diagram is further proposed. Segmented integration is used to calculate the constellation's airspace coverage rate.

This invention discloses a satellite positioning method, system, device, and medium, relating to the field of positioning technology. The method includes the following steps: acquiring multi-band GNSS data; employing double-difference observation, fixing integer ambiguity parameters, and calculating the quadratic difference between the receiver and satellites for the multi-band GNSS data to obtain independent positioning results for each system; setting an optimization logic based on multiple threshold conditions to select the system with the highest accuracy score; performing adaptive weight allocation using a normalization method based on the real-time accuracy scores of each GNSS system in the horizontal and vertical directions; and obtaining a coordinate fusion result as the satellite positioning result by weighted summing of the coordinate components calculated by each GNSS system with their adaptive weights in the corresponding directions. Through dynamic optimization and weighted fusion of satellite constellations from different satellite navigation and positioning systems, the reliability and environmental adaptability of the positioning solution are significantly enhanced.

A communications system may include user equipment (UE) that transmits data to a recipient via a network. The UE may receive user input and may generate the data based on the input. When a terrestrial network is unavailable to the UE, the UE may transmit segments of the data over a satellite constellation as the UE continues to receive input and while connectivity to the constellation exceeds a threshold. If a portion of the input includes an edit to a previous segment, the UE may include an edit flag in the corresponding segment. Once input has finished, the UE may sign the segments and may transmit a signature over the constellation. The network may store the segments as received from the constellation, may replace edited segments with more recent segments containing edit flags, and may compile and transmit all of the segments to the recipient upon receipt of the signature.

An inter-satellite fault knowledge sharing method based on federated learning, when a master satellite or a slave satellite in a satellite constellation appears a fault, first, a model is trained with local data of the satellite; after the model training is completed, the model parameters of the satellite are transmitted to other satellites, and other satellites update their own models based on the transmitted model parameters. The present application reduces the amount of information exchanged between satellites by transmitting the parameters of each model between satellites without directly transmitting fault data, and simultaneously updates the multi-satellite fault diagnosis model based on the transmitted model parameters, thereby realizing the continuous updating of the fault diagnosis model on each satellite, and further improving the accuracy of subsequent constellation fault diagnosis.

This application discloses a navigation channel early warning method, device, and storage medium based on a low-Earth orbit (LEO) satellite constellation, relating to the field of sea ice monitoring technology. The method includes: a first satellite acquiring navigation channel images; inputting sea ice images contained within the navigation channel images into a pre-trained gradient calculation model to generate corresponding gradient feature maps; classifying the sea ice images to determine their brightness categories; and then calling a first U-Net network, a second U-Net network, and a transition matrix corresponding to the brightness category to determine the sea ice edge lines of the sea ice images. If the first satellite determines that the sea ice poses a threat to a preset navigation channel based on the edge lines, it transmits sea ice-related early warning information to a second satellite in the LEO satellite constellation; the second satellite then transmits the early warning information to vessels within the coverage area. Thus, this application achieves on-orbit identification and real-time broadcasting of navigation channel risks, as well as feature enhancement and targeted processing of sea ice images under different lighting conditions.

The application discloses a routing method, medium, equipment and product of a low-orbit satellite constellation, relates to the technical field of satellite routing, and comprises the following steps: according to a quality of service parameter, performing snapshot freezing on a current network topology to construct a static topology graph structure; constructing a basic quality of service parameter cost function for each link; performing an offline ant colony optimization algorithm to globally evaluate a satellite topology library constructed in advance, constructing a heuristic function according to a link basic quality of service parameter cost; initializing a pheromone value for each link, and updating the pheromone in an iteration process according to the heuristic function; adjusting the cost function based on the pheromone; taking the cost of the discounted pheromone as the final link weight of the satellite network, constructing a weighted graph structure, and adopting a shortest path search algorithm to calculate a routing path between a source node and a target node, so that an optimal routing path is obtained. The application solves the problems of high-speed time-varying satellite link state adaptability and poor quality of service.

This invention relates to a multi-agent reinforcement learning-based interference avoidance method for low-Earth orbit (LEO) satellite constellations, comprising: step 1, environment construction and parameter initialization; step 2, local state information acquisition; step 3, global state aggregation and Critic evaluation; step 4, reverse updating of each Actor based on the system-level reward and advantage function output by the Global Critic, etc. The superiority of this invention lies in its departure from traditional static rule allocation or single optimization criteria. Through multi-agent reinforcement learning, it performs online learning and adaptive decision-making on interference relationships in multi-satellite, multi-beam scenarios, better adapting to the actual environment of rapidly changing topology, frequent service link switching, and dynamic changes in interference modes in LEO satellite constellations. A multi-objective joint reward function composed of local and global cooperative rewards is constructed, overcoming the problem of local optima leading to global imbalance in existing technologies, thereby improving the overall spectrum utilization efficiency and communication stability of the system from a mechanistic perspective.

This invention relates to a ground flight control and operation support system for a very low Earth orbit (UEO) satellite constellation. It incorporates predicted space environment information, satellite attitude change information, and orbit control information into the high-precision satellite orbit prediction process, effectively ensuring higher orbit prediction accuracy for the UEO constellation and maximizing the assistance to ground control stations during satellite transits in capturing and tracking the satellite. The satellite attitude and orbit control system simulation module performs real-time simulations of the impact of attitude control and orbit control on orbital maneuvers, thereby achieving higher orbit control accuracy and providing better assurance for the precise execution of missions by the UEO constellation. Automatic scheduling of Earth remote sensing and data transmission tasks, along with ground system fault identification and handling, and collision warning, provide more intelligent support for the operation of the UEO constellation.

This utility model discloses a satellite constellation orbit correction device based on inter-satellite links, belonging to the field of aerospace technology. It includes a ground station body, with a receiver mounted on the top of the ground station body. Four supports are fixedly mounted on the bottom of the receiver, and the outer side of each support is provided with an insulating layer. This inter-satellite link-based satellite constellation orbit correction device controls an electric push rod to move a lifting plate. Through the limiting of a sliding groove, a slider assists the lifting plate in moving up and down within a receiving slot. At this time, the shielding mesh can be pulled up to achieve isolation and protection from the outside world. A discharge tube can reduce lightning damage to the equipment during thunderstorms. An antenna cover can effectively prevent rainwater from corroding the antenna elements. A filter can enhance signal transmission, enabling the antenna elements to stably send detection signals to the satellite constellation. Finally, through the receiver and external computing equipment, the satellite constellation orbit can be corrected.

A communications system may include user equipment (UE) devices that communicate with a network via a constellation of satellites. A UE may transmit a registration message to the network via a satellite, including information usable by the network to identify a first temporary user identifier (TUID) of the UE. The network may transmit a registration acknowledgment (ACK) that includes include the first TUID. In response to receiving the registration ACK, the UE may convey wireless data with the network under an assumption that the UE is in a registered / connected communications session with the network. The UE may perform these communications based on a second TUID that is different than the first TUID. If the network is unable to perform a successful integrity check on reverse link messages from the UE, the network may transmit a TUID flash message including the second TUID on all signal beams of the satellite.

This invention discloses a method for calculating inter-satellite communication windows for remote sensing satellite missions, belonging to the field of satellite communication technology. The technical implementation steps are as follows: Setting the orbital parameters and simulation time period of the satellite constellation; establishing an inter-satellite communication geometric constraint model considering Earth obstruction and maximum distance limitations; based on orbital dynamics principles, analytically deriving the upper bound of the distance change rate and the upper bound of the line-of-sight tangent point altitude change rate, characterizing the relative motion of the constellation; initializing the simulation time; calculating the geometric margin based on the current relative positions of the two satellites; and calculating the adaptive safety step size for the current time in conjunction with the aforementioned upper bounds of the change rates; if a visibility state jump is detected, numerical iterative search is used within the step size interval to lock the window boundary. This invention introduces dynamic boundary parameters to construct an adaptive step size mechanism, significantly reducing the number of invalid calculations while ensuring the accuracy of communication window calculation, thus significantly improving the computational efficiency of inter-satellite link planning.

The utility model relates to carding device technical field, especially a kind of quick carding device of suspension satellite constellation static display model.Its technical scheme includes roof, the bottom surface of the roof is fixedly provided with multiple lifting ropes, the lower end of the lifting rope is fixedly provided with fixed disc, globe is fixedly connected between the fixed disc;Orbit center ring is arranged on the outer wall of fixed disc, multiple orbit side rings are arranged between the orbit center ring, the clamping assembly for limiting is arranged between the orbit center ring and orbit side ring.The utility model can avoid the point-by-point screwing step of screw fastening cumbersome, greatly save assembly time and labor cost, significantly improve the installation efficiency of display model, meet the demand of quick assembly.

This invention provides a method for analyzing the cost uncertainty of a satellite constellation considering parameter uncertainties, comprising: estimating the total launch mass of the satellites, calculating the total launch mass of the satellite constellation based on the dry weight of a single satellite, the number of satellites, the wet weight to dry weight ratio, and the mass of the satellite distributor; calculating the launch segment cost, determining the number of launches based on the ratio of the total launch mass to the launch vehicle's carrying capacity, and calculating the total launch segment cost in conjunction with the price per launch; calculating the space segment cost, calculating the R&D cost and production cost separately, wherein the R&D cost is calculated based on the dry weight of the single satellite, and the production cost is calculated based on the dry weight of the satellites, the number of satellites, and the learning curve effect; calculating the total cost, adding the space segment cost and the launch segment cost to obtain the total cost of the satellite constellation; and assessing the uncertainty of cost parameters, constructing a Jacobian matrix of the total cost with respect to the uncertainty parameters, and analyzing the quantitative impact of the input parameter uncertainty propagating to the total cost estimation result.