662 results about "Satellite" patented technology

A system, method, and receiver control architecture for a Symbolic Resonant Energy Transfer Network (SRETN) configured to distribute electrical power wirelessly across planetary-scale distances under cryptographic, economic, and biological safety governance. The system comprises a distributed mesh of terrestrial resonant transmission towers and orbital relay satellites configured to deliver energy via directed magnetic resonance coupling. A Symbolic Energy Kernel governs authorization and transmission, preventing energization of any transmission vector unless a secure cryptographic energy handshake is completed. The handshake verifies: (i) authenticity and compliance of a requesting receiver device; (ii) real-time solvency of an associated decentralized energy ledger account; and (iii) clearance of the transmission path through active radar and lidar-based biological exclusion scanning. Energy is transmitted as discrete, tokenized packets, each cryptographically metered and acknowledged by the receiver prior to continuation. The system enables a wireless, infrastructure-light energy distribution paradigm in which electrical power is accessed on demand with transaction-level auditability and enforced safety constraints.

The application provides a user positioning method and device for low-orbit satellite communication and satellite network equipment, relates to the technical field of satellite communication, and the device comprises a receiving unit configured to receive a transmission delay and a Doppler frequency shift reported by a terminal device; a first processing unit configured to control the satellite network equipment to perform the following first operation: calculating a first included angle from the terminal device to a subsatellite point via a satellite according to the transmission delay and an orbital height of the satellite; calculating a second included angle from the subsatellite point to the terminal device in a satellite moving direction via the subsatellite point from a satellite overhead angle according to the first included angle, the Doppler frequency shift, a carrier frequency and a satellite moving speed; and determining position information of the terminal device according to the first included angle and the second included angle. The application can automatically estimate the position information of the terminal device without the terminal device reporting the position information, ensure the service continuity of a communication architecture depending on the terminal device information, and protect the user privacy and safety.

To provide a positioning device that can reduce the risk of decreased positioning accuracy in an environment of spoofing attacks. [Solution] A positioning device comprising: a receiving unit that receives a first satellite signal in a first frequency band and a second satellite signal in a second frequency band different from the first frequency band transmitted from a first satellite; a positioning unit; a determination unit that compares the value of a predetermined parameter included in the first satellite information of the first satellite based on the first satellite signal with the value of the predetermined parameter included in the second satellite information of the first satellite based on the second satellite signal to determine whether or not the first satellite is spoofed; and a control unit that controls the positioning unit so as not to perform positioning using the first satellite information and the second satellite information of the first satellite when the determination unit determines that the first satellite is spoofed.

This invention discloses a method for measuring the integrity of a spaceborne embedded system based on link symbol topology. In the static injection phase, a linker script is configured to inject symbols at critical memory segment boundaries, generating hierarchical hybrid fingerprints and redundantly persisting them to non-volatile storage. In the dynamic verification phase, a lightweight program is started before the operating system takes over, performing hierarchical dual-dimensional and SEU-resistant temporal redundancy verification, supporting multi-container dedicated isolation verification. In the linkage blocking phase, anomalies are forcibly blocked and primary / backup linkage is triggered, collecting eight types of fault contexts and supporting on-orbit updates. This invention solves the problems of traditional hash methods failing to detect layout anomalies and high time consumption, reducing complexity to O(K), achieving sub-millisecond-level measurement decoupled from image volume, adapting to spaceborne radiation-resistant, cloud-native, and redundancy scenarios, and meeting the high reliability requirements of aerospace.

The application provides a master-slave type star cluster cooperative SAR-GMTI system and method, which comprises: an azimuth multi-channel master star M1, a small satellite cluster M2 along a heading direction, and an on-board joint processing module M3; the azimuth multi-channel master star M1 is used for transmitting radar signals in a full array and receiving radar signals in an azimuth direction; the small satellite cluster M2 along the heading direction is composed of at least two small satellites in a receiving mode only, and the small satellite cluster is linearly distributed along the heading direction; and the on-board joint processing module M3 is used for fusing SAR image data of the azimuth multi-channel master star M1 and the small satellite cluster M2 along the heading direction, and completing target detection and relocation through space-time adaptive processing. The application effectively solves problems such as a large minimum detectable speed of a single platform system and speed ambiguity of a distributed system, and provides important technical support for subsequent spaceborne SAR earth imaging observation.

The application provides a satellite communication power adaptive regulation method, system and device, which divides the space where satellite communication belongs into multiple space grid areas according to a preset space division scale; acquires satellite sensing data, space weather data and near-earth weather data in each space grid area to determine communication link loss evaluation data corresponding to each space grid area; generates space interference summary information according to the loss evaluation data corresponding to each space grid area and location data thereof; and adjusts the transmission power of satellite communication in each space grid area according to the space interference summary information. The method and system of the application collect weather data in the space area and the near-earth area thereof to determine loss evaluation data, and realize dynamic adaptive adjustment of satellite transmission power in each space grid area based on the loss evaluation data, thereby improving the reliability of satellite communication in a complex space environment.

The application provides a method for analyzing a pointing angle of an inter-satellite link, comprising: obtaining orbital elements of a satellite and orbital parameters of a target satellite matched with an SGP4 model in a J2000.0 inertial coordinate system; determining a target recursion time t; obtaining positions of the satellite and the target satellite at the time t in the J2000.0 inertial coordinate system; determining a pointing vector from the satellite to the target satellite at the time t in the J2000.0 inertial coordinate system; determining the pointing vector in a satellite orbital coordinate system; determining the pointing vector in a satellite body coordinate system; determining the pointing vector in a satellite antenna coordinate system; determining a pointing angle of the satellite antenna coordinate system at the target recursion time; and determining whether a cycle number reaches a set cycle number, if the cycle number does not reach the set cycle number, continuously obtaining the pointing angle of the satellite antenna coordinate system at a next target recursion time until the pointing angle of the satellite antenna coordinate system at the set cycle number is obtained.

This invention provides an optical system and method for free-space quantum key distribution. The optical telescope employs a transmission-type telescope and a simplified rear optical path terminal, effectively avoiding secondary mirror obstruction and vignetting. The optical telescope system has a smaller axial dimension and is lighter than a Cassette-type reflecting telescope of the same aperture, making it more suitable for large-scale use in short-range free-space quantum communication. It can be carried and deployed by a single person and has all-day quantum key distribution capabilities. Furthermore, the transmitting and receiving telescopes are interchangeable, meaning the system can function as both a transmitter and a receiver, extending quantum communication coverage to areas inaccessible by fiber optics and satellites, and enabling rapid deployment in various emergency and unforeseen circumstances.

This application provides a method for batch handover of user terminals in a low-Earth orbit satellite network, comprising: a source satellite-borne base station sending measurement indicators of multiple user terminals entering its edge radii to multiple neighboring satellites to a satellite-borne decision center; the satellite-borne decision center inputting the measurement indicators into a packet handover decision model, outputting packet handover decision results, and returning the packet handover decision results to the source satellite-borne base station; the source satellite-borne base station determining the target neighboring satellites to which the multiple user terminals should handover based on the packet handover decision results and initiating batch handover request messages; and each target neighboring satellite, based on the batch handover request messages, cooperating with the source satellite-borne base station and each user terminal to complete the service handover. The dedicated signaling process for batch handover and the accompanying signaling compression method designed above can significantly reduce the transmission pressure of inter-satellite links. Furthermore, by using a deep learning model to consider the complex states and constraints of multiple users and multiple satellites for joint decision-making, it can more accurately select the satellites for handover.

The present application relates to the technical field of satellite altimetry and ocean surveying and mapping, and in particular to a GNSS-R sea surface height measurement method based on variable step line segment intermediate frequency data processing, which can effectively improve the measurement accuracy and efficiency, comprising obtaining satellite-borne GNSS-R original intermediate frequency data, calculating mirror reflection points through a new variable step line segment (NVSLSM), generating a delay Doppler map (DDM), and performing sea surface height inversion. Compared with the prior art, the NVSLSM is used to process the mirror reflection points, the calculation time is increased by about 2.04 times and 1.47 times compared with the line segment bisection method and the QH method, and on the premise of ensuring the convergence accuracy, the stable solution can be reached through fewer iteration steps, thereby reducing the calculation cost per sample; in the delay Doppler map generation link, the overall calculation efficiency is increased by more than about 90%.

The application discloses a kind of based on intelligent non-stationary control's satellite-ground fusion security transmission method, comprising the following steps;Step one: construct time-frequency dual-dimensional satellite-ground fusion transmission model, the construction of overall application scene is carried out;Step two: based on time-frequency dual-dimensional satellite-ground fusion transmission model, the acquisition of low interference continuous usable frequency slot is carried out, and frequency slot set is obtained;Step three: by the information sequence in the frequency slot set is changed into orthogonal non-stationary waveform signal, it simultaneously presents the dynamic non-stationary characteristic of no rule in time, space, frequency and multiple dimensions, to obtain final sequence;Step four: the performance analysis of the non-stationary control sequence obtained;Step five: based on performance analysis, by theoretical derivation, the security and reliability of the proposed method overall are tested.The application has the characteristics of strong anti-interference ability, high transmission stability, excellent security performance, adaptive complex time-varying channel environment.

The application relates to a satellite energy acquisition system based on space charged particle collection, belonging to the technical field of spacecraft power supply. The application aims at solving the problem that the discharge phenomenon of the space charged particles deposited on the surface of a satellite can cause physical damage to materials. The application comprises a collection capacitor used for capturing the space charged particles, forming a high-voltage electrostatic field through the accumulated charges of the space charged particles; an energy-taking conversion circuit used for converting the high-voltage electrostatic field energy stored in the collection capacitor into low-voltage electrostatic field energy and transferring the low-voltage electrostatic field energy to an energy storage capacitor; the energy storage capacitor is used for storing the low-voltage electrostatic field energy, setting a target electric field energy according to the working requirement of a rear-end load, and discharging after the target electric field energy is reached; and a switch voltage stabilizing circuit used for adjusting the discharging output voltage of the energy storage capacitor, realizing constant voltage power supply for the rear-end load. The application can reduce the charging and discharging fault risk of the surface of the satellite by collecting the particles radiated to the satellite and controllably transferring and utilizing the particles.

This invention discloses a fire detection device for satellites, belonging to the field of aerospace remote sensing technology. The method includes: a first detection device and a second detection device installed on the satellite; the first detection device is communicatively connected to the satellite's control computer, and the second detection device is communicatively connected to the satellite's data management computer; the first detection device has a first field of view and a first resolution, used to determine the location of a fire point and send the fire point location to the control computer, so that the control computer can determine a maneuvering target based on the fire point location and send the maneuvering target to the data management computer; the data management computer is used to control the working state of the second detection device based on the maneuvering target; the second detection device has a second field of view and a second resolution, used to image the fire point under the control of the data management computer; wherein, the first field of view is larger than the second field of view, and the first resolution is lower than the second resolution. This invention, through the collaborative mechanism of the first and second detection devices, enables rapid detection and precise detailed investigation of global fire points by satellites, significantly improving observation efficiency and resource utilization.

The application relates to an intelligent satellite assembly storage system, which comprises a computer control center, a material center and an assembly tool platform. The computer control center comprises a workbench, a computer, a digital-analog display module and a personnel operation area. The computer is used for operating the storage system, the digital-analog display module is used for checking the installation information of the satellite, and the personnel operation area is used for inputting instructions to the computer. The material center comprises a cabinet body, an import and export channel, a taking and using platform and a material conveying system. The import and export channel is used for the import and export of material boxes in the storage system, the taking and using platform is used for supporting the material boxes in the storage system, and the material conveying system is used for storing and feeding the materials. The assembly tool platform comprises a tool vehicle body and a material receiving area which is used for receiving the materials in the material conveying system. The intelligent satellite assembly storage system realizes intelligent and automatic operation of the whole system, improves the efficiency and accuracy of satellite assembly, reduces human errors and improves the assembly quality.

This invention belongs to the field of BeiDou deformation monitoring technology, specifically disclosing a method for quantifying the occlusion rate of a single BeiDou deformation monitoring station under complex observation environments. First, the elevation and azimuth information of the satellites are extracted from the observation data of the GNSS monitoring station. Then, cutoff elevation angle points are continuously extracted using the elevation and azimuth information. Next, the cutoff elevation angle points are smoothly fitted, and the smoothed fitting curve is obtained. Finally, the occlusion area and occlusion rate are calculated by integration. This invention requires no external equipment, relying solely on the observation data collected by the receiver. Furthermore, the observation data itself inverts the occlusion, naturally including the comprehensive occlusion effects of terrain, vegetation, buildings, and dynamic mechanical equipment. It can also automatically update as the observation data is updated, thus adapting to the dynamic changes in the occlusion environment. This invention is simple to operate, can be automated, and is particularly suitable for environmental self-assessment after rapid deployment of UAVs.

This invention provides a satellite photoelectric guidance method and system for space observation. The method includes: First, a photoelectric sensing device senses targets around the satellite, completes target measurement and orbit calculation, and after orbit recursion, matches the target data with a ground-based target database to update the target database and preliminarily search for and identify potential collision sources and interference sources; Second, an onboard integrated electronic computer requests target observation data from the photoelectric sensing device and receives the target observation data; Third, the onboard integrated electronic computer filters and sorts the received targets, locating collision sources and interference sources requiring key attention; Finally, the onboard integrated electronic computer programmatically activates the optical payload equipment and electronic payload equipment, and sends angle information to the optical payload equipment and electronic payload equipment to achieve detailed observation of space targets.

By appropriately selecting a positioning method, the accuracy of detecting the position of the work machine is improved. [Solution] The support system for the work machine includes a support device having a selection unit that selects either first correction information based on a satellite signal from a positioning satellite received by a base station and a reference point of the base station that received the satellite signal, or second correction information including the satellite signal received by three or more predetermined base stations and a virtual reference point based on the reference points of the three or more base stations, and a work machine that receives the first correction information or the second correction information selected by the selection unit, wherein the selection unit selects the first correction information or the second correction information according to the positional relationship between the polygonal area formed by connecting the reference points of the three or more base stations and the work machine.

The application provides a vehicle positioning method, a system, an electronic device and a computer storage medium, and relates to the technical field of automatic driving. In the absence of a fixed base station, the observation data of visible satellites is shared by two vehicles, so that the construction and maintenance costs can be saved, and the two-vehicle sharing can also be adapted to complex scenes and network-uncovered areas. In the positioning process, single-difference and double-difference processing is performed on the common visible satellites of the two vehicles, satellite clock errors, receiver clock errors and most atmospheric errors are eliminated, a high-precision relative baseline vector is obtained, and the obtained perception data of the two vehicles are fused and optimized to obtain the absolute positioning of the two vehicles, so that the positioning precision is improved and the absolute positioning reaches a centimeter-level precision. The purpose of providing stable and high-precision vehicle absolute positioning in a dynamic environment without relying on a fixed base station is achieved.

A multifunctional integrated ground testing system for spaceborne equipment is disclosed, covering the multifunctional testing field of spaceborne equipment. It provides reliable support for the functional performance testing of spaceborne equipment. The system includes an integrated management module, a telemetry and data processing unit, an interface forwarding simulator, a Ka-band converter, an RF link network, an interface forwarding network, and power supply equipment. Adopting a modular design, it features data interaction between the various components of the integrated ground testing system, human-machine interaction, remote control command parsing and distribution, telemetry information parsing, display and storage, health information monitoring, and dynamic signal simulation parameter calculation and distribution. This system solves major problems such as the limited number of connected spaceborne equipment and the single nature of functional performance test items, providing reliable and stable technical support for the ground testing of spaceborne equipment.

The application relates to the technical field of low-orbit satellite communication, and discloses a satellite communication-oriented traffic prediction method, device, equipment and medium, which are applied to a satellite-borne system, wherein the method comprises the following steps: receiving a self-description model package sent by a ground terminal in a standby area, and keeping an old model currently running in an active area to execute an inference task; obtaining original traffic data in a preset sliding window, determining a data correction factor of an adaptive ground model based on the difference between the original traffic data and statistical information; loading the data correction factor to the ground model to obtain a corrected new model; and in response to a model switching instruction, updating a global active model pointer from a memory address pointing to the old model to a memory address pointing to the new model by atomic operation. The technical scheme provided by the application can realize seamless hot updating of a model from the ground to the satellite without interrupting real-time inference services of the satellite-borne system.

This invention provides a payload software reconfiguration method for LEO satellites, applicable to ground control stations, payload management equipment within LEO satellites, and target payload units. The method divides the payload software reconfiguration of the target payload unit into two stages: In the first stage, within the data transmission arc, the ground control station fully utilizes the uplink bandwidth of the space-to-ground data transmission link to rapidly upload the software reconfiguration file to the payload management equipment for storage. In the second stage, the payload management equipment transmits the software reconfiguration file to the target payload unit via the internal interconnection bus, thus achieving software reconfiguration of the target payload unit. Furthermore, the accuracy of the software reconfiguration file transmission can be quickly determined through the first feedback information sent by the payload management equipment and the second reception feedback information sent by the target payload unit, allowing for timely re-transmission of the software reconfiguration file. Therefore, this method effectively improves the efficiency and accuracy of payload software reconfiguration for LEO satellites.

The application provides a method and device for applying target satellite timing and a readable storage medium, and relates to the technical field of communication. The method comprises the following steps: sending first indication information to a base station, wherein the first indication information is used for indicating that a UE acquires synchronization of a target satellite. The method solves the interference problem that may occur in a soft satellite switch scenario, thereby reducing the scheduling complexity of the base station.

The application provides a satellite-borne sunlight reflection device and a satellite-borne sunlight reflection control method, and the satellite-borne sunlight reflection device comprises at least one on-satellite reflection plate and a satellite main body; the satellite main body is used for adjusting an attitude reflection angle between the on-satellite reflection plate and parallel sunlight; the on-satellite reflection plate is connected with the satellite main body, and in operation, a reflection surface faces a direction of irradiation of the parallel sunlight and is used for reflecting the parallel sunlight to a dark area on the earth surface; the satellite main body adjusts the attitude reflection angle of the on-satellite reflection plate by adjusting an attitude, and adjusts a ground reflection light intensity. The satellite-borne sunlight reflection device can adjust sunlight reflection to a shadow position on the earth, so as to accurately control the reflectivity, and the reflectivity and reflection position of a reflection area can be accurately controlled, and the influence of the satellite-borne sunlight reflection on other areas is reduced.

The embodiment of the application provides a satellite structure, and relates to the technical field of spaceflight equipment. The satellite structure comprises: a main frame; a cabin plate; and a connecting assembly arranged between the main frame and the cabin plate. The cabin plate is movably arranged on the main frame through the connecting assembly and is fixed to any position after movement through the connecting assembly. The satellite structure can improve the test efficiency of electronic equipment during ground heat dissipation test.

The application provides a satellite task planning method and system under a task synthesis mechanism, and relates to the technical field of satellite task scheduling. The application comprehensively considers task observation benefits and satellite posture adjustment time when selecting tasks, and simultaneously considers synthesis and insertion when planning tasks. Angle adjustment constraints and longest start-up time constraints need to be verified when inserting, and first or second synthesis constraints and observation benefit constraints need to be verified when synthesizing. In the process of facing continuously changing task resources, selection can be made from a global perspective, so that a more optimal planning result is obtained, and resource utilization efficiency is improved.

This invention discloses an intelligent processing method for spaceborne lidar column concentration to improve global data coverage, comprising the following parts: feature set construction, auxiliary data acquisition and preprocessing, extreme random tree model construction and training, and global gap-free carbon dioxide column concentration (XCO2) reconstruction. In the auxiliary data acquisition and preprocessing part, the XCO2 product from the spaceborne IPDA lidar is used as the core data source, and the data undergoes quality control, type grouping, and spatiotemporal matching by merging other auxiliary data. In the extreme random tree model construction and training part, the XCO2 from the atmospheric environment monitoring satellite is used as the target output variable. Based on the differentiated feature sets of land and ocean, an annual extreme random tree model is trained to establish the mapping relationship between input features and XCO2. Finally, the gap values ​​detected by the spaceborne IPDA lidar are reconstructed based on multi-source auxiliary data, achieving 0.25° resolution and seamless global XCO2 data generation.

The application relates to a mobile phone direct connection S-band phased array radio frequency system based on a multi-layer mixed pressing plate technology, and belongs to the technical field of low-orbit satellite wireless communication, and specifically relates to a mobile phone direct connection S-band phased array radio frequency system based on a multi-layer mixed pressing plate technology. The phased array radio frequency system contains a plurality of single-channel radio frequency components, each single-channel radio frequency component is internally integrated with a radio frequency SIP module, a power supply SIP module, a radio frequency PA and a transceiving filter; the complete radio frequency transceiving link and the calibration branch are highly integrated in the single-channel TR component with the size of 60*50*8mm, the overall structure and the peripheral interconnection design of the component are greatly simplified, the single-channel radio frequency component multiplexing and the small-size and light-weight design of the component are realized, and the S-band low-orbit satellite engineering application is adapted.

The application provides a novel satellite-rocket electrical interface system, which comprises an interface assembly arranged on the outer surface of a satellite cabin plate, the interface assembly comprising X1F connectors, X2F connectors and X10B connectors arranged side by side; a ground test cable assembly, one end of which is provided with a first connector for connecting a satellite ground test device, and the other end of which is provided with a second connector for being connected with the X1F connectors and the X2F connectors; wherein a working port is arranged on the rocket fairing at a position corresponding to the interface assembly, and the working port is configured to allow the ground test cable assembly to be connected with the satellite connectors of the interface assembly before launch or to be manually disconnected and withdrawn. Thus, the application simplifies the satellite-rocket interface relationship, improves the reliability of satellite-rocket separation, improves the launch capacity, and reduces the system development cost.

This invention relates to the field of information and communication technology, and provides a satellite ground base station and its multi-operator sharing method. The method includes: the satellite ground base station supporting the establishment of NG links with multiple core networks; the satellite ground base station supporting the broadcast of public terrestrial mobile networks supported by multiple core networks; the satellite ground base station supporting the configuration of air interface resource ratios for multiple operators; and the satellite ground base station allocating air interface time and frequency resources according to the air interface resource ratios of each operator. In satellite communication systems, through the method of allocating air interface resources according to operators using the satellite ground base station of this invention, satellite terminals of different operators can access the same satellite ground base station, sharing the satellite ground base station hardware and air interface time and frequency resources, meeting the needs of independent operation of different services, and reducing network deployment and operation costs.