36 results about "Earth satellite" patented technology

The invention discloses an ultra-low orbit guarantee method, system and equipment for a near-earth satellite. Comprising the following steps: determining a satellite orbit element at the current moment based on an atmospheric resistance perturbation item, a conventional perturbation item and a small thrust perturbation item, and inputting the satellite orbit element at the current moment into an orbit mechanical model; based on the orbit mechanical model and the satellite orbit elements, determining a first velocity position parameter of the satellite at the prediction moment under the ICRS coordinate system, and converting the first velocity position parameter into an ECEF coordinate system to obtain a second velocity position parameter at the prediction moment; inputting the time characteristic, the satellite state characteristic, the space environment characteristic and the second speed position parameter of the current moment into an orbit correction model to obtain a target error prediction value; adjusting the second speed position parameter based on the target error prediction value to obtain a target speed position parameter of the satellite at the prediction moment; and performing orbit attenuation risk early warning based on the target speed and position parameters of the satellite at the prediction moment.

The invention discloses an ultra-low orbit determination method and device for a near-earth satellite, a medium and a product. Comprising the following steps: acquiring a thrust vector of a satellite engine under a satellite body coordinate system under the condition that the thrust of an ion propeller of a satellite is constant; obtaining a first rotation matrix of the satellite attitude angle relative to the geocentric inertial coordinate system, and converting the thrust vector to the geocentric inertial coordinate system based on the first rotation matrix to obtain thrust components of the thrust vector on three coordinate axes of the geocentric inertial coordinate system; combining the satellite mass, the real-time on-off state of the engine and the thrust components on the three coordinate axes to obtain a small thrust perturbation item; and adding a small thrust perturbation item on the basis of the atmospheric resistance perturbation item and the conventional resistance perturbation item to obtain an input parameter, and inputting the input parameter to the orbit mechanical model, so that the orbit mechanical model determines the satellite orbit element based on the atmospheric resistance perturbation item, the conventional perturbation item and the small thrust perturbation item.

The invention discloses a method for estimating the safety communication rate of a near-earth satellite by using an SDFS cooperating with a GLRT. The method comprises the following steps: constructing a communication system model between the near-earth satellite and a ground terminal; analyzing the signal and channel characteristics, and obtaining the distance between the nodes, the channel gain and the received signal distribution; under the condition that the transmitting power of each monitoring party is unknown, estimating the transmitting power by adopting generalized likelihood ratio test, and independently executing the generalized likelihood ratio test based on the observation data of each monitoring party; the superior manager performs joint judgment based on a soft decision fusion scheme in combination with the generalized likelihood ratio test result of each monitoring party and a joint threshold so as to estimate the detection error probability of the monitoring party; a joint optimization strategy of the transmitting power and the number of continuous transmission time slots is constructed, and the total throughput of the system is maximized under the condition that the cooperative concealment constraint is met; according to the invention, an innovative solution is provided for reliable communication of the near-earth satellite in a complex monitoring environment.

The invention discloses a method for identifying a to-be-optimized space of a built environment based on a form hierarchical model. The method comprises the steps of collecting and preprocessing data of the built environment, preliminarily performing form hierarchical operation of the built environment, correcting the form hierarchical operation of the built environment, preliminarily identifying the to-be-optimized space, identifying the hierarchical operation of the to-be-optimized space, and interacting and feeding back identification results. According to the method, data acquisition is carried out through a laser radar system, an aerial photography unmanned aerial vehicle, a street scene acquisition vehicle and a near-earth satellite, and recognition and display of a to-be-optimized space of a built environment are carried out in combination with multi-task Bayesian federal learning, an XGBoost model, a Vision Transformer and a convolutional neural network. According to the method, the rapid identification of the to-be-optimized space of the built environment in the urban planning field can be assisted, and the rationality and accuracy of the identification result of the to-be-optimized space of the built environment are improved through form classification.

The invention provides a constellation software batch automatic upgrading method and system based on a laser link. Firstly, a ground control center generates a plurality of reconstruction packets, and the reconstruction packets are sequentially sent to a low-orbit earth satellite through a high-bandwidth microwave communication channel. Then, after the satellite receives the reconstructed packets, the correct reconstructed packets are reserved, and data increment packets are extracted at the same time; after the database receives the information that the satellite completes reconstruction, other satellites with software version numbers lower than those of the satellites in the constellation network to which the satellites belong are counted immediately, and the models of the satellites are transmitted to the satellites. And the satellite divides the incremental packet into a plurality of small packets, and after forward error correction coding and numbering processing, the small packets are multiplexed by using a DVB-S2 protocol and transmitted to a target satellite through an optimal laser link. The target satellite restores the complete incremental package, software updating is carried out in the dynamically determined idle time period, meanwhile, unified updating of ground database configuration is carried out, and therefore efficient and reliable batch upgrading is achieved.

The invention discloses a near-earth satellite communication task unloading method based on ground cooperative computing and a program product, a satellite communication task unloading model is established, and the satellite communication task unloading model aims at the minimum task unloading total time delay. A task unloading rate strategy of a satellite, an unloading path strategy of a task on the satellite and an unloading path strategy of the task on a ground station are used as variables to be solved; the task unloading total time delay is specifically the sum of the calculation time delay of the task on the satellite, the transmission time delay of the task unloading from the satellite to the ground station, the transmission time delay of the task between the ground stations and the calculation time delay of the task on the ground station, and then solving the satellite communication task unloading model to obtain a task unloading strategy. According to the method, the unloading strategy is relatively small in time delay and high in robustness, the defect that the LEO calculation capability is limited is effectively overcome, the upper limit of the task quantity accepted by a single LEO is greatly increased, and meanwhile, the problem of non-uniform task processing distribution of a ground station is solved.

The present application discloses an agricultural information management system and method based on a big data platform, which relates to the field of intelligent management technology. The system acquires farmland remote sensing data collected by near-Earth satellites; extracts data features from the farmland remote sensing data to obtain a divergence topology global farmland remote sensing feature matrix; and determines the level of pests and diseases in the farmland based on the divergence topology global farmland remote sensing feature matrix. The system can timely and accurately monitor and identify the extent of pests and diseases, improve agricultural production efficiency and ensure food security.

The present invention discloses a method and a program product for offloading near-earth satellite communication tasks based on ground collaborative computing. In the present invention, a satellite communication task offloading model is established. Among them, the satellite communication task offloading model aims to minimize the total task offloading delay, and takes the task offloading rate strategy of the satellite, the offloading path strategy of the task on the satellite, and the offloading path strategy of the task on the ground station as variables to be solved. The total task offloading delay is specifically the sum of the computing delay of the task on the satellite, the transmission delay of the task from the satellite to the ground station, the transmission delay between ground stations, and the computing delay of the task on the ground station. Then, the satellite communication task offloading model is solved to obtain the task offloading strategy. The offloading strategy of the present invention has a small delay, high robustness, effectively overcomes the disadvantage of limited computing power of LEO, greatly raises the upper limit of the task volume received by a single LEO, and at the same time solves the problem of uneven task distribution in ground station processing.

The utility model discloses a near-earth satellite communication device based on a reconfigurable intelligent surface. The near-earth satellite communication device comprises a satellite transmit-receive device and an RIS device. The satellite transceiving device comprises a first main control module, and a first power supply module, a first Bluetooth transceiving module and a satellite antenna which are connected with the first main control module; the RIS device comprises an RIS control board and an RIS antenna board connected with the RIS control board; the RIS control board comprises a second main control module, and a second power supply module, a second Bluetooth transceiver module, a GPS module and an attitude calibration unit which are connected with the second main control module; the RIS antenna board is provided with an antenna array composed of a plurality of patch antenna units. By introducing the intelligent reconfigurable metasurface, the system can sense and adapt to a continuously changing communication environment in real time and automatically adjust the configuration of the metasurface, so that the efficiency and stability of signal transmission are improved; the system realizes global coverage through a satellite network, is especially suitable for places such as remote areas, mountainous areas or islands, and the metasurface communication device does not depend on complex infrastructures and can be more flexibly deployed in different areas.

1. The name of the design product: Launch Vehicle (Chirei 6). 2. The use of the design product: used for space transportation, sending the payload such as artificial earth satellites, manned spacecraft, space stations or space probes into the predetermined space orbit. 3. The design points of the design product: the combination of shape, pattern and color. 4. The picture or photo that best shows the design points: perspective view. 5. The design claimed contains color.

The present application relates to the technical field of communication antenna, in particular to a kind of main bearing structure of satellite communication antenna on earth, including bearing seat, and the bearing seat is equipped with feed source component, further including the adjusting rod of rotation installation in the two sides of bearing seat, the outside rotation installation of adjusting rod is equipped with support part, and the lock unit for the locking of support part is installed on adjusting rod;And installation on the driving component of bearing seat, driving component is used to drive bearing seat to move;And the connecting portion of support part is matched with docking, connecting portion is connected with support part, the length of support part is extended, meet around the outside of rod, connecting piece is installed between two adjacent connecting portions, the support part of the present application is designed to cooperate with connecting portion, can be directly wound on the outside of rod body, and through driving component, drive bearing seat and feed source component to carry out corresponding lifting, to satisfy when the height of feed source component is improved by the way of climbing along the rod in lower terrain, to facilitate the acceptance of signal.

A low cost adaptive phase lighting system, which cancels the effect of sky-glow on the detection of terrestrial and celestial targets. It comprises a synchronization signal (26) radio transmitter (25), an adaptive modulated lighting phase receiver (12), and a synchronous optical detection receiver (12). The system permits the unification of outdoor lightings (10) phase to allow synchronous optical detection of faint target (18) berried in heavy light-pollution (17), protects astronomical observatories (21) from urban sprawl, helps terrestrial surveillance, earth satellites and airborne optical imaging device (22) to detect intruder targets under extreme sky-glow, and boosts homelands security.

The invention discloses a space traffic information sensing method based on a star sensor network. The space traffic information sensing method comprises a space end and a ground end. At a space end, a plurality of artificial earth satellites form a regional or global network, and each satellite is provided with a star sensor, so that a star sensor network is formed, and the star sensors dynamically shoot space images in real time; an onboard computer of a star sensor is used for processing an original image according to the processes of image acquisition, feature extraction / centroid positioning, star map matching, target recognition / astronomical attitude determination and target orientation calculation, and space target measurement data is obtained. Space target measurement data are downloaded to a data processing center at a ground end, and the data processing center analyzes the space target measurement data according to processes of segmental arc association, maneuvering detection, cataloguing library updating, collision early warning and the like, and generates data products including a space target track, maneuvering information, a collision probability, a collision avoidance strategy and the like. And wide-area and rapid space traffic information perception is realized.

A ground antenna determines the current time and its own position from received signals that were transmitted by artificial earth satellites for communication. A high-gain multi-beam electrically-steered antenna is combined with a processing system to measure the angles between two or more satellites and determine the present distance to each satellite by the information broadcast on the TT&C channel. The knowledge of the angles and distances, as well as the trajectory of the satellites, can be combined with their locations as predicted by the satellite ephemeris data to triangulate the location of the receiver. This system is different from conventional GPS antennas because it does not require the cooperation of active communication with the satellites to derive a location estimate. The location is computed by the ground terminal, not by the satellite. This system can be used in cases where other locating services are offline, jammed, or otherwise unavailable to maintain location and time synchronization.

The application discloses a method for calibrating a roll angle of an emergency anti-solar time of a satellite on the earth, which is beneficial to reestablishing a three-axis attitude of the satellite on the earth. Firstly, an angle between a projection of a sun vector on an orbit plane and an orbit system-X axis is calculated; then, whether a current orbit position meets a requirement is determined according to the angle between the projection of the sun vector on the orbit plane and the orbit system-X axis, and whether an absolute attitude reference is available at present is determined, if the current orbit position meets the requirement and the absolute attitude reference is available at present, the roll angle is calibrated at a current control beat; otherwise, the roll angle is not calibrated at the current control beat; if the roll angle is calibrated at the current control beat, the roll angle is calculated based on the absolute attitude reference; if the roll angle is not calibrated at the current control beat, the roll angle is calculated by using gyro inertia angular velocity integration. The application can provide high-precision and reliable attitude information for reestablishing the attitude of the satellite on the earth.

The present invention proposes an ocean observation and monitoring system based on a deep-sea underwater bottom-mounted platform, which belongs to the technical field of ocean observation and monitoring; it includes several deep-sea platforms, which are fixedly arranged at a certain depth below the water surface, and are used to generate electricity and locally store electric energy under the action of ocean currents, and conduct deep-sea monitoring in the adjacent range to obtain deep-sea environmental information; several cross-media aircraft, which are used to receive deep-sea environmental information sent by the deep-sea platforms, conduct joint detection in underwater areas near the several deep-sea platforms, or conduct joint detection in low-altitude areas above the water surface, and send the obtained deep-sea environmental information or joint detection results to the outside; several high-altitude airships, which are deployed at high altitude positions in the sea area, and are used to communicate with the several cross-media aircraft and receive deep-sea environmental information or joint detection results; near-earth satellites, which are used to communicate with the several high-altitude airships and receive deep-sea environmental information or joint detection results forwarded by the several high-altitude airships, to achieve background synchronization and remote storage.

A ground antenna determines the current time and its own position from received signals that were transmitted by artificial earth satellites for communication. A high-gain multi-beam electrically-steered antenna is combined with a processing system to measure the angles between two or more satellites and determine the present distance to each satellite by the information broadcast on the TT&C channel. The knowledge of the angles and distances, as well as the trajectory of the satellites, can be combined with their locations as predicted by the satellite ephemeris data to triangulate the location of the receiver. This system is different from conventional GPS antennas because it does not require the cooperation of active communication with the satellites to derive a location estimate. The location is computed by the ground terminal, not by the satellite. This system can be used in cases where other locating services are offline, jammed, or otherwise unavailable to maintain location and time synchronization.

A method for setting the RF operating frequency of an MRI system (1) uses a first reference frequency signal obtained from a geostationary satellite system as a stable long-term frequency reference. The first frequency reference signal is used to calibrate a second frequency source (24), which is then used as the master clock of the MRI system (1) for setting the RF operating frequency.

The present invention relates to the field of power emergency, and in particular to a power supply and distribution switching system based on power emergency, comprising: a satellite acquisition module for acquiring satellite remote sensing images monitored by artificial earth satellites, a fire monitoring module for preprocessing the satellite remote sensing images, determining the fire area, forming corresponding fire point preprocessing data, and generating a fire dynamic monitoring map, a matching module for analyzing the fire dynamic monitoring map, calculating the corresponding real-time fire area, and comparing it with the fire area threshold, an emergency switching module for determining the corresponding power supply emergency plan, switching the power supply station, and clearly understanding the operation sequence of the power supply station in an emergency by identifying and analyzing fire characteristics to protect the power infrastructure and ensure the stability of the power supply, thereby achieving a rapid response to the fire and dynamic adjustment of the power supply, and optimizing the real-time monitoring of the fire and the intelligent management of the power supply.

According to the method for applying the space-time positioning and the three-dimensional communication to the rail transit through the near-earth satellites, the positioning precision is improved and the initial positioning time is shortened by transmitting navigation enhancement information through a near-earth satellite constellation communication navigation time service function or a transmission channel, or / and the navigation signal strength is enhanced through the positioning satellite function of the near-earth satellites, and the positioning accuracy is improved. Reliable train-ground communication, train-train communication, train head-tail communication, trackside equipment and stations and inter-station communication of a train in a satellite communication section are achieved by providing a switching method between near-earth satellite constellation satellites or wave beams, and the satellite communication section can be obtained through train positioning or prompted by a ground transponder through marking in line data by dividing the satellite communication section. Switching between a satellite communication section and other communication sections can be realized, and the transportation efficiency is improved.

The present application discloses a method, device, medium and product for determining the ultra-low orbit of a near-earth satellite. The method includes: when the thrust of the ion thruster of the satellite is constant, obtaining the thrust vector of the satellite engine in the satellite body coordinate system; obtaining the first rotation matrix of the satellite attitude angle relative to the geocentric inertial coordinate system, and converting the thrust vector to the geocentric inertial coordinate system based on the first rotation matrix to obtain the thrust components of the thrust vector on the three coordinate axes of the geocentric inertial coordinate system; combining the satellite mass, the real-time on / off state of the engine, and the thrust components on the three coordinate axes to obtain a small thrust perturbation term; adding the small thrust perturbation term on the basis of the atmospheric drag perturbation term and the conventional drag perturbation term to obtain an input parameter, and inputting the input parameter into the orbital mechanics model, so that the orbital mechanics model determines the satellite orbit elements based on the atmospheric drag perturbation term, the conventional perturbation term and the small thrust perturbation term.

The application provides a constellation software batch automatic upgrading method and system based on a laser link. First, a ground control center generates multiple reconstruction packages and sequentially sends the multiple reconstruction packages to a low-orbit earth satellite through a high-bandwidth microwave communication channel. Then, the satellite retains correct reconstruction packages while extracting data incremental packages after receiving the reconstruction packages. After receiving information that the satellite completes reconstruction, a database immediately counts other satellites in a constellation network to which the satellite belongs and having a software version number lower than that of the satellite, and transmits the types of the other satellites to the satellite. The satellite divides the incremental packages into multiple small packages, processes the small packages through forward error correction coding and numbering, multiplexes the small packages using a DVB-S2 protocol, and transmits the small packages to a target satellite through an optimal laser link. The target satellite restores complete incremental packages, performs software updating in a dynamically determined idle period, and simultaneously performs unified updating configured by a ground database, so that efficient and reliable batch upgrading is realized.

1. Name of the product in this design: Launch Vehicle (Chitu 6A). 2. Purpose of this design: For use in space transportation vehicles to send payloads such as artificial Earth satellites, manned spacecraft, space stations, or space probes into predetermined space orbits. 3. The key design elements of this product are the combination of shape, pattern, and color. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The design for which protection is sought includes color.

The present application discloses an ultra-low orbit guarantee method, system and device for a near-earth satellite. The method includes: determining the satellite orbit elements at the current moment based on the atmospheric drag perturbation term, the conventional perturbation term and the small thrust perturbation term, and inputting the satellite orbit elements at the current moment into the orbit mechanics model; determining the first velocity position parameters of the satellite in the ICRS coordinate system at the prediction moment based on the orbit mechanics model and the satellite orbit elements, and converting the first velocity position parameters into the ECEF coordinate system to obtain the second velocity position parameters at the prediction moment; inputting the time feature, satellite state feature, space environment feature at the current moment, and the second velocity position parameters into the orbit correction model to obtain the target error prediction value; adjusting the second velocity position parameters based on the target error prediction value to obtain the target velocity position parameters of the satellite at the prediction moment; and performing an orbit decay risk warning based on the target velocity position parameters of the satellite at the prediction moment.

The application discloses a kind of based on point iteration earth satellite orbit fast calculation method and system, belong to aerospace technology field, selected single time calculation interval step and the point number in each calculation interval;According to the initial position and velocity of earth satellite, set the position and velocity estimation value of each point time of earth satellite in calculation interval;Local point feedback iteration method is used to carry out iterative correction to the position and velocity estimation value of earth satellite at each point time;It is judged whether the position and velocity state of earth satellite in all running time have been completely calculated, repeat the preceding steps, until the end time of calculation interval reaches target calculation time length stops.The application estimates and corrects the position and velocity information of earth satellite using feedback iteration method, uses point method to avoid integral symbol operation to reduce calculation amount, uses CGL point to improve the calculation precision of earth satellite velocity and position at the end of each interval, provides a kind of high-efficiency high-precision calculation method for earth satellite orbit prediction.

Dynamic access control of at least one communication terminal to the satellite communication resources of a low-Earth satellite constellation. The present invention relates to a method (36) for dynamically controlling access of a terminal to the satellite resources of a low-Earth satellite constellation, comprising the following steps, for a predetermined mission: - prior geolocated planning (38) of the allocation partition of all satellite resources according to a geolocated need associated with said mission, and the predetermined path of each satellite; - dynamic access control (44) of said terminal to said satellite resources by applying, at each predetermined time of said mission, the following substeps: - identification and location (48) of said terminal; - determination (50) of the nature of the service required from said terminal;- routing of said terminal to a piece of said partition according to said identification, said location and said nature of service. Figure for the abbreviation: Figure 2;

The invention discloses a low-orbit near-earth satellite flight control system execution method and module, and belongs to the technical field of instruction management for spacecrafts. According to the execution method, an instruction channel and an instruction value are sent to a satellite, after the satellite receives the instruction channel and the instruction value, verification is conducted through a verification instruction so as to detect whether a transmission error exists or not, and if verification passes, a specific instruction is analyzed according to the content of the instruction channel and the instruction value; then the satellite executes a corresponding task according to the analyzed instruction and the delay output instruction; and if an exception occurs in the execution process, triggering an error correction mechanism according to an output enabling error correction instruction, and outputting a corresponding error correction instruction to correct an error. According to the method, the flexibility and the intelligent degree of the control system are improved by increasing the instruction delay output capability, whether the instruction code after error correction is output or not can be effectively controlled by increasing the error correction instruction output enabling part, and the reliability and the accuracy of anti-error instruction output of the control system are greatly improved.

The utility model provides a near-earth satellite-borne phased array signal processing system (short for 5G NR-NTN), comprising a front-end 5G signal transceiving system connected through a high-speed FMC interface (short for O-RU); the data front-end processing system is connected with the front-end 5G signal transceiving system through the high-speed FMC interface (O-DU for short); the data co-processing system is connected with the data front-end processing system (called O-CU for short) through a high-speed XMC connector; wherein the front-end 5G signal receiving and transmitting system is used for receiving and transmitting 5G signals, the data front-end processing system is used for processing the signals, the data co-processing system is used for exchanging data, and the front-end 5G signal receiving and transmitting system, the data front-end processing system and the data co-processing system form an integrated signal processing module. According to the utility model, a high-performance CX8242 chip is adopted as the core of a front-end 5G signal transceiving system, and the ADC and DAC with high sampling rate and high resolution and the ADCFB with low noise are combined, so that the precision and efficiency of signal processing are effectively improved.

The invention relates to the technical field of communication antennas, in particular to a main bearing structural member of a near-earth satellite communication antenna, which comprises a bearing seat, a feed source component mounted on the bearing seat, adjusting rods rotatably mounted on two sides of the bearing seat, and supporting parts rotatably mounted on the outer sides of the adjusting rods, a locking unit for locking and limiting the supporting part is mounted on the adjusting rod; the driving part is mounted on the bearing seat and is used for driving the bearing seat to move; the supporting parts are matched with the connecting parts, the connecting parts are in butt joint with the supporting parts in a matched mode, the connecting parts are connected with the supporting parts, the length of the supporting parts is increased, the supporting parts are wound on the outer side of the rod, and a connecting piece is installed between every two adjacent connecting parts. The lifting mechanism drives the bearing seat and the feed source component to lift correspondingly, so that the height of the feed source component is increased by climbing up along the rod when the terrain is low, and signals can be received conveniently.

The invention provides an intelligent multi-scale sea-land-air-space global expression method based on a Columbus view, relates to the technical field of geospatial visualization, and realizes unified expression of complex multi-target spatial data through the steps of spatial classification, height conversion and height optimization. According to the method, the spatial height of the earth satellite is divided into user-defined intervals which can be defined by a user, and clear distribution of the multi-target height in the view is achieved by combining the mapping relation and proportional adjustment. In the final rendering process, the target subjected to height processing is fused into a Columbus view in a pseudo three-dimensional mode, the two-dimensional tiling characteristic is reserved, and the space understanding ability is improved. The method is suitable for task planning, remote sensing analysis and military monitoring in a complex multi-target scene, and has the remarkable characteristics of high flexibility, clear expression and strong expansibility.