80 results about "Geostationary orbit" patented technology

The invention discloses a directional communication radio frequency signal hiding processing system based on a geostationary orbit satellite link, and belongs to the technical field of directional communication, and the system comprises an analog signal interface module which is used for collecting an analog signal and converting the analog signal into a digital signal; the random directional communication channel generation module is used for dynamically generating a random communication channel which comprises sending time randomization and sending direction randomization; the dynamic signal modulation module is used for carrying out randomized modulation and coding on the target signal; the complex signal shielding module is used for generating shielding signals similar to target signal features and covering the existence and parameter features of real communication signals; and the direct radio frequency modulation module is responsible for modulating the digital signal to a radio frequency band and transmitting the digital signal through an antenna. According to the invention, the random directional communication channel is designed, so that the risk that a signal is interfered by adopting a conventional channel is avoided; secondly, complex signal shielding is carried out on the sent signal, so that the risk that the target signal is intercepted and cracked is reduced;

The invention discloses an image transmission method and system suitable for a geostationary orbit satellite. The method mainly comprises the following steps that (1) a sending end collects an image; (2) determining a target edge coordinate; (3) intelligent cutting; (4) encoding the cut image; (5) dynamic fragmentation processing; (6) sending the fragmented data to a receiving end; (7) the receiving end receives the fragmented data and recombines the fragmented data; and (8) the transmitting end retransmits the lost fragment data according to the lost fragment list. According to the technical scheme provided by the invention, through intelligent cutting, dynamic fragmentation and UDP transmission, the characteristics of high delay and limited bandwidth of satellites are adapted, redundant data transmission is reduced, the image transmission efficiency and reliability are improved, and the problems of low transmission efficiency and weak interference resistance of a traditional method are solved.

The invention discloses a fast response flood disaster monitoring method and system based on super-resolution reconstruction. The method comprises the following steps: continuously acquiring a plurality of geostationary orbit satellite remote sensing images of an affected area and preprocessing the images; inputting the preprocessed geostationary orbit satellite remote sensing image into the trained super-resolution image reconstruction deep learning model, and outputting a reconstructed disaster area remote sensing image; and inputting the reconstructed disaster area remote sensing image into the trained flood disaster monitoring neural network model, and outputting a disaster range extraction result and a disaster situation evaluation result. According to the method, the characteristic of high time resolution of the geostationary orbit satellite is utilized to provide emergency response when a disaster occurs, cloud removal processing, super-resolution reconstruction and flood disaster area extraction are completed based on pure vision and a deep learning model algorithm, application under various extreme weathers can be supported, and the method has a wide application prospect. And a quick-response basic data service is provided for timely rescue and disaster relief and economic loss estimation.

The invention discloses a conditional diffusion method for reconstructing multi-source meteorological data for tropical cyclones. The conditional diffusion method comprises the following steps: acquiring an infrared radiation brightness set, a polarization correction temperature set and a sea surface wind speed of different tropical cyclones in a specified historical period; constructing a polarization correction temperature reconstruction model based on the conditional diffusion model; the input of the polarization correction temperature reconstruction model is an infrared radiation brightness temperature set, and the output target is a polarization correction temperature set; carrying out transfer learning on the trained polarization correction temperature reconstruction model to form a sea surface wind speed reconstruction model; the input of the sea surface wind speed reconstruction model is an infrared radiation brightness temperature set, and the output target is the sea surface wind speed. Therefore, the mapping relation from the infrared radiation brightness temperature to the multi-source meteorological data is established through generative deep learning of conditional diffusion, so that the multi-source meteorological data with the temporal-spatial resolution the same as that of geostationary orbit observation is reconstructed, and good performance is shown on various meteorological indexes and computer vision indexes.

The invention discloses a high-efficiency laser interference transmit-receive color separation film with good space environment tolerance, which belongs to the technical field of optical thin films and is characterized in that a multifunctional beam splitting film is plated on the front surface of a fused quartz substrate, and a thermal stress compensation-free antireflection film is plated on the back surface of the fused quartz substrate. A front film system adopts TiO2 and SiO2 as high and low refractive index materials, and a main film system based on a rear cut-off filter superposed multi-layer energy regulation and control structure is designed, so that efficient reflection of 1550 + / -10nm laser is realized; and a half-wave hole is eliminated by matching an asymmetric equivalent layer, so that neutral light splitting at the wave band of 750-900nm is realized. The back film is composed of Ta2O5 and SiO2, so that the residual reflection (ghost image) is efficiently eliminated, and the surface distortion caused by the front film layer is compensated. The laser interference transmit-receive color separation film is good in spectrum stability, can tolerate a severe environment directly exposed in a geostationary orbit, and can also be used for spectrum and energy regulation and control of other laser ranging cameras.

To provide a method of routing data traffic in non-geostationary orbit (NGSO) satellite systems.SOLUTION: The method utilizes, at satellites 102-107, backbone route tables that define different snapshots of time-varying backbone topology of an NGSO satellite system 100. Because each satellite 102-107 may refer to a different portion of the backbone topology, the backbone route tables at the satellites 102-107 are different from each other. In addition, the backbone route tables at the satellites 102-107 are active at different times because the backbone topology changes over time. Different routing groups of backbone route tables are defined to realize different routing options for packets arriving at the satellites 102-107.SELECTED DRAWING: Figure 1

This application provides a method, device, and computer-readable storage medium for evaluating the on-orbit calibration error of a microwave radiometer calibration system used in geostationary orbit. The application evaluates the on-orbit calibration error of the microwave radiometer calibration system by determining the errors of the calibration cold source, calibration heat source, Earth observation radiation brightness temperature, and Earth target brightness temperature. By separately evaluating the errors of the calibration cold source, calibration heat source, Earth observation radiation brightness temperature, and Earth target brightness temperature in the microwave radiometer calibration system used in geostationary orbit, each error is quantified, thus quantifying the on-orbit calibration error of the microwave radiometer calibration system. Furthermore, the different radiation transmission paths are considered during the evaluation of each error, making the evaluation of the sources of on-orbit calibration error of the microwave radiometer calibration system used in geostationary orbit not only effective and accurate but also highly implementable.

This invention discloses a high-efficiency laser interferometric transceiver dichroic film with good space environment tolerance, belonging to the field of optical thin film technology. The dichroic film has a multifunctional beam-splitting film deposited on the front side of a fused silica substrate, and a thermal stress-free antireflection film deposited on the back side. The front film system uses TiO2 and SiO2 as high and low refractive index materials, and is designed with a main film system based on a back-cutoff filter superimposed with a multi-layer energy control structure to achieve efficient reflection of 1550±10nm laser light; and eliminates half-wave apertures by matching asymmetric equivalent layers to ensure neutral beam splitting in the 750-900nm band. The back film system is composed of Ta2O5 and SiO2, which not only efficiently eliminates residual reflections (ghost images) but also compensates for surface distortion caused by the front film layer. This laser interferometric transceiver dichroic film exhibits good spectral stability and can withstand the harsh environment of direct exposure to geostationary orbit. It can also be used for spectral and energy control of other laser rangefinders.

A satellite in a communication system may be equipped with an antenna system that includes various configurations of antenna arrays on one or more sides of the satellite to receive and transmit signals, and a transponder system coupled with such antenna arrays that is configured to route signals between one or more reception ports and one or more transmission ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and a transponder system may perform one or more aspects of signal processing. A satellite may be configured with particular combinations of components in a reception system and a transmission system, and a corresponding transponder system may include various signal paths that support combinations of couplings and associated signal processing between the output ports and input ports to support various techniques for relaying communications via the satellite.

The invention relates to a multi-satellite collaborative observation probability estimation method for a window type target. The method comprises the following steps: inputting a statistical time range, an orbital element number and a load observation range of a guiding constellation A, and an orbital element number and a load observation range of a guided constellation B; and determining a to-be-observed area O, based on whether the constellation A is a geostationary orbit satellite, calculating the collaborative observation probability that the constellation A guides the low-orbit constellation B, and outputting a collaborative observation probability result. According to the method, the defect that the time dynamic characteristics of the window type target are not fully considered when the collaborative observation probability of the satellite to the land target is analyzed in the existing method is overcome, and the problem that the window type target collaborative observation success probability is inaccurately estimated in the existing method is solved.

This invention is embodied in a system and device for transporting assets (small satellites, commodities, or other payloads) in space. The preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. The orbits are complimentary to each other so that the relay stations can transfer mass from one station to another. In this way, the system can support different logistical networks connecting the space between orbits such as Low Earth orbit (LEO), geostationary orbit (GEO), and Low Lunar orbit (LLO), and even between Earth and Mars.

This invention belongs to the field of satellite telemetry, tracking, and command (TT&C) technology, and provides a method and system for real-time scheduling of short message resources during overseas orbit control. The method includes: satellite control software constructing a short message frame library and pre-configuring fixed-length normal frames and orbit control-specific frames; attitude and orbit control software monitoring orbit control status in real time, satellite control software identifying orbit control ignition commands and orbit control stage markers, and initiating a dual-queue parallel transmission mechanism; configuring the link for relay satellites according to the dual-queue parallel transmission mechanism and implementing frequency division multiplexing downlink; and entering a transition period after orbit control monitoring ends, performing periodic attenuation control on the orbit control-specific frames. This invention solves the problem of real-time status monitoring failure for geostationary orbit satellites during overseas orbit control, increasing the orbit control anomaly identification rate to over 99%, breaking through monitoring real-time limitations, and significantly improving the safety and controllability of overseas orbit control; optimizing resource utilization, enhancing adaptive capabilities, and achieving second-level on-demand downlink of key parameters and dynamic optimization of channel resources.

The invention relates to a spectrum resource allocation method and device, equipment, a storage medium and a program product. The method comprises the following steps: acquiring multi-dimensional state parameters of a coexistence system of a geostationary orbit and a non-geostationary orbit sharing the same frequency band; processing the multi-dimensional state parameters based on a preset spectrum demand calculation model, and predicting the spectrum demand of the coexistence system in the next time period; monitoring an aggregated interference value generated by the non-geostationary orbit system to the geostationary orbit system, and if the aggregated interference value exceeds a preset safety threshold value, determining a frequency spectrum division proportion of the geostationary orbit system and the non-geostationary orbit system based on the aggregated interference value and the safety threshold value; and according to the frequency spectrum division proportion and the frequency spectrum demand, performing frequency spectrum resource allocation for the geostationary orbit system and the non-geostationary orbit system in the next time period. By adopting the method, the reasonable allocation of the spectrum resources of the GSO and NGSO coexistence system can be realized, and the satellite communication service quality is ensured.

The invention discloses a rotating tether system maneuvering method for load transmission between different-plane orbits, and the method systematically designs a load throwing mechanism by constructing a double-body rotating tether system architecture: firstly, planning a load release mode based on the characteristics of a double-body rotating tether system; deducing speed increment and position increment parameters required for realizing the release mode; by calculating the total mass and length of the tether and combining the relative position vector and the velocity vector between the end body satellites required by load throwing, the key parameters of the throwing rotation surface are accurately calculated; and finally, constructing a rotating surface maneuvering control strategy of a full task period based on the parameters. Compared with a traditional coplanar orbit transfer scheme, the non-coplanar orbit transfer task of the effective load from the initial inclined low earth orbit to the target equator geostationary orbit is achieved in a breakthrough mode. The method has obvious technical reference value and engineering application prospect in orbit inclination angle adjustment maneuvering tasks in a satellite launching stage.

The invention discloses a stationary satellite surface emissivity collaborative inversion method based on background field reconstruction, and belongs to the technical field of satellite remote sensing information processing, and the method comprises the steps: constructing a background field of surface temperature and atmospheric temperature space structure collaborative constraint, employing a three-dimensional variational assimilation cost function to assimilate the actually measured surface temperature of a surface meteorological observation station, and calculating the surface emissivity of a stationary satellite. The obtained surface temperature analysis field is used as a surface temperature initial guess field for inverting surface emissivity by a one-bit variation inversion cost function; generating a ground surface emissivity background field by using the ground surface emissivity in the ground surface element historical data set, and constructing a ground surface item background error covariance matrix capable of representing a coupling relationship between the ground surface emissivity and the ground surface temperature based on the ground surface element historical data set so as to construct a one-dimensional variation inversion cost function; and the inversion of the surface emissivity can be realized by combining the satellite observation brightness temperature of the clear sky observation pixel observed by the infrared window area channel of the stationary orbit radiation imager, so that the inversion level of the surface emissivity is improved.

A satellite in a communication system may be equipped with an antenna system that includes various configurations of antenna arrays on one or more sides of the satellite to receive and transmit signals, and a transponder system coupled with such antenna arrays that is configured to route signals between one or more reception ports and one or more transmission ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and a transponder system may perform one or more aspects of signal processing. A satellite may be configured with particular combinations of components in a reception system and a transmission system, and a corresponding transponder system may include various signal paths that support combinations of couplings and associated signal processing between the output ports and input ports to support various techniques for relaying communications via the satellite.

The invention relates to a load balancing method and device based on a space-ground integrated core network, and communication equipment. Wherein a data plane satellite-borne network element is newly added to each network node of the space-ground integrated core network, and the space-ground integrated core network is used for parallel transmission of a control plane link and a data plane link in an inter-satellite link based on a service interface (SBI) / data transmission interface (DTI) dual-bus link. The method comprises the following steps: a first network node receives a user task, wherein the user task is a task which is unloaded to a space-based network for execution after a ground data network performs a load balancing decision; the first network node makes a load balancing decision according to the geosynchronous orbit GEO node state information to obtain a first GEO node, and the first GEO node is used for executing a load balancing strategy to send a user task to a corresponding low earth orbit LEO node through an inter-satellite link for data processing. According to the invention, the average processing time delay of user tasks can be reduced.

A satellite in a communication system may be equipped with: an antenna system including various configurations of an antenna array on one or more sides of the satellite to receive and transmit signals; and a transponder system coupled with such an antenna array, the transponder system configured to route signals between the one or more receiving ports and the one or more transmitting ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and the repeater system may perform one or more aspects of signal processing. A satellite may be configured with a particular combination of components in a receive system and a transmit system, and a corresponding transponder system may include various signal paths that support a combination of coupling and associated signal processing between an output port and an input port, to support various techniques for relaying communications via the satellites.

A satellite in a communication system may be equipped with an antenna system comprising: various configurations of an antenna array on one or more sides of the satellite for receiving and transmitting signals; and a transponder system coupled with such an antenna array, the transponder system configured to route signals between the one or more receiving ports and the one or more transmission ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and the repeater system may take one or more aspects of signal processing. A satellite may be configured with a particular combination of components in a receive system and a transmit system, and a corresponding repeater system may include various signal paths that support a combination of coupling and associated signal processing between output and input ports to support various techniques for relay communications via the satellite.

A satellite in a communication system may be equipped with an antenna system that includes various configurations of antenna arrays on one or more sides of the satellite to receive and transmit signals, and a transponder system coupled with such antenna arrays that is configured to route signals between one or more reception ports and one or more transmission ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and a transponder system may perform one or more aspects of signal processing. A satellite may be configured with particular combinations of components in a reception system and a transmission system, and a corresponding transponder system may include various signal paths that support combinations of couplings and associated signal processing between the output ports and input ports to support various techniques for relaying communications via the satellite.

The invention discloses a method for determining a visual time window of a non-geostationary orbit satellite system, and the method comprises the steps: taking the position of a ground station as a tangent plane, and constructing a target coordinate system; converting the earth-centered earth-fixed coordinate value of the satellite into a target coordinate system; determining the visible range radius of the ground station on the tangent plane according to the minimum communication elevation angle parameter; according to the first coordinate values of the satellites in the target coordinate system at the current moment and the previous moment, determining second coordinate values of intersection points of connecting lines of the satellites with the earth center and the tangent plane at the two moments; and finally, determining the visual time window of the satellite according to the second coordinate values of the intersection points of the connecting line of the satellite and the earth center and the tangent plane at the two moments. The future visual time length can be predicted only based on the double-time-slot satellite coordinate value, the system computing resource occupancy rate is remarkably reduced, the computing efficiency of the visual time window is improved, and the method is particularly suitable for a space-borne computing platform or a ground station computing resource limited scene.

A satellite in a communication system may be equipped with a phased array antenna system that includes various configurations of antenna arrays on one or more sides of the satellite.

A Low Earth orbit (LEO) satellite congestion control routing method is disclosed, including: Step 1: A LEO satellite periodically detecting queue lengths of a plurality of ports and informing a Geostationary Earth Orbit (GEO) satellite of queue lengths of congested ports in the plurality of ports; Step 2: The GEO satellite sending the queue lengths of congested ports to a ground station, and a computing center of the ground station calculating link status weights according to the queue lengths of congested ports; Step 3: According to the link status weights, the computing center of the ground station determining a congestion area; Step 4: The computing center of the ground station calculating a routing table of satellites in the congestion area, and the ground station sending the routing table to a LEO satellite inside the congestion area; Step 5: The LEO satellite in the congestion area receiving the routing table, and performing end-to-end transmission of data packets to a destination LEO satellite according to the routing table.

A satellite in a communication system may be equipped with an antenna system that includes various configurations of antenna arrays on one or more sides of the satellite to receive and transmit signals, and a transponder system coupled with such antenna arrays that is configured to route signals between one or more reception ports and one or more transmission ports. Such antenna arrays may be configured to support directional reception, directional transmission, or both, and a transponder system may perform one or more aspects of signal processing. A satellite may be configured with particular combinations of components in a reception system and a transmission system, and a corresponding transponder system may include various signal paths that support combinations of couplings and associated signal processing between the output ports and input ports to support various techniques for relaying communications via the satellite.

The application discloses a method for resisting satellite Internet of Things uplink interference attack, and a satellite Internet of Things system comprises a central gateway, a plurality of service areas and a space segment; the service area comprises a plurality of legal terminal nodes, and the space segment is composed of one or more communication satellites in geostationary or non-geostationary orbits. Each communication satellite provides a single or multiple beams to cover different service areas, the satellite can connect the service areas to the central gateway, and then store collected messages and transmit the messages to the central gateway. The method comprises the following steps: calculating a MAC layer load G, calculating a preamble time, calculating an average data packet arrival number, and calculating a minimum IC step length under a specified detection probability through a Poisson distribution. The application has the advantages that the system performance decline caused by the preamble camouflage attack can be resisted, the preamble deception interference which has a great influence on the system performance is effectively eliminated, and the system stability is greatly improved.

The application provides a spacecraft thruster fault response method, comprising: transferring a small geostationary orbit satellite from an earth transfer orbit to a geostationary orbit through three stages; the small geostationary orbit satellite comprises an orbit transfer chemical thruster, an attitude control chemical thruster and an electric thruster, wherein, in the second stage of the transfer of the small geostationary orbit satellite, a fault response scheme is started according to a fault response strategy of "first electric propulsion, then orbit transfer chemical thruster, and then attitude control chemical thruster", and the fault response scheme comprises: when the electric thruster is faulty, the orbit transfer chemical thruster is started; when both the electric thruster and the orbit transfer chemical thruster are faulty, the attitude control chemical thruster is started.

The invention discloses a satellite federated learning local model transmission scheduling method based on model compression and GEO relay, which comprises the following steps: (1) in a system initialization stage, establishing communication links between an LEO satellite network and a ground station GS and between the LEO satellite network and a relative geostationary orbit satellite GEO, and setting a maximum compression ratio threshold value Pmax; (2) calculating the minimum compression ratio PGS when the LEO satellite directly communicates with the GS; (3) judging the size relationship between the PGS and the Pmax; selecting to directly upload to a ground station or upload through a GEO relay, or excluding the LEO node; (4) carrying out global model aggregation; (5) judging whether a convergence condition is met or not; if not, skipping to the step (2); and if the convergence condition is reached, ending the training, and outputting final global model parameters. According to the method, the transmission mode is dynamically selected in combination with the real-time link state, and the differentiated aggregation strategy is designed, so that the global model convergence speed and the communication efficiency of federated learning are improved.

A method (and associate apparatus) operates by receiving a first tracking area code (TAC) list corresponding to Non Geostationary (NGSO) Non-Terrestrial Network (NTN); performing cell selection in a mobile network based NGSO NTN, wherein the UE selects a first cell associated with the first TAC list; performing a registration procedure with a first TAC from the first TAC list; performing cell reselection and selecting a second cell, wherein the second cell is associated with a second TAC list; and determining whether the first TAC is included in the second TAC list, wherein the UE initiates a TA update (TAU) procedure when the first TAC is not included in the second TAC list, wherein the TAU procedure involves the UE sending a TAU Request message, and wherein the UE receives a TAU Accept message and the UE is registered to a second TAC from the second TAC list.

A method includes receiving a measurement configuration from a serving cell of a user equipment (UE) in a non-terrestrial network (NTN) providing mobile communication service based on satellites. The satellites can be low Earth orbiting (LEO) satellites, geostationary Earth orbiting (GEO) satellites, and the like. The measurement configuration indicates a first synchronization signal block (SSB) based measurement timing configuration (SMTC) and a second SMTC. The first SMTC specifies first SMTC windows aligning with SSB signals from the serving cell of the UE. The second SMTC specifies second SMTC windows aligning with SSB signals from a first neighbor cell of the UE. The serving cell is associated with a first flying object, and the first neighbor cell is associated with a second flying object. The UE performs a measurement based on the first SMTC corresponding to the serving cell and the second SMTC corresponding to the first neighbor cell.