49 results about "Geostationary orbit" patented technology

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 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.

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 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.

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.

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.

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.

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.

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. The satellite may be configured to communicate signaling between a gateway terminal and user terminals while steering towards a location of a service area. In some examples, the satellite may be configured to communicate with multiple user terminals (e.g., concurrently) using a single beam, with communications of the user terminals being assigned to different frequency bands. For example, a first frequency band based on the location of the first user terminal and associated with the single beam may be used to communicate with the first user terminal, and a second frequency band based on the location of the second user terminal and associated with the single beam may be used to communicate with the second user terminal.

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

A satellite in a communication system may be equipped with a phased array antenna system that includes various configurations of an antenna array on one or more sides of the satellite. The satellite may be configured to communicate signaling between the gateway terminal and the user terminal while steering toward a location of the service area. In some examples, the satellite may be configured to communicate with multiple user terminals (e.g., concurrently) using a single beam, where communications of the user terminals are assigned to different frequency bands. For example, a first frequency band based on a location of a first user terminal and associated with the single beam may be used to communicate with the first user terminal, and a second frequency band based on a location of a second user terminal and associated with the single beam may be used to communicate with the second user terminal.

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.

Systems and methods for communication between user terminals and core network through satellite network and ground network are disclosed herein. The system facilitates connectivity through inter-satellite links in the satellite network. The system provides an air interface based on 5G protocols with satellite specific enhancements at lower layers, low latency, standards based physical layer design on both user and feeder links, beam-hopping design that minimizes end-to-end delay, software defined networking for route management to minimize payload complexity, efficient flow control between ground network and satellite to minimize buffering requirements in satellite payload, differentiated quality of service, advanced scheduler designs to cater to traffic types and full / half duplex terminals, end-to-end Layer 2 transport, direct user terminal to user terminal communications, adaptive modulation and coding, scalable gateway, and the like.

The application discloses a static satellite ground surface emissivity cooperative inversion method based on background field reconstruction and belongs to the technical field of satellite remote sensing information processing, which comprises the following steps: constructing a background field of spatial structure cooperation constraint of ground surface temperature and atmospheric temperature, adopting a three-dimensional variation assimilation cost function to assimilate the measured ground surface temperature of a ground meteorological observation station, obtaining a ground surface temperature analysis field as a ground surface temperature initial guess field of a one-dimensional variation inversion cost function to invert the ground surface emissivity; generating a ground surface emissivity background field from the ground surface emissivity in a ground surface element historical data set, constructing a ground surface item background error covariance matrix capable of representing the coupling relationship between the ground surface emissivity and the ground surface temperature based on the ground surface element historical data set, and further constructing a one-dimensional variation inversion cost function; and combining the satellite observation brightness temperature of a clear sky observation pixel observed by an infrared window channel of a geostationary orbit radiometer, so that the inversion of the ground surface emissivity can be realized, and thus the ground surface emissivity inversion level is improved.

In an aspect of the disclosure, a method, a computer-readable medium, and an apparatus are provided. The apparatus may be a user equipment (UE). The UE transmits a first message to a network through a Geostationary Earth Orbit (GEO) satellite access. The first message comprises a capability indication that indicates support by the UE for Internet Protocol Multimedia Subsystem (IMS) voice communication using the GEO satellite access. The UE receives a second message from the network. The second message comprises a network capability indication that indicates support by the network for the IMS voice communication using the GEO satellite access.

The application discloses a kind of geostationary satellite multi-pulse high-precision autonomous position keeping control methods, comprising: according to the instantaneous orbital elements of satellite, the average orbital elements of satellite are determined;According to the average orbital elements of satellite, the in-plane and out-of-plane pulse control sequence of satellite orbit is determined;According to the in-plane and out-of-plane pulse control sequence of satellite orbit, the switch logic of thruster is determined;According to the switch logic of thruster, the switch of thruster is controlled, realizes geostationary satellite multi-pulse high-precision autonomous position keeping control.The method of the application realizes geostationary satellite multi-pulse high-precision autonomous position keeping control.

In a non-geostationary orbit (NGSO) satellite mobile communication system, a communication device receives a synchronization signal block (SSB), which is subjected to partial pre-compensation, from an NGSO satellite transmitter through a downlink (DL) beam, and then transmits the received synchronization signal block (SSB) to the NGSO satellite transmitter through the downlink (DL) beam. And realizing cell synchronization with the NGSO satellite transmitter by using the SSB subjected to partial pre-compensation. A center frequency of a primary synchronization signal and a center frequency of a secondary synchronization signal within the partially pre-compensated SSB are pre-offset by the NGSO satellite transmitter by an integer number of subcarriers relative to a center frequency of the partially pre-compensated SSB to achieve a correlation with movement of the NGSO satellite transmitter relative to the coverage on the earth of the DL beam According to the method, partial pre-compensation of Doppler shift (DS) is carried out. Even if Doppler frequency offset is large due to high mobility of an NGSO satellite, cell synchronization can be simplified.

The invention discloses an on-orbit field-free calibration method for a high-orbit linear array optical remote sensor, solves the key problem of on-orbit high-precision radiometric calibration of a geosynchronous orbit linear array optical satellite so as to eliminate stripe noise caused by inconsistent response of detector pixels, and belongs to the technical field of remote sensing data application. The calibration method comprises the following steps: setting imaging parameters of a linear array optical remote sensor carried by a high-orbit satellite; selecting a calibration scene; according to the calibration scene, the optical axis direction of the linear array optical remote sensor and the pixel distribution characteristics of an image plane detector of the linear array optical remote sensor, setting a satellite attitude, and enabling each pixel of the linear array optical remote sensor to sequentially image the same object point on the ground; and calculating a relative radiometric calibration coefficient according to the acquired image. According to the invention, the completely equal ground feature radiance is obtained for radiometric calibration, and the high relative radiation precision of the high-orbit satellite is ensured.

A balancing device for the center of mass O of a telecommunications satellite placed in geostationary orbit in a local orbital frame (X, Y, Z) centered at O, where X is the axis parallel to a velocity vector of the satellite's movement, is proposed. The satellite comprises a body with two faces (1222, 1224) parallel and orthogonal to X, and a payload instrument fixed to face 1222 with a given mass and length. The center of mass is displaced by a perturbation acting on the satellite. The balancing device comprises: a deployment device fixed to face 1224, the deployment device having a length greater than the instrument's length; a balancing element fixed to the end of the deployment device, the balancing element having a mass less than the instrument's mass; and the deployment device being configured to move the balancing element along X. Figure for the abstract: Fig. 4

A core network (CN) of a wireless network such as a 5G (5th generation) network is adapted to provide support for non-terrestrial network (NTN) types to optimize signaling for effective resource and mobility management. The CN uses signaling with a next generation radio access network (NG-RAN) to determine when user equipment (UE) and network capabilities are mismatched with regard to supported satellite types (including geostationary satellite orbit (GSO) and non-geostationary satellite orbit (NGSO) types) to ensure that unnecessary paging is not implemented. The CN is further arranged to utilize an expanded tracking area identity (TAI) list that enables a unique tracking area code (TAC) to be defined and utilized for specific NTN cells. The CN is further arranged to utilize a target identifier (ID) used in handovers involving an NTN cell.