51 results about "Geosynchronous orbit" patented technology

A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

The present invention relates to a solar proton energy spectrum modulator design method, comprising the following steps: calculating the integrated total area of ​​the geosynchronous orbit solar proton energy spectrum; dividing the geosynchronous orbit solar proton energy spectrum into multiple energy spectrum intervals and solving for the average value of the proton energy in each interval; calculating the proportion of each energy spectrum interval in the entire geosynchronous orbit solar proton energy spectrum based on the average value of the proton energy in each interval; selecting a total material thickness, and sequentially reducing the total material thickness in a preset shape according to the thickness and corresponding area proportion required for the average energy corresponding to each energy spectrum interval to form an energy reduction sheet; supporting the energy reduction sheet and enabling the energy reduction sheet to rotate along its geometric center at a set speed. The present invention also provides a solar proton energy spectrum modulator design system. Using the solar proton energy spectrum modulator design method and system of the present invention, a radiation environment comparable to the solar proton energy spectrum in space can be obtained.

Systems and methods are described for connecting with LEO satellites while reducing emissions toward GEO satellite communications. A system to implement the instant techniques may include a system comprised of a user communications equipment and a LEO constellation. The user equipment (“UE”) may comprise a communications modem and an active antenna unit with a transmit and receive beamformer. In further implementations, the UE may include additional receive only beamformers. The LEO constellation can have a regenerative payload or bent pipe, and can include orbits at different altitudes. Methods as described herein may include a procedure by which the user equipment and LEO satellite work together to identify candidate serving satellites, and select the one that allows to meet the power density requirements to avoid interfering with the GEO satellites.

The invention discloses a satellite remote measurement, operation and control system, which relates to the technical field of measurement, operation and control, and comprises the following steps: adopting a measurement and control link combination of a low-orbit satellite, a geosynchronous orbit satellite and a high-altitude platform, dynamically selecting an optimal measurement and control path through reinforcement learning, and optimizing measurement and control scheduling based on a link state, a task priority and a resource competition condition. The measurement and control coverage rate and the resource utilization rate are improved; in the task execution process, the integrated AI model monitors the satellite task state in real time, obtains the task state, the equipment load and the communication link delay data, and predicts the abnormal condition in combination with the Bayesian probability model and the LSTM neural network, thereby avoiding the potential risk in advance and improving the stability of the measurement and control task. The measurement and control mode can be automatically adjusted after anomaly detection, track parameters are dynamically corrected through a predictive control model, or ground instruction adjustment is executed after a measurement and control link is recovered, and the track maintaining capacity is improved.

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.

Various solutions for connected mode measurement enhancements in global navigation satellite system (GNSS) operations are described. A device can connect to a serving cell associated with a first non-geosynchronous orbit (NGSO) satellite to operate in a connected mode. The device can also receive, from the serving cell, a configuration of one or more neighboring cells associated with a second NGSO satellite. The serving cell and the one or more neighboring cells operate within a same frequency band. The device can then perform, based on the configuration, inter-frequency measurements of the one or more neighboring cells if at least one condition is satisfied.

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 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 provides a luminosity curve anomaly detection method based on a long and short term memory network, and relates to the technical field of space target intelligent perception. In view of the problems of dependence on labeled data, noise sensitivity, insufficient local anomaly capture capability and the like in the prior art, high-precision anomaly recognition is realized by constructing an unsupervised learning framework. According to the method, the time sequence dependency relationship is modeled through the long and short term memory network, and the time attention mechanism is introduced to dynamically focus the key time step, so that the anomaly detection precision of the model is improved. The invention provides an efficient solution for sensing the abnormal movement of the space target, and is suitable for real-time monitoring of complex scenes such as a geosynchronous orbit and earth-moon space.

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 GEO SAR time-varying ionosphere error compensation method based on maximum contrast self-focusing, and belongs to the technical field of GEO SAR (Geosynchronous Earth Orbit Synthetic Aperture Radar). The method selects distance line signals from a GEO SAR image, the distance line signals are the signals with the same distance time in the azimuth direction, the average power of each distance line signal in the image is calculated, a part of the distance line signals are selected, then the contrast of the SAR image is used to iteratively estimate the quadratic phase error coefficient, the cubic phase error coefficient is iteratively estimated based on the quadratic phase error coefficient, and finally the obtained quadratic and cubic phase error coefficients are used for phase compensation of the original SAR image, so that the SAR image affected by the time-varying ionosphere is accurately compensated. Experiments prove that the contrast of the compensated SAR image is improved by the method, and the compensated image is good, and is close to the image not affected by the time-varying ionosphere.

The invention relates to the technical field of spacecraft control, and provides a spacecraft rendezvous control method based on a disturbance observer and related equipment, and the method comprises the steps: constructing a kinetic model of orbit rendezvous of a target spacecraft at an earth-moon translation point, and designing the disturbance observer based on the kinetic model; defining a cost function based on the system state quantity of the target spacecraft, and constructing an action controller of the target spacecraft according to the cost function; calculating a control interference estimated value of the target spacecraft according to the interference observer, and calculating an optimal control value according to the action controller; and calculating a final control value of the target spacecraft based on the control interference estimated value and the optimal control value, and performing orbit intersection control on the target spacecraft based on the final control value. According to the method, the spacecraft rendezvous control precision can be improved.

The application relates to the technical field of satellite communication, in particular to a satellite communication terminal crystal oscillator calibration method, which comprises the following steps: triggering a crystal oscillator calibration process when a terminal is started or in a communication idle period; tuning the terminal to the frequency point of a geosynchronous orbit satellite, searching for and capturing the synchronization signal of the geosynchronous orbit satellite; performing correlation operation on the received synchronization signal and a reference signal generated by a local crystal oscillator of the terminal, and calculating the frequency deviation value between the synchronization signal and the reference signal; and generating a crystal oscillator control signal according to the frequency deviation value, and finely adjusting the frequency of the local crystal oscillator. The application realizes accurate, robust and verifiable calibration of the terminal crystal oscillator without an external high-precision reference source.

The application relates to the technical field of spacecraft control, and provides a spacecraft rendezvous control method based on an interference observer and related equipment, the method comprising the following steps: constructing a dynamic model of target spacecraft rendezvous on a geosynchronous orbit, and designing an interference observer based on the dynamic model; defining a cost function based on system state quantities of the target spacecraft, and constructing an action controller of the target spacecraft according to the cost function; calculating a control interference estimation value of the target spacecraft according to the interference observer, and calculating an optimal control value according to the action controller; calculating a final control value of the target spacecraft based on the control interference estimation value and the optimal control value, and performing orbit rendezvous control on the target spacecraft based on the final control value. The method can improve the precision of spacecraft rendezvous control.

The invention discloses a geosynchronous orbit satellite position protection method with an unconstrained thruster installation direction, and belongs to the field of satellite attitude and orbit control. The method comprises the following steps: calculating an orbit parameter estimation value of a satellite according to a future orbit position obtained by recursion of a current orbit position; generating a corresponding satellite orbit position keeping strategy according to orbit parameters which do not meet a preset threshold range in the orbit parameter estimation values; and determining whether the satellite orbit position keeping strategy meets the sunlight avoidance constraint and the thruster layout constraint, and if not, adjusting the satellite orbit position keeping strategy according to the sun vector position, the sunlight avoidance demand and the thruster layout at the future position keeping moment. The method can greatly improve the position protection operation efficiency and guarantee the satellite load safety.

The application provides a precipitation prediction method and device, electronic equipment and storage medium, the method comprises the following steps: obtaining a plurality of frequency polarization channel brightness temperature data and infrared channel brightness temperature data of a target area based on a polar orbit satellite and a geosynchronous orbit satellite; determining whether a target area has a precipitation event according to the obtained data; if so, filtering the target frequency polarization channel brightness temperature data according to the sea-land classification result of the target area; determining the precipitation prediction result of the target area according to the target frequency polarization channel brightness temperature data and the infrared channel brightness temperature data. By combining the meteorological monitoring data of the polar orbit satellite and the geosynchronous orbit satellite, the temporal and spatial resolution of the meteorological monitoring data is improved, and the passive microwave data, infrared data including water vapor channel data are integrated, thereby improving the accuracy of the precipitation prediction.

Techniques are described for automated satellite power management (ASPM) for a satellite communication system having a constellation of non-geosynchronous orbit (NGSO) small satellites (smallsats). The techniques can be resource- and / or mission-aware. Embodiments control power used by the constellation by evaluating subsets of the NGSO smallsats determined to be covering each of a number of grid regions (GRs) segmenting a coverage area at any particular timestep. For each timestep for each subset, the evaluating includes: determining whether any payloads of the subset are mutable payloads for the timestep (i.e., can be shut down to conserve power without violating mission objectives); and communicating with the subset to control power to the payloads, so that all the mutable payloads are muted for the timestep and all other payloads of the plurality of payloads are unmuted for the timestep.

The present invention relates to the field of communications, and provides a data communication method and system and an electronic device. The method comprises: by means of a pre-constructed satellite data warehouse, receiving data name information uploaded by a producer, the satellite data warehouse comprising at least three geosynchronous orbit satellites and a plurality of low earth orbit satellites, and the data name information representing the position of the moved producer; and, on the basis of the data name information, updating data in the satellite data warehouse. The present invention solves the defect in NDN network architecture that after producers have moved, it is difficult for consumers to determine new positions of the producers and thus sent packets of interest will reach old positions of the producers, such that the packets are lost, greatly affecting the accuracy and efficiency of data transmission. The solution of the present application can buffer data packets of moved producers in pre-constructed satellite data warehouses, thereby effectively avoiding effects on network performance caused by movement of the producers.

The present disclosure relates to the field of communication and provides a method, a system and an electronic device of date communication. The method includes: the data name information uploaded by the producer is received through the pre-built satellite data depot, which includes at least three geosynchronous earth orbit satellites and several low-orbit satellites, and the data name information characterizes the data characterized by the producer; and the data in the satellite data depot is updated based on the data name information. In order to solve the defect that if a producer moves in an NDN network architecture, a consumer is difficult to locate a new position of the producer, so that a sent interest packet reaches an old position of the producer, and the packet is lost, which greatly affects the accuracy and efficiency of data transmission, the data packet of the moving producer can be cached in the data depot based on the pre-built satellite data depot in the solution of the present application, so that the influence of the movement of the producer on the network performance can be effectively shielded.

The application provides a photometric curve anomaly detection method based on a long short-term memory network and relates to the technical field of intelligent perception of space targets. In view of the problems of dependence on labeled data, noise sensitivity and insufficient local anomaly capturing capacity in the prior art, a high-precision anomaly recognition is realized through the construction of an unsupervised learning framework. The long short-term memory network is used for modeling the time sequence dependence relationship, and a time attention mechanism is introduced to dynamically focus on key time steps, so that the anomaly detection precision of the model is improved. The application provides an efficient solution for space target abnormality perception and is suitable for real-time monitoring of complex scenes such as geosynchronous orbits and earth-moon space.

Disclosed methods and apparatuses involve the coordinated use of two or more satellites operating in inclined orbits, with a defined phase offset in terms of their latitudinal oscillations above and below the geosynchronous arc.

Methods, systems, and devices for wireless communications are described. A core network node may send a transmission request message to a first network entity, which may forward the transmission request message to another network entity. The first network entity may forward the transmission request message to the second network entity immediately upon reception, after transmitting a threshold quantity of repetition of the message, after a timer has expired, or upon receiving a request to do so. Additionally, or alternatively, the core network node may send the transmission request message to a buffering node (e.g., a geosynchronous orbit (GSO) satellite), which may then forward the transmission request message to a next the core network node may send the transmission request message to a buffering node (e.g., a stationary GSO satellite), which may then forward the transmission request message to a next network entity.

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.

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.

The invention discloses a transfer orbit design method in on-orbit service of a synchronous orbit satellite. The problem of how to effectively image a high-orbit target satellite with low fuel consumption is solved. Belongs to the technical field of space. Comprising the following steps: determining total transfer time according to different initial states of a service satellite and a target satellite; constructing a transfer orbit mathematical model based on the total transfer time to obtain the running time of the service satellite on the initial orbit, the transfer orbit and the approaching orbit in the transfer process and the speed increment for completing the Horman transfer; taking a relative position vector included angle and an illumination angle of two stars at the end of intersection as an objective function, taking total transfer time as a constraint condition, taking the operation time of a service star in an initial orbit and an approaching orbit as an optimization variable, optimizing the objective function by using a genetic algorithm based on an HPOP model, and correcting parameters of a transfer orbit mathematical model to obtain a transfer orbit mathematical model; obtaining a transfer orbit mathematical optimization model; according to the method, effective imaging of the high-orbit target with low burnup is realized through the mathematical optimization model of the transfer orbit.

The present invention relates to the field of communications, and provides a data communication method, system, and electronic device. The method includes: receiving, by means of a pre-constructed satellite data warehouse, data name information uploaded by a producer, where the satellite data warehouse includes at least three geostationary orbit satellites and a number of low-earth orbit satellites, and the data name information represents the position of the producer after movement; and updating the data in the satellite data warehouse based on the data name information. This is used to solve the defect that in an NDN network architecture, when the producer moves, it is difficult for the consumer to locate the new position of the producer, resulting in the interest packets sent reaching the old position of the producer, thereby causing packet loss and greatly affecting the accuracy and efficiency of data transmission. In the solution of this application, the data packets of the mobile producer can be cached in the pre-constructed satellite data warehouse, so that the impact of the producer's movement on network performance can be effectively shielded.

A satellite yaw attitude regulation and control method based on a sun position comprehensively considers an orbit inclination angle, attitude pointing, a sun irradiation condition, a sunlight avoidance condition and the like, and comprises the following steps: firstly, confirming satellite task information, calculating nominal rolling attitude information and nominal pitching attitude information corresponding to each moment, and calculating a yaw attitude of the satellite; and the obtained attitude information is utilized to calculate the included angle projection at each moment, so that the optimization of the cabin plate illumination condition of the geosynchronous orbit satellite is realized through the average value of the included angle projection, the heat dissipation efficiency is improved, equivalently, the burden and weight of a thermal control system are reduced under the same condition, and the improvement of the comprehensive capability of the whole satellite is facilitated.

The invention discloses an XY seat frame antenna gain test method and related equipment. The method comprises the following steps: selecting any geosynchronous orbit satellite in the field of view of an antenna as a beacon source, and enabling the optical axis of the antenna to point to the geosynchronous orbit satellite; reading and recording the rotation angle of the X-axis motor and the rotation angle of the Y-axis motor at the moment when the peak searching of the signal level received by the frequency spectrograph reaches the maximum value, and taking the rotation angle of the Y-axis motor as a projection deflection angle; under the condition that the projection deflection angle is kept unchanged, single-degree-of-freedom scanning is executed to obtain the angle difference of the relative accurate star pointing positions of the X-axis motor and the Y-axis motor; and constructing a space geometric projection relation based on the projection deflection angle, executing space projection correction on the obtained angle difference of the X-axis motor, and calculating a real antenna beam width in combination with the angle difference of the Y-axis motor so as to carry out gain test. The problem that the antenna gain test is inaccurate due to the fact that physical alignment is tedious and an AZ-EL correction formula is misused in the existing test can be solved.

A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. Satellite terminals may be used to communicate with the satellite constellation. The satellite terminals may have control circuitry that dynamically adjusts phased antenna array circuitry to steer antenna beams towards one or more satellites. Multiple antenna beams may be steered in different directions simultaneously. A satellite terminal may be used in simultaneously transmitting and receiving data from different respective satellites and may be used in transmitting and receiving satellite signals in multiple satellite bands. The satellite terminal may have an outdoor unit that is coupled to an indoor unit over a digital communications path. The outdoor unit may include the phased antenna array circuitry and transceiver and modem circuitry, whereas the indoor unit may cache media and serve as a firewall, router, and wireless access point.

The invention provides an adjacent geosynchronous orbit satellite false-tracking prevention implementation method for a multi-beam antenna, aiming at the characteristic that a plurality of sets of independent feed source units in a bifocus multi-beam antenna are mounted on a feed source orbit through a movable pulley, a high-precision magnetic grid ruler is mounted along the feed source orbit, and a magnetic grid reading head is mounted on the feed source pulley; measuring the absolute position of the feed source pulley on the feed source track; according to the information of the to-be-tracked satellite, the theoretical position of the feed source unit corresponding to the to-be-tracked satellite on the feed source orbit is determined; according to the absolute position and the theoretical position, after the feed source unit is controlled to move to the theoretical position, the AGC level is used for finally determining the position of the feed source unit, and accurate tracking of the satellite to be tracked is achieved.