50 results about "Satellite motion" patented technology

The invention discloses a multi-satellite service converged communication management control optimization method, which belongs to the technical field of satellite communication networks, and comprises the following steps: acquiring a service priority index and satellite ephemeris data, calculating the relative position between a satellite and a terminal at a future moment, and generating a satellite motion trail prediction result and an interference risk prediction result; and obtaining a load state of the satellite, dynamically calculating a resource allocation weight matrix to switch a satellite link in combination with a service priority index, a satellite motion track prediction result and an interference risk prediction result, and generating a resource allocation instruction and a switching command. According to the method, the resource allocation weight matrix is dynamically calculated by adopting the fusion service priority index, the satellite motion and interference prediction and the satellite load state, and link switching and resource allocation are performed according to the resource allocation weight matrix, so that prospective optimization management and intelligent control of multi-satellite communication resources can be realized, and the continuity and reliability of service fusion communication are improved.

The invention relates to the technical field of satellite communication, in particular to a dynamic beam adjustment system for medium and low orbit satellite communication. Comprising a beam demand sensing unit; the dynamic beam calculation unit counteracts the influence of a complex environment on beam coverage through a multi-factor cooperative compensation mechanism; the beam execution adjustment unit is used for realizing beam accurate pointing and interference suppression through an adaptive phase optimization algorithm; and a satellite-ground cooperation unit. Through a multi-factor cooperative compensation mechanism, a beam theory pointing angle is calculated based on a spherical geometrical relationship, compensation amounts are determined by combining satellite motion, user movement and atmospheric refraction, and a communication scene is determined according to a satellite elevation angle, a user terminal motion speed and a communication link signal-to-noise ratio. The weight of each compensation amount is dynamically adjusted and synthesized into the total compensation amount, and finally the actual beam pointing angle is obtained, so that the coupling influence of multiple factors on beam coverage in a complex environment is effectively counteracted, and the beam pointing precision is improved.

The invention provides a communication method and a communication device for a wireless access network and a core network, and the method comprises the steps that terminal equipment can determine a first reference point list, the first reference point list comprises a plurality of points where beams are projected to the ground, and a second beam is determined based on the first reference point list and the motion direction of a first satellite. When the access beam is selected, the movement direction of the first satellite is considered, so that the problem of beam switching in the access process caused by satellite movement can be avoided, a broadcast beam with the largest beam coverage range in the movement direction is selected based on the reference points in the first reference point list, and smooth access is ensured.

The invention provides a large-scale low-orbit constellation topology construction method and system based on the reliable reachable distance of an optical transceiver and a storage medium, and the method comprises the steps: 1, building an inter-satellite laser link probability evaluation model based on the capturing probability of an aiming-capturing-tracking system and the motion characteristics of satellites; 2, on the basis of the inter-satellite laser link probability evaluation model, constructing a giant satellite network topology evaluation model with inter-satellite link time average stability, satellite hop count and communication time delay as core optimization targets, and outputting a globally optimized laser link connection scheme; and 3, for a laser link connection scheme, proposing a giant constellation network topology design algorithm based on a capture probability, and constructing a constellation topology by adopting a minimum unit of a space symmetric constellation. The method has the beneficial effects that the constellation topology is constructed by adopting the minimum unit of the space symmetric constellation, so that the topological structure is stabilized, the channel gain is improved, the end-to-end delay is shortened, and the average hop count and the variance of the network are reduced.

The invention discloses a low-orbit satellite Internet of Things terminal baseband communication system, and relates to the technical field of Internet of Things communication. The system comprises a data frame construction unit, a channel regulation and control unit, a bandwidth tracking unit and a decoding correction unit, wherein the data frame construction unit generates an initial frame according to an Internet of Things protocol and dynamically adjusts a frame structure in combination with channel characteristic parameters to complete data packing; and the channel regulation and control unit judges a coding modulation mode according to real-time channel quality and satellite motion parameters, processes a transmitting link, dynamically adjusts the transmitting power of the high-frequency analog signal based on path loss estimation, and finally transmits the high-frequency analog signal through an antenna. At a receiving end, a bandwidth tracking unit adaptively adjusts the loop bandwidth according to the switching characteristic parameter, and dynamically filters the received signal; and the decoding correction unit performs adaptive early stop correction of iterative decoding according to the decoding convergence rate, and finally completes data analysis.

The application discloses a kind of distributed multi-curved surface array full airspace beam continuous control methods, comprising: setting satellite TT&C relay trigger event, trigger according to including satellite and TT&C station uplink and downlink state monitoring, orbit control instruction and pre-configured trigger instruction of switching condition;With satellite TT&C relay as the control core of random access node, utilize curved surface array tracking receiver state parameters and the partial satellite orbit information cached, based on TT&C relay trigger event, adaptively trigger curved surface array inter-beam switching process, ensure the continuous tracking of curved surface array to satellite.The present application can realize low-latency and low TT&C resource overhead distributed multi-curved surface array full airspace beam continuous control, support the low-latency TT&C relay demand of satellite in future large-scale constellation, realize on-demand switching without pre-planning, real-time capacity optimization, improve the adaptability to station network resources and the dynamic change of satellite motion state.

The invention provides a key bearer link determination method and device, equipment and a storage medium, and relates to the technical field of satellite communication, and the method comprises the steps: constructing a network topology of a satellite Internet at a current moment; for each node pair, based on nodes and edges in the network topology, determining a first non-coincident average path length when a source node and a destination node in the node pair are accessed to a satellite moving in the same direction at the current moment, and a second non-coincident average path length when the source node and the destination node are accessed to a satellite moving in the opposite direction at the current moment; determining a path length difference value based on the first non-coincident average path length and the second non-coincident average path length; based on the path length difference value corresponding to each node pair, a target key bearing link in the satellite internet is determined, and the target key bearing link is a satellite-ground link which is most influenced by the satellite motion direction. According to the invention, the accuracy of the determined key bearer link can be improved.

The invention relates to a multi-radar synchronous satellite orbit determination resource scheduling method based on reinforcement learning, and the method comprises the following steps: (10) radar perception situation acquisition: a radar acquires a networking radar state and a satellite motion orbit based on historical information, and completes the parameter collection; (20) measuring and calculating a satellite observation geometric positioning precision factor by networking radars: detecting satellites in sequence based on different radar combinations, and calculating geometric positioning precision factors under different strategies; (30) resource scheduling scheme characterization and problem modeling: modeling a time sequence optimization problem based on detection capability constraints of multiple radars, and realizing high-precision target orbit determination; and (40) generating a multi-radar synchronous satellite orbit determination resource scheduling scheme: solving the time sequence optimization problem to obtain the multi-radar synchronous satellite orbit determination resource scheduling scheme, and issuing the scheme. According to the method, rapid solving can be realized, the GDOP maximum value of all targets in the whole scene is reduced, and the orbit determination precision is further improved.

A low-orbit remote sensing satellite three-axis rapid maneuvering attitude trajectory planning and tracking method relates to the technical field of aerospace, in particular to the technical field of low-orbit remote sensing satellite three-axis rapid maneuvering attitude trajectory planning and tracking, which effectively solves the balance problem of maneuverability and stability in the process of attitude transformation and improves the superiority of anti-interference capability. The method comprises the following steps: establishing a satellite kinematics model and a satellite dynamics model; calculating the quaternion of the desired coordinate system relative to the satellite initial coordinate system at the maneuvering starting moment; completing attitude trajectory planning through an improved tracking differentiator; calculating the total control rate; obtaining the real control rate through an actuator; calculating the quaternion of the satellite body coordinate system relative to the inertial coordinate system and the angular velocity of the satellite body coordinate system relative to the inertial coordinate system; obtaining the real body quaternion and the real body angular velocity through a measuring mechanism; and cyclically planning the trajectory and tracking.

This invention discloses a reinforcement learning-based method for optimizing the performance of FAS-assisted satellite-to-ground communication. In air-to-ground communication, when the direct path is blocked by obstacles, the signal is transmitted through a mixture of reflection from moving scatterers and the direct path. This invention describes the communication environment between the mobile transmitter and the ground user through geometric stochastic modeling, establishes a dynamic optimization framework based on FAS, couples satellite motion characteristics with adjustable FAS parameters to construct a three-dimensional channel model, designs an improved Memetic PPO reinforcement learning algorithm to dynamically optimize the FAS configuration set at the ground user in the discrete action space through a local search mechanism, and jointly optimizes channel capacity and modeling accuracy to generate the optimal strategy. This method reveals the nonlinear relationship between satellite motion and channel characteristics, significantly improves communication performance in complex obstruction environments, provides a new method for dynamic channel optimization of satellites, and has significant application value.

The application discloses a satellite-ground communication time offset and Doppler frequency offset pre-compensation device, which has high estimation accuracy and can complete wide-range time offset and frequency offset estimation and pre-compensation without acquiring satellite ephemeris information of a terminal. The application is realized by the following technical scheme: a DoA estimation unit estimates the arrival angle DoA of a satellite signal by using an array signal processing algorithm; the estimation unit estimates the arrival angle DoA of a satellite signal; the acquired satellite azimuth angle and elevation angle information is divided into two paths, one path is sent to a distance calculation unit, a time offset calculation unit and a time offset pre-compensation unit, the propagation time delay between the satellite and the terminal is calculated and time offset pre-compensation is performed; the other path is output to a velocity vector calculation unit, a Doppler frequency offset calculation unit, a Doppler ambiguity resolution unit and a frequency offset pre-compensation unit, the Doppler frequency offset caused by satellite movement is calculated and frequency offset pre-compensation is performed, the residual time offset and frequency offset are estimated, and the residual time offset and frequency offset are accurately adjusted.

The application discloses a kind of solving method of unmanned aerial vehicle equivalent simulation spacecraft kinematics characteristics, steps are as follows: the inertial coordinate system required for constructing equivalent model and satellite orbit coordinate system, relative motion equation in orbit coordinate system is established;According to the equation, the spacecraft orbit kinematics parameters and unmanned aerial vehicle equivalent kinematics parameters are determined;Combining each parameter basic dimension, dimension matrix is listed, and the basic parameter quantity describing physical process is determined according to the rank of matrix;Based on the similarity of model and prototype, the similarity condition is applied to dimensionless number, the equation describing two systems is established, and then the scale factor of each kinematics parameter is derived.The method makes full use of the controllable characteristics of unmanned aerial vehicle flight height, speed and vertical climbing / descending speed, and realizes the simulation of satellite motion process by unmanned aerial vehicle through formulating reasonable space-time scaling rules, combining spacecraft kinematics characteristics and unmanned aerial vehicle flight control technology.

This disclosure relates to a proactive service migration method and system for space-based computing networks. The proactive service migration method applied to a first satellite includes: proactively generating a corresponding service migration task; selecting a target satellite from all data-processing satellites in the acquired space-based computing network based on satellite motion patterns, the target service area, and target service resource requirements; selecting a second satellite from the target satellites according to satellite selection criteria; sending a service migration request corresponding to the service migration task to the second satellite, and transmitting the target service request and the latest calculation results obtained by the first satellite in response to the target service request to the second satellite, so that the second satellite continues to execute the target service request. This disclosure enables proactive satellite service migration, eliminating dependence on ground control, and reduces search overhead by considering satellite motion patterns when determining subsequent service satellites.

The application relates to a combined orbit determination method based on SLR and intersatellite links, which comprises the following steps: S100, determining a nonlinearized intersatellite observation equation according to intersatellite observation data; S200, determining a nonlinearized SLR observation equation according to SLR observation data; S300, determining a state transition matrix and a linearized satellite orbit determination observation equation according to a satellite motion equation and the nonlinearized satellite orbit determination observation equation; S400, determining a linearized SLR observation equation according to the nonlinearized SLR observation equation, the state transition matrix and the linearized satellite orbit determination observation equation; S500, determining a linearized intersatellite observation equation according to the nonlinearized intersatellite observation equation, the state transition matrix and the linearized satellite orbit determination observation equation; and S600, performing satellite combined orbit determination according to the linearized intersatellite observation equation and the linearized SLR observation equation. The application can simultaneously exert the technical advantages of SLR and intersatellite links, and can obtain a high-precision satellite orbit.

The invention discloses a deep expansion network-based remote sensing video satellite motion small target detection method, which is applied to the field of target detection and comprises the following steps of: decomposing a low-rank sparse matrix decomposition task into a background solving task, a foreground solving task and a Lagrange multiplier updating task based on an alternating direction multiplier method; constructing a background recovery layer based on a background solving task, constructing a foreground reconstruction layer based on a foreground solving task, and constructing a Lagrange multiplier updating layer based on a Lagrange multiplier updating task; constructing a deep expansion network based on the background recovery layer, the foreground reconstruction layer and the Lagrange multiplier update layer, and training the deep expansion network based on remote sensing video satellite video data; and after the training is completed, inputting to-be-detected video data into the deep expansion network to obtain an output moving small target detection result. Priori knowledge is brought into the network to guide network learning through the deep expansion network, and the method has high operation efficiency and good generalization ability while maintaining interpretability and low parameter sensitivity.

The application provides a satellite signal positioning and error correction method, system, positioning terminal and program, and belongs to the communication technical field.The method comprises the following steps: constructing a received signal model of satellite movement; using the received signal model to perform layered processing on the received signal, and using a maximum likelihood method to perform interference source position estimation under long-time observation according to the layered processing result; performing error correction on the interference source position estimation, and completing positioning and error correction on the satellite signal.The application proposes a direct positioning method under long-time observation aiming at the interference source positioning problem under the condition that the adjacent satellite received signal is a weak signal.The method considers satellite movement in the received signal model, and interference source position estimation is obtained by using coherent and non-coherent processing modes.In addition, the application also proposes an error correction algorithm aiming at satellite retransmission frequency error, and the application realizes high-precision positioning of the interference source by using the adjacent satellite weak signal.

The invention relates to the technical field of wireless communication, and discloses a single-antenna terminal time-varying arrival angle prediction method based on equivalent and prior information, which comprises the following steps: establishing a motion model of a satellite relative to a terminal, and determining model parameters to be estimated; on the basis of displacement equivalence, signals sent by a satellite at different moments and different positions and received by a fixed single-antenna terminal are equivalent to signals sent by the satellite at the same moment and received by a virtual array antenna terminal, and a single-antenna equivalent array manifold matrix is constructed; according to the constructed equivalent array popular matrix, processing a received signal by using a MUSIC algorithm to obtain signal arrival angle information; performing model fitting on the estimation results of the plurality of different moments and an undetermined satellite motion model through a least square fitting algorithm to obtain a final satellite motion model, and retaining or updating the arrival angle prediction model to obtain a new prediction model of a satellite service period; according to the method, the arrival angle estimation capability of the single-antenna Internet of Things terminal on the high-dynamic satellite downlink signal is improved.

The application discloses a measurement control method, device and equipment of NTN mobile cell and medium, and belongs to the technical field of wireless communication network. The method comprises the following steps: determining satellite motion state information of a plurality of signaling epoch times in the future based on satellite ephemeris information of a satellite associated with the NTN mobile cell and basic ephemeris time, and determining the position of a ground reference point of a satellite coverage beam based on the satellite motion state information and satellite beam direction information; determining a measurement decision distance related to the position of the ground reference point; and updating system broadcast information and terminal measurement configuration information of the NTN mobile cell based on the position of the ground reference point corresponding to the signaling epoch time and the measurement decision distance. According to the technical scheme, the position of the ground reference point of the triggering measurement mechanism and the measurement decision distance are dynamically adjusted, so that the triggering measurement mechanism can adapt to the dynamic motion of the satellite and the difference in cell beam coverage, and the stability and service quality of non-ground network sliding beam cell communication are ensured.

The invention relates to a communication method, equipment and a storage medium. The method comprises: receiving first information sent by a network device, the first information comprising a transmission configuration indication (TCI) state table and first indication information, the TCI state table comprising a corresponding relationship between a TCI state and a reference signal, the wave beam corresponding to the TCI state table is a wave beam which is determined according to a satellite motion track of a satellite network to which the terminal equipment belongs and can provide service for the terminal equipment, the first indication information is used for indicating the position of a first TCI state in the TCI state table, and the first TCI state is a TCI state corresponding to a current service wave beam of the terminal equipment; and executing TCI switching according to the first information. That is to say, the terminal device can perform TCI switching according to the TCI state table configured by the network device, so that the terminal device does not need to send the TCI state and indicate the to-be-switched beam to the terminal device during each beam switching, thereby saving the signaling overhead and improving the beam switching efficiency.

This application relates to the field of satellite positioning technology and discloses a carrier phase cycle slip correction method, electronic device, storage medium, and product, including: determining the cycle slip number of a first frequency point with a large cycle slip based on the Doppler frequency offset of each frequency point in the current epoch, the Doppler frequency offset of the previous epoch, the carrier phase of the current epoch, and the carrier phase of the previous epoch; obtaining a first carrier phase correction value for the current epoch based on the cycle slip number of the first frequency point; constructing a small cycle slip estimation model based on the first carrier phase correction value to determine the cycle slip number of a second frequency point with a small cycle slip among all frequency points; obtaining a second carrier phase correction value based on the cycle slip number of the first frequency point and the cycle slip number of the second frequency point; and determining the target carrier phase based on the satellite motion state information of the target satellite, the receiver motion state information of the receiver, and the second carrier phase correction value to ensure the repair accuracy of carrier phase observations in the fusion scenario of low-Earth orbit satellites and medium-Earth orbit satellites.

The application discloses a Doppler-code phase two-dimensional joint search same-frequency multi-target signal detection method and relates to the field of spaceflight measurement and control. The application generates a global energy matrix through two-dimensional joint correlation calculation and incoherent accumulation at a receiving end according to the Doppler frequency shift caused by satellite movement and the code phase offset caused by signal propagation time delay difference, calculates an adaptive threshold, suppresses strong signal sidelobe interference by defining a protection area, and improves weak signal detection probability to more than 90%. The application allocates tracking channels in descending order of energy, and achieves the purpose of efficient detection of multiple targets at the same time. The application is especially suitable for Doppler-code phase two-dimensional joint search same-frequency multi-target signal detection in a low-orbit satellite constellation or a dense satellite network, and solves the problems of low spectrum utilization and complex pseudo code management of traditional frequency division / code division technology.

The invention provides a satellite combination selection method based on an optimal DOP value, and the method comprises the steps: obtaining all visible satellites through obtaining satellite constellation ephemeris data and service region position information; calculating the visible time of the satellite to the service area according to the movement speed of the satellite and the pitch angle; and selecting the satellite combination with the optimal DOP value from the satellites meeting the visible time requirement. The method is clear in physical significance, small in calculation amount, adaptive to the satellite-borne software operation environment, effective in screening result and high in service stability, and the positioning precision and the practical value of the satellite navigation enhancement system can be remarkably improved.

The invention discloses a method for calculating a visible time period between a satellite and any area of the ground, relates to the technical field of visible time period calculation, and aims to solve the problems of orbit perturbation errors, low intensive transit efficiency and coverage blind areas in satellite visible time period calculation. Through three technical means of dynamic resistance correction, space-time clustering optimization and inter-satellite link cooperation, a resistance compensation mechanism fuses real-time change of atmospheric density and a satellite motion direction, an accumulative error of orbit prediction is corrected, and it is ensured that starting and ending moments of a visible window accurately correspond to an actual transit event; the space-time clustering algorithm performs grouping processing on dense transit satellites, so that repeated calculation of satellite coverage in the same time-space domain is avoided, and the large-scale constellation scheduling response time is remarkably shortened; the inter-satellite link cooperation mechanism breaks through the geometric limitation of single-satellite direct connection, indirectly covers the traditional blind area through the relay satellite, and improves the service continuity of high-latitude and complex terrain areas.

The application discloses an inter-satellite baseline high-precision measurement and estimation method, and is characterized in that the method comprises the following steps: S1. Estimating and calibrating GNSS measurement information through a star sensor and laser ranging information; S2. Determining a measurement noise variance matrix R, and estimating in combination with satellite motion characteristics and noise characteristics; and S3. Adopting an interactive multiple model unscented Kalman filtering method to perform information processing. In the application, the problems that a measurement scale of an existing method does not meet long-interference baseline measurement requirements, measurement information is single, measurement precision is unknown, and an information processing method is not suitable are overcome, and a method for realizing fusion of GNSS, laser link and star sensor measurement information by using an interactive multiple model unscented Kalman filtering is provided, so that inter-satellite high-precision real-time baseline measurement information is obtained, the demand of future multi-spacecraft formation cooperation for high-precision inter-satellite measurement information is met, and mm-level inter-satellite baseline measurement precision is achieved.

This disclosure provides methods and apparatuses. The method includes, when obtaining measurement configuration information, a terminal device may directly obtain NTN parameter information needed for measurement or determine the NTN parameter information based on indication information. Further, the terminal device performs measurement based on the measurement configuration information and the NTN parameter information. The terminal device may supplement or adjust, based on ephemeris information in the NTN parameter information, an offset that is of a measurement frequency, measurement time, or the like and that is caused by movement of a satellite.

The present disclosure relates to a communication method, a device, and a storage medium. The method comprises: receiving first information sent by a network device, wherein the first information comprises a transmission configuration indicator (TCI) state table and first indication information, the TCI state table comprises correspondences between TCI states and reference signals, the beam corresponding to the TCI state table is a beam that can provide a service for a terminal device and is determined on the basis of the satellite motion trajectory of a satellite network to which the terminal device belongs, the first indication information is used for indicating the position of a first TCI state in the TCI state table, and the first TCI state is a TCI state corresponding to the current serving beam of the terminal device; and performing TCI switching on the basis of the first information. In other words, the terminal device can perform TCI switching on the basis of the TCI state table configured by the network device. In this way, there is no need to send a TCI state each time beam switching is performed, so as to indicate to the terminal device a beam to be switched, thereby saving signaling overheads, and improving the beam switching efficiency.

The invention discloses a resolving method for equivalent simulation of spacecraft kinematics characteristics by an unmanned aerial vehicle, which comprises the following steps of: constructing an inertial coordinate system and a satellite orbit coordinate system required by an equivalent model, and establishing a relative motion equation in the orbit coordinate system; determining spacecraft orbit kinematics parameters and unmanned aerial vehicle equivalent kinematics parameters according to the equation; a dimension matrix is listed in combination with the basic dimensions of the parameters, and the number of basic parameters describing the physical process is determined according to a matrix rank; on the basis of the similarity between a model and a prototype, similar conditions are applied to dimensionless numbers, an equation is established to describe two systems, and then scale factors of kinematics parameters are deduced. According to the method, the controllable characteristics of the flight height, the flight speed and the vertical climbing / descending speed of the unmanned aerial vehicle are fully utilized, a reasonable space-time scaling criterion is formulated, and the kinematics characteristics of a spacecraft and the flight control technology of the unmanned aerial vehicle are fused, so that simulation of the unmanned aerial vehicle on the satellite motion process is realized.

The invention discloses a dynamic satellite communication uplink Doppler frequency offset and time delay estimation and compensation method aiming at double challenges of large transmission time delay and dynamic Doppler frequency shift caused by satellite-ground high-speed relative motion in 3GPP NTN communication. Different from a traditional static compensation scheme, an ephemeris-driven satellite motion state real-time resolving model is constructed, and the timeliness of the pre-compensation scheme is improved. A dynamic ephemeris updating period adjusting strategy is provided through quantitative analysis of a Doppler frequency shift derivative, and the signaling interaction frequency is effectively reduced on the premise that the system performance is guaranteed. The orbit equation is suitable for most satellites and compatible with heterogeneous constellation systems such as GEO and MEO, the pre-compensation analysis method is suitable for various NTN uplink channels, suitable compensation schemes can be summarized according to different channel characteristics and different satellite orbits, and an extensible technical path is provided for satellite-ground cooperative transmission.

The application discloses a service function chain embedding method fusing features, and comprises the following steps: step S1, feature aggregation; step S2, embedding a virtual node into a physical node to be embedded; step S3, route selection; and step S4, PPO model updating. Through the application, the end-to-end transmission delay in the service function chain embedding process caused by satellite movement can be optimized and reduced in a dynamic network environment.

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