80 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 discloses a satellite group collaborative prediction method based on Lie group differential manifold and covariant optimization, and mainly solves the problems of inaccurate disturbance modeling, poor physical interpretation and large prediction error in the prior art. According to the scheme, the method comprises the following steps: mapping the position and attitude of a satellite to an SE (3) manifold, and describing the movement speed of the satellite by using Lie algebra; establishing a multi-level Lie algebra disturbance decomposition mechanism including absolute perturbation, relative coupling and observation noise; constructing a Riemannian loss function by using the orbit state after Lie group manifold embedding and the orbit state deviation obtained by disturbance decomposition; defining an orbital state updating rule by using a covariant derivative of the function, and iteratively solving the orbital state updating rule on the SE (3) manifold to output an orbital state prediction result of the satellite; for an abnormal state of inter-satellite link interruption, a differential geometric connection form is defined, and virtual relative position observation of an integral generation orbit state is carried out. According to the method, the physical interpretability and long-term prediction stability of orbit prediction can be improved, prediction errors are reduced, and the method can be used for low orbit communication constellation deployment of frequency band inter-satellite links.

A GNSS receiver, a method of estimating position, and an associated computer program are provided. An example method includes calculating a first (full) position solution based on pseudorange measurements made at a first time. One or more position updates are then calculated based on the first position solution, using delta carrier range measurements which compare first carrier range measurements, made at the first time, with second carrier range measurements, made at a second time. When calculating the one or more position updates, the delta carrier range measurements may be corrected to compensate for satellite motion between the first time and the second time. Corrections may also be made to compensate for changes in ionospheric delay.

The invention provides a low-orbit satellite ground terminal air interface performance test method and device, and the method comprises the steps: calculating satellite position data observed by a to-be-tested ground terminal at different moments according to a preset ground terminal position and low-orbit communication satellite ephemeris data, and generating a visible satellite motion track of the ground terminal position; selecting a preset number of track points on the visible satellite motion track as test points, and importing satellite position data of the test points into a test system; when the measurement antenna moves to the first test point, satellite position data corresponding to the first test point is transmitted back to the ground terminal to be tested; the to-be-tested ground terminal generates wave beams according to the received satellite position data, connection is established, and the test system completes air interface wireless performance measurement of the first test point; all the test points are traversed through the processing process, air interface wireless performance measurement of the ground terminal to be tested is completed, and air interface wireless performance measurement results corresponding to all the test points are obtained.

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 relates to an uplink and downlink time-frequency offset joint estimation compensation method, which comprises the following steps of: receiving ephemeris broadcasted by a satellite, and acquiring self position information; extrapolating the satellite position and speed at the downlink signal receiving moment according to the ephemeris, and calculating downlink frequency offset caused by satellite motion by combining the own position information; estimating downlink residual frequency offset and downlink sampling offset brought by the crystal oscillator according to the reference signal; calculating a frequency offset compensation value for the downlink signal according to the downlink frequency offset brought by the satellite motion and the downlink residual frequency offset brought by the crystal oscillator; and adjusting a received time domain signal by using the frequency offset compensation value of the downlink signal, and adjusting a received frequency domain signal by using the downlink sampling offset. According to the invention, the pre-compensation precision of the uplink frequency offset can be improved, and the estimation compensation of the downlink frequency offset and the sampling offset can be realized with lower complexity.

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 application discloses a kind of laser warning device passive sensing space non-cooperative target state calculation methods, first establish the relative motion state model of our satellite and enemy satellite and laser warning device observation model, then obtain observation angle information, according to the initial relative state quantity and initial relative state quantity error estimation value of our spacecraft and enemy satellite according to observation angle information, according to the relative state information between our satellite and enemy satellite is obtained according to the relative motion state model of our satellite and enemy satellite, laser warning device observation model and initial relative state estimation value and its error estimation value, again the relative state information between our satellite and enemy satellite is filtered and estimated, finally the estimation value of target satellite motion information is obtained, the position and velocity information of enemy satellite can be high-precision estimation.

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 discloses a same-frequency multi-target signal detection method for Doppler-code phase two-dimensional joint search, and relates to the field of spaceflight measurement and control. Through Doppler frequency shift generated by satellite motion and code phase deviation caused by signal propagation time delay difference, two-dimensional joint correlation calculation and incoherent accumulation are carried out at a receiving end to generate a global energy matrix, an adaptive threshold is calculated, strong signal side lobe interference is suppressed by defining a protection area, the weak signal detection probability is increased to 90% or above, and the detection accuracy is improved. Tracking channels are distributed according to an energy descending order, and the purpose of simultaneously and efficiently detecting multiple targets is achieved. The method is particularly suitable for same-frequency multi-target signal detection based on Doppler-code phase two-dimensional joint search in a low-orbit satellite constellation or a dense satellite network, and solves the problems of low spectrum utilization rate, complex pseudo code management and the like of the traditional frequency division / code division technology.

The invention discloses a visual multi-satellite orbit relative relation control method and device, equipment and a medium. The method comprises the steps that target satellite parameters are set; configuring configuration parameters by the prefabricated configuration library; acquiring approaching satellite parameters according to the target satellite parameters and the configuration parameters; and drawing and displaying relative movement track information of the two satellites in real time according to the parameters of the two satellites. According to the method, four types of eleven standardized orbit configuration libraries are constructed, a complex relative motion mathematical model is modularized, a user does not need to manually derive an orbit equation, a preset configuration parameter library can be directly called, and dynamic parameter adjustment functions (such as a semi-major axis, eccentricity, simulation time and the like) are combined; satellite motion forms meeting different task requirements (such as reconnaissance, accompanying flight and orbit avoidance) are rapidly generated, the efficiency is improved, and the efficient multi-form orbit control capability is achieved.

The invention relates to a multi-satellite stacking system. The multi-satellite stacking system comprises a rocket adapter and a plurality of satellites which are sequentially stacked on the rocket adapter and locked by a release device. The release device comprises a locking part and an ejection part, the locking part comprises a first locking piece and a second locking piece which are movably connected, the first locking piece and the second locking piece are tensioned by a releaser, the first locking piece is hinged to the rocket adapter, the top end of the second locking piece presses the end face of the topmost satellite, and after the releaser releases, the second locking piece moves towards the topmost satellite through a first elastic piece to be unlocked; the ejection part is movably connected with the rocket adapter and pre-presses the first locking piece through the second elastic piece, and after the second locking piece is unlocked, the ejection part ejects the first locking piece through the second elastic piece. The multi-satellite stacking system disclosed by the invention has very high engineering implementation value, the unlocking and ejection processes of the release device are precisely connected, the release clamping stagnation of the multi-layer satellites is avoided, the safety of satellite release is improved, and the multi-satellite stacking system has the advantages of high compression rigidity, light weight, high bearing capacity, reliable separation and the like.

The present invention proposes a GNSS simulator mathematical simulation system, which includes a constellation satellite orbit and clock parameter simulation subsystem, a navigation message generation subsystem, a user trajectory simulation subsystem, an integrity simulation subsystem, a space environment effect simulation subsystem and a simulation data generation subsystem for data interaction; the constellation satellite orbit and clock parameter simulation subsystem is composed of a space-time system model, an auxiliary database, satellite theoretical orbit data, and satellite clock theoretical parameters; the space-time system model has a built-in time system model and a coordinate system model, and the auxiliary database has built-in astronomical constants and environmental parameter values in the constellation satellite orbit and clock parameter simulation; the satellite theoretical orbit data calculates gravitational acceleration based on the input initial time, initial position velocity, integration time, and model selection control parameter data, and then uses the satellite motion equation to perform numerical integration operations on it to obtain the constellation satellite motion orbit.

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 present invention discloses a GNSS occultation open-loop prediction method based on a cubic spline interpolation algorithm, and relates to the field of occultation open-loop prediction. The method comprises: determining whether the current navigation satellite is atmospheric occulted using an occultation event prediction algorithm; obtaining position and velocity information of the atmospheric occultation and the low Earth orbit; performing occultation prediction calculations on the atmospheric occultation using an atmospheric model to obtain a model Doppler caused by satellite motion and a model pseudorange caused by a neutral atmosphere; obtaining interpolation parameters of the model Doppler and model pseudorange by caching n seconds of model Doppler, model pseudorange, and open-loop prediction time of the occultation in a 1 Hz mission using cubic spline interpolation; obtaining the 100 Hz model Doppler and model pseudorange by interpolation using the interpolation parameters; and calculating the signal transmission time using the model pseudorange; calculating the signal transmission time deviation value using the signal transmission time of the 100 Hz mission cycle, and converting the calculated signal transmission time deviation value into a hardware adjustment count for input into the FGPA adjustment, thereby performing open-loop tracking of the atmospheric occultation.

This invention discloses a satellite motion attitude adjustment method, device, satellite motion system, and satellite, relating to the field of satellite control. The method involves acquiring the output current and actual measured rotational speed; determining a reference current based on the actual measured rotational speed, a preset reference rotational speed, and the outer velocity loop control strategy in a preset dual-loop control strategy; determining an adjustment reference voltage based on the reference current, output current, and the inner current loop control strategy in the preset dual-loop control strategy; determining a control signal output to the drive module based on the adjustment reference voltage; and controlling the drive module to adjust the operating speed of the reaction flywheel to the preset reference rotational speed, so that the reaction flywheel generates a first target torque corresponding to the target angular momentum, used to change the satellite's motion attitude. This scheme uses a reaction flywheel for satellite motion attitude adjustment, which helps reduce costs, and the preset dual-loop control strategy achieves reliable and accurate adjustment of the reaction flywheel, resulting in good control stability.

The invention discloses an antenna scheduling method in multi-constellation navigation signal environment simulation. The antenna scheduling method comprises a planning software platform and an antenna scheduling method implemented through the platform. The scheduling method relates to signal simulation sources, antennas, navigation satellites and the like, the process comprises the steps of finding satellites, picking satellites, obtaining the space relation between the satellites and the antennas, and distributing and planning the antennas and the simulation satellites, and optimization logic under different priority conditions of a navigation system, precision, frequency points and the like is fully combined under the condition that the distributing and planning particularly relates to limited resources. According to the method, the contradiction between a limited number of antennas and continuous satellite motion is solved, an efficient and orderly utilization scheme of the antennas is optimized, navigation satellite signals of different coming directions and different types are realistically simulated to the maximum extent, a mapping distribution relation from the navigation satellite to the antennas is formed, and the navigation satellite distribution efficiency is improved. And multi-antenna navigation signal broadcasting constructed by multi-constellation navigation environment simulation in a test environment is supported, and the requirement for a space navigation signal environment in a navigation receiver test is met.

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.

This invention provides a method, apparatus, and related equipment for channel state information (CSI) feedback in a multi-user communication system. It extracts peak features of the channel signal in the angle-delay domain and regional correlation features of the channel signal in the angle-delay domain; fuses the peak features and regional correlation features; inputs the sparsity variation feature matrix of the low-Earth orbit (LEO) satellite channel as the satellite moves to different orbital positions into a channel state information (CSI) model to obtain a low-dimensional vector; transmits the low-dimensional vector to the satellite, so that the satellite can reconstruct the low-dimensional vector into a high-dimensional CSI matrix using the CSI model; wherein the CSI model is trained based on the high-dimensional CSI matrix. By compressing and reconstructing the CSI using the CSI model, the overhead of CSI feedback is reduced, improving system communication performance; the CSI model can extract changing data features from the channel matrix, improving reconstruction accuracy and further enhancing system performance.

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.