994 results about "Satellite orbit" patented technology

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses a satellite orbit prediction method, device and equipment based on multivariate features. Comprising the following steps: determining a speed position parameter of a satellite at a prediction moment under an ICRS coordinate system based on an orbit mechanical model to obtain a first speed position parameter; converting the first speed position parameter into an ECEF coordinate system to obtain a second speed position parameter; time features, satellite state features and space environment features at the current moment are obtained, the satellite state features are in an ECEF coordinate system, and the space environment features are in a geodetic coordinate system; performing feature fusion on the time feature, the satellite state feature, the space environment feature and the second speed position parameter to obtain an input feature, and inputting the input feature to an orbit correction model; evaluating the error of the second speed position parameter based on an orbit correction model to obtain a target error prediction value; and adjusting the second speed position parameter based on the target error prediction value to obtain a target speed position parameter of the satellite at the prediction moment.

The invention discloses a spaceborne interference source Doppler observation strategy optimization method, which comprises the following steps: acquiring an original radio frequency signal and satellite orbit data, predicting mutation characteristics in Doppler data, and generating a self-adaptive observation scheme; according to the self-adaptive observation scheme, energy-aware resource scheduling is carried out, observation is executed, and enhanced Doppler observation data is obtained; and carrying out positioning calculation and performance evaluation based on the enhanced Doppler observation data, and generating parameters for iteratively optimizing an observation strategy. According to the invention, intelligent matching of the observation resource and the signal information content is realized, and the resource utilization efficiency, the key event capturing capability and the final positioning precision are improved.

The invention discloses a satellite-based enhancement information generation method and system based on a low-orbit constellation, and relates to a satellite navigation enhancement technology, and the method comprises the steps: decoding and processing Beidou PPP-B2b message information, so as to obtain a Beidou satellite high-precision orbit and a clock error; smoothing the pseudo-range observation value by using the low-orbit satellite carrier phase observation value; constructing an ionosphere-free combined observation value by using the observation data of the low-orbit satellite, and resolving the real-time position of the low-orbit satellite based on the obtained high-precision orbit and clock correction of the Beidou satellite to obtain the position information and clock correction information of the low-orbit satellite; performing satellite-based enhanced differential correction calculation by using the obtained low-orbit satellite position information, low-orbit satellite observation data and GNSS basic navigation messages to obtain a satellite-based enhanced orbit and clock differential correction; and carrying out pseudo-range residual error correction according to the obtained satellite-based enhancement difference correction number, and carrying out satellite-based enhancement integrity parameter calculation based on a correction result. According to the method, the position of the low-orbit satellite can be determined synchronously without depending on an external high-precision GNSS satellite orbit and clock error data, and the state of the low-orbit satellite is monitored.

The invention relates to the technical field of satellite orbit prediction, and discloses a satellite orbit prediction method based on a physical information neural network, a terminal and a medium. The method comprises the following steps: constructing a sample set based on satellite position data, sun position data and moon position data in the same time period; constructing a physical information neural network; the network takes satellite historical position data as input to predict a satellite orbit position at a future moment; training a physical information neural network by using the sample set, and executing a satellite orbit prediction task by using the trained physical information neural network; the trained loss function comprises data loss, physical loss and smoothness loss; the data loss is used for measuring the difference between network prediction output and actual observation data; the physical loss is jointly calculated by the earth aspheric perturbation, the three-body gravitational perturbation and the solar light pressure physical perturbation borne by the satellite; the smoothness loss is used for constraining the smoothness of the predicted satellite orbit. According to the invention, the prediction precision and robustness of the satellite orbit are improved.

The invention relates to the technical field of landslide displacement data prediction, in particular to a GCN-MHA-GRU-based landslide displacement prediction method for a black square platform. Acquiring synthetic aperture radar monitoring data of the black square table area; extracting landslide surface deformation data of the black square table area from the synthetic aperture radar monitoring data; decomposing the landslide earth surface deformation data by adopting a three-dimensional deformation decomposition method according to a satellite orbit; establishing a landslide prediction model based on a graph neural network, a multi-head attention mechanism and a gating circulation unit; inputting the decomposed landslide surface deformation data into the landslide prediction model for training; and carrying out landslide displacement prediction on the black square table area according to the trained landslide prediction model. According to the method, an efficient, accurate and robust landslide displacement prediction model is constructed, and powerful technical support can be provided for scientific prevention and control of geological disasters.

The invention discloses a navigation satellite high-precision orbit forecasting method based on a bidirectional long short-term memory network, and relates to the technical field of satellite orbit forecasting, and the method comprises the following steps: (1) obtaining a reference orbit; (2) extrapolating a dynamic orbit; (3) constructing an orbit forecast error sequence; (4) training a network model; (5) predicting orbit forecast errors at future moments; and (6) compensating a forecast result. According to the method, the orbit prediction error sequence is constructed to describe the difference between the dynamic model and the real space environment, and the change rule of the orbit prediction error is captured and learned by adopting the bidirectional long-short-term memory network, so that the orbit error at the future moment is predicted, and the orbit prediction result based on the dynamic model is corrected; therefore, the defects of dynamic modeling in comparison with a real space environment are compensated, the trend that orbit errors are rapidly diverged along with the increase of forecasting time is inhibited, and a high-precision orbit forecasting task of a navigation satellite is effectively realized.

The invention provides a satellite communication method and device supporting fire rescue, and the method comprises the steps: carrying out the time alignment processing of real-time multi-source data collected from a fire rescue site and a pre-stored multi-source scene database, forming a time synchronization data set, and generating a terminal state data set and a scene feature data set; performing spatial geometric analysis based on the stored satellite orbit data and terminal position data, and generating available channel data in combination with meteorological monitoring data; task priority data and resource allocation demand data are generated through service feature analysis and task feature calculation; generating network configuration data and terminal access data based on slice configuration and resource allocation; and generating real-time resource data and terminal parameter data according to load statistical analysis and service quality calculation. According to the invention, through multi-source data fusion and dynamic resource adjustment, the reliability and service quality of satellite communication in a fire rescue scene are improved.

The invention discloses a low-orbit satellite measurement and control orbit determination method, device and equipment and a medium, and the method comprises the steps: obtaining a satellite-borne GNSS pseudo-range observation value and a GNSS broadcast ephemeris, and carrying out the calculation through a pseudo-range single-point positioning algorithm, and obtaining a self-positioning result of a low-orbit satellite; when the number of GNSS satellites used by pseudo-range single-point positioning is lower than a first threshold value, or a satellite space distribution characteristic value of a positioning epoch is greater than a second threshold value, removing a corresponding self-positioning result; polynomial fitting is carried out on the filtered self-positioning results by adopting a sliding window, the self-positioning results with fitting residual errors larger than a third threshold value are removed, then interpolation processing is carried out, and optimized self-positioning results are obtained; and orbit determination is carried out in combination with a dynamic fitting method, and a final low-orbit satellite measurement and control orbit is obtained. The method is low in calculation cost and good in real-time performance, gets rid of the dependence of a ground station, is less affected by low-orbit satellite orbit maneuver, and can reflect a more accurate satellite position.

The invention discloses a time synchronization method suitable for a satellite communication system, and the method comprises the steps: analyzing a forward broadcast signal, and obtaining the reference time of a network clock; constructing a geometric prediction handle based on satellite orbit data, and predicting one-way propagation time delay between a terminal and a satellite by using the geometric prediction handle; estimating the processing delay of the terminal according to the symbol rate and the equipment working condition of the terminal and the delay calibration data; fusing the network clock reference time with the processing delay estimate to synthesize a terminal local time; and the sending time of the return link is calculated based on the local time and the propagation delay prediction. According to the method, the synchronization precision can be improved to a microsecond level, the convergence speed in a dynamic scene is accelerated, adaptive compression of the guard interval is supported, and the stability and spectrum efficiency of a satellite communication system are effectively improved.

The invention relates to the technical field of data processing, and discloses a data fusion method and system based on multi-source satellite altimeter data. The method comprises the following steps: performing multi-satellite intersection analysis and orbit error data correction on preprocessed multi-source satellite altimeter data to obtain satellite orbit error correction data; carrying out height subtraction processing on the earth water surface height and the average sea surface height on the sea surface height measured by the correction satellite, obtaining along-orbit sea surface height data, carrying out abnormal height data screening, obtaining coastal height abnormal data, carrying out space-time interpolation processing on the coastal height abnormal data, and obtaining a coastal height data set; the method comprises the steps of obtaining interpolation coastal height abnormal data, performing multi-source fusion to obtain gridded sea surface height abnormal fusion data, and performing abnormal reason analysis on the gridded sea surface height abnormal fusion data to obtain a predicted abnormal reason. According to the invention, the accuracy of data fusion based on the multi-source satellite altimeter data is improved.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses an LEO on-orbit real-time precision orbit and clock error determination method and system based on PPP-B2b enhancement, and belongs to the technical field of low-orbit satellite high-precision autonomous orbit determination and clock error estimation. According to the method, enhanced information broadcasted by Beidou No.3 B2b signals is used for correcting a BDS-3 / GPS satellite orbit and clock correction, under the support of the regional BDS-3 / GPS enhanced information, when a new BDS-3 / GPS tracking satellite exists, before measurement updating, the inter-epoch clock correction variable quantity obtained through calculation by using a carrier phase time difference method is used as two orbit determination filtering clock correction parameters for constraint, so that the measurement accuracy is improved. In-orbit real-time separation of receiver clock error and non-difference floating point ambiguity parameters is carried out; and finally, substituting an LEO precision orbit output by orbit determination filtering and a non-difference floating point ambiguity parameter into a phase observation equation to calculate the precision clock error of the BDS-3 / GPS receiver. The method is suitable for the situation that only regional GNSS enhancement information support exists, and the influence of orbital maneuver is small.

The invention discloses an ultra-low orbit guarantee method, system and equipment for a near-earth satellite. Comprising the following steps: determining a satellite orbit element at the current moment based on an atmospheric resistance perturbation item, a conventional perturbation item and a small thrust perturbation item, and inputting the satellite orbit element at the current moment into an orbit mechanical model; based on the orbit mechanical model and the satellite orbit elements, determining a first velocity position parameter of the satellite at the prediction moment under the ICRS coordinate system, and converting the first velocity position parameter into an ECEF coordinate system to obtain a second velocity position parameter at the prediction moment; inputting the time characteristic, the satellite state characteristic, the space environment characteristic and the second speed position parameter of the current moment into an orbit correction model to obtain a target error prediction value; adjusting the second speed position parameter based on the target error prediction value to obtain a target speed position parameter of the satellite at the prediction moment; and performing orbit attenuation risk early warning based on the target speed and position parameters of the satellite at the prediction moment.

The invention discloses an ultra-low orbit determination method and device for a near-earth satellite, a medium and a product. Comprising the following steps: acquiring a thrust vector of a satellite engine under a satellite body coordinate system under the condition that the thrust of an ion propeller of a satellite is constant; obtaining a first rotation matrix of the satellite attitude angle relative to the geocentric inertial coordinate system, and converting the thrust vector to the geocentric inertial coordinate system based on the first rotation matrix to obtain thrust components of the thrust vector on three coordinate axes of the geocentric inertial coordinate system; combining the satellite mass, the real-time on-off state of the engine and the thrust components on the three coordinate axes to obtain a small thrust perturbation item; and adding a small thrust perturbation item on the basis of the atmospheric resistance perturbation item and the conventional resistance perturbation item to obtain an input parameter, and inputting the input parameter to the orbit mechanical model, so that the orbit mechanical model determines the satellite orbit element based on the atmospheric resistance perturbation item, the conventional perturbation item and the small thrust perturbation item.

The invention belongs to but not limited to the technical field of passive positioning, and particularly relates to a near space passive positioning method and system based on a low-orbit satellite, and the method comprises the steps: S1, satellite orbit design: carrying out the orbit design of a satellite formation for a target area; s2, acquiring a required observation value, acquiring a time difference and a frequency difference between two paths of signals by using a second-order cross-ambiguity function, and estimating an arrival angle of an incoming wave signal by using a multiple signal classification algorithm; s3, joint positioning: establishing an equation set about the position of the radiation source by using the geometrical relationship between the satellite and the position of the radiation source and the definitions of TDOA and FDOA; s4, solving an estimated value of the position of the radiation source; and S5, the formation satellites solve the positions of the radiation sources through the simultaneous positioning equation set and then send the positions to the ground station, and the ground station reprocesses the received possible positions of the radiation sources.

The invention relates to the technical field of GNSS (Global Navigation Satellite System) navigation and positioning, in particular to a GNSS real-time precise single-point positioning ambiguity fixing method for a complex environment. The method comprises the steps of obtaining and processing data, obtaining a precision satellite orbit and a precision satellite clock error from original observation data, broadcast ephemeris and an SSR correction number which are originally obtained in sequence, obtaining original frequency point non-difference floating point ambiguity, obtaining fixed integer inter-satellite single-difference wide-lane ambiguity, and obtaining floating point inter-satellite single-difference narrow-lane ambiguity. And finally, selecting the complete set ambiguity according to the precision index of the floating point narrow lane ambiguity, and carrying out iteration to obtain an ambiguity subset meeting the optimal aperture check rule. Through the method, the ambiguity fixing reliability can be further improved, and the convergence time is shortened.

The invention belongs to the technical field of satellite positioning, and discloses an unmanned aerial vehicle positioning cruise method and system based on satellite-based enhancement, and the method comprises the steps: setting an unmanned aerial vehicle cruise region range, a high-coverage cruise route and flight time; and checking software and hardware equipment of the unmanned aerial vehicle, taking off from a safe area, and starting automatic cruise. Observation data, broadcast ephemeris and Beidou B2b and Galileo HAS products are obtained through an unmanned aerial vehicle receiver. Carrying out decoding and correction number matching on the B2b and the HAS messages; correcting the satellite orbit, the clock error and the code and phase deviation according to the correction number provided by the B2b and the HAS; performing gross error elimination, clock jump repair and cycle slip detection on the data; and performing parameter estimation by using Kalman filtering to obtain high-precision position coordinates. If an emergency occurs, an operator can send a return instruction to the unmanned aerial vehicle through a Beidou short message. And after the cruise task is finished or a return instruction is received, the unmanned aerial vehicle completes safe landing at the planned return point.

The invention relates to an inter-satellite link communication simulation system and method based on a satellite constellation. The system comprises a satellite orbit simulation module, a satellite attitude simulation module, an inter-satellite communication link simulation module, a visualization and interaction technology module and a data interaction and system test module. The satellite orbit simulation module is used for calculating a movement track of a satellite in an earth gravitational field; the satellite attitude simulation module is used for accurately simulating a satellite attitude; the inter-satellite communication link simulation module is used for evaluating inter-satellite communication quality; the visualization and interaction technology module is used for presenting real-time states of satellite orbits, attitudes and inter-satellite links; and the data interaction and system test module is used for smoothly exchanging data, and comprehensively testing and checking the correctness and performance of satellite orbits, attitudes and communication functions. The method has the beneficial effects that the real-time states of the satellite orbit, the attitude and the inter-satellite link are efficiently presented, so that a user can easily monitor and control the simulation process.

The invention belongs to the technical field of satellite orbit prediction, and provides a low-orbit satellite orbit state prediction method based on artificial intelligence, which comprises the following steps of: dividing step lengths of a predicted orbit according to a time window, calculating a resultant acceleration of each step length, performing stress input on an initial position and speed, and obtaining a nominal orbit state sequence; forming an augmented state vector with aerodynamic synthesis parameters; inputting a time sequence neural network model, and performing rolling updating on the augmented state according to the output; obtaining an original standard deviation through mapping by using uncertainty measurement, calculating a standardized residual error, solving a right side weighted quantile according to a normalized time weight, comparing the right side weighted quantile with a preset threshold value, and carrying out adaptive deviation adjustment; and calculating risk measurement by using the acquired data, comparing the risk measurement with a set threshold value and a priority rule, automatically executing a judgment action on the risk measurement, recording a trigger reason and the judgment action, and updating parameters in the time sequence neural network model.

The invention relates to a satellite communication encryption method resistant to channel interference. According to the method, satellite orbit parameters are dynamically mapped into a chaos spread spectrum sequence, an anti-interference pseudo-random sequence and a dynamically decoupled encryption key are synchronously generated based on the chaos sequence, a spread spectrum code and the key are completely isolated mathematically, chaos parameters and a channel state are hidden and embedded into a physical layer signal, and therefore the anti-interference pseudo-random sequence and the dynamically decoupled encryption key are obtained. According to the method, deep cooperation of anti-interference and encryption is achieved, the concealment and the anti-interception capability of signals in a complex channel are enhanced through chaos spread spectrum, the synchronization precision of a decryption end is guaranteed through real-time binding of a dynamic key and channel parameters, and finally synchronous improvement of the anti-interference capability and the information security is achieved in a satellite communication high-dynamic environment.

The invention discloses a high-precision positioning method based on combination of a Beidou satellite and 5G-Mesh, and relates to the technical field of satellite positioning, and the method comprises the steps: receiving a navigation signal of the Beidou satellite and a communication signal of a 5G-Mesh network in real time; the topological structure change of the 5G-Mesh network is monitored in real time, and the connection relation between the nodes is dynamically adjusted in combination with network performance indexes; the receiver performs pseudo-range measurement on the signals of the visible satellites; a navigation message is demodulated from the received satellite signal, and the accurate position of each satellite at the current moment is calculated by using a satellite orbit calculation model; constructing a signal intensity fingerprint database; outputting a reference position having the highest similarity with the current signal strength characteristic to carry out error modeling on the Beidou satellite signal and the 5G-Mesh network signal; and fusing the two kinds of position information by adopting a weighted fusion algorithm. By fusing the technical advantages of the two positioning technologies, the positioning precision and reliability are improved, and the requirement for high-precision positioning in a complex scene is met.

The invention discloses an orbit-driven atmospheric density estimation method. The method comprises the following steps: acquiring historical orbit element data and screening satellite numbers in a required time range; based on the obtained historical orbit element data and the screened satellite number, calculating a propagation orbit of the satellite in a future time period through an orbit propagation model; defining historical orbit element data as a real orbit, and calculating a propagation error at the same time point according to the real orbit and the propagation orbit; dividing the propagation errors into a regular class and an irregular class, and selecting satellite orbit parameters of the regular class; constructing an atmospheric density prediction model, and inputting the selected rule-class satellite orbit parameters into the atmospheric density prediction model for training and evaluation to obtain an optimized atmospheric density prediction model; and inputting the orbit parameter, the state vector, the space environment index and the error of the front and back orbit propagation in the previous time period into the optimized atmospheric density prediction model to obtain the atmospheric density at the future moment.

The invention provides a GNSS data quality prediction method and device based on a fisheye camera, and a medium, and belongs to the technical field of data processing, and the method comprises the steps: determining the satellite orbit information of a future time period with a to-be-evaluated observation station as a reference point based on ephemeris prediction; according to the fisheye sky image shot at the to-be-evaluated observation station and the satellite orbit information, determining satellite feature data of a future time period and the occlusion porosity of the future time period; respectively inputting the occlusion porosity of the future time period and at least part of satellite feature data of the future time period into a general prediction model and an observation station prediction model corresponding to the observation station to be evaluated for data quality evaluation, and obtaining a first data quality evaluation index and a second data quality evaluation index; and determining a data quality prediction result based on the first data quality evaluation index and the second data quality evaluation index. A general prediction model and an observation station exclusive prediction model are introduced to carry out double-model evaluation, and accurate prediction of GNSS observation data quality is realized.

The invention provides an inter-satellite link communication simulation method and system based on a satellite constellation and a program product, and the method comprises the following steps: calculating the position and speed data of at least two satellites in a preset time sequence based on a satellite orbit parameter and acting force model; calculating attitude data of the at least two satellites in a preset time sequence based on the satellite attitude parameters and an attitude dynamics model; on the basis of the position, speed and attitude data and preset link parameters, inter-satellite link key parameters between the at least two satellites are calculated, and the key parameters comprise link delay, bandwidth, signal strength and bit error rate; and carrying out three-dimensional visual display on the position, speed, attitude data and inter-satellite link key parameters. The problems that in the prior art, a simulation system cannot comprehensively reflect the actual communication condition, and it is difficult to accurately simulate the electromagnetic wave propagation particularity in the space environment are solved, the performance of the communication link can be predicted more accurately, and the reliability of inter-satellite communication link simulation is enhanced.

The invention provides a satellite orbital transfer control method and device, electronic equipment and a storage medium, and relates to the technical field of satellite control. The satellite orbital transfer control method comprises the following steps: constructing a three-dimensional centralized monitoring area corresponding to a target satellite based on acquired first operation information of the target satellite; based on the three-dimensional centralized monitoring area, generating a monitoring instruction, and based on the monitoring instruction, controlling a monitoring terminal corresponding to the target satellite to perform centralized monitoring on the three-dimensional centralized monitoring area; when it is monitored that the target terminal exists in the three-dimensional centralized monitoring area, second operation information corresponding to the target terminal in a unit time period is obtained, and a control mode corresponding to the target satellite is determined based on the first operation information and the second operation information; and based on the control mode, controlling the target satellite to perform orbital transfer operation. According to the invention, the orbital transfer capability of the target satellite can be improved and the collision probability can be reduced.

The invention relates to a laser communication system autonomous pointing method based on an inter-satellite link. The method comprises the steps that a laser communication system receives link building target satellite instantaneous orbit parameters transmitted by the inter-satellite link; the laser communication system converts the link establishment target satellite instantaneous orbit parameter transmitted by the inter-satellite link into a singular-point-free average orbit element, and the singular-point-free average orbit element serves as a link establishment target satellite orbit initial value of an inter-satellite link source; the laser communication system selects a link establishment target orbit initial value of an inter-satellite link source according to the instruction or the state, and calculates real-time orbit data of a link establishment target satellite; and the laser communication system automatically calculates a laser beam pointing angle according to the attitude and orbit data of the satellite and the real-time orbit data of the link building target satellite. According to the invention, the dependence of maintaining the inter-satellite laser link on the measurement and control conditions of the ground station can be reduced, and the laser beam pointing precision can be effectively improved.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses a forecasting method and device for an atmospheric resistance coefficient of a low-orbit satellite in the technical field of satellite navigation. The forecasting method comprises the following steps: acquiring satellite orbit determination data and a space environment index in a preset time period before forecasting; according to the satellite orbit determination data, performing simplified dynamic precise orbit determination on a low-orbit satellite, and fitting an atmospheric resistance coefficient in the simplified dynamic precise orbit determination process; performing data preprocessing on the space environment index and the atmospheric resistance coefficient and generating a sample set; constructing an LSTM prediction model, and training, adjusting and evaluating the LSTM prediction model through the sample set; predicting an atmospheric resistance coefficient in a future preset time period according to the finally obtained LSTM prediction model; and applying the atmospheric resistance coefficient in the future preset time period to the atmospheric resistance perturbation model of the low-orbit satellite for orbit forecasting. According to the method, the atmospheric resistance coefficient in the LEO satellite orbit prediction process is predicted in a high-precision manner through the LSTM prediction model, so that the orbit prediction precision is effectively improved.

The invention relates to the technical field of communication, and discloses a network optimization method and device based on multi-orbit satellite access, equipment and a medium, and the method comprises the steps: obtaining satellite orbit information from a network data analysis function module in response to an access request of user equipment; selecting a target orbit satellite from the multi-orbit satellites according to parameter requirements in the access request and satellite orbit information, and accessing the user equipment to the target orbit satellite; obtaining a Qos strategy based on the access request of the user equipment and the current network state of each orbital satellite, and configuring a network slice; and based on the Qos strategy and the network slice, constructing a data transmission session to enable the user equipment to perform data transmission with the user plane function module through the target orbit satellite. The optimal satellite orbit and the optimal network slice are intelligently selected by monitoring user requirements and network states in real time, dynamic flow routing and Qos configuration are achieved, and therefore it is ensured that a user obtains stable service quality in different scenes.