806 results about "Satellite orbit" patented technology

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 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 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.

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 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 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 belongs to the technical field of satellite positioning, and particularly discloses a high-precision PPP (Point-to-Point Protocol) positioning method based on SSR (Simple Sequence Repeat) correction prediction, which comprises the following steps that: a receiver receives and stores an SSR correction in real time to obtain an SSR sequence; inputting the stored SSR sequence into a pre-trained prediction model, and outputting an SSR correction number prediction value in a future time period; the broadcast ephemeris is corrected through the predicted SSR correction number, and a precise satellite orbit and clock correction are obtained; and constructing an ionosphere-free combination model based on the double-frequency observation value, and resolving the position of the receiver through Kalman filtering in combination with the corrected satellite orbit and clock correction. According to the method, long-time-sequence prediction is carried out on the SSR correction number through the prediction model, the problem of positioning precision jump caused by satellite correction data interruption is effectively solved, it is guaranteed that PPP positioning continuously outputs centimeter-level precision results under the scenes of signal shielding, network delay and the like, and the limitation that traditional PPP strongly depends on real-time SSR data is broken through.

The invention discloses a satellite orbit forecasting method based on deep learning physical constraint loss, and the method comprises the following steps: 1, carrying out the normalization preprocessing of input data, forming a training data set and a test data set, and constructing batch processing training data; and 2, performing dimension expansion on sample data points in each window in the batch processing data formed in the step 1, constructing a multi-dimensional feature space of the sample points, and forming a batch processing input data format capable of being introduced into the model. And 3, performing forward reasoning on the batch data formed in the step 2 by using a model, and obtaining a batch processing orbit prediction value output by the model at the next moment through a CNN lightweight spatial-temporal feature extraction module and a BiLSTM bidirectional time sequence neural network module. And 4, taking the track prediction value obtained in the step 3 and the truth value label in the training set obtained in the step 1 as input, calculating to obtain a loss value of a current training iteration batch through a multi-random learning loss module fusing physical constraints, and performing reverse updating of model parameters to complete model training. And step five, through the steps two to four, performing reasoning verification on the model by using the test set formed in the step one, and comparing with a truth value in the test set to obtain a model test result.

The present disclosure is a device and methods for satellite trajectory control and collision avoidance. Embodiments of the disclosure are comprised of a smart satellite device performing a process three steps. First, sensors collect data about the satellite's physical landing environment, passing information to satellite's database and processors. Second, the processors manipulate the information with a deep reinforcement learning program to produce instructions. Third, the instructions steer the satellite body by manipulating the satellite's panels for optimal trajectory and collision avoidance. The purpose for the present disclosure is to help solve the space debris problem.

The invention discloses a single base station PPP-RTK (point-to-point protocol-real-time kinematic) positioning method and equipment. The method comprises the following steps: firstly, according to acquired single base station observation data, single base station accurate coordinates and ephemeris data, satellite end error corrections and atmospheric delay corrections are respectively obtained based on different resolving models, and the satellite end error corrections comprise satellite clock error corrections and satellite orbit error corrections; the atmospheric delay correction number comprises an ionosphere delay correction number and a troposphere delay correction number of the first frequency; calculating an atmospheric delay difference between the single base station and the user based on an empirical model, and substituting the atmospheric delay difference into the atmospheric delay correction number to obtain an atmospheric delay correction number which can be used for the user; obtaining observation values of users to construct a PPP-RTK observation equation so as to eliminate error terms related to a single base station; and the satellite end error correction number and the atmospheric delay correction number are substituted into a user end PPP-RTK observation equation, so that single base station PPP-RTK positioning can be realized.

The invention provides an imaging spectrometer motion compensation imaging model construction method, an imaging model and a device, and relates to the technical field of space remote sensing. The method comprises the following steps: establishing a satellite orbit model, and defining a plurality of coordinate systems such as a detector coordinate system and a spectrometer imaging coordinate system and a conversion relation thereof; constructing a detector-scanning mirror-lunar surface ideal geometric mapping model based on the load optical parameters and a ray tracing method; determining the relation between the rotation angle of the scanning mirror and imaging spectrum view field positioning by using a reflecting prism conjugation theory; a quantitative relation is established by combining parameters such as satellite orbits and position postures, and finally a motion compensation imaging model is established. According to the method, the influence of the on-orbit error on the compensation imaging model is analyzed, and the error is used as an uncertainty component to be coupled into the model. According to the method, the problems of low model precision, neglect of influence of orbit observation parameters on imaging and the like in the prior art are solved, high-precision motion estimation and compensation can be realized, and the quality of data acquired by an imaging spectrometer is remarkably improved.

The invention belongs to the field of satellite communication, and provides a high-safety anti-interception satellite communication method based on a double-beam user terminal and double satellites aiming at the problem that a satellite communication system is easily intercepted and threatened due to open channels and relatively fixed satellite orbit information. Two beams of a double-beam user terminal are respectively aligned with two communication satellites, user service data are split in the two beams according to a configured proportion and then are sent in parallel, effective information cannot be decoded and intercepted under the condition that potential opponent detection receives a single-path communication signal, and even if two-path communication signals are detected, the effective information cannot be decoded and intercepted due to the fact that an information splitting rule cannot be obtained, so that the user service data cannot be decoded and intercepted. And effective information is difficult to decode and recover, so that extremely high information security and anti-interception capability of a user communication service are formed. According to the method, the non-partner information interception difficulty is high, and the method is particularly suitable for design and development work of key user satellite communication systems and user terminals with safety and anti-interception communication requirements as the main.

The invention discloses a lunar satellite orbit intelligent prediction method and system. The method comprises the following steps: constructing a basic motion model; constructing a prediction error data set; constructing a deep learning model; training a deep learning model; performing error estimation by using the basic motion model and the deep learning model; and generating a final orbit prediction result according to the estimated error. The system comprises a model construction unit, a data set construction unit, a model training unit, a data acquisition unit, an initial prediction unit, an error prediction unit and a final output unit. By using the method, high-precision orbit prediction data can be provided for the lunar satellite. The method can be widely applied to the field of satellite orbit prediction.

The invention provides a constellation phase keeping method and device and electronic equipment, and the method comprises the steps: obtaining the mean root semi-major axis of each satellite in a target constellation in a target epoch, and selecting a satellite with the maximum mean root semi-major axis as a reference satellite; and constellation phase keeping is carried out based on the reference satellite. According to the scheme, only a relatively small period difference needs to be adjusted, the overall orbit adjustment amplitude and frequency can be reduced, and then fuel consumption and the complexity of orbit control operation are reduced; the influence of atmospheric resistance on the reference satellite is relatively small, so that the condition that other satellites frequently perform orbit control due to frequent change of the reference satellite orbit can be reduced; constellation configuration confusion caused by instability of the reference satellite itself is reduced in the face of various perturbation force and environment changes; the operation period of the reference satellite is long, the orbit is relatively stable, and too complex orbit change conditions do not need to be considered when an orbit control strategy is formulated, so that an orbit control algorithm and operation are easier to implement.

The invention relates to the technical field of communication security, in particular to a satellite signal tamper-proofing method and system.The satellite signal tamper-proofing method comprises the following steps that a current communication data frame is obtained through a satellite orbit number, a real-time position vector and a timestamp, the data frame is input into a Hadamard integral segment algorithm to execute non-equal-length segment block cutting, a segment block index table is generated, and the segment block index table is stored in a database; recording an initial address bit, a segment block length value and an initial weight bit value; according to the method, non-equal-length cutting is carried out on a data frame through a Hadamard integral segment algorithm, a segment block index table is generated, a weight bit value is recorded, sub-keys and XOR parameters are extracted based on a main key group to execute logic rotation, a dynamic jump path is constructed, the association degree of a shielding area is calculated by combining satellite coordinates and timestamps, risk coefficients are quantified, and risk segment blocks are positioned. A dynamic key is called to generate a re-encryption key through dual linear perturbation, local protection is enhanced through byte-by-byte XOR and complement mapping, and a dynamic cutting, path generation, risk perception and key updating closed-loop mechanism is formed.

The invention provides a precise point positioning method and system based on broadcast ephemeris satellite clock speed forecast, and the method comprises the steps: collecting broadcast ephemeris clock speed data, and filtering the broadcast ephemeris clock speed data through a dynamic sliding window; preprocessing the filtered broadcast ephemeris clock speed data, and removing abnormal state data to obtain preprocessed broadcast ephemeris clock speed data; fitting the preprocessed broadcast ephemeris clock speed data by adopting a linear period combination model and utilizing a least square method to obtain a fitted clock speed model of each satellite, and obtaining a satellite clock speed predicted value based on the fitted clock speed model; according to the satellite clock speed predicted value, user information and satellite information are combined, user equivalent distance measurement errors of a satellite orbit and clock error jump when broadcast ephemeris of each satellite is updated are calculated, the user equivalent distance measurement errors are applied to precise single-point positioning data for calculation and adjustment, and a corrected precise single-point positioning result is obtained.

The invention provides a ground positioning method and device fusing Doppler and pseudo-range of a low-orbit satellite, and the method comprises the steps: collecting pseudo-range observation values and Doppler frequency shift observation values of a plurality of epoch signals through a ground receiver in a transit time period of the low-orbit satellite by employing an enhanced link between the low-orbit satellite and the ground, and obtaining a Doppler frequency shift observation value of the multiple epoch signals; the orbital position, the running speed and the clock error of the low-orbit satellite corresponding to the epoch signal are collected; calculating the position, speed and clock error of the low-orbit satellite at the emission moment of each epoch signal; when the number of the accumulated observation equations reaches a preset threshold value, a fixed weight least square algorithm is adopted to fuse pseudo-range observation values and Doppler information to solve the position of a ground user receiving end; performing post-test residual error test on the calculation result; and if the after-test residual error test is passed, outputting a positioning result.

The invention belongs to the technical field of spaceflight measurement and control and artificial intelligence, and particularly relates to a high-precision low-orbit satellite forecasting method and system, and the method comprises the steps: obtaining the observation data of a low-orbit satellite, and the parameter data of the earth center gravitational force and non-spherical gravitational force perturbation; the method comprises the following steps: decomposing observation data of a low-orbit satellite into long-term trend data, medium-term fluctuation data and short-term change data; constructing a long-term dynamic model, and fitting the long-term trend data and the long-term dynamic model to obtain a long-term fitting result; constructing a medium-term dynamic model, and fitting the medium-term fluctuation data and the long-term dynamic model to obtain a medium-term fitting result; constructing a short-term dynamic model, and fitting the short-term change data with the short-term dynamic model to obtain a short-term fitting result; fusing the fitting results to obtain a satellite orbit state fitting result; and updating parameters of all the dynamic models, and calculating orbit forecast information of the low-orbit satellite. And the orbit forecasting precision of the low-orbit satellite is effectively improved.