707 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 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 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 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.

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 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 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 discloses a multi-target road transportation path planning method and system based on multiple parameters A * and NSGA-II, and belongs to the technical field of road transportation path optimization. The method comprises the following steps: constructing a large-scale road network directed graph structure; establishing a satellite orbit model and a risk distribution model, calculating a dynamic risk value of a roadside, and forming dynamic road network data; a three-stage initialization strategy is adopted to generate an initial population, transportation time and reconnaissance risks are taken as double targets, evolutionary optimization is carried out through an NSGA-II algorithm, and a Pareto optimal path set is output. The system comprises a corresponding road network module, a risk module and a planning module. According to the method, the technical problems of multi-target conflict, low initial population quality and satellite risk avoidance of a traditional method are solved, and the timeliness, the concealment and the algorithm efficiency of path planning are remarkably improved.

The invention relates to the technical field of low-orbit satellite communication, in particular to an orbit optimization method and system for dynamically and autonomously tracking a low-orbit satellite based on a ground station, and the method comprises the steps: collecting TLE orbit element data, constructing an SGP4 orbit prediction model, and obtaining a prediction result; low-earth-orbit satellite orbits with different inclination angles are determined through STK software modeling based on a ground station, and corresponding standard results are obtained; comparing the prediction result with a standard result to obtain an error result; dynamically optimizing the Bstar parameter based on an error result by adopting a genetic algorithm, and determining an optimal Bstar parameter; adjusting the SGP4 orbit prediction model based on the optimal Bstar parameter, and obtaining an optimization result through the adjusted SGP4 orbit prediction model; according to the method, optimization is carried out based on an existing SGP4 model, optimal Bstar parameters are dynamically searched through a genetic algorithm, accumulative errors caused by the fact that TLE data are not updated in time are compensated, stable tracking of a ground station is guaranteed, and the precision of medium and long term orbit forecasting is improved.

The invention discloses a vehicle transportation management system based on Beidou positioning, which belongs to the technical field of vehicle transportation and comprises a Beidou positioning module, a data processing module, a multi-source heterogeneous data fusion module, a vehicle state monitoring module, a data analysis module, a transportation route planning module, a transportation route optimization module and a data report generation module. Through the high-precision positioning function of the Beidou positioning module and in combination with the error correction technology, more accurate vehicle position information can be provided, the accuracy and reliability of transportation are improved, the received data including satellite orbit errors, atmospheric delay errors and the like are processed, the positioning accuracy is further improved, and the positioning accuracy is improved. A comprehensive vehicle running state view is formed by combining Beidou positioning information with a vehicle sensor and an external data source, so that information from different data sources can be compared and analyzed on a common time axis, and the accuracy and effectiveness of data analysis are improved.

The invention relates to the technical field of unmanned aerial vehicle trapping, and discloses an unmanned aerial vehicle trapping method for emitting a navigation deception signal, which comprises the following steps: step 1, generating a navigation deception signal synchronized with the time reference of a satellite navigation system through an atomic clock synchronization mechanism; step 2, injecting dynamically predicted satellite orbit parameters based on the navigation deception signal; 3, subcarrier pseudo-arbitrary frequency hopping control is carried out on the navigation deception signal with the injected parameters; and 4, collecting multi-source data of the radar and the optical sensor, and fusing the multi-source data to generate a motion track of the unmanned aerial vehicle. According to the invention, an atomic clock synchronization mechanism is adopted to generate a high-precision time reference, a technical scheme of dynamic orbit prediction and pseudo-random frequency hopping control is combined, time synchronization with a satellite system is realized through an atomic clock, satellite orbit parameters are dynamically corrected through a long and short-term memory network, and rapid hopping modulation of a subcarrier frequency band is realized. The technical effects of high space-time consistency of deception signals and dynamic disguising of spectrum characteristics are achieved.

The embodiment of the invention provides a low-orbit giant constellation resource management and control method, device and equipment and a medium, and relates to the technical field of low-orbit giant constellation system architecture design. The method comprises the following steps: dividing a constellation operation sky domain into a plurality of sky domain partitions according to a C-60 molecular structure, dividing satellites in each satellite cluster into a main satellite and a plurality of auxiliary satellites at each operation moment, generating a satellite cluster division table of each satellite, and formulating a management rule base, and each satellite operates in orbit according to the stored management rule base and the satellite cluster division table. A low-orbit giant constellation is uniformly divided into a plurality of satellite clusters without omission according to a C-60 molecular structure, so that the pressure of a ground centralized management and control center is relieved, constellation resource management and control and task management distributed deployment are realized, meanwhile, a satellite cluster division table is determined, the in-orbit calculation amount of a satellite is reduced, the task response speed is increased, and the task management efficiency is improved. The method is suitable for the satellite detection task of the low-orbit giant constellation on the time-sensitive moving target.

The focus of the present disclosure relates to a secure global satellite network that securely transmits data from a ground station to one or more geosynchronous orbit satellites within a communicatively linked constellation of geosynchronous satellites. The communicatively linked constellation of geosynchronous satellites covers the entire planet, allowing access to users anywhere on the planet. The communicatively linked constellation of geosynchronous satellites also covers satellites in orbit above the planet, enabling any satellite to send or receive data through the communicatively linked constellation of geosynchronous satellites at any point in the satellite's orbit. The communicatively linked constellation of geosynchronous satellites functions as a communications backbone, enabling global communications coverage between any points on the earth, between any point on the earth and a satellite anywhere in its orbit, or between two satellites anywhere in their orbit.

The invention discloses an aerial target height estimation method based on satellite-borne radar networking. The radar networking is composed of a radar group consisting of two or more satellite-borne radars. The aerial target height estimation method comprises the following steps: step S1: using the radar group to respectively measure the radial distance and azimuth of the aerial target; step S2: using a position calculation model of the aerial target in the radar array coordinate system to calculate the position of the aerial target in the radar array coordinate system by using the least squares method; step S3: calculating the position of the aerial target in the satellite orbit coordinate system according to the position of the aerial target in the radar array coordinate system; step S4: calculating the altitude of the aerial target according to the position of the aerial target in the satellite orbit coordinate system and the radius of the earth where the aerial target is located. The invention establishes an equation group containing unknown variables such as the target altitude, thereby solving the problem that a single satellite-borne detection radar has a large target tracking pitch angle error and is unable to estimate the altitude of the aerial target.

The invention relates to a satellite communication encryption authentication method and system based on a dynamic key. According to the method, network topology is predicted based on satellite orbit parameters, time slices are divided to generate a dynamic key pool, a key is divided into sub-key segments, an encryption key segment set is constructed in a forward association encryption mode, and credible tracing of a key distribution path is realized in combination with pre-distribution path planning and a block chain hash verification mechanism. And the key is recombined through dynamic decryption, and a bidirectional authentication process is carried out. The problems of high key synchronization delay, easy leakage of the pre-distributed key and low verification efficiency in the high dynamic satellite network are solved, the real-time optimization of key distribution, single-point leakage risk isolation and lightweight security authentication are realized, and the forward security and anti-attack ability of a satellite communication link are significantly improved.

The invention discloses a satellite secure transmission optimization method and system based on joint anomaly detection, mainly solving the problem of low end-to-end transmission reliability under the condition of network attack in the prior art, and the implementation scheme comprises the following steps: constructing a time-varying network topology according to constellation configuration; periodically updating a network topology and a satellite neighbor node set according to the law of satellite orbital motion; the network is monitored in real time based on an anomaly detection mechanism, whether the current network is subjected to interference attack and DoS attack is judged in time, and whether the current satellite can safely transmit data is judged; and according to indexes such as node states, link hops, detection precision, node load capacity and link transmission delay, and according to a network topology and a neighbor node set at the current moment, determining a routing control optimization problem, and guiding each satellite to select an optimal transfer satellite along a transmission direction according to an optimal solution to obtain an end-to-end optimal transmission path. The method can actively trigger a detection mechanism to quickly identify abnormal nodes, obtains a safe and reliable end-to-end transmission path, and can be used for a low earth orbit satellite network.