490 results about "Satellite orbit" patented technology

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 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 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 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 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 discloses a multi-beam spatial frequency conflict resolution method which is suitable for a large-scale low-orbit satellite constellation system. According to the method, high-orbit satellites are used as centralized control nodes, orbit states and service requirements of low-orbit satellites in a system are received, and allowable transmission practice windows and required continuous transmission time slot numbers of the low-orbit satellites are analyzed; on the basis, calculating a space intersection area and a potential interference time period between the low-orbit tracks; and aiming at the differentiated transmission requirements, according to a preset orbit priority sequence, sequentially allocating transmission time slot resources to each low-orbit satellite transmission service. According to the invention, the overall perception of a high-orbit satellite on the orbit state and service requirements of a low-orbit satellite, the search and judgment of orbit cross interference beams and time periods, and the comprehensive decision of service transmission time sequence optimization distribution are carried out; the method achieves the effective avoidance of potential same-frequency interference of transmission services of satellites with different orbits in an intersection region in a complex space-time dynamic environment, and remarkably improves the transmission success rate and the overall resource utilization rate of a large-scale low-orbit constellation system.

The invention provides a special high-throughput satellite communication terminal for electric power, and relates to the technical field of electric power communication, and the special high-throughput satellite communication terminal comprises a baseband processing module which is used for carrying out differential encryption processing on different types of electric power data; the high-throughput satellite radio frequency module is used for suppressing sidelobe interference while realizing automatic satellite beam tracking through a beam forming algorithm during satellite communication, and calculating the optimal transmitting power through a self-adaptive power regulation algorithm; the communication transmission module is used for presetting a data priority based on a priority mapping table during data transmission and preempting satellite beam resources according to the data priority; the electric power Internet of Things protocol adaptation layer is used for realizing conversion between an electric power dedicated protocol and a satellite IP protocol, differential coding compression of electric power data and interrupted transmission in a link; and the beam optimization module is used for dynamically optimizing the beam pointing angle based on the satellite orbit parameters and the terminal geographic position. According to the scheme, the coverage degree of electric power communication in remote areas can be improved, and the safety and reliability of data transmission are improved.

The invention provides a satellite communication SoC chip power consumption control method and device, and the method comprises the steps: monitoring the comprehensive operation parameters of all function modules in real time, calculating the power consumption demand through combining the characteristics of a satellite orbit, generating a power consumption control instruction, carrying out the intelligent clock gating and frequency adjustment operation of the function modules, and achieving the power consumption control of the function modules. And finally, accurate distribution control of power consumption is realized. According to the method, real-time optimization management of power consumption can be realized according to dynamic changes of satellite communication services and orbit periodicity characteristics, the in-orbit service life of a satellite is effectively prolonged, and the overall power consumption level is reduced.

The invention relates to an agile satellite visibility analysis method based on an along-longitude push-broom mode, relates to the technical field of satellite task planning and visibility analysis, and solves the technical problem that an existing target visibility analysis method is difficult to accurately reflect a real visibility state in a satellite continuous imaging process. The method comprises the following steps: acquiring an imaging center point coordinate, an imaging duration, satellite imaging parameter information, satellite orbit information and a target shooting period; the visibility of the imaging center point in the shooting period is calculated, division is carried out according to the number of orbital circles, and a visible information set of the center point is obtained. The agile satellite visibility analysis method based on the along-longitude push-broom mode is suitable for efficient visibility calculation of an agile optical remote sensing satellite and oriented to an along-longitude imaging scene, the visibility state of a target in the imaging process can be accurately evaluated on the basis of considering satellite attitude maneuver characteristics and orbit constraints, and the accuracy of the visibility analysis is improved. Therefore, accurate support is provided for task arrangement and resource scheduling.

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

The invention discloses a global ionosphere modeling method based on a spherical radial basis function, and the method comprises the steps: laying Reuter grid points at an interval of 10 degrees on an ionosphere thin layer, and converting the Reuter grid points into a daily fixed geomagnetic coordinate system for modeling. Cycle slip monitoring and abnormal value identification and elimination are carried out on obtained satellite observation data (O file), then a precise satellite orbit position is obtained through interpolation in combination with a precise ephemeris file (SP3), hardware deviation is corrected through differential code deviation (DCB file), an AbBPoisson spherical surface radial basis function is adopted and converted into a 15-order truncated AbBPoisson spherical surface radial basis function, and finally, a precise satellite orbit position is obtained. The bandwidth is set to be 0.25, L2 regularization optimization is used, parameters of a radial basis function are solved through a least square method, and therefore global ionosphere modeling is carried out. Different from a traditional spherical harmonic function method, the abbeposon spherical radial basis function controls the control range of a radial base point by adjusting the bandwidth, higher precision can be provided in a data-intensive area, and the adaptability is higher.

The invention discloses a high-precision beam alignment method for an Internet of Vehicles ground-non-ground converged communication system and a vehicle-mounted communication terminal, and belongs to the technical field of cellular and satellite converged communication. A two-stage control strategy of'coarse tracking + fine tracking 'is adopted. The method comprises the following steps: firstly, based on GNSS / INS fusion positioning and satellite orbit prediction (SGP4 model), quickly calculating and finishing initial coarse alignment of a wave beam; and then, constructing a local beam scanning window, collecting received signal intensities (RSSI) in multiple directions as observed values, introducing an extended Kalman filter (EKF) algorithm, and establishing a state space model for recursive estimation, thereby realizing high-precision and dynamic closed-loop optimization and tracking of a beam pointing angle. According to the invention, the speed and the precision of beam alignment are obviously improved, the anti-interference capability and the link stability of the system in a dynamic environment are enhanced, and the continuous communication service in the sky-ground fusion Internet of Vehicles is effectively guaranteed.

The invention provides a low-orbit navigation enhanced satellite orbit and clock error integrated determination method, which comprises the following steps that: a low-orbit navigation enhanced satellite carries a GNSS (Global Navigation Satellite System) receiver, can receive a multi-system GNSS satellite navigation signal and can issue a navigation enhanced signal at the same time, a downlink signal and a satellite-borne GNSS receiver clock share the same source, and a deviation exists between the clock error and the clock error of the satellite-borne receiver; the satellite-borne observation data of the low-orbit satellite, the GNSS of the ground station and the observation data of the low-orbit satellite are fused, an observation model for fusion processing is given, and the orbit of the low-orbit navigation enhanced satellite, the receiver clock error and the downlink signal time delay deviation are integrally determined. Unified adjustment and parameter joint calculation of satellite-borne and downlink observation values of the low earth orbit satellite are realized.

A weather data assimilation assistance device includes a wet delay calculator and a wet delay variance calculator. The wet delay calculator calculates a wet delay in a satellite line-of-sight based on observable data indicating an observable of a radio wave from a positioning satellite measured by a receiver to receive the radio wave from the positioning satellite and based on atmospheric delay data indicating an atmospheric delay in the satellite line-of-sight calculated based on a correction value for at least one of a satellite clock or a satellite orbit of the positioning satellite, and outputs data indicating the wet delay. The wet delay variance calculator calculates a variance of the wet delay based on the wet delay and a covariance matrix of the correction value for at least one of the satellite clock or the satellite orbit, and outputs data indicating the variance of the wet delay.

The invention discloses a satellite-ground fusion network MPQUIC data packet transmission scheduling method, which comprises the following steps: adopting a real-time path index cache and sliding time window mechanism to measure the round-trip time and packet loss rate of a satellite and a ground path in real time so as to obtain the instantaneous quality state of the path; a comprehensive path scoring model combining the bandwidth, the buffer area utilization rate, the round-trip delay and the packet loss rate is constructed, an award factor and a penalty factor are dynamically adjusted, and a current optimal transmission path is adaptively selected; a switching event of a satellite link is predicted based on satellite orbit data, and data packet transmission of the path is skipped in advance. According to the method, the problems caused by path isomerism and high dynamics in the satellite-ground convergence network are solved; according to the invention, higher throughput and lower flow completion time can be realized, and the transmission stability is greatly improved.

The invention discloses a low-orbit satellite joint frequency offset estimation and channel equalization method in a high-speed moving scene, which comprises the following steps of: constructing a dynamic coupling state space model to realize joint estimation of frequency offset and channel parameters; associating a frequency offset change rate with the dynamic change of multipath time delay through a state transition equation; the association is based on relative motion parameters and radio wave propagation characteristics of the satellite and the mobile terminal; according to the method, state estimation is carried out by adopting a filtering algorithm, channel multipath sparsity constraint is introduced into the filtering algorithm, and satellite orbit parameters and navigation data of a mobile terminal are fused to serve as priori information, so that joint estimation of frequency offset and channel parameters is realized through a dynamic coupling state space model; the problem of parameter error accumulation in traditional separated processing is solved, and the estimation precision is improved; a pilot frequency-data dual-drive mechanism is combined with time-frequency orthogonal pilot frequency and data feedback, and the estimation real-time performance and the dynamic adjustment capability of the equalizer are both considered.

The invention provides a high-precision satellite tracking method and system, a storage medium and electronic equipment. The high-precision satellite tracking method comprises the steps of setting at least one tracking time period of a to-be-tracked target satellite; predicting observation data of the target satellite in the tracking time period, wherein the observation data comprises satellite orbit data and satellite transit data of the target satellite; based on the observation data, tracking parameters of the target antenna for tracking the target satellite are calculated, and the tracking parameters comprise the orientation and the pitching angle of the target antenna; adjusting tracking parameters according to a preset stride, and monitoring a beacon signal of a target satellite in real time; and under the condition that the beacon signal of the target satellite is monitored to reach the optimal signal condition, controlling the target antenna to track the target satellite according to the currently adjusted tracking parameter. By applying the method provided by the invention, the tracking parameters of the antenna are calculated, and the tracking parameters are dynamically adjusted in combination with the real-time beacon signals of the satellite, so that accurate tracking of the satellite is realized.

The invention discloses a satellite clock error resolving method considering signal distortion deviation, and belongs to the technical field of satellite navigation and positioning. According to the method, a signal distortion deviation parameterization model is constructed, and the satellite clock error and the signal distortion deviation are solved in a combined mode. The method specifically comprises the following steps: selecting a global or regional reference station network to obtain double-frequency observation data; classifying the receivers and unifying the distortion delay of the same kind of signals; and introducing signal distortion deviation modeling based on an ionosphere elimination combination observation equation, combining precise satellite orbit data, and resolving satellite clock correction and signal distortion deviation parameters through least square or Kalman filtering adjustment. When a terminal user uses a satellite clock error product for positioning, the terminal user can directly use or dynamically estimate the signal distortion deviation according to the type of a receiver, and the positioning precision is improved. By compensating the system error, the limitation that the signal distortion deviation is not modeled in the traditional method is solved, the satellite clock error is accurately estimated, and reliable support is provided for high-precision positioning, navigation and time service.

The invention discloses an anti-interference unmanned aerial vehicle cellular edge removal computing resource allocation method in an air-space-ground integrated network, which comprises the following steps of: firstly, constructing an air-space-ground integrated network architecture comprising a low-orbit satellite, an unmanned aerial vehicle cluster and a ground user, and establishing satellite interference space distribution mapping based on a satellite orbit and an interference measurement result; and then adopting a user-centered dynamic clustering strategy, combining with a large-scale fading coefficient and interference intensity, adaptively selecting a cooperation cluster scale and member composition, and forming an unmanned aerial vehicle cooperation cluster. Then establishing an uplink communication model of an explicitly introduced satellite direct-connected user co-frequency interference term, and on the basis, constructing a three-section end-to-end time delay model comprising wireless transmission time delay, parallel computing time delay and forward pass and backhaul time delay related to a cooperative cluster scale and a quantization bit number; according to the method, the cooperative cluster scale and the quantization bit number are used as time delay optimization variables together, controllable optimization of end-to-end time delay is achieved, the propulsion energy consumption of the unmanned aerial vehicle is considered, and therefore the unloading efficiency and the overall energy efficiency of the cellular edge removal computing system are improved.

The invention discloses a low-orbit satellite Doppler frequency offset pre-compensation dynamic optimization algorithm, which comprises the steps of multipath signal separation and path identification: identifying a line-of-sight path and at least one non-line-of-sight reflection path through power delay spectrum analysis of satellite receiving signals, wherein the signal power of the non-line-of-sight reflection path is not lower than-10dB of the line-of-sight path power; and reflection path geometric parameter extraction: based on time delay information of each path in the power time delay spectrum, reversely deducing propagation distances corresponding to a line-of-sight path and a non-line-of-sight reflection path, calculating a direct distance between the satellite and the terminal and a total distance of a reflection path from the satellite to a reflection point and then to the terminal by combining satellite orbit parameters and real-time position information of the terminal, and calculating geometric parameters of the reflection path. According to the method, the multi-path scene compensation precision is improved, the limitation that only the sight distance path is compensated traditionally is broken through by independently identifying the non-sight distance reflection path and establishing the exclusive frequency offset model, the frequency offset superposition error caused by multi-path propagation is solved, and the demodulation error rate in a complex environment is remarkably reduced.

The invention relates to the technical field of satellite wireless laser communication, particularly provides an initial pointing method for a satellite-borne laser communication terminal, and aims to solve the problems that in the prior art, the calculation process occupies time, and the initial pointing effect of the laser communication terminal becomes poor. In order to achieve the purpose, the satellite-borne laser communication terminal initial pointing method comprises the following steps that six orbital elements of two satellites are obtained; calculating a predicted mean anomaly of the satellite at the aiming moment of the laser communication terminal; the true anomaly of the satellite at the aiming moment of the laser communication terminal is calculated; respectively calculating position vectors of the two satellites in a satellite orbit coordinate system based on the true anomaly of the two satellites; calculating a pitch angle and an azimuth angle of the laser communication terminal; and controlling the laser communication terminal to steer based on the pitch angle and the azimuth angle. Compared with the prior art that delay needs to be calculated firstly and then compensation needs to be performed, the time consumed by calculation is reduced, and the initial pointing precision is remarkably improved.

Method, electronic device, system, and computer-readable medium embodiments are disclosed. Some embodiments include a signal processing workflow incorporating a graphical user interface for displaying orbital information for satellites and other spacecraft. In some embodiments, a generative adversarial network (GAN) is employed for evaluating satellite orbital positions, for predicting future orbital movements, for detecting orbital maneuvers of a satellite, and for analyzing such maneuvers for potential nefarious intent.

The application provides an orbit transfer strategy optimization method and system for a large-ellipse frozen orbit satellite orbiting, comprising the following steps: acquiring a satellite-rocket separation orbit and a station parameter, calculating an elevation angle of the satellite and the station, and then determining a range of a true anomaly angle of pulse ignition meeting a measurement and control requirement; in combination with the range of the true anomaly angle of pulse ignition, generating a fuel most-probable pulse orbit change strategy of the satellite from an initial orbit to a target orbit, determining an orbit change speed increment, an ignition position and an ignition frequency; determining ignition-on and ignition-off conditions of each orbit change and a drift circle number between adjacent two orbit changes; according to the pulse orbit change strategy, respectively determining an initial value of an ignition time length, an ignition time and a thrust direction of each orbit change, and determining the final ignition time length, the ignition time and the thrust direction of each orbit change. The application adopts a non-apogee double-pulse orbit change strategy to design a fuel optimal orbit transfer strategy of a large-ellipse frozen orbit satellite orbiting, and solves the design method problem of the orbit transfer strategy.

The invention relates to an interferometric synthetic aperture radar (InSAR)-based measurement method and system, and the method comprises the steps: determining the prior positions of a plurality of targets, and providing the prior positions to a ground processing unit; shooting an area where a plurality of targets are located by using an SAR satellite, and sending the obtained data to a ground processing unit; determining a phase difference between the targets for a single shot of the target; according to the determined phase difference and the SAR load wavelength, the slope distance between the targets is calculated through a ground processing unit; according to the slope distance and the satellite orbit information, the position relation between the targets is determined through a ground processing unit. The measuring system at least comprises a ground processing unit and an acquisition unit. According to the invention, shooting at the same track inclination angle and different track inclination angles can be realized, the limitation of heavy track shooting conditions in the prior art is broken through, and high-frequency and high-precision surface micro deformation measurement can be realized for different application scenes.

The invention discloses a time-frequency offset tracking method in a Tiantong satellite monitoring low-orbit satellite system, which belongs to the field of satellite communication, and comprises the following steps: acquiring satellite orbit information, satellite ephemeris information and positioning information of a low-orbit satellite, and resolving current Doppler frequency offset information; performing frequency pre-compensation according to the Doppler frequency offset information, and performing compensation by using the frequency offset captured by the FCCH; the satellite-borne terminal receiver carries out carrier frequency estimation by using a downlink channel, so that the carrier residual frequency difference of a received signal is estimated, and frequency correction is carried out; starting downlink timing tracking; uplink frequency offset compensation is started, so that the frequency of a signal from the low-orbit satellite to the Tiantong satellite is the expected carrier frequency of the Tiantong satellite; and carrying out transmission timing correction by adopting the spaceborne terminal timing drift rate, and carrying out uplink timing adjustment. According to the method, normal access and stable data transmission of the satellite-borne terminal can be realized.

The invention relates to the technical field of satellite orbit extrapolation rapid calculation, and discloses a satellite orbit extrapolation rapid calculation method and system based on a low-performance chip, and the satellite orbit extrapolation rapid calculation method based on the low-performance chip comprises the steps: constructing a simplified satellite orbit calculation model based on main perturbation force; carrying out state vector integration by adopting an optimized fourth-order Runge-Kutta integrator; calculating main perturbation acceleration; the main perturbation acceleration is uniformly converted into a J2000 coordinate system through coordinate system conversion, the total perturbation acceleration is synthesized in the J2000 coordinate system, and a six-dimensional state derivative function is constructed; performing cyclic integration on the six-dimensional state derivative function to update the state vector until the target extrapolation time is reached; outputting the state vector of the satellite at the target moment as a forecast result; according to the method, the optimized fourth-order Runge-Kutta integrator is adopted, so that the calculation complexity is reduced, and the orbit extrapolation calculation can be efficiently executed on a low-performance chip.

The invention belongs to the technical field of communication satellite measurement and control technologies, and provides a satellite measurement and control system based on multi-modal fusion, which comprises a multi-modal signal fusion module used for receiving measurement and control data, fusing information from a plurality of signal sources, carrying out data time and space alignment and establishing a state estimation equation for prediction, outputting accurate satellite state data; the intelligent orbit prediction module is used for predicting the orbit of the satellite in real time and calculating the future change of the satellite orbit according to the received satellite state data and external information; the satellite control module is used for controlling and adjusting the orbit and attitude of the satellite in real time, and running the satellite according to the preset orbit and attitude through monitoring and control; and the task planning and instruction scheduling module is used for planning and scheduling satellite tasks, generating corresponding instructions according to task requirements, and reasonably allocating resources by scheduling and evaluating various indexes of satellites so as to enable the instructions to be executed on time.

The invention discloses a satellite orbit kilometer post parameter prediction method and device, equipment and a medium, and relates to the technical field of satellite data processing. The method comprises the following steps: converting longitude and latitude in satellite positioning data into UTM coordinates; vector projection is carried out on the UTM coordinates on the line segments, and kilometer posts of all key position points are determined; performing multi-time-step lagging feature splicing and differential processing on the satellite positioning data and the kilometer post respectively, generating final feature matrixes of the satellite positioning data and the kilometer post at each key position point, and performing robust standardization; training the double-layer long-short-term memory network to obtain a kilometer post prediction model; and inputting the satellite feature sequence of the to-be-measured position point on the railway track section into the kilometer post prediction model, and outputting the kilometer post of the to-be-measured position point on the railway track section. According to the method, the accuracy of kilometer post parameter prediction can be effectively improved.