119 results about "Satellite technology" patented technology

The invention relates to the technical field of low earth orbit satellites, and discloses a method and equipment for improving the signal-to-noise ratio of a low earth orbit satellite signal, and the method comprises the steps: carrying out the multi-dimensional signal collection and processing of a received signal of a low earth orbit satellite downlink, and obtaining a signal tensor model; executing structured decomposition based on the signal tensor model to obtain a channel factor matrix group; performing multi-stage sequential processing according to the channel factor matrix group to obtain low-orbit satellite channel state information; inputting the low-orbit satellite channel state information into an interference identification module for feature extraction and interference type analysis to obtain an interference type and probability distribution thereof; performing multi-dimensional adaptive filtering on the received signal to obtain a target signal; and performing modulation coding and beam forming parameter joint optimization on the target signal and the low-earth-orbit satellite channel state information to obtain a low-earth-orbit satellite communication link, thereby solving the problem of large fluctuation of the signal-to-noise ratio in a satellite rapid moving scene, and realizing balance of power efficiency and anti-interference performance at the same time.

The invention relates to the technical field of satellites, and discloses a virtualization and distribution-based satellite network simulation method and system, which are applied to a satellite network simulation system, and the system comprises a main node and working nodes; the method comprises the following steps: receiving new satellite group topology information sent by the upstream through the main node; determining a corresponding target instruction through the main node based on a comparison result of the new satellite group topological information and pre-stored historical topological information; executing a corresponding simulation task through the working node based on the obtained target instruction; and updating the current state of the star group through the main node based on the obtained execution result feedback of the simulation task. According to the technical scheme provided by the invention, the construction cost of a simulation environment can be reduced, the network simulation efficiency can be improved, and further, larger-scale satellite network simulation can be borne.

The invention of system of observation and monitoring the earth warming and changes in polar ice behavior using LoRa to satellite technology is a system for measuring, observing and monitoring weather and environmental conditions in order to determine the effects of environmental conditions and climate changes on the way ice masses change in the polar regions of the earth. This invention is related to the rocket equipped with several modules for measuring the conditions of the surrounding environment as well as data transmission through the LoraWan protocol to a fixed or deployable station. Also, in this invention, if there is a need to calibrate any of the modules in the meteorological rocket, the central server structure, which is equipped with an artificial intelligence analyzer, can calibrate the device by comparing the arrays received from the surrounding rockets and analyzing the data received from these systems.

The invention relates to the technical field of satellite positioning, and discloses an emergency rescue method and system based on satellite positioning, and the method comprises the steps: obtaining the real-time information of a region and the function information of an emergency unit, dispatching a satellite to carry out image collection and signal linkage, analyzing a satellite image and signal data, and constructing an emergency rescue real-time model; a multi-search scheme is formulated according to the model and issued to each emergency rescue unit, search work is executed, the rescue scheme is dynamically adjusted according to feedback information, and a cyclic execution mechanism is formed. According to the method, real-time and accurate data support is provided through the satellite technology, the efficiency, accuracy and strain capacity of emergency rescue are improved, and the rescue efficiency is improved. Rapid and effective disaster area rescue is ensured, and the problem of poor linkage between a satellite and a ground unit in emergency rescue in the prior art is solved.

The embodiment of the invention provides a bridge monitoring satellite data quality control method based on signal-to-noise ratio grid comparison, and belongs to the technical field of satellites. The method comprises the following steps: carrying out pseudo-range single-point positioning calculation according to an observation value file and a broadcast ephemeris file to obtain observation data of each satellite; performing grid division on the satellite sky map according to a preset elevation angle interval and an azimuth angle interval to obtain a standard grid; on the basis of a standard grid, independently stacking observation data of each observation station to obtain a signal-to-noise ratio grid model corresponding to each observation station; performing preferential fusion according to the signal-to-noise ratio grid models of all the observation stations to obtain a high-quality grid model; performing data comparison on the signal-to-noise ratio grid model of each observation station and the high-quality grid model to obtain an available data area of each observation station; and performing quality control on the current observation data according to the available data area to obtain high-quality data. According to the invention, the observation area which is not subjected to interspersed shielding interference can be identified, and data quality control is realized.

The invention provides a memory error simulation method and device based on a satellite-borne intelligent computing system, a medium and a simulator, and relates to the technical field of satellites. The method comprises the following steps: inputting a deep learning neural network engine into a deep learning reasoning program of a satellite-borne intelligent computing system; executing a deep learning reasoning program to read a process page table; based on the DRAM standard file, the DRAM mapping file and the address mapping relation, determining a memory active area of the deep learning neural network engine in the virtual memory model; performing construction processing on the memory active area, constructing an error injection space represented in a bitmap tree form, and determining an error information injection position in the error injection space according to particle flipping error model information and a Monte Carlo random algorithm; and performing reverse translation processing on the physical address in the virtual memory model, and determining a target virtual address of the deep learning reasoning process. And a single-particle upset memory error and a multi-particle upset memory error caused by space radiation can be effectively simulated.

The invention discloses a GNSS satellite elastic power real-time detection method and system based on multi-frequency data, and belongs to the technical field of global navigation satellites. The method comprises the following steps: acquiring satellite signal carrier-to-noise ratio data, satellite multi-frequency observation data and satellite ephemeris; calculating a satellite power adjustment monitoring index according to the satellite signal carrier-to-noise ratio data, judging whether the satellite power is adjusted or not according to the satellite power adjustment monitoring index and a preset threshold value, and obtaining the satellite power adjustment time when the satellite power is adjusted; calculating MP combined observation values of different observation codes according to the satellite multi-frequency observation data, and judging the type of satellite power adjustment according to the MP combined observation values when the satellite power is adjusted; and when the satellite power is adjusted, calculating the influence range of the satellite power adjustment according to the satellite ephemeris and the satellite power adjustment time.

The invention relates to the technical field of satellites, in particular to a three-super platform actuator eddy current sensor fault autonomous reconstruction method. Comprising the following steps: according to a parallel mechanism kinematics relationship of each actuator, determining a first relationship between axial displacement measured by an actuator eddy current sensor and a load relative to a six-degree-of-freedom pose of a satellite platform; determining a parallel mechanism kinematics relationship of the fault-free eddy current sensor, and determining a second relationship between the axial displacement and the load measured by the fault-free eddy current sensor and the six-degree-of-freedom pose of the satellite platform; according to the first relation and the second relation, matrix reconstruction is carried out on the remaining fault-free actuator eddy current sensors, and an autonomous reconstruction matrix is obtained; and according to the autonomous reconstruction matrix and the measurement of the fault-free actuator eddy current sensor, obtaining all actuator eddy current measurement values of the actuator where the fault eddy current sensor is located. According to the method, when the eddy current sensor has a fault, the eddy current sensor distribution array is reconstructed, and three-super control is recovered.

The present invention relates to the technical field of communications, and provides a 6G space-air-ground-sea integrated fusion architecture based on software-defined cloud-edge collaboration, comprising: three tiers of cloud nodes from low to high: an edge cloud, a space-based cloud, and a core cloud; the edge cloud comprises 6G-enabled ships based on software-defined networking and mobile edge computing technologies; the space-based cloud comprises low earth orbit satellites based on software-defined satellite technology and low earth orbit satellite constellations connected by means of an inter-satellite link; the core cloud comprises a space-based 6G core network; the edge cloud, the space-based cloud, and the core cloud follow a task offloading mechanism and an information feedback mechanism; the task offloading mechanism is configured to select, on the basis of characteristics of a task, a cloud node of a target tier for task processing; and the information feedback mechanism is configured such that the cloud node of the upper tier sends feedback information to a cloud node of the lower tier, so as to optimize task processing of the lower tier. The present invention achieves fast and flexible networking for a 6G space-air-ground-sea integrated fusion network, thereby realizing efficient utilization and collaborative management and control of resources.

The present invention discloses a low-orbit satellite communication link switching system based on machine learning, which belongs to the field of low-orbit satellite technology and includes: a data collection module, configured to collect real-time data of low-orbit satellite communication links; a data processing module, configured to process real-time data of low-orbit satellite communication links; a model training module, configured to predict changes in the quality of low-orbit satellite communication links and determine the prediction results of the quality of low-orbit satellite communication links; a switching decision module, configured to select the best switching time and target satellite according to the prediction results; and a switching execution module, configured to optimize the switching process of low-orbit satellite communication links. The present invention solves the problem that the existing low-orbit satellite communication links cannot be effectively switched based on machine learning, resulting in low continuity and stability of satellite communications. The present invention can achieve accurate prediction of link status and precise grasp of switching timing, reduce the number of link switching times, and improve communication continuity and stability.

The invention provides an adjacent satellite adjusting method and device based on satellite damage reconstruction, and relates to the technical field of satellites, whether a target satellite is damaged or not is judged according to telemetry data of the target satellite, and if it is judged that the target satellite is damaged, the adjacent satellite is adjusted according to a preset double-row element and an orbit model. Determining the real-time position data of the target satellite and the real-time position data of the adjacent satellites of the target satellite according to the real-time position data of the target satellite, the double-row element number of the target satellite and the double-row element number of the adjacent satellites of the target satellite; determining a mean anomaly change value required by the adjacent satellite to move from the current position to the target position, updating the number of double rows of the adjacent satellite according to the mean anomaly change value, and adjusting the orbit position of the adjacent satellite based on the updated number of double rows; according to the method, satellite damage reconstruction can be quickly realized at low cost through adjacent satellite adjustment.

A user equipment (UE) performs a public land mobile network (PLMN) scan for a higher priority PLMN, and reports a list of candidates PLMNs based on the scan. An identity of a first one of the candidate PLMNs includes a shared mobile country code (MCC). The shared MCC has a value between 900 and 999 and is also used for performing access with satellite technology. The UE selects the first one of the candidate PLMNs from among the list of candidate PLMNs. Each of the candidate PLMNs has either a mobile country code (MCC) the same as an identity of a serving PLMN or the shared MCC, when the identity of the serving PLMN does not comprise the shared MCC. The selecting is based on the first one of the candidate PLMNs having a higher priority than the serving PLMN.

The embodiment of the invention provides a data processing method and device and electronic equipment, and relates to the technical field of satellites.The method comprises the steps that star sensor data obtained by collecting spacecraft attitude information through a star sensor and gyroscope data obtained by collecting spacecraft attitude information through a gyroscope are obtained and comprise data from the k-n moment to the k moment; carrying out fusion and linear interference filtering processing on the data of the star sensor and the gyroscope at each moment by using Kalman filtering to obtain preliminary prediction data of attitude information, and calculating a first residual value of the data of the star sensor; the star sensor data, the gyroscope data and the first residual value from the k-n moment to the k moment are input into the trained LSTM network, a second residual value of the preliminary prediction data at the k moment is predicted, and the second residual value represents an error of nonlinear interference; and compensating the second residual value to the preliminary prediction data to obtain attitude information of the spacecraft at the moment k. According to the embodiment of the invention, the error of spacecraft attitude information acquisition is reduced.

The application provides a satellite splicing imaging posture maneuver angle error correction method and related device, and relates to the technical field of satellites. A plurality of ground imaging points are acquired, and then actual posture angles of the satellite pointing to each ground imaging point are obtained respectively; and simulation posture angles of the satellite pointing to each ground imaging point obtained by using a satellite simulation tool are obtained respectively. Finally, based on the actual posture angles and the simulation posture angles of each ground imaging point, a posture angle deviation mean value is obtained. In this way, the posture angle error of the collected remote sensing image can be corrected based on the real-time flight state of the satellite using the posture angle deviation mean value, so that deviation of the collected remote sensing image is avoided.

The present invention discloses a method, device, medium, and system for autonomous power consumption optimization of a transit satellite payload. These methods, which pertain to the field of satellite technology, include an autonomous entry / exit decision process, which rapidly determines the entry / exit status of a satellite payload by calculating distance. This process adapts to the impact of changes in orbital altitude after a satellite orbit change. The transit payload autonomously calculates the satellite's exit and entry delays, and, in conjunction with the satellite's energy management unit, enables autonomous shutdown of the transit payload while it is operating outside the country and autonomous startup before entering the country, thus saving energy consumed by the transit payload during standby operation outside the country. The present invention can address the issue of satellite energy shortages and promote satellite development and application.

The invention provides a terminal equipment positioning method and device based on a satellite direct connection network, and relates to the technical field of satellites. The terminal equipment positioning method based on the satellite direct connection network comprises the following steps: acquiring target communication signaling at a plurality of moments from the satellite direct connection network; according to the target communication signaling at the multiple moments, extracting position clues of the terminal equipment at the multiple moments; acquiring track point information of satellites which correspond to the multiple moments and provide satellite direct connection network services; and determining the position information of the terminal equipment according to the position clues at the multiple moments and the track point information of the satellite at the multiple moments. The satellite network can be directly connected through the terminal device, and a terminal device positioning function is provided for a user.

The invention relates to the technical field of power grid mountain fire monitoring and early warning, and provides a power grid mountain fire monitoring and early warning method, system and device based on a satellite technology, which can improve the power grid mountain fire monitoring and early warning efficiency. The method comprises the following steps: preprocessing multiband satellite remote sensing real-time data; based on the preprocessed multi-band satellite remote sensing real-time data, determining a multi-band satellite remote sensing real-time image containing the real-time distribution condition of the mountain fire points; superposing the multiband satellite remote sensing real-time image and the power grid facility distribution map, and determining the power grid facility influenced by the forest fire in real time; and determining an emergency response plan of the power grid facility influenced by the forest fire based on the forest fire point risk level.

The application discloses a stackable aluminum extrusion profile frame satellite structure, and relates to the technical field of aerospace satellites, comprising: at least one stackable sub-frame; each stackable sub-frame comprises: a plurality of L-shaped extrusion forming structures, a plurality of outer wall plates and an inner partition plate; wherein each outer wall plate is composed of a plurality of I-shaped extrusion forming structures; the inner partition plate is composed of a plurality of I-shaped extrusion forming structures; when the stackable sub-frames are multiple, two adjacent stackable sub-frames are modularly stacked by aligning and splicing the upper end and the lower end of the L-shaped extrusion forming structures at the corresponding positions, and the lower end of the L-shaped extrusion forming structure of the upper stackable sub-frame is adaptively connected with the upper end of the L-shaped extrusion forming structure of the lower stackable sub-frame. The application can improve the mechanical bearing performance of the satellite structure, effectively improve the space utilization rate of the launch vehicle fairing, and realize the mixed stacking of satellite structures of different models, thereby meeting the installation requirements of equipment of different sizes.

The utility model discloses a sliding unfolding device for a micro-nano satellite, and relates to the technical field of satellites. According to the technical key points, the satellite comprises a satellite main body, solar wing plates are hinged to the opposite sides of the satellite main body respectively, and elastic driving pieces are arranged at the joints of the solar wing plates and the satellite main body; a telescopic supporting unit is installed in a shell of the satellite body, the top of the supporting unit is connected with a horizontal linkage rod, and the two ends of the horizontal linkage rod are slidably connected with the shell of the satellite body in the vertical direction. The two ends of the horizontal linkage rod are each provided with a clamping head, and the two solar wing plates are each provided with a clamping groove. An adjusting unit capable of controlling the position of the horizontal linkage rod at the top of the supporting unit in the vertical direction is arranged on the upper side of the middle position of the horizontal linkage rod. According to the unfolding device, the solar wing plate can be rapidly unfolded according to needs, and components in a satellite can be effectively prevented from being damaged by high temperature when the unfolding device is used.

The present application relates to the technical field of satellite, in particular to a kind of solar elevation angle calculation method of multi-view axis reference.The view axis is executed for each view axis, and reference coordinate system of view axis is constructed;According to the current attitude of the satellite carrying the view axis and the reference coordinate system of the view axis, the attitude of the view axis under the reference coordinate system is calculated;According to the scaling matrix of the earth ellipsoid under the inertial system, the satellite position vector under the inertial system, the attitude of the view axis under the reference coordinate system, the conversion matrix from the inertial system to the orbital system and the earth radius, the distance vector from the center of the earth to the view axis pointing point in the inertial system is determined;According to the distance vector from the center of the earth to the view axis pointing point in the inertial system, the scaled vector from the center of the earth to the view axis under the inertial system and the unit vector of the sun under the inertial system, the solar elevation angle of the view axis pointing point is determined.The present application can simultaneously accurately calculate the solar elevation angle for multi-view axis reference.

The invention relates to the technical field of satellites, and provides a task planning method and device for networking of a satellite and a ground station, an Internet of Things system, a storage medium and a computer program product, and the method comprises the steps: obtaining a task planning time period when the satellite and the ground station need to be networked, and obtaining ephemeris orbit prediction information of the task planning time period; according to ephemeris orbit forecast information, based on a genetic algorithm, designing a task planning algorithm for coverage optimization of an Internet of Things system for networking of satellites and ground stations; and the designed task planning algorithm is utilized to perform coverage optimization on the Internet of Things system with the networked satellite and ground station so as to improve the duration of the Internet of Things system capable of being connected with the satellite in the target area of the ground station. According to the scheme, a task planning algorithm oriented to coverage optimization of the satellite Internet of Things can be designed, coverage optimization is carried out on the satellite Internet of Things by using the task planning algorithm, the time length of the Internet of Things system capable of being connected with the satellite in the target area is prolonged, the accuracy of task planning is improved, and the coverage range is expanded.

The invention discloses a satellite low-brightness design and analysis method based on a satellite thermal control model, and belongs to the technical field of satellites. The method comprises the steps of task analysis, star catalogue thermal control low-brightness design, satellite thermal control-brightness analysis integrated modeling, thermal control feasibility analysis, satellite brightness analysis based on a thermal control model, index satisfaction degree analysis and the like. At present, a theoretical calculation method of a simplified model is generally used for brightness analysis of a satellite, and can not be effectively iterated and updated in time according to a thermal control star catalogue design condition of the satellite. According to the design and analysis method, the thermal control design and the brightness design and analysis of the satellite are integrated, and the low-brightness design is realized while the thermal control design is performed; and establishing an analysis model with unified thermal control and brightness analysis, and carrying out statistical analysis of the satellite brightness based on thermal analysis model data. According to the method, the satellite low-brightness design and the thermal design are organically combined, and the efficiency and the accuracy of the brightness design are improved.

The present invention relates to the field of satellite technology, and specifically discloses an optimization deployment method and system for a low-earth orbit large-scale satellite constellation. The method includes: S1, constructing a constellation deployment network model according to the low-earth orbit large-scale constellation, satellite parameters and carrier vehicle parameters; S2, establishing an objective function of multivariable mixed-integer optimization based on the information contained in the nodes and edges of the constellation deployment network model; S3, determining the restricted master problem RMP and sub-problems of the objective function, and solving the RMP through the column generation algorithm to obtain the objective value and dual variables; S4, when there is a new column in any sub-problem, and adding the new column to the RMP makes the objective value decrease, adding the new column to the RMP to update the objective value and dual variables; S5, when there are no new columns in all sub-problems, or adding all new columns to the RMP cannot make the objective value decrease, directly outputting the satellite launch deployment plan or outputting the satellite launch deployment plan after solving for the integer objective value according to the branch and bound method.

The application relates to a high-reliability cryocooler micro-vibration insulation system and belongs to the technical field of satellites; a support Dewar is installed on the upper surface of a cold finger flange; a coupling substrate is placed on the top of the support Dewar; the top end of a support column is connected with the coupling substrate, and the bottom end is connected with the cold finger flange; a pyrotechnic cutter and a conductive sensor are arranged on the support column; a detector Dewar cover is installed on the coupling substrate; a splicing substrate is installed on the coupling substrate; a detector device is installed on the splicing substrate; a cryocooler cold head extends into the inner cavity of the support Dewar from the bottom of the cold finger flange; a flexible cold chain is arranged on the top of the cryocooler cold head and is connected with the coupling substrate; a vacuum pump is in communication with the detector Dewar; a water cooler is in communication with the cold finger flange; the application can not only guarantee that the launch section effectively supports the detector assembly but also guarantee that the support end and the detector assembly are physically isolated during the in-orbit period, so that the micro-vibration generated by the cryocooler during in-orbit work is insulated from the detector.

The invention discloses a stripe layout method based on an artificial potential field and electronic equipment, and belongs to the technical field of satellites. The method comprises the following steps: determining a middle latitude line corresponding to a large area according to vertex latitude and longitude coordinates of the large area; determining a plurality of strips according to the plurality of time windows corresponding to the large area, and determining an initial state corresponding to each strip; mapping the position of each strip to the middle latitude line, and calculating the resultant force of each strip; and moving each strip according to the resultant force of each strip, and obtaining a strip layout result. According to the method, the relative positions of all strips are dynamically and globally adjusted through an artificial potential field method, large-area strip layout is achieved, the strip layout efficiency is improved, and the calculated amount and time consumption are reduced.

The invention discloses a satellite-borne computer device based on a D2000V processor, and belongs to the technical field of satellites. Comprising a processor module, a control module, a storage module, a power module and an external interface module. The processor module adopts a Feiteng D2000V processor to form a minimum hardware system for CPU (Central Processing Unit) operation of the processor; the control module adopts an anti-fuse type or Flash type FPGA (Field Programmable Gate Array) to realize a control management function, and mainly comprises health management functions such as remote control and telemetering information processing, program reconstruction management function, storage channel selection, CPU (Central Processing Unit) start control, CPU on-orbit operation state management, fault diagnosis and the like; the storage module realizes a program storage function of the processor and adopts a multi-redundancy physical backup form, the power supply module realizes input power supply conversion and provides a basic power supply function for the spaceborne computer device, and the external interface module realizes external information interaction of the spaceborne computer device. The reconstruction scheme is flexible, the integration level is high, external interfaces are rich, the space environment adaptability is high, and various satellite processing load requirements are met.

The invention provides a remote sensing satellite observation parameter pre-analysis method, calling method, system and equipment, and relates to the technical field of remote sensing satellites. Known remote sensing satellite ephemeris data, gridding coding is carried out on a remote sensing satellite sub-satellite point through an earth space grid coding rule, a remote sensing satellite sub-satellite point grid is taken as a center, and a remote sensing satellite imaging point moves east or west along a latitude line by taking the grid as a step length; under the condition of considering a remote sensing satellite imaging point grid, a satellite position, a satellite breadth and constraints, a satellite side-sway angle observation parameter and a coverage grid are calculated and stored in a database so as to be conveniently called at any time when a remote sensing task is executed, a task of observation parameter analysis is completed in advance, the time spent on executing the remote sensing task is shortened, and the remote sensing task execution efficiency is improved. The occupation of computing resources is reduced, and the response speed is improved.

The present invention provides a space-based, sensorless harassment device and method, relating to the field of microsatellite technology. The space-based, sensorless harassment device includes a micro-carrier satellite and a force-current multi-field coupling actuator mounted on the micro-carrier satellite. The micro-carrier satellite is used to drive the force-current multi-field coupling actuator toward a target satellite and, by adjusting its attitude, align its jet nozzle with the target satellite's reconnaissance lens. The force-current multi-field coupling actuator is used to spray a harassing liquid from the jet nozzle toward the target satellite's reconnaissance lens under electrostatic pressure, thereby achieving a "blinding" effect on the target satellite's reconnaissance lens. Compared to existing directed energy anti-satellite technologies or parasitic soft-kill methods, the device not only has the advantages of simple structure, low manufacturing cost, and low energy consumption, but can also achieve long-term effective harassment by spraying the harassing liquid toward the target satellite's reconnaissance lens.

The present application relates to the technical field of satellite, in particular to a RDSS system frequency offset compensation method and RDSS system, the present application embodiment provides a kind of frequency offset compensation method of RDSS system, comprising: determining target Beidou satellite;Wherein, the target Beidou satellite is the nearest Beidou satellite of remote sensing satellite or the normal of the antenna of the RDSS system and the angle formed when the straight line connecting the RDSS system and Beidou satellite is at the minimum time corresponding Beidou satellite;According to the speed of remote sensing satellite and the speed of target Beidou satellite, the relative speed between remote sensing satellite and target Beidou satellite is determined;According to the relative speed, frequency offset value is obtained;The sending frequency of the RDSS system is compensated using the frequency offset value.The present application embodiment provides a kind of frequency offset compensation method of RDSS system, and makes remote sensing satellite and Beidou satellite again communicate between disconnection.

The invention relates to a method and a system for forecasting the position of a medium-high orbit equatorial orbit satellite, and belongs to the technical field of satellites, the method for forecasting the position of the medium-high orbit equatorial orbit satellite comprises the following steps: preprocessing multi-source observation data, determining initial orbit parameters, constructing an equatorial orbit adaptive orbit dynamics model, and determining the position of the medium-high orbit equatorial orbit satellite; and orbit forecasting calculation based on adaptive numerical integration, dynamic error compensation and multi-source data fusion optimization, forecasting result output and precision verification. The core innovation of the invention focuses on deep adaptation of orbit characteristics of medium-high orbit equatorial orbit satellites, and the precision bottleneck of the existing method in equatorial orbit application is solved through the full-process technical innovation of model optimization, integral improvement, error compensation and data fusion.