45 results about "Satellite tracking" patented technology

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 relates to the technical field of satellite communication, and discloses a satellite tracking method and device based on satellite signal fusion, and the device comprises a multi-source information collection unit, a central processing unit, and a phased array antenna unit. The central processing unit judges and obtains a mode signal representing the current working mode according to the obtained signal to noise ratio of the signal and the triaxial angular velocity vector; selecting one of preset control logics according to the mode signal, and adaptively weighting or selecting a signal feedback correction vector, a predictive attitude compensation vector, a real-time attitude compensation vector and the like so as to calculate a beam pointing adjustment vector; and finally, generating a final beam pointing vector to drive the phased-array antenna unit. Through the dynamic switching control strategy, the problem that different working conditions are difficult to consider in a traditional method is solved, the tracking precision, the dynamic response speed and the signal recapturing capability of the system in a complex environment are remarkably improved, and the overall stability and robustness are enhanced.

The invention relates to a high and low orbit satellite tracking method based on geomagnetic correction. The method comprises the following steps: constructing a geomagnetic model, calculating an azimuth angle and carrying out magnetic field interference analysis; carrying out factory calibration by utilizing a three-dimensional geometric calibration mode, including horizontal correction and vertical correction; the current azimuth angle and pitch angle are continuously corrected based on the carrier coordinate system by using the signal intensity, and the deviation is obtained so as to continuously approach the real angle; utilizing the known coordinates of the three-dimensional space to inversely calculate the current position; and the current data is corrected by using the big data, so that the current data meets the use requirements. The current attitude angle and the satellite signal receiver are used for tracking the target satellite, and then the known azimuth angle is used for correcting the geomagnetic data, so that the azimuth angle precision is improved, the cost of a phased-array antenna or a mechanical antenna is reduced, the tracking precision is improved, and the tracking speed is improved.

The application provides a satellite cooperative tracking and pointing moving target method and system based on multi-agent reinforcement learning, the method comprising: loading a trained strategy network on each satellite and initializing an interaction scene; constructing a local observation of the satellite, inputting the strategy network, and outputting a satellite tracking and pointing action at each time; the strategy network comprising a parallel convolution channel and a fully connected channel; after the convolution channel and the fully connected channel are spliced in a feature dimension, an action probability distribution is output through a fusion layer, and a satellite tracking and pointing action is obtained according to probability sampling. The application has the advantages that: the response time delay is significantly shortened; the tracking continuity and accuracy are improved; the energy consumption and maneuvering safety are controlled; and good scalability and fault tolerance are achieved.

The invention provides a beam determination method and device, equipment, a storage medium and a chip, and the method comprises the steps: carrying out the signal measurement based on a plurality of beams corresponding to a first beam in the random beam access process, obtaining a first measurement result, and determining a second beam based on the first measurement result; signal measurement is carried out in the service beam access process based on the multiple beams corresponding to the second beam to obtain a second measurement result, a target beam is determined based on the second measurement result, and the target beam is used for satellite tracking. Therefore, the ground station equipment applying the phased-array antenna can determine the beam for satellite tracking through signal measurement, and satellite tracking of the ground station applying the phased-array antenna is realized. In addition, compared with a mode of satellite tracking through mechanical driving, the mode of determining the wave beams through signal measurement for satellite tracking is high in precision, and rapid satellite tracking is facilitated.

The application discloses a kind of star tracking methods, comprising the following steps: S100, satellite signal is tracked by linear scanning, and automatic star device is adjusted according to the satellite antenna of provided theory star angle, and visual angle scanning is carried out;S200, satellite signal is tracked twice by cross scanning, and based on the theory star angle of S100 acquisition, visual angle scanning is driven to automatic star device and micro antenna;S300, if satellite signal is tracked in S100 linear scanning process, its corresponding antenna returns starting point;If satellite signal is tracked in S200 cross scanning process, its corresponding antenna keeps signal tracking state;Linear scanning is combined with cross scanning, it is solved that star efficiency is low, linear scanning is more strict to field environment requirement, if it is not straight line, but curve, cross scanning can improve satellite signal tracking efficiency, star time is shortened, fault tolerance is high.

The embodiment of the invention provides a low-orbit satellite searching method and system, computer equipment and a storage medium, and the method comprises the steps that a satellite terminal sends an access request to a synchronous satellite based on preset information; after receiving an access response signal returned by the synchronous satellite based on the access request, sending a low earth orbit satellite search request to the synchronous satellite, so that the synchronous satellite forwards the low earth orbit satellite search request to a ground base station synchronous satellite signal; real-time almanac information forwarded by the ground base station through a synchronous satellite is received, and the real-time almanac information is generated after the ground base station analyzes the satellite searching request of the low-orbit satellite; and calculating the real-time position of the target low-orbit satellite according to the real-time almanac information, and adjusting the direction of the antenna to realize satellite tracking. According to the scheme, the synchronous satellite is used for assisting satellite searching, and the real-time almanac generated by the ground base station is issued to the satellite terminal, so that the satellite terminal realizes accurate satellite following, the satellite searching efficiency is improved, meanwhile, the requirement of the terminal for regularly maintaining the almanac is eliminated, and the maintenance cost is reduced.

An efficient satellite vehicle (SV) tracking mode that, when utilized by user equipment (UE), consumes less power and / or computing resources of the UE than a default SV tracking mode of tracking all visible SV, while maintaining consistent signal quality and / or positional, navigational, and / or timing information accuracy standards. Furthermore, use of the efficient SV tracking mode may be determined and implemented based on a signal environment associated with a location of the UE. In particular, the efficient SV tracking mode may be associated with a location based on a determination that signal quality thresholds are met during use of the efficient SV tracking mode at the location. Additionally or alternatively, the location may be associated with a geofenced area. The geofenced area may define a geographical area corresponding to implementation of the efficient SV tracking mode by a UE located within the geofenced area.

This invention discloses a method and related equipment for predicting the visibility of low-Earth orbit (LEO) satellites without prior information. It relates to the field of signal processing technology for LEO satellites in GNSS (Global Navigation Satellite System). The method includes: acquiring the LEO satellite; tracking the LEO satellite when it is successfully acquired; monitoring and recording the tracking parameters of the LEO satellite while tracking is active; recording the continuous invisible time of the LEO satellite when tracking is lost; obtaining the current tracking parameters and comparing them with historical tracking parameters when the LEO satellite is reacquired and re-enters tracking mode to determine the consistency between the two tracking states; and estimating the remaining invisible time based on the current time, the recording time of the historical tracking parameters, and the continuous invisible time of the LEO satellite. This invention achieves effective prediction of the visibility of LEO satellites.

The invention discloses a Ka-band two-dimensional sum-difference beam liquid crystal phased-array antenna based on liquid crystal, and belongs to the technical field of microwave antennas. The antenna comprises a radiation unit, a glass substrate, an antenna floor, a liquid crystal layer, a phase shift layer, a microstrip ground, a sum-difference beam feed network and a double-layer dielectric substrate. The sum-difference feed network is used for generating a sum beam, an azimuth difference beam and a pitch difference beam, and configuring a sum channel, a pitch difference channel and an azimuth difference channel; the sum-difference feed network and the phase shifter layer are connected through metalized via holes; a beam scanning function can be realized by driving different voltages to change liquid crystal dielectric constants; the two-dimensional sum-difference beam phased-array antenna is formed by using liquid crystal phase shift, has the characteristics of low cost, low power consumption, easiness in processing and the like, and has a wide prospect in the fields of satellite tracking communication and antenna signal arrival angle estimation.

The invention provides a satellite tracking method and an antenna terminal, relates to the technical field of communication, and is applied to the antenna terminal, a satellite set corresponding to the current moment is acquired, and each first satellite included in the satellite set is in a visible range of the antenna terminal; predicting a carrier-to-noise ratio between each first satellite and the antenna terminal at different moments in a transit process in the satellite set; adjusting the carrier-to-noise ratio corresponding to each first satellite based on the switching response speed of the antenna terminal and the shielding degree of the current environment to each first satellite; and switching from the currently linked second satellite to a target satellite in the plurality of first satellites based on the adjusted carrier-to-noise ratio. Through the satellite tracking method provided by the invention, the response speed of the antenna terminal can be improved, the condition of chain breakage caused by too slow response speed can be avoided, and the reliability and stability of information communication between the antenna terminal and the target satellite can be improved.

The invention belongs to the technical field of satellite gravitational field measurement, and particularly discloses an SST gravitational field measurement system and method based on inspection mass spacing measurement. The system is applied to two satellite platforms on a target orbit, and comprises a control unit, two laser interference measurement systems and two quality inspection units, wherein one laser interference measurement system and one inspection quality unit are correspondingly arranged on one satellite platform; on two gravitational field measurement satellites of a low satellite tracking satellite, laser interference is utilized to directly measure the distance and the variation rate between the inspection masses installed on the two satellites, and the measurement of the global gravitational field is realized. According to the invention, the space-between-satellite measurement and the non-conservative force measurement are integrated, the unification of the space-between-satellite measurement coordinate reference and the non-conservative force measurement coordinate reference is realized, the disturbance effect introduced by the conversion of two sets of independent coordinate systems and the change of a coordinate frame in the existing scheme is reduced, and the measurement sensitivity and confidence level are higher.

An emergency response activation (ERA) system comprising a graphical user interface (GUI) located at a dashboard of a vehicle, four or more global positioning system (GPS) satellites, a driving center, a 5G-communication control tower, an emergency response center (ERC) system, and 5G-enabled unmanned semi-autonomous aerial vehicles (UAVs). The GUI comprises distinct emergency activation buttons (EABs), each associated with a specific emergency. The GPS satellites provide a precise location of the vehicle associated with the specific emergency. The driving center receives information of the specific emergency via the GPS satellites once the EAB is pressed by an occupant of the vehicle. The 5G-communication control tower transmits the information from the driving center to a specific emergency response center via the GPS satellites. The ERC system dispatches emergency response personnel from the specific emergency response center at the precise location of the vehicle.

The invention discloses a low-orbit phased array terminal satellite capture and inertial navigation real-time calibration method, device and system and a medium, and belongs to the field of satellite mobile communication, and the method comprises the following steps: after a satellite is successfully captured and stabilized, an antenna enters a satellite tracking state, and inertial navigation data is continuously calibrated in the tracking state; wherein the phased-array antenna is divided into four array planes, namely an A array plane, a B array plane, a C array plane and a D array plane, and the receiving powers of the four array planes respectively correspond to the power PA, the power PB, the power PC and the power PD; the antenna is provided with four power detection circuits which are used for detecting the combined receiving power of the four array plane combinations, the combined receiving power corresponds to PA and PB, PC and PD, PA and PC, PB and PD, and the antenna beam pointing error is calculated and corrected. According to the invention, the attitude data can be calibrated in real time by receiving the signal, so that the cost and the design complexity of the phased-array antenna are reduced.

The invention provides a communication-in-motion tracking signal transmission method and system without GNSS assistance, and relates to the technical field of signal transmission, and the method comprises the steps: collecting the acceleration information of a target communication-in-motion based on a gyroscope, and carrying out the disturbance compensation, including pitching compensation and rolling compensation; receiving a satellite alignment instruction, calculating an initial alignment parameter of the target satellite-in-motion communication, and controlling the satellite alignment execution component to point to the initial alignment parameter; controlling the satellite alignment execution assembly to rotate according to a preset angular velocity, and synchronously acquiring a signal-to-noise ratio value fed back by the signal receiver to obtain a time sequence signal-to-noise ratio set; and according to the time sequence signal-to-noise ratio set, taking the azimuth angle at the maximum signal-to-noise ratio value as a theoretical azimuth angle, performing alignment control and signal feedback transmission based on the theoretical azimuth angle, and performing zero offset compensation on the gyroscope in combination with a preset compensation period. The technical problems of large antenna tracking deviation and unstable communication link caused by loss of lock of GNSS signals or reduction of precision of the GNSS signals in a complex scene in the prior art are solved.

The application discloses a time-varying gravity field model establishment method of a new generation of low-low satellite tracking satellite scheme based on Chinese regional enhancement, belongs to the field of satellite gravitation, and refers to selection indexes of a global optimal double-track four-star formation scheme to determine multiple double-track four-star formation schemes in the Chinese region, select an optimal scheme from the multiple double-track four-star formation schemes, independently solve low-order and high-order gravity potential spherical harmonic coefficients by using different data in the optimal scheme, weaken the negative influence of time domain aliasing effect on the precision of the time-varying gravity field model, reduce the error of the high-order gravity potential spherical harmonic coefficients to a certain extent, and finally obtain a Chinese regional gravity field model with higher precision. The final result shows that, compared with an independent polar orbit formation, the application not only greatly weakens the north-south strip error caused by the north-south tracking mode in the Chinese region, but also avoids problems such as gravity signal leakage caused by a post-processing process, and finally obtains a Chinese regional gravity field model with smaller error and higher signal-to-noise ratio.

A distribution method for improving remote sensing constellation target capacity through three-dimensional coordinate different-satellite fusion comprises the steps that two-dimensional coordinates of the same observation target group are generated on two task satellites executing an observation task, and three-dimensional coordinate fusion and numbering sorting are carried out based on the two-dimensional coordinates; distributing the two-dimensional coordinates which are not fused to the satellites which do not execute the observation task according to the upper limit of the capability of calculating the three-dimensional coordinates by the satellites, and performing three-dimensional coordinate fusion by the satellites which do not execute the observation task by receiving the two-dimensional coordinates which are sent by the two satellites and have the same serial number. After the two-dimensional coordinates are successfully fused in the upper limit range of the capability of calculating the three-dimensional coordinates, the two-dimensional coordinates are sent back to the task satellite, the part exceeding the upper limit range of the capability of calculating the three-dimensional coordinates is sent to another satellite which does not execute the observation task, and so on until all the two-dimensional coordinates are fused, and the target tracking capacity of the satellite is increased. The method overcomes the limitation of the calculation capability of the existing single satellite, and provides a mode that the satellites networked in the stationary orbit do not need to interact through a fixed rule.

According to the satellite tracking method provided by the invention, a high-frequency dynamic gradient increasing algorithm is combined with program tracking, so that factors such as ephemeris errors and atmospheric disturbance are compensated in real time. The correction direction is directly calculated by the gradient method, and compared with serial search of step tracking, the convergence speed is higher, the gradient method is particularly suitable for the rapid motion characteristic of an LEO satellite, and the average received signal strength can be remarkably improved; according to the method, a predictive switching strategy based on multi-target QoS evaluation is introduced, the next service satellite can be selected from the global optimum angle, and the short vision of a traditional strategy is avoided. By comprehensively balancing the link quality, the service duration and the switching time consumption, the scientificity of the switching decision is ensured, and the switching frequency and the total signal interruption time can be effectively reduced, so that the data throughput and the operation efficiency of the whole ground station are improved.

The application provides an earth gravity field inversion method in an inter-satellite tracking mode based on an optical clock, comprising: using a numerical simulation method, the accuracy of the inversion of the earth gravity field in the inter-satellite tracking mode of the satellite-borne optical clock satellite is systematically evaluated. The simulator generates simulated observation data as input in the orbit of the gravity satellite (such as the GOCE and GRACE orbits), and estimates the gravity field coefficients by using a strict least square method. The accuracy of the results is evaluated by comparing the coefficient difference between the inversion model and the reference model. The application evaluates the accuracy of the inversion of the earth gravity field in the inter-satellite tracking mode based on the optical clock through the numerical simulation method, and verifies the potential of the optical clock in the high-precision gravity field measurement. In the future research, the optical clock noise model and the multi-sensor fusion method will be further optimized to improve the inversion accuracy of the high-order gravity field, and more accurate data support will be provided for the earth science and global climate change research.

Embodiments of the present disclosure provide a communication satellite tracking method, a storage medium, and an electronic apparatus. The method comprises: on the basis of an initial antenna pointing position point of a satellite tracking device, acquiring a first detection plane and a second detection plane on a spherical surface taking the satellite tracking device as the center, wherein the first detection plane corresponds to a first detection direction, and the second detection plane corresponds to a second detection direction; respectively acquiring a first detection point and a second detection point on the basis of the first detection direction and the second detection direction; and determining a tracking direction on the basis of the received signal strength of the first detection point and the second detection point and the received signal strength of the initial position point.

The invention discloses a medium and low orbit satellite real-time and delay monitoring alarm information pushing system and method, and the system comprises a real-time diagnosis module which carries out the real-time diagnosis of real remote data received by each frame, and generates a real-time diagnosis result; according to the real-time diagnosis result, alarm information of real-time diagnosis is generated and stored in an alarm information list; the delay diagnosis module caches the received delay data, after measurement and control tracking of a measurement and control station on a satellite is finished, all the delay data measured and controlled at this time are ranked according to on-satellite acquisition time in an incremental mode and then subjected to playback diagnosis, and a delay diagnosis result is generated; generating alarm information of delay diagnosis, and storing the alarm information in an alarm information list; the client sends the IDs and the timestamps of all the alarm information obtained last time to the server, and requests to obtain the alarm information needing to be updated; displaying or deleting the alarm information; and the server side returns a result to the client side according to the ID value of the alarm information in the request of the client side.

A system and method of the disclosure relates to satellite tracking. The system may comprise a tracking receiver that includes a first analog-to-digital (A / D) converter coupled between a sum input and a digital signal processor (DSP), a second A / D converter coupled between a difference input and the DSP, and a calibration output coupled to the sum input and coupled to the difference input. The first A / D converter may convert an signal received at the sum input into a sum digital signal, and provide the sum digital signal to the DSP. The second A / D converter may convert an signal received at the difference input into a difference digital signal, and provide the difference digital signal to the DSP. The tracking receiver may generate an calibration signal and provide the calibration signal through the calibration output.

The application provides a GNSS-aided satellite tracking signal transmission method and system, and relates to the technical field of signal transmission. The method comprises: collecting acceleration information of a target satellite tracking system based on a gyroscope to perform disturbance compensation, including pitch compensation and roll compensation; receiving a satellite pointing instruction, calculating initial alignment parameters of the target satellite tracking system, and controlling a satellite pointing execution component to point to the initial alignment parameters; controlling the satellite pointing execution component to rotate at a preset angular velocity, and synchronously collecting a signal-to-noise ratio value fed back by a signal receiver to obtain a time sequence signal-to-noise ratio set; according to the time sequence signal-to-noise ratio set, the azimuth angle at the maximum value of the signal-to-noise ratio value is a theoretical azimuth angle, alignment control and signal feedback transmission are performed based on the theoretical azimuth angle, and zero offset compensation is performed on the gyroscope in combination with a preset compensation period. The technical problem that the antenna tracking deviation is large and the communication link is unstable due to the loss of GNSS signal locking or the decrease in precision of the satellite tracking system in the prior art under a complex scene is solved.

The application discloses an azimuth-cross-pitch type pedestal system suitable for extremely high sea conditions and belongs to the field of satellite communication antennas. The system comprises an azimuth-cross-pitch type pedestal, motors for driving rotation of the shafts, a driver for controlling the rotation of the motors, encoders for collecting azimuth, cross and pitch shaft angle information, and a controller for receiving driver information, encoder information and navigation information. After the encoders collect the shaft angle code information, the information is reported to the driver. The driver analyzes the received code information and reports the information to the controller in the form of CAN messages as the feedback of the shafts. The controller controls the driver to realize stable satellite tracking of the antenna. The application has high structural strength, a large cross shaft movement range, low cost and can realize stable satellite tracking under extremely high sea conditions.

The application discloses a portable ground station and a satellite tracking method, wherein the ground station comprises a support module, a rotating table module installed on the support module, a channel module which is detachably installed on the rotating table module, the channel module comprising a feed source unit and a signal processing unit, the feed source unit being connected with the signal processing unit, and an antenna surface module comprising a plurality of antenna panels, the plurality of antenna panels being circumferentially surrounded around the feed source unit to form an antenna surface, and the antenna panels being detachably connected with the feed source unit. The antenna surface is designed as a detachable structure surrounded by the plurality of antenna panels, and the whole system is divided into independent modules such as the support, the rotating table, the channel and the antenna surface, so that the volume and the weight of each module are reduced, the ground station is convenient to carry or transport by using a conventional vehicle, meanwhile, on-site operators can complete the butt joint, assembly of each module and the assembling and unfolding of the antenna surface in a short time, and the deployment efficiency of the ground station is improved.

An efficient satellite vehicle (SV) tracking mode that, when utilized by user equipment (UE), consumes less power and / or computing resources of the UE than a default SV tracking mode of tracking all visible SV, while maintaining consistent signal quality and / or positional, navigational, and / or timing information accuracy standards. Furthermore, use of the efficient SV tracking mode may be determined and implemented based on a signal environment associated with a location of the UE. In particular, the efficient SV tracking mode may be associated with a location based on a determination that signal quality thresholds are met during use of the efficient SV tracking mode at the location. Additionally or alternatively, the location may be associated with a geofenced area. The geofenced area may define a geographical area corresponding to implementation of the efficient SV tracking mode by a UE located within the geofenced area.

The invention provides a giant satellite constellation transit tracking method and device, a storage medium and electronic equipment. The giant satellite constellation transit tracking method comprises the steps that a transit display graph of a giant satellite constellation is generated; on the basis of the ground station information and the basic information of the giant satellites, marking satellite tracks of observable giant satellites in the observation time period in the transit display graph; generating a satellite observation list with priority based on a priority evaluation rule; and according to the priority in the satellite observation list, carrying out resource allocation on each giant satellite in the satellite observation list to generate a satellite tracking task list corresponding to the observation time period. By applying the method provided by the invention, the trails of the giant satellites can be intuitively observed by generating the transit display graph, the decision of the user is determined in a man-machine interaction mode, and reasonable resource planning is performed for each giant satellite in the observation time period in combination with the decision of the user and the priority evaluation rule in the system; and optimal tracking is realized under limited resources.

The invention discloses a double-shaft turntable for coarse tracking of satellites, and relates to the technical field of coarse tracking of low-orbit satellites. Comprising a rotary table mechanical table body, a rotary table electric control system, an equipment cable and an image recognition assembly. The rotary table mechanical table body is of a U-T horizontal structure and comprises an outer ring base, and a first support and a second support are fixedly arranged on the two sides of the outer ring base respectively. An outer ring shaft is rotationally installed between the first support and the second support, an inner ring shaft is rotationally installed on the outer ring shaft, the outer ring shaft rotates around a pitching axis, the pitching axis is in the horizontal direction, the inner ring shaft rotates around an azimuth axis, the azimuth axis is in the vertical direction, and the azimuth axis can be located at different space positions around the pitching axis. The outer ring shaft and the inner ring shaft rotate continuously and infinitely; the rotary table electric control system is used for completing motion control, state monitoring and remote control of the rotary table; the rotary table is small in overall motion envelope size and convenient to move; the control system is placed in the table body frame, so that the system design is simplified.

The invention discloses a dual-mode parabolic antenna system for low-orbit satellite tracking, and belongs to the field of electronic information. The system configuration of two parabolic antennas, two satellite terminals and a dual-mode switching unit is adopted. When a low-orbit satellite works, the two parabolic antennas alternately track in a relay mode, and signals are transmitted to any satellite terminal through the dual-mode switching unit on the premise that reference is not interrupted, so that communication is not interrupted. When the two antennas need to work respectively, the two antennas transmit signals to the dual-mode switching unit, and the dual-mode switching unit distributes the signals to the two satellite terminals so that the two antennas can conduct communication and tasks at the same time.

The invention discloses a low-orbit satellite vehicle-mounted tracking control method, device and system. The low-orbit satellite vehicle-mounted tracking control method comprises the steps that the longitude and latitude and the altitude of a vehicle-mounted antenna, the forward included angle between the axial direction of a vehicle-mounted platform and the due north direction and the TLE orbit parameters of a target satellite are obtained; calculating coordinates of the vehicle-mounted platform in an earth coordinate system according to the latitude and longitude of the vehicle-mounted platform and the altitude; calculating the coordinates of the target satellite in an earth coordinate system based on the SGP4 / SDP4 model and the TLE orbit parameters of the target satellite; calculating the coordinate of the target satellite in the station center coordinate system according to the coordinate of the vehicle-mounted platform in the earth coordinate system and the coordinate of the target satellite in the earth coordinate system by taking the vehicle-mounted antenna as a coordinate origin; target satellite tracking control parameters are calculated according to the coordinates of the target satellite in the station center coordinate system; and sending the target satellite tracking control parameters to a vehicle-mounted antenna control unit. According to the invention, after the vehicle carrying platform reaches the target position, the azimuth pitch angle of the low-orbit satellite can be quickly tracked.