110 results about "Satellite tracking" patented technology

The invention provides a satellite tracking method and device for a mechanical-electrical integration small planar phased-array antenna, and belongs to the technical field of satellite communication. The method comprises the following steps: starting and electrifying the small planar phased-array antenna and adjusting the small planar phased-array antenna into a preparation attitude; using the central array element to complete satellite searching to obtain ephemeris information; in the satellite and satellite top-crossing tracking stage, the expected beam direction is calculated, the beam direction is controlled in a beam forming and mechanical angle compensation combined mode, and satellite and satellite tracking operation is achieved; and the antenna receives the satellite switching instruction and adjusts the satellite switching instruction to a preparation attitude, and the next round of satellite tracking operation is carried out. According to the invention, mechanical angle compensation is carried out on the wave beam by adjusting the orientation of the antenna array surface, the satellite alignment and tracking performance of the antenna in a low satellite elevation scene is improved, and the consistency of terminal communication performance in the satellite top-crossing process is ensured.

The invention discloses a phased array ground station multi-satellite tracking method, device, equipment and product, and relates to the technical field of satellite communication, and the method comprises the steps: obtaining the ephemeris information of each satellite, and correspondingly calculating the satellite initial state of each satellite according to the ephemeris information of each satellite; and based on the satellite initial states of the satellites, the motion trails of the satellites are correspondingly calculated according to the satellite trajectory prediction model, the angles of the satellites relative to the phased array ground station are calculated according to the motion trails of the satellites and the corresponding satellite estimation angles, the direction to which an antenna should point is accurately calculated, and it is ensured that beams are always aligned with the satellites. According to the angle of each satellite relative to the phased array ground station, the antenna beam of the phased array ground station is correspondingly adjusted, the phased array antenna can track multiple satellites at the same time by flexibly adjusting the beam, and by accurately adjusting the beam direction and the beam width, the direction error is reduced, the resource waste is avoided, and the resource utilization rate of the ground station is improved.

The invention provides a satellite tracking method, and belongs to the technical field of communication. The satellite tracking method disclosed by the invention comprises the following steps: acquiring track information and antenna attitude information of communication-in-moving equipment in real time; for the target satellite, calculating a theoretical directional angle of an antenna beam according to the orbit parameters of the target satellite and the track information of the communication-in-moving equipment; correcting the theoretical directional angle of the antenna beam according to the antenna attitude information of the communication-in-moving equipment to obtain an actual directional angle of the antenna beam; based on the actual directional angle of the antenna beam, controlling a receiving phased-array antenna in the communication-in-moving equipment to form the antenna beam; in response to the situation that the signal strength of the satellite signal is larger than or equal to a preset value, data information of the received satellite signal is obtained, and the actual directional angle of the current antenna beam is corrected; according to the corrected actual directional angle of the antenna beam, controlling the transmitting phased-array antenna to form the antenna beam; and establishing a communication link, and updating ephemeris data of the target satellite.

A satellite tracking channel has a frequency loop tracking a carrier frequency of a satellite signal. A first indication of a spoofed signals is generated based on a determined satellite signal noise floor value associated with the satellite tracking channel and a tracking channel signal noise threshold associated with the satellite tracking channel. A second indication of a spoofed signal is generated based on a determining satellite tracking phase noise associated with the satellite tracking channel and a tracking channel phase noise threshold associated with the satellite tracking channel. Reception of a spoofed signal on the satellite tracking channel is detected based on the generated first indication of a spoofed signal and the generated second indication of the spoofed signal.

The invention provides an IGSO satellite tracking method and device of an automatic satellite tracking antenna and a medium. The method comprises the steps that orbit parameters and epochs of a target IGSO satellite are acquired; extrapolating the orbit from the orbit epoch moment, setting the extrapolation time as an orbit period T and calculating the step length S; converting the orbit data into earth-fixed system coordinate system coordinates and sub-satellite point data at corresponding moments; and calculating the direction vector of the antenna pointing to the satellite according to the latitude and longitude of the tracking antenna and the earth-fixed system coordinate data at the corresponding moment, and converting the direction vector into an azimuth angle and a pitch angle, thereby generating an antenna guide data file. And then calculating a guide data sequence number at the current moment through a date difference value between the current system time and the track epoch moment. And finally, the antenna orientation and the pitching motor are controlled to move to the target position corresponding to the guide data serial number, and the technical scheme provided by the invention can realize the tracking of the traditional automatic satellite tracking antenna on the IGSO satellite on the premise of not changing the antenna form.

The invention discloses a feedback implementation method and system for receiver vector tracking, a medium and equipment. The method comprises the following steps: firstly, carrying out EKF processing and extracting data participating in calculation of NCO adjustment amount at an ARM end; data coding is carried out at the ARM end; data communication between the ARM and the FPGA is carried out; satellite position and speed calculation and code / carrier NCO adjustment amount calculation at any moment are completed at the FPGA end; and new ranging codes and carriers are generated at the FPGA end by using the NCO adjustment amount to participate in tracking operation. If the newly generated ranging code and carrier cannot enable satellite tracking to be successful, transmitting a tracking operation result to the ARM end, performing a new round of EKF, completing new round of data updating iteration, and repeating the steps to complete feedback closed loop; and if the newly generated ranging code and carrier can enable the satellite to track successfully, iteration can be stopped, and a result is output. According to the method, parallel high-precision calculation of vector tracking and feedback adjustment of a hardware design vector tracking loop can be carried out, the execution efficiency is improved, and the processing speed is increased.

The invention discloses a method for realizing inter-satellite beam switching of a low-orbit satellite communication terminal and a medium, and belongs to the technical field of low-orbit satellite communication, and the method comprises the steps: tracking a target satellite based on an obtained initial ephemeris, and receiving a satellite signal of the target satellite; receiving a low earth orbit satellite ephemeris sent by the low earth orbit satellite communication system and updating the ephemeris; and based on the residual service time of the target satellite and the signal-to-noise ratio of the satellite signal, judging whether to perform inter-satellite beam switching, if so, performing inter-satellite beam switching based on the ephemeris of the low-orbit satellite, and if not, continuing to perform satellite tracking based on the initial ephemeris so as to solve the problem existing in the inter-satellite beam switching process and improve the satellite tracking efficiency. And the problem of data link instability or communication interruption is solved.

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 antenna tracking, and particularly discloses an antenna self-tracking system, a control method, computer equipment and a readable storage medium. The method comprises the following steps: controlling an antenna to track satellites according to a forecast program, and continuously detecting centimeter-wave satellite signals and millimeter-wave satellite signals; when the centimeter-wave satellite signal is detected, determining whether the centimeter-wave satellite signal meets a tracking condition, and if yes, controlling the antenna to perform satellite tracking according to the centimeter-wave satellite signal; and when the millimeter wave satellite signal is detected, determining whether the millimeter wave satellite signal satisfies a tracking condition, and if so, controlling the antenna to perform satellite tracking according to the millimeter wave satellite signal. Therefore, the signal tracking mode can be intelligently switched according to the actual situation and the priority while continuous satellite tracking is ensured.

Methods, systems, and devices for satellite operations are described. Positioning data for non-geo stationary satellites may be received from the non-geo stationary satellites via one or more satellites in orbits that are higher than the orbits of the non-geostationary satellites. Based on the positioning data, trajectories may be calculated for the non-geostationary satellites. Based on the trajectories calculated for a set of non-geostationary satellites, a distance between the set of the non-geostationary satellites may be predicted to come within a threshold distance and an alert that the distance between the set of non-geostationary satellites is predicted to come within a threshold distance may be communicated to the one or more operators of the set of non-geostationary satellites.

The present disclosure belongs to the technical field of communications. Provided is a satellite tracking method. The satellite tracking method disclosed in the present disclosure comprises: acquiring track information and antenna attitude information of a communications-on-the-move device in real time; for a target satellite, performing calculation on the basis of orbital parameters of the target satellite and the track information of the communications-on-the-move device, so as to obtain a theoretical pointing angle of an antenna beam; on the basis of the antenna attitude information of the communications-on-the-move device, correcting the theoretical pointing angle of the antenna beam, so as to obtain an actual pointing angle of the antenna beam; on the basis of the actual pointing angle of the antenna beam, controlling a receiving phased-array antenna in the communications-on-the-move device to form an antenna beam; in response to the signal strength of a satellite signal being greater than or equal to a preset value, acquiring data information of the received satellite signal, and correcting the actual pointing angle of the current antenna beam; on the basis of the corrected actual pointing angle of the antenna beam, controlling a transmitting phased-array antenna to form an antenna beam; and establishing a communication link, and updating ephemeris data of the target satellite.

The invention provides a satellite cooperative tracking and pointing moving target method and system based on multi-agent reinforcement learning, and the method comprises the steps: loading a trained strategy network on each satellite, and initializing an interaction scene; constructing local observation of satellites, inputting a strategy network, and outputting satellite tracking and pointing actions at each moment; the strategy network comprises a convolution channel and a full connection channel which are parallel; and after the convolution channel and the full-connection channel are spliced in the feature dimension, action probability distribution is output through a fusion layer, and satellite tracking and pointing actions are obtained according to probability sampling. The method has the advantages that the response time delay is obviously shortened; the tracking continuity and precision are improved; the energy consumption and the maneuvering safety are controlled; and the expandability and the fault tolerance are good.

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 discloses a GNSS (Global Navigation Satellite System) signal closed-loop tracking method and device based on an AXI4 bus. The tracking device mainly comprises a preprocessing module, a satellite tracking channel, a time module, an AXI4 interface module, a baseband processing clock circuit and a CPU (Central Processing Unit) module. Wherein the satellite tracking channel is composed of an NCO module, a narrow correlation module, a difference frequency down-conversion module, a correlator module and a TIC latch module. By using the device, a GNSS signal closed-loop tracking method can be realized at a single synchronous clock frequency which is more than two times higher than a signal sampling rate, and the device has the advantages of simple and reliable cross-clock domain processing, high bus frequency, hardware area resource saving, CPU (Central Processing Unit) machine hour saving and stable and reliable working performance.

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 discloses an offset sun alignment method suitable for DRO satellite measurement and control constraint, which comprises the following steps: firstly, determining a maximum allowable offset angle phi, then determining an offset sun vector S'b based on the size of a sun-earth included angle Ase and the maximum allowable offset angle phi, determining attitude angles # imgabs0 # theta in X-axis and Y-axis directions based on the offset sun vector S 'b, and finally, determining the attitude angles # imgabs1 # theta in the X-axis and Y-axis directions based on the attitude angles # imgabs1 # theta in the X-axis and Y-axis directions. And the attitude of the DRO satellite is controlled, so that the sun-pointing attitude angle is [0, 0, 0], and offset sun-pointing is realized. The method can reduce the maneuvering time of a single machine and reduce the satellite attitude adjustment frequency.

The invention discloses a high-utilization-rate service uninterrupted satellite following method for a gateway station antenna, and belongs to the technical field of low-orbit satellite communication. According to the method, satellites which do not run out of a view field at the same time in a visible range of a gateway station are divided into N satellite clusters according to ephemeris, the number of satellites in each satellite cluster is M1, M2,..., MN, and the remaining K satellites are satellites which run out of a view field area at the same time. In order to ensure that the feed links are not interrupted, the gateway station at least needs (M1 + 1) + (M2 + 1) +,..., + (MN + 1) + 2K antennas to carry out relay tracking, and M1 + + M2 +,..., + MN + K uninterrupted feed links are established in total. The antennas of the satellites in the cluster are guaranteed to always keep one antenna in a to-be-relayed state at each moment, and K antennas in the remaining 2K antennas are always kept in the to-be-relayed state. According to the method, a small-scale number of antennas are used for tracking a visual satellite at a gateway station of a low-orbit satellite communication system, so that the switching satellite feed link service is ensured not to be interrupted; compared with a traditional method that each satellite needs to be provided with two antennas to keep uninterrupted feed, the deployment scale of the antennas of the gateway station is reduced, and the utilization efficiency of the antennas is improved.

The invention discloses a GNSS land-based enhancement system and method for a railway trunk line. The GNSS land-based enhancement system comprises a data processing center, a satellite tracking base station, a pseudo satellite base station and a disaster emergency satellite base station, the satellite tracking base station is used for receiving GNSS satellite signals in real time; the data processing center is used for carrying out differential processing on the GNSS satellite signals, generating corresponding differential navigation data, broadcasting the differential navigation data through a railway broadcasting private network, and starting disaster emergency satellite base stations in a corresponding range when the signal-to-noise ratio and the duration of the GNSS satellite signals do not accord with corresponding threshold values; and transmitting a disaster positioning signal through the disaster emergency satellite base station, starting the pseudo-satellite base station in the corresponding range when the integrity and duration of the GNSS satellite signal do not accord with the corresponding threshold value, and transmitting a pseudo-satellite signal through the pseudo-satellite base station. According to the GNSS land-based augmentation system of the trunk railway, data processing and switching of the normal working mode, the standby working mode and the disaster working mode can be carried out according to different conditions.

The invention relates to the field of satellite communication, and discloses a satellite target identification and tracking method and device, equipment and a storage medium, and the method comprises the steps: obtaining orbit data, carrying out the satellite tracking according to the orbit data, and obtaining the original image information; performing centroid extraction and brightness optimization on the original image information to obtain centroid coordinates and optimized image information; performing image processing on the optimized image information according to the center-of-mass coordinates to obtain light spot data; performing light spot identification on the light spot data to obtain an identification result, and confirming and implementing a tracking strategy from a preset tracking strategy pool according to the identification result; when the tracking strategy is light spot tracking, obtaining an implementation result of the tracking strategy, and generating a satellite tracking instruction according to the implementation result; by introducing a tracking strategy selection and adjustment mechanism, the most suitable tracking strategy can be selected and implemented according to different tracking situations, and the stability and accuracy of satellite tracking and recognition can still be kept in a complex and changeable environment.

The invention relates to the technical field of satellite antennas, in particular to a satellite tracking method, system and device and electronic equipment, and the method comprises the steps: determining a communication state between a carrier and a satellite, and obtaining the attitude information of the carrier in real time; starting a correction strategy corresponding to the communication state to determine a target angle of the carrier pointing to the satellite, the correction strategy comprising: when the communication state represents a disconnection state, correcting the attitude information by using the tracking network, and correcting the first theoretical pointing angle by using the tracking network to obtain the target angle; wherein the first theoretical pointing angle is obtained based on the corrected attitude information; wherein the tracking network is obtained by training based on sample data corresponding to a plurality of continuous moments, the sample data is obtained when the communication state represents the connection state, and the sample data comprises an attitude information sample and an angle information sample; the angle information sample is a theoretical pointing angle of the carrier calculated based on the attitude information sample.

Multiple low noise block down converter feeds (LNBFs) independently move close to the surface of the lower half of a spherical lens to create N beams for simultaneous tracking of N satellites, preferably containing a visible hemisphere. A spiderlike robot with non-metal arms positions the LNBFs. Each LNBF can have several feeds for different satellite frequency bands. LNBFs can be carried by one or two circular rails, movable arc rails orthogonal to a circular rail, or magnetic coupling to the lens. RC platforms can be autonomous, with connections using Bluetooth™ or other radio links. be Single feeds can be arranged in a chess board arrangement, where each piece of the chess board is responsible for a small three-dimensional angle of the sky. In any of these embodiments, LNBFs can be positioned closer or farther from the lens to create a relative phase shift.

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 satellite tracking method and device based on an antenna pattern, and electronic equipment, and relates to the field of antenna tracking, and the satellite tracking method comprises the steps: determining the initial position coordinate of an antenna under the condition that a beacon signal transmitted by a communication satellite and received by the antenna is smaller than a preset signal threshold value, controlling the antenna to track the communication satellite for a preset step length in any direction, determining the current position coordinate and the level change state of the tracked antenna, and determining the center position coordinate and the gradient maximum direction of an antenna pattern based on the initial position coordinate, the current position coordinate, the level change state and the antenna pattern of the communication satellite, and taking the center position coordinate as a target position coordinate of the antenna tracking communication satellite, and controlling the antenna to move towards the target position coordinate along a gradient maximum direction to complete tracking of the communication satellite. According to the invention, the technical problem of low efficiency of tracking a communication satellite by an antenna in the prior art is solved.