70 results about "Satellite tracking" patented technology

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 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 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 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.

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.

Methods, systems, and devices for wireless communications are described. In general, the described techniques provide for a user equipment (UE) to perform a beam switching operation from a current beam to a target beam based on a beam switching duration. The UE may transmit a capability report that may include antenna pointing capabilities, a list containing one or more detailed capabilities, or both to another device, such as a network entity (e.g., a satellite). The UE may perform the beam switching operation based on the capability report. The UE may perform a random access procedure as part of an association change operation. The UE may receive a control message from the other device (which may be the network entity) that includes an identity of a target network entity, one or more resources for a random access procedure, an indication of a beam switching duration, or any combination.

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 utility model discloses a high-speed internet access system based on a high-throughput tablet portable station, and relates to the field of satellite communication. The core of the system is an antenna control unit, and the antenna control unit comprises a microprocessor, a BD positioning module and an antenna attitude resolving unit. The BD positioning module provides latitude and longitude, the antenna attitude resolving unit processes sensor data, and the latitude and longitude and the sensor data are both transmitted to the microprocessor; and the microprocessor drives the motor to adjust the attitude of the antenna through a 485 bus, and realizes automatic satellite tracking in combination with the strength of satellite signals received by the beacon machine. And after communication is started, a Modem modulation signal is amplified by the BUC and is sent to a satellite re-transmission gateway station by the antenna, so that network access and networking are completed. The power management module is provided with a lithium battery to support work without mains supply, and is provided with an OLED screen, a key, a WiFi module and an external storage unit, thereby facilitating operation, monitoring and data storage. The system is highly integrated and modularized, is high in portability, can cope with a complex environment, and supports high-bandwidth satellite and ground private network communication.

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 satellite measurement and control signal generation method, which is cooperatively executed by a CPU (Central Processing Unit) and a GPU (Graphics Processing Unit), and comprises the following steps of: in a telemetry signal generation stage, performing A / D (Analog to Digital) conversion on analog quantity in telemetry data at a GPU end by adopting polynomial fitting operation; framing the analog quantity subjected to A / D conversion and digital quantity telemetry data in the telemetry data at a CPU (Central Processing Unit) end to obtain a telemetry data frame; performing signal modulation on the telemetry data frame at the GPU end to generate a telemetry data signal; in the remote control signal demodulation and execution stage, Hilbert transformation is carried out on the received remote control signal by utilizing the GPU; performing phase demodulation and de-surround on the data subjected to the Hilbert transform, and extracting a net phase; eliminating high-frequency noise at the GPU end through FIR filtering, and extracting a remote control instruction; and executing the remote control instruction at the CPU end and updating the telemetering parameters based on the simulation effect of instruction execution so as to form closed-loop feedback. Therefore, the technical problem that the prior art is difficult to process high-speed telemetering data or is difficult to upgrade and maintain is solved.

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 invention provides a tracking and pointing device and method and a terminal, the tracking and pointing device comprises an optical antenna, a rotary table, a fine pointing mirror, a beam splitter, a light spot detector, a laser and a wavefront controller, the wavefront controller is used for carrying out wavefront modulation on a deflection angle and a beam divergence angle of an emergent laser beam, when the laser beam is emitted to an opposite-end satellite, the emergent laser beam is generated by the laser, and the light spot detector is used for detecting the deflection angle and the beam divergence angle of the emergent laser beam. After wavefront modulation by the wavefront controller, beam splitting by the beam splitter and accurate angle correction by the fine aiming mirror, the light is finally emitted by the optical antenna; the main controller is used for obtaining a deflection angle required by tracking and the movement speed of an opposite-end satellite according to the light spot information on the light spot detector; and according to the deflection angle and the movement speed of the opposite-end satellite, at least one of a wave surface controller, a fine aiming mirror and a rotary table is driven to deflect the emergent laser beam in real time, and whether the wave surface controller increases the beam divergence angle of the emergent laser beam or not is controlled. According to the invention, stable satellite tracking can be realized.

The invention belongs to the technical field of satellite communication, and relates to a global navigation satellite system (GNSS) starting method, which comprises the following steps that: a global navigation satellite system configures starting information for each satellite; dividing the satellites into odd-number groups of satellites and even-number groups of satellites according to the starting time Numbering odd groups of satellites to be started, traversing starting time information of all numbered satellites, and selecting the satellite with the maximum current configuration number from the satellites to be started; starting the satellites at the screening position, judging whether the current satellite is subjected to starting compensation or not, if yes, performing compensation starting on the current satellite according to Doppler information, if not, judging whether starting of the satellites is completed or not, and if starting is not finished, configuring a started satellite mark, and traversing satellite starting time information again; the starting process of the even-number-group satellites is the same as that of the odd-number-group According to the method, the information of at most 16 satellites is configured at a time in the quick start mode, so that the satellite tracking start efficiency is effectively improved.

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.

This invention discloses a high-altitude satellite station and its flight and satellite tracking methods, relating to the field of satellite communication, for achieving beyond-line-of-sight video image acquisition and transmission under obstruction conditions. The high-altitude satellite station includes a fuselage integrating a modem and a main unit; an antenna feed system is mounted on the top of the fuselage via a pitch mechanism; the modem is electrically connected to both the antenna feed system and the main unit; a rotor support is connected to the bottom of the fuselage, with multiple rotors circumferentially connected to the rotor support; a battery support is connected to the bottom of the rotor support; external hardpoints are connected below the rotor support, a BeiDou positioning antenna is mounted on the rotor support, and a flight antenna and a cellular mobile communication antenna are mounted below the rotor support. Through fuzzy inference, a PID control strategy is used for closed-loop control of the high-altitude satellite station's flight, achieving satellite tracking through blind scan, coarse aiming, and tracking phases. This invention enables beyond-line-of-sight video image acquisition and transmission under obstruction conditions, with stable flight and satellite tracking.