Satellite communication antenna control system and method

Abstract

The invention discloses a satellite communication antenna control system and method, and relates to the technical field of artificial intelligence, and the system comprises a unified measurement and control platform which is used for receiving satellite orbit data; the orbit determination calculation system is used for calculating and generating guide data of each terminal station based on satellite orbit data acquired from the unified measurement and control platform; the distribution system is used for distributing the guide data of each terminal site to the corresponding terminal site; and each terminal station controls the satellite communication antenna to rotate at a corresponding angle according to the guide data, so as to quickly complete satellite alignment and orbit determination calculation system based on the state feedback of the satellite communication antenna and satellite orbit data, and recalculate to generate the guide data of each terminal station so as to realize accurate control of the satellite communication antenna and improve the accuracy of the satellite communication antenna. The problem that accurate satellite alignment and stable control of the antenna cannot be realized in the prior art is solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of artificial intelligence, in particular to a satellite communication antenna control system and method. BACKGROUND

[0002] At present, satellite communication technology is widely used, and satellite fixed stations have become an important supplement to ground communication networks due to their stable and reliable communication links, and play a key role in emergency rescue, communication support in remote areas, etc.

[0003] However, on the one hand, the traditional satellite fixed station antenna in the satellite search mode highly depends on the beacon receiver signal for satellite angle adjustment, which is easily affected by rain, snow weather, local electromagnetic interference and other factors, resulting in invalid mechanical rotation of the antenna, and the antenna cannot accurately align with the satellite, and even a large deviation occurs. At the same time, frequent satellite search scanning aggravates the wear and tear of mechanical parts such as gears, greatly shortening the service life of the equipment. On the other hand, in the fixed mode, the antenna can only re-enter the satellite search tracking mode when the attitude deviates greatly or the preset time period ends, and it is difficult to respond to satellite orbit changes or environmental interference in real time during this period, resulting in large fluctuations in the communication link and seriously affecting the communication quality and stability. In addition, the existing antenna system has deficiencies in the balance between power consumption and satellite alignment accuracy, and it is difficult to meet the user's demand for low-power, high-reliability communication equipment.

[0004] Therefore, it is urgent to develop a high-precision, low-power, high-reliability satellite communication antenna control system to improve the quality and stability of satellite communication. SUMMARY

[0005] Therefore, the present application provides a satellite communication antenna control system and method, which can realize accurate satellite alignment and stable control of the antenna.

[0006] To achieve the above purpose, the present application provides the following technical scheme: A satellite communication antenna control system, comprising a unified measurement and control platform, an orbit calculation system, a distribution system and a terminal system: The unified measurement and control platform is used for receiving satellite orbit data; The orbit calculation system is connected with the unified measurement and control platform, and is used for calculating and generating guiding data of each terminal station based on the satellite orbit data obtained from the unified measurement and control platform; The distribution system is connected with the orbit calculation system, and is used for distributing the guiding data of each terminal station to the corresponding terminal station; The terminal system comprises respective terminal stations respectively connected with the distribution system, for receiving the guide data and controlling the satellite communication antenna to rotate at a corresponding angle to quickly complete the satellite tracking, and returning the calibration data, terminal sensor data and alarm data of the respective terminal stations to the distribution system; The distribution system is used for returning the calibration data, terminal sensor data and alarm data to the orbit calculation system, and the orbit calculation system is further used for recalculating the guide data of the respective terminal stations based on the satellite communication antenna condition feedback and the satellite orbit data, to realize the precise control of the satellite communication antenna.

[0007] Based on the above technical solution, the application can be further improved as follows: Optionally, the terminal system further comprises a servo system, a control sensing system and a sky feed system; The servo system is connected with the distribution system, for receiving the guide data of the respective terminal stations, and issuing angle data to the control sensing system at a corresponding time based on the guide data, to command the satellite communication antenna to track the satellite; The control sensing system is connected with the servo system, for receiving the angle data issued by the servo system, and completing the satellite tracking action based on the angle data; The sky feed system is connected with the control sensing system, for ensuring that the satellite communication antenna has the electrical performance index meeting the satellite tracking requirements.

[0008] Optionally, the servo system comprises an authentication communication module, a data storage module, a data processing module, a data acquisition module and an alarm module; The authentication communication module is used for realizing the bidirectional data transmission; The data storage module is used for storing the guide data, calibration data, terminal sensor data and alarm data; The data processing module is used for deciding whether to track the satellite by using the guide data according to the current condition, and ensuring that the satellite communication antenna angle meets the requirements and the satellite tracking accuracy is ensured by angle comparison and clock synchronization; The data acquisition module is used for acquiring the antenna angle, station longitude, latitude and height, and receiving the terminal sensor data; The alarm module is used for monitoring abnormal data and generating alarm data based on the abnormal data. Optionally, the control sensing system comprises a master control unit, an azimuth motor and an encoder, an azimuth sensor, a pitch motor and an encoder, a pitch sensor, a polarization motor and an encoder, a polarization sensor, a Beidou, an inertial navigation and a beacon machine: The master control unit is configured to receive the guiding data of each terminal station, control the operation of the azimuth motor and encoder, the elevation motor and encoder, and the polarization motor and encoder based on the guiding data, and complete the action of pointing to the satellite; The azimuth sensor, the elevation sensor, and the polarization sensor are configured to collect terminal sensor data and upload the terminal sensor data to the master control unit; The Beidou is configured to collect positioning information of the terminal station and upload the positioning information to the master control unit; The inertial navigation system is configured to monitor the antenna attitude information in real time and upload the antenna attitude information to the master control unit; The beacon machine is configured to configure relevant parameters according to the obtained carrier information, and assist the satellite communication antenna in accurately pointing to the satellite.

[0009] Optionally, the antenna and feeder system comprises a hat feed source parabolic antenna, a circular waveguide rotary joint, and an orthogonal mode sensor assembly. The hat feed source parabolic antenna comprises a main reflecting surface, a waveguide tube, a connecting column, and a secondary reflecting surface. The main reflecting surface and the secondary reflecting surface are configured to focus or emit signals. The waveguide tube is configured to transmit signals. The connecting column is configured to maintain structural stability. The circular waveguide rotary joint is configured to adjust the polarization angle. The orthogonal mode sensor assembly is configured to separate the transceiving port, and realize frequency division multiplexing.

[0010] A satellite communication antenna control system comprises: Receiving satellite orbit data, and calculating and generating guiding data of each terminal station based on the satellite orbit data; Distributing the guiding data of each terminal station to the corresponding terminal station; Each terminal station receives the guiding data, and controls the satellite communication antenna to rotate at a corresponding angle according to the guiding data, so as to quickly complete the pointing to the satellite; Based on the calibration data, the terminal sensor data, and the alarm data returned by each terminal station, and the satellite orbit data, the guiding data of each terminal station is recalculated to realize accurate control of the satellite communication antenna.

[0011] Optionally, the satellite communication antenna control method further comprises: Before starting, the terminal station identification number corresponding to each terminal station is generated in the orbit calculation system in advance; After the terminal station is installed, the terminal station is connected to the distribution system in a bidirectional manner using the corresponding terminal station identification number. The satellite communication antenna is adjusted to the best pointing to the satellite in a manual pointing manner, and the current data is returned to the distribution system for integration. The integrated data is transmitted to the orbit calculation system for calculation to obtain the guiding data of the corresponding terminal station in a subsequent period of time; Transmit the guiding data to the corresponding terminal station through the distribution system; The terminal station judges the guiding data and confirms whether there is a lack of data; If there is a lack of data, the terminal station continues to track by using the guiding data distributed last time, remains the existing angle unchanged if there is no previous guiding data, and re-applies for guiding data; If there is no lack of data, the guiding data is issued, and it is judged whether the guiding data in the terminal database is sufficient, if not, the guiding data is re-applied for after 1 day, and if the guiding data is sufficient, it is confirmed whether the guiding data needs to be issued according to the established judgment mode; After the distribution system obtains the guiding data application information, it is confirmed whether there is the latest guiding data in the system, if there is guiding data, the latest guiding data is issued; If there is no latest guiding data, the distribution system alarms and prompts that the guiding data is insufficient, the orbit calculation system re-provides the guiding data, and the terminal station retains the last guiding data as the guiding data angle for subsequent reference after the guiding data is used up, and continuously re-applies for the guiding data until the latest guiding data is issued.

[0012] Optionally, the satellite communication antenna control method further comprises: The servo system immediately starts to judge whether the guiding data of the terminal station needs to be issued after the guiding data of the terminal station is issued; By comparing the azimuth and elevation angle information returned by the terminal station in real time with the corresponding angle at the current time, if the angle deviation is greater than the set theoretical precision value, the latest guiding data is immediately issued to control the satellite communication antenna to adjust the angle.

[0013] An electronic device comprises a memory, a processor, and a computer program stored on the memory and running on the processor, and the processor implements the steps of the method when executing the computer program.

[0014] A non-transitory computer readable storage medium has a computer program stored thereon, and the computer program is executed by a processor to implement the steps of the method.

[0015] The present application has the following advantages: In the satellite communication antenna control system, the orbit calculation system generates guiding data according to satellite orbit data, and the terminal system can quickly control the antenna to rotate to complete the satellite alignment, greatly shortens the satellite alignment time, improves the satellite alignment efficiency, the terminal system returns calibration, sensing and alarm data, the orbit calculation system re-generates guiding data, realizes real-time dynamic adjustment of the antenna, ensures that the antenna is always accurately aligned with the satellite, and improves the stability and reliability of communication.

[0016] The satellite communication antenna control system in the present application is different from the traditional way of gradually adjusting the angle of the satellite by receiving signals from a beacon machine. The system controls the antenna by integrating multiple data, reducing the influence of interference factors such as rain, snow, and local electromagnetic environment on the antenna aiming at the satellite, and ensuring the accuracy of aiming at the satellite even in harsh environments.

[0017] The satellite communication antenna control system in the present application can quickly and accurately aim at the satellite, avoid ineffective mechanical rotation and frequent satellite searching scanning, reduce the wear of mechanical parts such as antenna gears, prolong the service life of the equipment, and reduce the maintenance cost. BRIEF DESCRIPTION OF DRAWINGS

[0018] For the purpose of illustration and not limitation, the present application will now be described in conjunction with the embodiments and the accompanying drawings, in which: Figure 1 The flowchart of the satellite communication antenna control system in the embodiment of the present application is shown. Figure 2 The schematic diagram of the main components of the satellite communication antenna control system in the embodiment of the present application is shown. Figure 3 The schematic diagram of the electronic equipment entity structure provided by the present application is shown. DETAILED DESCRIPTION

[0019] In order for those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor should be within the scope of protection of the present application.

[0020] It should be noted that the terms "first", "second", and the like in the specification and the above drawings are used to distinguish similar objects, and do not necessarily indicate a specific order or sequence. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present application described herein can be implemented. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, system, product or device including a series of steps or units does not necessarily limit to those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0021] It should be noted that the features of the embodiments of the present application and the embodiments can be combined with each other without conflict. The embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

[0022] Figure 1 Figure 1 is a schematic diagram of the main components of the satellite communication antenna control system in the embodiment of the present application. As shown in the figure, the satellite communication antenna control system 1 provided by the embodiment of the present application comprises a unified measurement and control platform 10, an orbit calculation system 20, a distribution system 30 and a terminal system 40. Figure 1

[0023] The unified measurement and control platform 10 is configured to receive satellite orbit data. The orbit calculation system 20 is connected to the unified measurement and control platform 10 and is configured to calculate and generate guiding data of each terminal site based on the satellite orbit data obtained from the unified measurement and control platform 10. The distribution system 30 is connected to the orbit calculation system 20 and is configured to distribute the guiding data of each terminal site to the corresponding terminal site. The terminal system 40 comprises each terminal site, each of which is connected to the distribution system 30 and is configured to receive the guiding data and control the satellite communication antenna to rotate at a corresponding angle according to the guiding data, to quickly complete the satellite tracking, and to return calibration data, terminal sensor data and alarm data of each terminal site to the distribution system 30. The distribution system 30 returns the calibration data, the terminal sensor data and the alarm data to the orbit calculation system 20, and the orbit calculation system 20 recalculates and generates the guiding data of each terminal site based on the satellite communication antenna condition feedback and the satellite orbit data, to realize the precise control of the satellite communication antenna.

[0024] The terminal system 40 further comprises a servo system, a control sensing system and a sky feed system. The servo system is connected to the distribution system 30 and is configured to receive the guiding data of each terminal site, to issue angle data to the control sensing system at a corresponding time based on the guiding data, to command the satellite communication antenna to track the satellite, and to automatically enter the fixed station mode after the terminal site completes the satellite tracking. The specific design goals of the servo system are as follows: In terms of functional indicators, the servo system has an automatic tracking function, and the tracking accuracy is not less than 1 / 8 of the half-power beam width. The servo system has an automatic leveling and calibration function, and can accurately align the satellite even in the case of ground offset. The servo system has a fixed station mode, and the motor does not rotate after the terminal site completes the satellite tracking at a regular time. The servo system has a power-off protection function, and the original data will not be lost after power-off and restart. The servo system has a fault alarm function, and the fault will be displayed on the terminal and the network management when it occurs. ​With remote monitoring and management functions, the network management system can monitor the state information of the antenna, can view the state of the site in real time, and can remotely manage the antenna. With manual adjustment function, the azimuth, elevation and polarization angle of the antenna can be manually adjusted through the antenna controller, with minimum step of 0.1 degree.

[0025] Environmental indicators: The equipment has good anti-seismic ability, and the terminal has the ability to resist 9 intensity earthquakes, ensuring that the site can still be used normally after an earthquake. Operating temperature range: -10~50℃; Storage temperature range: -50~70℃; Relative humidity range: 0%~95%; Altitude range: 5000 meters; The equipment has perfect lightning protection grounding to avoid safety accidents.

[0026] Other indicators: The equipment supports DC power supply, the power supply range is -40~-60V; the size of the indoor equipment is designed to meet the specification requirements, and it can be installed on a 19-inch standard rack. The control sensing system is connected with the servo system, used for receiving angle data issued by the servo system, and completing star action based on the angle data. The antenna feeder system is connected with the control sensing system, used for ensuring that the satellite communication antenna has electrical performance indicators that meet the requirements of the star.

[0027] The design requirements of the antenna feeder system and the control sensing system are as follows: Performance indicators: Antenna aperture: 1.0 meters; Working surface type: carbon fiber material is required; Operating frequency: receive 10.7-12.75GHz, transmit 13.75-14.5GHz; Transmit gain (including radome): ≥41.2dBi@14.25GHz. Not less than 40.5dBi in the whole operating frequency range; Receive gain (including radome): ≥40.2dBi@12.5GHz. Not less than 38.5dBi in the whole operating frequency range; Standing wave: <1.5; Cross-polarization isolation: ≥30dB in the main axis direction; Port isolation: >85dB (including blocking filter); First side lobe: ≤-14dB; The envelope line of the antenna surface design meets the standard: the peak value of 90% of the total side lobe shall not exceed the value of 32-25lgΦdBi; α≤Φ≤20°; Where: Φ is the angle between the deviation direction and the main beam axis. Unit: degrees. α is taken as 100(λ / D), where λ is the carrier wavelength and D is the antenna diameter; Radome transmission loss: ≤0.5dB; Feed insertion loss: ≤0.35dB; Antenna-to-LNB insertion loss: ≤0.35dB; Noise: On a clear day, at an elevation angle of 20°, ≤47K; Polarization mode: orthogonal linear polarization; Maximum off-axis EIRP spectral density: Within a 3° north and 3° south radius of the geostationary satellite orbit, at the specified Φ values, the EIRP spectral density of the maximum off-axis emission shall not exceed the following values: 33-25lgΦdBW / 40kHz 2°≤Φ≤7°; 12dBW / 40kHz 7°<Φ≤9.2°; 36-25lgΦdBW / 40kHz 9.2°<Φ≤48°; -6dBW / 40kHz 48°<Φ≤180; Furthermore, the cross-polarization component at the specified Φ value shall not exceed the following values: 23-25lgΦdBW / 40kHz 2°≤Φ≤7°; 2dBW / 40kHz 7°<Φ≤9.2°; Where Φ is the angle between the deviation direction and the beam's main axis. Unit: degrees. EIRP transmit stability: less than ±2dB / day; Environmental indicators: The equipment is equipped with a fairing with an IP66 protection rating or higher and has good rain and snow protection capabilities. In rainy or snowy weather, it will not have too much impact on outdoor equipment or affect its subsequent use. The equipment has good wind resistance and can operate normally under a relative wind speed of 21 m / s and will not be damaged under a relative wind speed of 35 m / s. Operating temperature range (outdoor): -40°C to +60°C; Storage temperature range: -50°C to +70°C; Relative humidity range (outdoor): 0% to 100%; Altitude range: 5000 meters; Rainfall: greater than 100 mm / hour; Outdoor equipment is waterproof, moisture-proof, salt spray-proof, and mildew-proof. Other specifications: Supports DC negative 48V power supply; The power consumption of the equipment should be kept as low as possible, with the total power consumption of the product ≤120W (excluding the power amplifier); The device is designed to be matched with an antenna stand column, the antenna stand column is higher than 0.8 meters, and can be further installed The angle fixing function is provided, and the original angle to the star is kept unchanged when power is off. The servo system comprises an authentication communication module, a data storage module, a data processing module, a data acquisition module and an alarm module; the authentication communication module is used for realizing bidirectional data transmission. According to the terminal identification number and the back-end distribution system 30, a bidirectional identification mode is established, on the one hand, the terminal receives the guide data belonging to the terminal, and on the other hand, the terminal transmits the state data (site longitude and latitude, alarm data and calibration data) of the terminal to the distribution system 30.

[0028] A 4 / 5G communication module is built in the ACU, and bidirectional data transmission with the back-end distribution system 30 is realized through the 4 / 5G link.

[0029] The terminal sends a heartbeat instruction to the platform every 10 seconds, which is used to assist the platform to confirm whether the terminal is online.

[0030] When the distribution system 30 applies for data information, the terminal can transmit the site information of the time period required by the distribution system 30; When the calibration data is set, the calibration data can be manually transmitted back; After automatic star alignment is completed, the calibration data can be automatically transmitted back; When an alarm is found and the alarm is eliminated, the alarm data and the current state data (actual azimuth, elevation, polarization angle data, tilt angle data, longitude and latitude data) of the site can be immediately and automatically transmitted back; The current sensor data can be transmitted back regularly according to the time period (every 1 minute, 10 minutes, 30 minutes, 1 hour) set by the platform; Real-time acquisition of each sensor data, comparison of the data information of each sensor at this time with the data information transmitted back last time to confirm the fluctuation, and transmission of the data at this time when the fluctuation is greater than the set threshold.

[0031] When the terminal data is insufficient or the received data is incomplete, the terminal actively applies for data to the distribution system 30.

[0032] The configuration file issued from the main station system can be received, and the terminal configuration can be automatically upgraded.

[0033] The data storage module is used for storing guide data, calibration data, terminal sensor data and alarm data; the guide data is stored: the guide data issued by the distribution system 30 is stored, the original guide data and the new guide data are combined and updated as new guide data, and the data is stored.

[0034] Store alarm data: store the alarm abnormal information generated during the operation of the site, set the total storage number, and update continuously.

[0035] Store terminal sensor data: store the current sensor data information of the site, and the information is retained for 1 month. Data exceeding 1 month is overlapped.

[0036] The data processing module is used to determine whether to use guiding data to star according to the current situation, and to ensure that the satellite communication antenna angle meets the requirements and the star accuracy by angle comparison and clock synchronization. By comparing the real-time returned azimuth, pitch angle information and the corresponding angle at the current time, if the angle deviation is greater than the set theoretical precision value, the latest angle data is immediately issued to control the adjustment of the angle.

[0037] The theoretical precision value is obtained as follows: According to the existing design target, in order to meet the tracking accuracy which can be less than 1 / 8 of the received half-power beam width, the received half-power beam width of a 1-meter antenna is: Theoretical precision value = 1 / 8 of the received half-power beam width = 1.53 / 8 = 0.19° Clock synchronization: the guiding data contains the azimuth and pitch angle information of each time period. By collecting the current Internet clock with the 4 / 5G module, the current time point is confirmed, and the current azimuth and pitch angle are determined.

[0038] The data collection module is used to collect antenna angle, site latitude and longitude, and inclination angle, and receive terminal sensor data. The alarm module is used to monitor abnormal data and generate alarm data based on the abnormal data.

[0039] When an alarm is found, the panel will display an alarm prompt.

[0040] Guiding data alarm: the distribution system 30 checks the issued guiding data to confirm whether the guiding data is complete and accurate.

[0041] Guiding data shortage alarm: when the guiding data stored in the data storage module is less than 1 day, a guiding data shortage alarm will be prompted.

[0042] Inclination alarm: the current antenna attitude information is monitored in real time by the inertial navigation system. When the antenna attitude changes, an inclination alarm is prompted.

[0043] Sensor interruption alarm: when the data collection module cannot collect certain sensor data, the terminal prompts a corresponding sensor interruption alarm.

[0044] The R&D product is responsible for communicating with the modem and interacting with the protocol. The device feeds back the state of the antenna and the geographic position information at this time to the modem, and receives the carrier, satellite position and other parameter information fed back by the cat at this time, and controls the antenna to adjust the polarization.

[0045] According to the carrier information obtained from the modem, the carrier frequency, bandwidth, etc. of the beacon machine are configured.

[0046] Panel display control: responsible for displaying the collected latitude and longitude data and the information of the satellite it is against. The rotation of the antenna azimuth, elevation and polarization can be manually controlled by pressing the keys. The menu can be entered by pressing the keys to upload the calibrated angle information. The control sensing system includes a master control unit, an azimuth motor and encoder, an azimuth sensor, an elevation motor and encoder, an elevation sensor, a polarization motor and encoder, a polarization sensor, a Beidou, an inertial navigation and a beacon machine. The master control unit is used to receive the guidance data of each terminal site, control the operation of the azimuth motor and encoder, the elevation motor and encoder and the polarization motor and encoder based on the guidance data, and complete the satellite tracking action. The master control unit is configured with an automatic tracking system, which can control the antenna to track the satellite according to the reception of the beacon machine when needed.

[0047] The azimuth sensor, the elevation sensor and the polarization sensor are used to collect terminal sensor data and upload it to the master control unit. The Beidou is used to collect the positioning information of the terminal site and upload it to the master control unit. The inertial navigation is used to monitor the antenna attitude information in real time and upload it to the master control unit. The inclination angle at this time is confirmed through the change of the attitude information and the guidance data. The beacon machine is used to configure related parameters according to the obtained carrier information to assist the satellite communication antenna in accurate satellite tracking.

[0048] The antenna and feeder system includes a hat feeder parabolic antenna, a circular waveguide rotary joint and an orthogonal mode sensor assembly. The hat feeder ring focus parabolic antenna includes a main reflecting surface, a waveguide tube, a connecting column and a secondary reflecting surface. The main reflecting surface and the secondary reflecting surface are used for focusing or emitting signals. The waveguide tube is used for transmitting signals. The connecting column is used to maintain structural stability. The circular waveguide rotary joint is used to adjust the polarization angle. The orthogonal mode sensor assembly is used to separate the transmit and receive ports to realize frequency division multiplexing.

[0049] The LNB amplifies the Ku band signal and converts the frequency to an intermediate frequency input to the modem. The modem provides a signal to the BUC, which converts the intermediate frequency signal to the Ku band and amplifies it, and transmits it to the satellite through the OMT, circular waveguide rotary joint and antenna system.

[0050] The tracking algorithm logic of the station is as follows: Before opening the station, the terminal station identification number corresponding to each terminal station is generated in the orbit calculation system 20 in advance; After the terminal station is installed, the terminal station is connected with the distribution system 30 using the corresponding terminal station identification number, at which time the serial number is bound to the device by default, and the serial number cannot be used for authentication operations unless the system is unbound; by manually pointing the satellite, the satellite communication antenna is adjusted to the best pointing, and the current data (time, azimuth, elevation angle, and local latitude and longitude information) is returned to the distribution system 30 for integration (the data can be returned regularly and multiple times for pointing to improve data reliability), and the integrated data is transmitted to the orbit calculation system 20 for calculation to obtain the guidance data (azimuth and elevation angle data corresponding to the time of the antenna) for the terminal station in the subsequent period of time; The guidance data is transmitted to the corresponding terminal station through the distribution system 30; The terminal station determines whether the guidance data is missing (checked by a check code); If there is a missing, the terminal station will continue to track using the last distributed guidance data, and if there is no previous guidance data, the existing angle will remain unchanged, and guidance data will be re-applied; If there is no missing, the guidance data is issued, and it is determined whether the guidance data in the terminal database is sufficient, if not, the guidance data is re-applied, and if the guidance data is sufficient, it is determined whether the guidance data needs to be issued according to the established determination method; After the distribution system 30 obtains the guidance data application information, it is determined whether there is the latest guidance data in the system, if there is guidance data, the latest guidance data is issued; If there is no latest guidance data, the distribution system 30 alarms and prompts that the guidance data is insufficient, and the orbit calculation system 20 provides guidance data again, and the terminal station retains the last guidance data as the reference guidance data angle for subsequent reference, and continuously re-applies guidance data until the latest guidance data is issued.

[0051] Whether to perform antenna tracking logic: On the one hand, to ensure that the terminal can immediately recover after the antenna angle deviates, and also to avoid repeated issuance or meaningless issuance causing the antenna to move frequently, the servo system immediately starts to determine whether to issue data after completing the issuance of data. The determination method is to determine whether the deviation between the current actual azimuth and elevation angle and the theoretical angle calculated at the current time is greater than 1 / 8 of the half-power beam width. Assuming that the deviation value is σ, the formula for calculating σ is as follows: The current actual azimuth and elevation angle information are obtained by real-time acquisition of the antenna azimuth and elevation angle information returned by the control sensor system.

[0052] The theoretical value is the current guiding data value.

[0053] Site opening process: Before the official launch, the terminal devices need to be configured in the distribution system 30 in advance to generate serial numbers for each terminal product. After the installation is completed on-site, the installers log in to the terminal through the front panel and enter the identification number of the site to bind the terminal to the site configured on the platform and complete the authentication. For the first time the station is opened, the antenna needs to be manually controlled to complete at least one satellite alignment, and the local accurate latitude, longitude and altitude information needs to be input into the terminal. This information, together with the existing angle and time information, will form calibration data for transmission back. The distribution system 30 stores the calibration data and uploads it to the orbit determination calculation system 20; The orbit determination calculation system 20 uses satellite orbit determination data and orbit control data, combined with local latitude and longitude, and deviation data confirmed from calibration data, to accurately determine the terminal's accurate azimuth and pitch angle in subsequent times; Daily operation process: During daily tracking, whenever the terminal receives data, it will perform a self-check to confirm whether the data is complete. If it is incomplete, it will continue to use the previous guidance data or keep the current angle unchanged, and apply for new guidance data from the distribution system 30. If the boot data is complete, then this boot data will be used as the new boot data, and subsequent control will use the new boot data; During routine tracking, the terminal will continuously determine whether there is more than one day of guidance data remaining (the time can be modified). If there is insufficient data, it will request guidance data. At the same time, when there is no guidance data, the last set of angles will be kept as the subsequent guidance angle value. During routine tracking, the terminal will collect the status of the field sensors in real time, combine the guidance data, and accurately calculate the azimuth and elevation angle that the antenna should be in at the current time. By checking whether the deviation between the actual and theoretical values ​​is greater than the set value, it will confirm whether angle adjustment is required.

[0054] Attitude calibration function: The antenna attitude calibration function focuses on how to confirm the tilt angle and how to calculate the required azimuth and elevation angles of the antenna using the tilt angle and guide data.

[0055] The inclination condition can be obtained by installing an inertial navigation system or an inclinometer, when the inertial navigation system or the inclinometer confirms that the antenna posture is inclined, the terminal can immediately re-calibrate in a carrier or beacon tracking mode. After calibration, the calibration data is returned to the distribution system 30, and the distribution system 30 transmits the calibration data to the orbit calculation system 20 for recalculation and distribution. Before receiving new guidance data, the terminal keeps the angle unchanged after automatic pointing, and no longer listens to the old guidance data.

[0056] The specific operation mode of the terminal antenna is as follows: The terminal real-time collects the current terminal sensor state, and confirms the ground inclination condition. When the antenna inclination is sensed, the automatic tracking mode is immediately adopted, and the guidance data is no longer issued until the antenna is locked. After the pointing is completed, the data at this time is returned to the distribution system 30 as calibration data. After the distribution system 30 receives the calibration data, it is transmitted to the orbit calculation system 20 for calculation by the orbit calculation system 20. After the calculation is completed, the new guidance data is distributed to the terminal system 40. When there is no inclination or the new guidance data has been completely received, the current angle data of each axis is collected in real time, and whether the angle of the guidance data issued and the existing angle is greater than the set threshold value is compared. If it is greater than the set threshold value, the guidance data is issued, and the antenna is controlled to rotate, and then returns to 1 to re-detect and determine. If it is not greater than the set threshold value, it returns to 1 to re-detect and determine, so as to ensure that the antenna can always be aligned with the satellite.

[0057] The inclination after the ground inclination can be realized by the inertial navigation and the inclinometer, and the theoretical pointing after the earthquake can be realized. However, the inclinometer has uncertainty in time progress and interface development. In terms of time progress, the existing manufacturer's antenna and control sensor system can be directly purchased by using the inertial navigation, the mature product is less changed, the time progress of product research and development can be ensured, and the adjustment of the inclinometer needs to be adapted by the antenna manufacturer, the structure needs to be redesigned, the internal circuit board needs to be adjusted, and the time is long and uncertain.

[0058] In summary, the inclination in the application is still determined by the inertial navigation.

[0059] Figure 2 The flowchart of the satellite communication antenna control system in the embodiment of the application is shown in Figure 2 The satellite communication antenna control system provided by the embodiment of the application includes the following steps S101 to S104.

[0060] S101, receiving satellite orbit data, and calculating and generating guidance data of each terminal station based on the satellite orbit data.

[0061] S102, distribute the guiding data of each terminal station to the corresponding terminal station.

[0062] S103, each terminal station receives the guiding data and controls the satellite communication antenna to rotate at the corresponding angle according to the guiding data, so as to quickly complete the pointing.

[0063] S104, based on the calibration data, terminal sensor data and alarm data and satellite orbit data returned by each terminal station, the guiding data of each terminal station is recalculated and generated to realize accurate control of the satellite communication antenna.

[0064] The satellite communication antenna control method further comprises: Before starting, the terminal station identification number corresponding to each terminal station is generated in the orbit calculation system in advance; After the terminal station is installed, the terminal station is connected to the distribution system using the corresponding terminal station identification number; the satellite communication antenna is adjusted to the best pointing by manual pointing, and the current data is returned to the distribution system for integration, and the integrated data is transmitted to the orbit calculation system for calculation to obtain the guiding data of the corresponding terminal station in the subsequent period of time; The guiding data is transmitted to the corresponding terminal station through the distribution system; The terminal station judges the guiding data to confirm whether there is a lack of missing; If there is a lack of missing, the terminal station will continue to track using the guiding data distributed last time, and if there is no previous guiding data, the existing angle will remain unchanged, and the guiding data will be re-applied; If there is no lack of missing, the guiding data will be issued, and it will be determined whether the guiding data in the terminal database is sufficient, if it is insufficient after 1 day, the guiding data will be re-applied, and if the guiding data is sufficient, it will be determined whether the guiding data needs to be issued according to the established judgment method; After the distribution system obtains the guiding data application information, it is confirmed whether there is the latest guiding data in the system, if there is guiding data, the latest guiding data will be issued; If there is no latest guiding data, the distribution system will alarm and prompt that the guiding data is insufficient, the orbit calculation system will provide the guiding data again, and the terminal station will keep the last guiding data as the reference guiding data angle for the subsequent reference, and will continuously re-apply the guiding data until the latest guiding data is issued.

[0065] The satellite communication antenna control method further comprises: The servo system immediately starts to determine whether the guiding data of the terminal station needs to be issued after the guiding data of the terminal station is issued; By comparing the azimuth and elevation angle information returned by the terminal station in real time with the corresponding angle at the current time, if the angle deviation is greater than the set theoretical precision value, the latest guidance data is immediately issued to control the satellite communication antenna to adjust the angle.

[0066] Figure 3 An electronic device physical structure diagram provided by the embodiment of the present application is shown in Figure 3 The electronic device 50 includes: a processor 501, a memory 502 and a bus 503; The processor 501 and the memory 502 communicate with each other through the bus 503. The processor 501 is configured to invoke program instructions in the memory 502 to execute the method provided by each method embodiment and execute the method provided by the embodiment of the present application.

[0067] The embodiment provides a non-transitory computer readable storage medium, which stores computer instructions, and the computer instructions cause a computer to execute the method provided by the embodiment of the present application.

[0068] Those skilled in the art can understand that all or part of the steps of the above method embodiments can be completed by program instruction related hardware, and the foregoing program can be stored in a computer readable storage medium, and the program executes the steps of the above method embodiments when executed; and the foregoing storage medium includes ROM, RAM, magnetic disc or optical disc and various storage media that can store program codes.

[0069] The above detailed description does not constitute a limitation on the protection scope of the present application. Those skilled in the art should understand that various modifications, combinations, sub-combinations and substitutions can occur depending on design requirements and other factors. Any modification, equivalent replacement and improvement within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A satellite communication antenna control system, characterized by, The unified measurement and control platform, the orbit calculation system, the distribution system and the terminal system are comprised: The unified measurement and control platform is used for receiving satellite orbit data; The orbit calculation system is connected with the unified measurement and control platform, and is used for calculating and generating guiding data of each terminal site based on the satellite orbit data obtained from the unified measurement and control platform; The distribution system is connected with the orbit calculation system, and is used for distributing the guiding data of each terminal site to the corresponding terminal site; The terminal system comprises each terminal site, each of which is connected with the distribution system, and is used for receiving the guiding data, and controlling the satellite communication antenna to rotate at a corresponding angle according to the guiding data, so as to quickly complete the satellite tracking, and simultaneously, the calibration data, the terminal sensor data and the alarm data of each terminal site are transmitted back to the distribution system; The distribution system is used for transmitting the calibration data, the terminal sensor data and the alarm data back to the orbit calculation system, and the orbit calculation system is further used for recalculating and generating the guiding data of each terminal site based on the condition feedback of the satellite communication antenna and the satellite orbit data, so as to realize the accurate control of the satellite communication antenna.

2. The satellite communication antenna control system of claim 1, wherein, The terminal system further comprises a servo system, a control sensing system and a sky feed system; The servo system is connected with the distribution system, and is used for receiving the guiding data of each terminal site, and issuing angle data to the control sensing system at a corresponding time based on the guiding data, so as to command the satellite communication antenna to track the satellite; The control sensing system is connected with the servo system, and is used for receiving the angle data issued by the servo system, and completing the satellite tracking action based on the angle data; The sky feed system is connected with the control sensing system, and is used for ensuring that the satellite communication antenna has the electrical performance index meeting the satellite tracking requirements.

3. The satellite communication antenna control system of claim 2, wherein, The servo system comprises an authentication communication module, a data storage module, a data processing module, a data acquisition module and an alarm module; The authentication communication module is used for realizing the bidirectional data transmission; The data storage module is used for storing the guiding data, the calibration data, the terminal sensor data and the alarm data; The data processing module is used for deciding whether to track the satellite by using the guiding data according to the current condition, and ensuring that the angle of the satellite communication antenna meets the requirements and the satellite tracking accuracy is ensured by angle comparison and clock synchronization; The data acquisition module is used for acquiring the antenna angle, the site longitude, latitude and height, the inclination angle, and receiving the terminal sensor data; The alarm module is used for monitoring abnormal data, and generating alarm data based on the abnormal data.

4. The satellite communication antenna control system of claim 3, wherein, The control sensing system comprises a master control unit, an azimuth motor and an encoder, an azimuth sensor, an elevation motor and an encoder, an elevation sensor, a polarization motor and an encoder, a polarization sensor, a Beidou, an inertial navigation and a beacon: The master control unit is used for receiving the guiding data of each terminal site, controlling the azimuth motor and the encoder, the elevation motor and the encoder and the polarization motor to operate based on the guiding data, and completing the satellite tracking action; The azimuth sensor, the elevation sensor and the polarization sensor are used for acquiring the terminal sensor data, and uploading the terminal sensor data to the master control unit; The Beidou is used for collecting positioning information of terminal sites and uploading to the master control unit; The inertial navigation is used for monitoring antenna attitude information in real time and uploading to the master control unit; The beacon machine is used for configuring relevant parameters according to the obtained carrier information, and assisting the satellite communication antenna in accurate pointing.

5. The satellite communication antenna control system of claim 4, wherein, The antenna feeder system comprises a hat feeder source parabolic antenna, a circular waveguide rotary joint and an orthogonal mode sensor assembly; The hat feeder source parabolic antenna comprises a main reflecting surface, a waveguide tube, a connecting column and a secondary reflecting surface, the main reflecting surface and the secondary reflecting surface are used for focusing or emitting signals, the waveguide tube is used for transmitting signals, and the connecting column is used for maintaining structural stability; the circular waveguide rotary joint is used for adjusting the polarization angle; The orthogonal mode sensor assembly is used for separating the transmitting and receiving ports to realize frequency division multiplexing.

6. A method of controlling a satellite communication antenna, characterized by, It comprises: Receiving satellite orbit data, calculating and generating guidance data of each terminal site based on the satellite orbit data; Distributing the guidance data of each terminal site to the corresponding terminal site; Each terminal site receives the guidance data and controls the satellite communication antenna to rotate at the corresponding angle according to the guidance data, so as to quickly complete pointing; Based on the calibration data, terminal sensor data and alarm data returned by each terminal site and the satellite orbit data, the guidance data of each terminal site is recalculated to realize accurate control of the satellite communication antenna.

7. The method of claim 6, wherein, The satellite communication antenna control method further comprises: Before starting, the terminal site identification number corresponding to each terminal site is generated in the orbit calculation system in advance; After the terminal site is installed, the terminal site is connected to the distribution system in both directions using the corresponding terminal site identification number; by manually pointing, the satellite communication antenna is adjusted to the best pointing, and the current data is returned to the distribution system for integration, and the integrated data is transmitted to the orbit calculation system for calculation to obtain the guidance data of the corresponding terminal site in the subsequent period of time; The guidance data is transmitted to the corresponding terminal site through the distribution system; The terminal site judges the guidance data to confirm whether there is a lack of data; If there is a lack of data, the terminal site will continue to track using the guidance data distributed last time, and if there is no previous guidance data, the existing angle will remain unchanged, and guidance data will be re-applied; If there is no lack of data, the guidance data will be issued, and it will be determined whether the guidance data in the terminal database is sufficient, if not, the guidance data will be re-applied, and if the guidance data is sufficient, it will be determined whether the guidance data needs to be issued according to the established judgment method; After the distribution system obtains the guidance data application information, it is determined whether there is the latest guidance data in the system, if there is the guidance data, the latest guidance data will be issued; If there is no latest guidance data, the distribution system will alarm and prompt that the guidance data is insufficient, the orbit calculation system will provide guidance data again, and the terminal site will keep the last guidance data as the reference guidance data angle after using the guidance data, and will continuously re-apply the guidance data until the latest guidance data is issued.

8. The method of claim 6, wherein the method further comprises: The satellite communication antenna control method further comprises: The servo system immediately restarts determining whether to perform the terminal station guiding data issuing after completing the terminal station guiding data issuing; By comparing the azimuth and elevation angle information returned by the terminal station in real time with the corresponding angle at the current time, if the angle deviation is greater than the set theoretical precision value, the latest guiding data is immediately issued to control the satellite communication antenna to adjust the angle.

9. An electronic device comprising a memory, a processor, and a computer program stored on the memory and running on the processor, characterized in that, The computer program comprises the method of any one of claims 6 to 8.

10. A non-transitory computer readable medium having stored thereon a computer program, characterized in that, The computer program comprises the method of any one of claims 6 to 8.

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