A beam pointing high refresh rate airborne satellite communication phased array antenna

Abstract

The application discloses a kind of beam pointing high refresh rate airborne satellite communication phased array antenna, it is characterized in that, including: a line, transceiving radio frequency channel, antenna unit, sub inertial navigation and main control board, after main control board obtains the low-frequency attitude information transmitted from aircraft, low-frequency attitude information is transmitted to sub inertial navigation by the 422 interface between main control board and sub inertial navigation;Sub inertial navigation calculates high-frequency antenna attitude information according to low-frequency attitude information;Sub inertial navigation again transmits high-frequency antenna attitude information to main control board by 422 interface;After main control board obtains antenna attitude information, the beam pointing of high refresh rate is solved, and the phase angle required by each TR component of antenna unit is obtained by the beam pointing of high refresh rate;Main control board transmits phase angle to each TR component by SPI interface, and the beam pointing of entire antenna can be controlled.The application avoids the loss of satellite communication signal in the process of high-speed movement of aircraft.

Description

Technical Field

[0001] This invention relates to the field of phased array antenna technology in satellite communication, and specifically to a beam-directing high refresh rate airborne satellite communication phased array antenna. Background Technology

[0002] Currently, half the world's population still lacks internet access. With technological advancements and societal progress, people demand communication anytime, anywhere, and satellite communication is the best solution to this need. Phased array antennas, employing electronically controlled beam scanning, can quickly achieve beam pointing to track different satellites. Typically, airborne satellite communication phased array antennas calculate the antenna's precise pointing to the Tiantong satellite in real-time based on the aircraft's attitude data, ensuring accurate communication even while the aircraft is in motion. However, because the aircraft's inertial navigation system provides attitude data with a low update frequency (approximately 40-50Hz), and the aircraft is constantly in high-speed motion, the phased array antenna cannot guarantee that the beam will always be pointing at the satellite during tracking. When tracking high-orbit satellites, this problem is not very obvious because the beam is wide and the satellite is stationary relative to the Earth. However, when tracking low-orbit satellites, both the satellite and the aircraft are moving at high speeds. The low update rate of attitude data causes the calculated beam pointing of the phased array antenna to often lag behind the changes in the aircraft's attitude. This can lead to the phased array antenna being unable to effectively track the satellite, resulting in deterioration or interruption of communication signal quality, and thus greatly affecting communication performance. Summary of the Invention

[0003] To address the aforementioned shortcomings in the prior art, this invention provides a beam-directed high refresh rate airborne satellite communication phased array antenna.

[0004] This invention provides a beam-directed high refresh rate airborne satellite communication phased array antenna, comprising: a single-line communication device, a transceiver radio frequency (RF) channel, an antenna element, a sub-inertial navigation system (INS), and a main control board. The single-line communication device is connected to the RF channel to transmit RF signals and supplies power to the RF channel via a cable. The single-line communication device is connected to the main control board to transmit attitude signals and supplies power to the main control board via a cable. The RF channel is connected to the antenna element to transmit RF signals. The main control board is connected to the antenna element via a pin header to supply power to the antenna element and transmit control signals. The main control board is connected to the RF channel to transmit control signals. The main control board is connected to the sub-INS.

[0005] An external access signal, which is synthesized from radio frequency signal, attitude signal and DC power supply, is processed by a multiplexer circuit in the one-line communication to obtain radio frequency signal, attitude signal and DC power supply respectively. The radio frequency signal enters the antenna unit through the transceiver radio frequency channel. The DC power supply is used to power the transceiver radio frequency channel and the main control board through the EMC filter circuit in the one-line communication. The attitude signal is demodulated by the OOK interface circuit of the main control board to obtain low frequency attitude information transmitted from the aircraft.

[0006] After acquiring the low-frequency attitude information from the aircraft, the main control board transmits the low-frequency attitude information to the sub-inertial navigation system via the 422 interface between the main control board and the sub-inertial navigation system.

[0007] The sub-inertial navigation system calculates the high-frequency antenna attitude information based on the low-frequency attitude information; the sub-inertial navigation system then transmits the high-frequency antenna attitude information to the main control board through the 422 interface;

[0008] After obtaining the antenna attitude information, the main control board calculates the high refresh rate beam pointing and then calculates the phase angle required for each TR component of the antenna unit from the high refresh rate beam pointing.

[0009] After the main control board transmits the phase angle to each TR component via the SPI interface, it can control the beam pointing of the entire antenna.

[0010] In some embodiments, the sub-inertial navigation system mainly includes a 3-axis MEMS gyroscope, a 3-axis MEMS accelerometer, a Kalman filter, and an inertial navigation calculation module containing an MCU chip.

[0011] The data from the 3-axis MEMS gyroscope and the 3-axis MEMS accelerometer generate internal attitude information. After lever arm effect compensation, the internal attitude information, together with the low-frequency attitude information of the aircraft, generates attitude error information. The attitude error information is then passed through a Kalman filter and compensated before being fed into the inertial navigation solution module to generate high-frequency antenna attitude information.

[0012] In some embodiments, the main control board includes an antenna tracking module and an angle calculation module.

[0013] After receiving high-frequency antenna attitude information, the main control board combines it with its pre-stored satellite information, uses a satellite selection strategy to determine the satellite to be beam tracked, and obtains the high refresh rate beam direction based on the antenna tracking module.

[0014] The angle calculation module is used to calculate the execution angle of the phased array antenna according to the satellite tracking algorithm, calculate the high refresh rate beam pointing into the phase shift and attenuation values ​​of the TR component, complete the configuration of phase shift and attenuation information through the SPI interface, and output the phase angle required for each TR component of the antenna unit.

[0015] In some embodiments, the main control board includes circuitry using a Zynq-7000 SOC chip for control and data processing, as well as RS422 interface circuitry, LVDS circuitry, OOK interface circuitry, SPI FLASH circuitry, DDR circuitry, level conversion circuitry, power supply circuitry, and clock distribution circuitry implemented using dedicated chips.

[0016] In some embodiments, the sub-inertial navigation system outputs antenna attitude information at a higher update frequency only after the alignment process is completed.

[0017] In some embodiments, the sub-inertial navigation system is also used for,

[0018] The equipment self-test process begins. If the self-test fails, the equipment information of the failed self-test is reported, and the entire workflow is terminated.

[0019] If the self-test is normal, it will start receiving and judging whether the low-frequency attitude information transmitted by the aircraft is valid. If the low-frequency attitude information transmitted by the aircraft is invalid, it will remain in a waiting state until the low-frequency attitude information is valid, and at the same time report that the low-frequency attitude information is invalid.

[0020] If the aircraft attitude information is continuously valid, the sub-inertial navigation system will begin the alignment process, first performing coarse alignment and then fine alignment.

[0021] If the alignment is not yet complete, the validity of the aircraft attitude information is continuously checked during the alignment process. If the low-frequency attitude information is valid, the fine alignment process continues. If the low-frequency attitude information is invalid, the fine alignment process waits for the next frame of valid low-frequency attitude information and reports that the low-frequency attitude information is invalid.

[0022] Once both coarse and fine alignments are completed, the alignment validity is checked. If the alignment is invalid, an alignment failure is reported and the process is terminated.

[0023] If the alignment is successful, the sub-inertial navigation system automatically switches to integrated navigation mode and outputs high-frequency antenna attitude information.

[0024] In some embodiments, the one-line circuit includes an isolation circuit formed by a multiplexer and a power supply circuit formed by an EMC filter.

[0025] In some embodiments, the transceiver radio frequency channel includes a radio frequency receiving and transmitting link formed by attenuators, filters, and amplifiers;

[0026] The transceiver radio frequency channel is used to receive the transmitted signal from the one-line communication and perform power amplification and filtering before transmitting it to the antenna unit, and to receive the received signal from the antenna unit, perform power amplification and filtering before transmitting it to the one-line communication.

[0027] In some embodiments, the antenna element includes an antenna array element, a TR component, and a feed network.

[0028] Antenna unit, used to receive and transmit satellite signals.

[0029] In some embodiments, the beam-directed high refresh rate airborne satellite communication phased array antenna further includes: structural components,

[0030] The entire structure is divided into two main parts: the upper part is the structural base plate, and the lower part is the bottom shell. The antenna unit is mounted on the top of the structural base plate, while the one-wire transmitter, the transceiver RF channel, the sub-inertial navigation system, and the main control board are mounted on the bottom of the structural base plate. The bottom shell is then placed on the structural base plate, enclosing the one-wire transmitter, the transceiver RF channel, the sub-inertial navigation system, and the main control board inside the bottom shell.

[0031] The structural component is used to install the one-line communication, transceiver radio frequency channel, and antenna unit, while also protecting and dissipating heat from them.

[0032] This invention discloses an airborne phased array antenna for satellite communication, specifically a phased array antenna capable of high-speed beam pointing refresh. This solves the problem of degraded communication quality or signal interruption caused by low beam pointing refresh rate during high-speed aircraft movement, while also achieving compatibility with high and low Earth orbit (HEO) communication satellites. Innovatively, a sub-inertial navigation system (INS) is incorporated within the airborne phased array antenna, and a complete operational process including the sub-INS is designed. This obtains high-frequency antenna attitude information, and by providing this high-frequency antenna attitude information during program tracking, the antenna beam pointing refresh rate is improved, rather than directly using the attitude information provided by the aircraft. This increases the overall beam refresh rate of the airborne phased array antenna. The high-speed beam pointing refresh function of the airborne phased array antenna proposed in this invention effectively prevents the loss of satellite communication signals during high-speed aircraft movement. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of a beam-pointing high refresh rate airborne satellite communication phased array antenna provided in an embodiment of the present invention;

[0034] Figure 2 This is a schematic diagram of the sub-inertial navigation principle provided in an embodiment of the present invention;

[0035] Figure 3 This is a flowchart of the overall antenna assembly process provided in an embodiment of the present invention. Detailed Implementation

[0036] Exemplary embodiments will be described more fully below with reference to the accompanying drawings; however, these exemplary embodiments may be embodied in different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and that those skilled in the art will fully understand the scope of the invention.

[0037] Where there is no conflict, the embodiments of the present invention and the features thereof can be combined with each other.

[0038] As used herein, the term “and / or” includes any and all combinations of one or more related enumerated entries.

[0039] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention. The singular forms “a” and “the” used herein are also intended to include the plural forms unless the context clearly indicates otherwise. It will also be understood that when the terms “comprising” and / or “made of” are used in this specification, the presence of the stated features, integrals, steps, operations, elements, and / or components is specified, but the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or groups thereof is not excluded.

[0040] Unless otherwise specified, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art. It will also be understood that terms such as those defined in commonly used dictionaries should be understood to have the meaning consistent with their meaning in the context of the relevant art and the invention, and will not be understood to have an idealized or overly formal meaning unless expressly so defined herein.

[0041] To enable those skilled in the art to better understand the technical solution, the following detailed description of a beam-directed high refresh rate airborne satellite communication phased array antenna provided by the present invention is provided in conjunction with the accompanying drawings.

[0042] like Figure 1 As shown, this embodiment of the invention provides a beam-directed high refresh rate airborne satellite communication phased array antenna, including: a single-line communication device, a transceiver radio frequency (RF) channel, an antenna element, a sub-inertial navigation system (INS), and a main control board. The single-line communication device is connected to the RF channel to transmit RF signals and supplies power to the RF channel via a cable. The single-line communication device is connected to the main control board to transmit attitude signals and supplies power to the main control board via a cable. The RF channel is connected to the antenna element to transmit RF signals. The main control board is connected to the antenna element via a pin header socket to supply power to the antenna element and transmit control signals. The main control board is connected to the RF channel to transmit control signals. The main control board is connected to the sub-INS.

[0043] An external access signal, which is synthesized from radio frequency signal, attitude signal and DC power supply, is processed by a multiplexer circuit in the one-line communication to obtain radio frequency signal, attitude signal and DC power supply respectively. The radio frequency signal enters the antenna unit through the transceiver radio frequency channel. The DC power supply is used to power the transceiver radio frequency channel and the main control board through the EMC filter circuit in the one-line communication. The attitude signal is demodulated by the OOK interface circuit of the main control board to obtain low frequency attitude information transmitted from the aircraft.

[0044] After acquiring the low-frequency attitude information from the aircraft, the main control board transmits the low-frequency attitude information to the sub-inertial navigation system via the 422 interface between the main control board and the sub-inertial navigation system.

[0045] The sub-inertial navigation system calculates the high-frequency antenna attitude information based on the low-frequency attitude information; the sub-inertial navigation system then transmits the high-frequency antenna attitude information to the main control board through the 422 interface;

[0046] After obtaining the antenna attitude information, the main control board calculates the high refresh rate beam pointing and then calculates the phase angle required for each TR component of the antenna unit from the high refresh rate beam pointing.

[0047] After the main control board transmits the phase angle to each TR component via the SPI interface, it can control the beam pointing of the entire antenna.

[0048] Among them, the One-Line Connector integrates the transmission and reception of radio frequency signals, aircraft attitude signals, power supply, etc. into one channel, and simultaneously performs functions such as power supply filtering, spike suppression, and power supply isolation.

[0049] The transceiver radio frequency channel receives the transmitted signal from the one-line communication and performs power amplification, filtering and other processing before transmitting it to the antenna unit. The receiving signal from the antenna unit is amplified and filtered before being transmitted to the one-line communication.

[0050] The antenna unit is capable of receiving and transmitting satellite signals.

[0051] Among them, the sub-inertial navigation system has the function of receiving low-frequency aircraft attitude information in real time, performing integrated navigation calculations, and outputting higher-frequency measurement information such as angular velocity, acceleration, velocity, position, and attitude.

[0052] The main control board is capable of calculating the execution angle of the phased array antenna based on the satellite tracking algorithm, and can convert the execution angle into the phase shift and attenuation values ​​of the TR component, and configure the phase shift and attenuation information through the SPI interface.

[0053] The structural components are equipped with functions such as mounting a one-line communication line, a transceiver radio frequency channel, and an antenna unit, while also providing protection and heat dissipation.

[0054] It should be noted that the OOK circuit uses the TI SN65HVD62 chip, which integrates an AISG transceiver and an active bandpass filter in its receiver. After acquiring the low-frequency attitude information from the aircraft, the main control board transmits the aircraft's attitude information to the sub-INS via the 422 interface between the main control board and the sub-INS.

[0055] This invention discloses an airborne phased array antenna for satellite communication, specifically a phased array antenna capable of high-speed beam pointing refresh. This solves the problem of degraded communication quality or signal interruption caused by low beam pointing refresh rate during high-speed aircraft movement, while also achieving compatibility with high and low Earth orbit (HEO) communication satellites. Innovatively, a sub-inertial navigation system (INS) is incorporated within the airborne phased array antenna, and a complete operational process including the sub-INS is designed. This obtains high-frequency antenna attitude information, and by providing this high-frequency antenna attitude information during program tracking, the antenna beam pointing refresh rate is improved, rather than directly using the attitude information provided by the aircraft. This increases the overall beam refresh rate of the airborne phased array antenna. The high-speed beam pointing refresh function of the airborne phased array antenna proposed in this invention effectively prevents the loss of satellite communication signals during high-speed aircraft movement.

[0056] Currently, antennas used in airborne satellite communication typically have low beam pointing refresh rates. This can easily lead to phased array antennas failing to effectively track satellites during high-speed aircraft movement, resulting in degraded or interrupted communication signal quality and impacting antenna performance. Furthermore, due to their low beam pointing refresh rates, most satellite communication antennas used in civilian or military communications can only track high-Earth orbit (HEO) satellites. The high-beam pointing refresh rate airborne satellite communication antenna provided by this invention can track both HEO and low-Earth orbit (LEO) satellites, achieving compatibility with both systems.

[0057] In some embodiments, such as Figure 2 As shown, the sub-inertial navigation system mainly includes a 3-axis MEMS gyroscope, a 3-axis MEMS accelerometer, a Kalman filter, and an inertial navigation calculation module containing an MCU chip.

[0058] The data from the 3-axis MEMS gyroscope and the 3-axis MEMS accelerometer generate internal attitude information. After lever arm effect compensation, the internal attitude information, together with the low-frequency attitude information of the aircraft, generates attitude error information. The attitude error information is then passed through a Kalman filter and compensated before being fed into the inertial navigation solution module to generate high-frequency antenna attitude information.

[0059] In this embodiment of the invention, due to the lever arm effect between the aircraft's built-in inertial navigation system (INS) and the sub-INS, the sub-INS has displacement relative to the aircraft's INS. The sub-INS integrates a gyroscope and an accelerometer, and the data from the gyroscope and accelerometer can generate internal attitude information, thereby obtaining the error between the internal attitude information and the aircraft's attitude information.

[0060] In some embodiments, the main control board includes an antenna tracking module and an angle calculation module.

[0061] After receiving high-frequency antenna attitude information, the main control board combines it with its pre-stored satellite information, uses a satellite selection strategy to determine the satellite to be beam tracked, and obtains the high refresh rate beam direction based on the antenna tracking module.

[0062] The angle calculation module is used to calculate the execution angle of the phased array antenna according to the satellite tracking algorithm, calculate the high refresh rate beam pointing into the phase shift and attenuation values ​​of the TR component, complete the configuration of phase shift and attenuation information through the SPI interface, and output the phase angle required for each TR component of the antenna unit.

[0063] In some embodiments, the main control board includes circuitry using a Zynq-7000 SOC chip for control and data processing, as well as RS422 interface circuitry, LVDS circuitry, OOK interface circuitry, SPI FLASH circuitry, DDR circuitry, level conversion circuitry, power supply circuitry, and clock distribution circuitry implemented using dedicated chips.

[0064] In some embodiments, the sub-inertial navigation system outputs antenna attitude information at a higher update frequency only after the alignment process is completed.

[0065] In this embodiment of the invention, the alignment process of the sub-inertial navigation system is integrated into the overall antenna operation. The sub-inertial navigation system will output antenna attitude information with a higher update frequency only after the alignment process is completed.

[0066] In some embodiments, such as Figure 3 As shown, after the airborne power supply powers the low-cost, highly covert portable GPS spoofing device, the sub-inertial navigation system is also used for...

[0067] The equipment self-test process begins. If the self-test fails, the equipment information of the failed self-test is reported, and the entire workflow is terminated.

[0068] If the self-test is normal, it will start receiving and judging whether the low-frequency attitude information transmitted by the aircraft is valid. If the low-frequency attitude information transmitted by the aircraft is invalid, it will remain in a waiting state until the low-frequency attitude information is valid, and at the same time report that the low-frequency attitude information is invalid.

[0069] If the aircraft attitude information is continuously valid, the sub-inertial navigation system will begin the alignment process, first performing coarse alignment and then fine alignment.

[0070] If the alignment is not yet complete, the validity of the aircraft attitude information is continuously checked during the alignment process. If the low-frequency attitude information is valid, the fine alignment process continues. If the low-frequency attitude information is invalid, the fine alignment process waits for the next frame of valid low-frequency attitude information and reports that the low-frequency attitude information is invalid.

[0071] Once both coarse and fine alignments are completed, the alignment validity is checked. If the alignment is invalid, an alignment failure is reported and the process is terminated.

[0072] If the alignment is successful, the sub-inertial navigation system automatically switches to integrated navigation mode and outputs high-frequency antenna attitude information.

[0073] In some embodiments, the one-line circuit includes an isolation circuit formed by a multiplexer and a power supply circuit formed by an EMC filter.

[0074] In some embodiments, the transceiver radio frequency channel includes a radio frequency receiving and transmitting link formed by attenuators, filters, and amplifiers;

[0075] The transceiver radio frequency channel is used to receive the transmitted signal from the one-line communication and perform power amplification and filtering before transmitting it to the antenna unit, and to receive the received signal from the antenna unit, perform power amplification and filtering before transmitting it to the one-line communication.

[0076] In some embodiments, the antenna element includes an antenna array element, a TR component, and a feed network.

[0077] Antenna unit, used to receive and transmit satellite signals.

[0078] In some embodiments, the beam-directed high refresh rate airborne satellite communication phased array antenna further includes a structural component, which is divided into two main parts: an upper structural substrate and a lower bottom shell. The antenna unit is mounted on top of the structural substrate, while the one-wire transmitter, transceiver radio frequency channel, sub-inertial navigation system, and main control board are mounted below the structural substrate. The bottom shell is then placed on the structural substrate, enclosing the one-wire transmitter, transceiver radio frequency channel, sub-inertial navigation system, and main control board within the bottom shell.

[0079] The structural component is used to install the one-line communication, transceiver radio frequency channel, and antenna unit, while also protecting and dissipating heat from them.

[0080] Example embodiments have been disclosed herein, and while specific terminology has been used, it is for general illustrative purposes only and should not be construed as limiting. In some embodiments, it will be apparent to those skilled in the art that features, characteristics, and / or elements described in connection with particular embodiments may be used alone, or in combination with features, characteristics, and / or elements described in connection with other embodiments, unless otherwise expressly indicated. Therefore, those skilled in the art will understand that various changes in form and detail may be made without departing from the scope of the invention as set forth by the appended claims.

Claims

1. A beam-directing high refresh rate airborne satellite communication phased array antenna, characterized in that, include: The system includes a one-line connector, a transceiver RF channel, an antenna unit, a sub-inertial navigation system, and a main control board. The one-line connector connects to the transceiver RF channel to transmit RF signals and supplies power to the transceiver RF channel via a cable. The one-line connector connects to the main control board to transmit attitude signals and supplies power to the main control board via a cable. The transceiver RF channel connects to the antenna unit to transmit RF signals. The main control board connects to the antenna unit via a pin header socket to supply power to the antenna unit and transmit control signals. The main control board connects to the transceiver RF channel to transmit control signals. The main control board connects to the sub-inertial navigation system. An external access signal, which is synthesized from radio frequency signal, attitude signal and DC power supply, is processed by a multiplexer circuit in the one-line communication to obtain radio frequency signal, attitude signal and DC power supply respectively. The radio frequency signal enters the antenna unit through the transceiver radio frequency channel. The DC power supply is used to power the transceiver radio frequency channel and the main control board through the EMC filter circuit in the one-line communication. The attitude signal is demodulated by the OOK interface circuit of the main control board to obtain low frequency attitude information transmitted from the aircraft. After acquiring the low-frequency attitude information from the aircraft, the main control board transmits the low-frequency attitude information to the sub-inertial navigation system via the 422 interface between the main control board and the sub-inertial navigation system. The sub-inertial navigation system calculates the high-frequency antenna attitude information based on the low-frequency attitude information; The sub-inertial navigation system then transmits the high-frequency antenna attitude information to the main control board via the 422 interface; After obtaining the antenna attitude information, the main control board calculates the high refresh rate beam pointing and then calculates the phase angle required for each TR component of the antenna unit from the high refresh rate beam pointing. After the main control board transmits the phase angle to each TR component via the SPI interface, it can control the beam pointing of the entire antenna. The sub-inertial navigation system outputs antenna attitude information at a higher update frequency only after the alignment process is completed; Sub-inertial navigation is also used for, The equipment self-test process begins. If the self-test fails, the equipment information of the failed self-test is reported, and the entire workflow is terminated. If the self-test is normal, it will start receiving and judging whether the low-frequency attitude information transmitted by the aircraft is valid. If the low-frequency attitude information transmitted by the aircraft is invalid, it will remain in a waiting state until the low-frequency attitude information is valid, and at the same time report that the low-frequency attitude information is invalid. If the aircraft attitude information is continuously valid, the sub-inertial navigation system will begin the alignment process, first performing coarse alignment and then fine alignment. If the alignment is not yet complete, the validity of the aircraft attitude information is continuously checked during the alignment process. If the low-frequency attitude information is valid, the fine alignment process continues. If the low-frequency attitude information is invalid, the fine alignment process waits for the next frame of valid low-frequency attitude information and reports that the low-frequency attitude information is invalid. Once both coarse and fine alignments are completed, the alignment validity is checked. If the alignment is invalid, an alignment failure is reported and the process is terminated. If the alignment is successful, the sub-inertial navigation system automatically switches to integrated navigation mode and outputs high-frequency antenna attitude information.

2. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, The sub-inertial navigation system mainly includes a 3-axis MEMS gyroscope, a 3-axis MEMS accelerometer, a Kalman filter, and an inertial navigation calculation module containing an MCU chip. The data from the 3-axis MEMS gyroscope and the 3-axis MEMS accelerometer generate internal attitude information. After lever arm effect compensation, the internal attitude information, together with the low-frequency attitude information of the aircraft, generates attitude error information. The attitude error information is then passed through a Kalman filter and compensated before being fed into the inertial navigation solution module to generate high-frequency antenna attitude information.

3. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, The main control board includes an antenna tracking module and an angle calculation module. After receiving high-frequency antenna attitude information, the main control board combines it with its pre-stored satellite information, uses a satellite selection strategy to determine the satellite to be beam tracked, and obtains the high refresh rate beam direction based on the antenna tracking module. The angle calculation module is used to calculate the execution angle of the phased array antenna according to the satellite tracking algorithm, calculate the high refresh rate beam pointing into the phase shift and attenuation values ​​of the TR component, complete the configuration of phase shift and attenuation information through the SPI interface, and output the phase angle required for each TR component of the antenna unit.

4. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, The main control board includes circuits that use the Zynq-7000 SOC chip for control and data processing, as well as RS422 interface circuits, LVDS circuits, OOK interface circuits, SPI FLASH circuits, DDR circuits, level conversion circuits, power supply circuits, and clock distribution circuits implemented using dedicated chips.

5. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, A single-line circuit includes an isolation circuit formed by a multiplexer and a power supply circuit formed by an EMC filter.

6. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, The transceiver radio frequency channel includes attenuators, filters, and amplifiers forming the radio frequency receiving and transmitting links; The transceiver radio frequency channel is used to receive the transmitted signal from the one-line communication and perform power amplification and filtering before transmitting it to the antenna unit, and to receive the received signal from the antenna unit, perform power amplification and filtering before transmitting it to the one-line communication.

7. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, Antenna elements include antenna array elements, TR components, and feed network. Antenna unit, used to receive and transmit satellite signals.

8. The beam-directing high refresh rate airborne satellite communication phased array antenna according to claim 1, characterized in that, Also includes: The structural component is divided into two main parts: the upper part is the structural base plate, and the lower part is the bottom shell. The antenna unit is mounted on the top of the structural substrate, the one-line communication, the transceiver radio frequency channel, the sub-inertial navigation and the main control board are mounted on the bottom of the structural substrate, and then the bottom shell is put on the structural substrate to wrap the one-line communication, the transceiver radio frequency channel, the sub-inertial navigation and the main control board inside the bottom shell. The structural component is used to install the one-line communication, transceiver radio frequency channel, and antenna unit, while also protecting and dissipating heat from them.

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