Near-earth satellite communication device based on reconfigurable intelligent surface

Abstract

The utility model discloses a near-earth satellite communication device based on a reconfigurable intelligent surface. The near-earth satellite communication device comprises a satellite transmit-receive device and an RIS device. The satellite transceiving device comprises a first main control module, and a first power supply module, a first Bluetooth transceiving module and a satellite antenna which are connected with the first main control module; the RIS device comprises an RIS control board and an RIS antenna board connected with the RIS control board; the RIS control board comprises a second main control module, and a second power supply module, a second Bluetooth transceiver module, a GPS module and an attitude calibration unit which are connected with the second main control module; the RIS antenna board is provided with an antenna array composed of a plurality of patch antenna units. By introducing the intelligent reconfigurable metasurface, the system can sense and adapt to a continuously changing communication environment in real time and automatically adjust the configuration of the metasurface, so that the efficiency and stability of signal transmission are improved; the system realizes global coverage through a satellite network, is especially suitable for places such as remote areas, mountainous areas or islands, and the metasurface communication device does not depend on complex infrastructures and can be more flexibly deployed in different areas.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite communication, in particular to a near-earth satellite communication device based on a reconfigurable intelligent surface. Background Art

[0002] Traditional Internet infrastructure has insufficient coverage in remote areas and places with incomplete ground infrastructure. Traditional communication systems are often restricted by the limitations of ground infrastructure and cannot provide efficient and flexible coverage, which requires a high investment in ground infrastructure equipment in remote areas. Therefore, there is an urgent need for a near-Earth satellite communication device based on a reconfigurable smart surface to solve the above problems. Utility Model Content

[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a near-earth satellite communication device based on a reconfigurable intelligent surface.

[0004] The technical solution adopted by an embodiment of the utility model to solve the technical problem is: a near-earth satellite communication device based on a reconfigurable intelligent surface, including a satellite transceiver device and a RIS device;

[0005] The satellite transceiver device includes a first main control module, a first power supply module connected to the first main control module, a first Bluetooth transceiver module and a satellite antenna;

[0006] The RIS device includes a RIS control board and a RIS antenna board connected to the RIS control board. The RIS control board includes a second main control module and a second power supply module connected to the second main control module, a second Bluetooth transceiver module, a GPS module and an attitude calibration unit. The second Bluetooth transceiver module communicates with the first Bluetooth transceiver module. The RIS antenna board is provided with an antenna array composed of a plurality of patch antenna units.

[0007] The satellite transceiver is used to calculate the Starlink ephemeris, and the RIS device is used to receive satellite wireless signals sent by the satellite transceiver and reflect them to the satellite, or receive satellite wireless signals sent by the satellite and reflect them to the satellite transceiver.

[0008] As one of the preferred embodiments of the utility model, the patch antenna unit includes a first patch antenna, a second patch antenna, an H-slot, a radio frequency reflecting surface, and a control module stacked in sequence and connected to the first patch antenna and the second patch antenna, and also includes an insulating layer arranged between two adjacent ones of the first patch antenna, the second patch antenna, the H-slot, and the radio frequency reflecting surface.

[0009] As one of the preferred embodiments of the present utility model, the near-earth satellite communication device based on the reconfigurable smart surface further includes an antenna isolation layer arranged between the second patch antenna and the H-slot.

[0010] As one of the preferred embodiments of the present utility model, the first power supply module and / or the second power supply module is configured as a POE module.

[0011] As one of the preferred embodiments of the present utility model, the attitude calibration unit includes an accelerometer, a gyroscope and a magnetometer, which are used to detect the tilt angle.

[0012] As one of the preferred embodiments of the present utility model, the near-earth satellite communication device based on the reconfigurable smart surface further includes a first status indication module connected to the first main control module.

[0013] As one of the preferred embodiments of the present utility model, the near-earth satellite communication device based on the reconfigurable smart surface further includes a second state indication module connected to the second main control module.

[0014] Beneficial effects of the utility model: a near-earth satellite communication device based on a reconfigurable intelligent surface comprises a satellite transceiver and a RIS device; the satellite transceiver comprises a first main control module and a first power supply module connected to the first main control module, a first Bluetooth transceiver module and a satellite antenna; the RIS device comprises a RIS control board and a RIS antenna board connected to the RIS control board, the RIS control board comprises a second main control module and a second power supply module connected to the second main control module, a second Bluetooth transceiver module, a GPS module and an attitude calibration unit, the second Bluetooth transceiver module communicates with the first Bluetooth transceiver module; a plurality of patch antenna units are arranged on the RIS antenna board The antenna array is composed of a satellite transceiver for solving the Starlink ephemeris, and a RIS for receiving satellite wireless signals sent by the satellite transceiver and reflecting them to the satellite, or receiving satellite wireless signals sent by the satellite and reflecting them to the satellite transceiver. By introducing an intelligently reconfigurable metasurface, the system can sense and adapt to the ever-changing communication environment in real time. The intelligent algorithm analyzes the communication conditions and automatically adjusts the configuration of the metasurface, thereby improving the efficiency and stability of signal transmission. Global coverage is achieved through satellite networks, which is especially suitable for remote areas, mountainous areas, islands and other places. In addition, the metasurface communication device does not rely on complex infrastructure and can be more flexibly deployed in different regions. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0016] Figure 1 A diagram showing the actual use of a near-Earth satellite communication device based on a reconfigurable smart surface;

[0017] Figure 2 This is a schematic diagram of the device distribution of the satellite transceiver mainboard;

[0018] Figure 3 This is a schematic diagram of the device distribution of the RIS control board;

[0019] Figure 4 This is a schematic diagram of the device distribution of the RIS antenna board;

[0020] Figure 5 It is a schematic diagram of the structure of the patch antenna unit;

[0021] Figure 6 This is the working diagram of the IO expansion chip;

[0022] Figure 7 The working flow chart of the near-Earth satellite communication device based on the reconfigurable smart surface in the launch mode;

[0023] Figure 8 This is a workflow diagram of the near-Earth satellite communication device based on reconfigurable smart surface in receiving mode. DETAILED DESCRIPTION

[0024] This section will describe in detail the specific embodiments of the utility model. The preferred embodiments of the utility model are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the utility model, but it cannot be understood as a limitation on the protection scope of the utility model.

[0025] In the description of the present utility model, the meaning of "more than" is more than two, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used for the purpose of distinguishing technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0026] In the description of the present invention, it should be understood that descriptions involving orientation, such as up, down, front, back, left, right, etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0027] In the present invention, unless otherwise clearly defined, the words "set", "install", "connect" and the like should be understood in a broad sense, for example, they can be directly connected or indirectly connected through an intermediate medium; they can be fixedly connected or detachably connected or integrally formed; they can be mechanically connected; they can be the internal connection of two elements or the interaction relationship between two elements. Those skilled in the art can reasonably determine the specific meanings of the above words in the present invention in combination with the specific content of the technical solution.

[0028] Reference Figures 1 to 8 , a near-earth satellite communication device based on a reconfigurable smart surface, comprising a satellite transceiver device 10 and a RIS device 20;

[0029] The satellite transceiver device 10 includes a first main control module 11, a first power supply module 12 connected to the first main control module 11, a first Bluetooth transceiver module 13 and a satellite antenna 14;

[0030] The RIS device 20 includes a RIS control board 21 and a RIS antenna board 22 connected to the RIS control board 21. The RIS control board 21 includes a second main control module 211 and a second power supply module 212 connected to the second main control module 211, a second Bluetooth transceiver module 213, a GPS module 214 and a posture calibration unit 215. The second Bluetooth transceiver module 213 communicates with the first Bluetooth transceiver module 13. The RIS antenna board 22 is provided with an antenna array composed of a plurality of patch antenna units 30.

[0031] The satellite transceiver 10 is used to solve the ephemeris of the star link, and the RIS device 20 is used to receive the satellite wireless signal sent by the satellite transceiver 10 and reflect it to the satellite, or receive the satellite wireless signal sent by the satellite and reflect it to the satellite transceiver 10.

[0032] ① In the present utility model, the satellite transceiver device 10 includes a housing, a mainboard, a switch, a Type-C (debugging and charging function), a POE module (a first power supply module 12) and a satellite antenna 14, wherein a first main control module 11 and a first Bluetooth transceiver module 13 are arranged on the mainboard. The satellite transceiver device 10 is responsible for solving the ephemeris of the Starlink, calculating the antenna pattern after obtaining the ephemeris of the Starlink and sending it to the RIS control board 21 through the first Bluetooth transceiver module 13; the satellite antenna 14 uses a horn antenna, such as Figure 1 As shown; the satellite antenna 14 is used to transmit 13GHz signals and receive 11.7GHz signals. The satellite transceiver 10 is also provided with an LED indicator light (first status indication module 15) to indicate whether the device is working normally, wherein green represents that the device is in standby mode, blue represents that the device is working, and red represents that there is a fault in the device; the POE module can not only provide power supply, but also provide Internet connection for the satellite transceiver.

[0033] ②RIS device 20 includes RIS control board 21, RIS antenna board 22 and housing;

[0034] The RIS control board 21 includes a second main control module 211 (main control chip nRF52833), a second Bluetooth transceiver module 213, an LED indicator light (a second status indication module 216), a GPS module 214, a second power supply module 212 and an attitude calibration unit 215. The second Bluetooth transceiver module 213 is only used for communication between the satellite transceiver device 10 and the RIS control board 21. The LED indicator light indicates whether the device is working normally, where green represents that the device is in standby mode, blue represents that the device is working, and red represents that there is a fault in the device. The GPS module provides the location of the RIS device 20. The second power supply module 212 includes a Type-C debugging interface, a POE module, etc. to provide different power supply methods. The attitude calibration unit 215 includes an accelerometer, a gyroscope and a magnetometer, which can detect the tilt angle of the metasurface, which is helpful for subsequent adjustment of the phase shift of the antenna on the metasurface device.

[0035] The RIS antenna board 22 is preferably provided with 4096 patch antenna units 30 (i.e., a 64x64 antenna array); Figure 5 The patch antenna unit 30 adopts a patch antenna, wherein the first patch antenna 31 is used to reflect the 11.7 GHz signal, the second patch antenna 32 is used to reflect the 13 GHz signal, the insulating layer 36 realizes the electrical insulation between the layers, the antenna isolation layer 37 prevents interference or signal distortion, and protects the antenna structure from external factors; the H slot 33 realizes the function of supporting circular polarization; the control module 35 (front-end chip and feeder) controls the first patch antenna 31 and the second patch antenna 32 respectively, and the radio frequency reflection surface 34 is used to enhance signal reflection; the front-end chip is used to switch the transmission and reception modes of the RIS device 20, that is, to use different antennas; the above-mentioned antenna array position is fixed and distributed at equal intervals, the first patch antenna 31 for reflecting the 11.7 GHz signal has a diameter of 1.24 cm and a wavelength of 25.7 mm; the second patch antenna 32 for reflecting the 13 GHz signal has a diameter of 1.15 cm and a wavelength of 23.1 mm; the antenna spacing is selected as 1.48 cm here.

[0036] Further, refer to Figure 4, 1024 IO expansion chips 40 are arranged on the RIS antenna board 22, each IO expansion chip 40 controls 4 patch antenna units 30 respectively, and the IO expansion chip 40 requires 4 inputs: CS, MISO, MOSI and SCK, and the outputs are 4 CS chip select signals and 12 V. The CS chip select signal output by the IO expansion chip 40 is used by the next-level IO expansion chip 40; the 4 patch antenna units 30 have V1, V2, and V3, so each patch antenna unit 30 can adjust 8 phases of 0°, 45°, 90°, 135°, 180°, 225°, 270°, and 315°; the 4×4 RIS patch antenna unit 30 is used as a minimum unit mode, for example, the 12 V on the IO expansion chip 40-1 controls the phase of the input 0, 1, 64, and 65 patch antenna units 30, and the 12 V on the IO expansion chip 40-2 controls the input 2, 3, 66, and 67 patch antenna units 30, the 12 V control inputs 128, 129, 192, 193 of the IO expansion chip 40-3 control the phase of the patch antenna unit 30, the 12 V control inputs 130, 131, 194, 195 of the IO expansion chip 40-4 control the phase of the patch antenna unit 30, and at the same time, each IO expansion chip 40 can also expand 4 secondary chip select signals as the chip select control of the next level IO expansion chip 40; the first level IO expansion chip is composed of 4 IO expansion chips 40 (for example: 40-1, 40-2, 40-3, 40-4), the CS chip select signal is transmitted from the RIS control board 21 to the first level IO expansion chip 40 through the FPC socket, and the CS chip select signal of the second level IO expansion chip 40 is transmitted through the first level IO expansion chip 40, etc.; the RIS antenna board 22 has a total of 4096 patch antenna units 30, and a total of 1024 expansion chips are required, so five levels of expansion chips 40 (4+4 2 +4 3 +4 4 +4 5 =1364>1024), the expansion method of the third-level, fourth-level, and fifth-level IO expansion chips is the same as the expansion method of the second-level IO expansion chip.

[0037] ③ The distance between the satellite and the RIS device 20 is about 550 km, and the distance between the satellite and the center of the earth is about 6921 km. It can be calculated that the satellite moving speed is 0.06° / s. The elevation angle does not change much when the satellite moves, and the maximum azimuth angle change is 7° / s. Therefore, the adjustment speed of the RIS device 20 can be set to 7° / s, and the maximum adjustable reflection angle is 100°. In order to ensure the quality of the signal, the maximum access time is set to 3 minutes. When the maximum access time is reached, it is necessary to switch to another satellite.

[0038] The satellite transceiver 10 and the RIS device 20 will automatically switch between the transmission and reception modes. The transmission and reception are realized by time division. In one second, about 74 milliseconds are used to transmit data from the satellite transceiver 10 to the RIS device 20 and then reflected to the satellite, and 926 milliseconds are used to transmit data from the satellite to the RIS device 20 and then reflected to the satellite transceiver 10. The 74 milliseconds are divided into 8 transmission time slots, and the 926 milliseconds are divided into 8 reception time slots. The transmission time slots and the reception time slots are alternately arranged within one second.

[0039] The communication device needs to be initialized when used. During the initialization process, the communication device will transmit satellite wireless signals when in the transmitting mode. The satellite wireless signals sent by the satellite transceiver 10 are reflected to the satellite by the RIS device 20. After receiving the satellite wireless signals, the satellite will send the satellite wireless signals of the satellite to the RIS device 20. After waiting for 2 transmitting time slots and 2 receiving time slots, if the gain of the satellite wireless signals received by the satellite transceiver 10 does not meet the standard, it is considered that no connection is established between the communication device and the satellite. At this time, the satellite transceiver 10 will send different antenna patterns to the RIS device 20 to adjust the antenna phase to scan the space until the gain of the satellite wireless signals received by the satellite transceiver 10 is strong enough. It is considered that the communication device and the satellite are successfully connected. After the connection is successfully established, the satellite transceiver 10 is connected to the network to solve the Starlink ephemeris, and the initialization work is completed.

[0040] Data sending process: first, the satellite transceiver device 10 and the RIS device 20 are switched to the transmission mode. The GPS module 214 in the RIS control board 21 will calculate the position of the RIS device 20 and transmit it to the satellite transceiver device 10 through the second Bluetooth transceiver module 213. The satellite transceiver device 10 calculates the antenna pattern according to the Starlink ephemeris and sends it to the second main control module 211 through the first Bluetooth transceiver module 13. The second main control module 211 is connected to the FPC socket. The RIS control board 21 and the RIS antenna board 22 are connected through the FPC socket; the satellite antenna 14 in the satellite transceiver device 10 transmits the satellite wireless signal to the RIS antenna board 22. The RIS antenna board 22 changes the phase of the antenna according to the antenna pattern and finally reflects the satellite wireless signal to the satellite.

[0041] The data receiving process is similar to the data sending process. First, the satellite transceiver 10 and the RIS device 20 are switched to the receiving mode. The GPS module 214 in the RIS control board 21 will calculate the position of the RIS device 20 and transmit it to the satellite transceiver 10 through the second Bluetooth transceiver module 213. The satellite transceiver 10 calculates the antenna pattern according to the Starlink ephemeris and sends it to the second main control module 211 through the first Bluetooth transceiver module 13. The second main control module 211 is connected to the FPC socket. The RIS control board 21 and the RIS antenna board 22 are connected through the FPC socket. The satellite transmits a satellite wireless signal to the RIS antenna board 22. The RIS antenna board 22 changes the phase of the antenna according to the antenna pattern and finally reflects the satellite wireless signal to the satellite transceiver 10.

[0042] The advantages of the utility model are as follows: by introducing an intelligently reconfigurable metasurface, the system can sense and adapt to the changing communication environment in real time, the intelligent algorithm analyzes the communication conditions, and automatically adjusts the configuration of the metasurface, thereby improving the efficiency and stability of signal transmission; global coverage is achieved through satellite networks, which is particularly suitable for remote areas, mountainous areas, islands and other places, and the metasurface communication device does not rely on complex infrastructure and can be more flexibly deployed in different regions.

[0043] As a preferred embodiment of the patch antenna unit 30, the patch antenna unit 30 includes a first patch antenna 31, a second patch antenna 32, an H-slot 33, a radio frequency reflecting surface 34 stacked in sequence, and a control module 35 connected to the first patch antenna 31 and the second patch antenna 32, and also includes an insulating layer 36 arranged between two adjacent ones of the first patch antenna 31, the second patch antenna 32, the H-slot 33 and the radio frequency reflecting surface 34.

[0044] In one embodiment, the near-earth satellite communication device based on the reconfigurable smart surface further includes an antenna isolation layer 37 disposed between the second patch antenna 32 and the H-slot 33 .

[0045] In one embodiment, the first power supply module 12 and / or the second power supply module 212 is configured as a POE module.

[0046] In one embodiment, the attitude calibration unit 215 includes an accelerometer, a gyroscope, and a magnetometer for detecting the tilt angle.

[0047] Of course, the present invention is not limited to the above-mentioned embodiments, and technicians familiar with the field may make equivalent modifications or substitutions without violating the spirit of the present invention. These equivalent modifications and substitutions are all included in the scope defined by the claims of this application.

Claims

1. A near-Earth satellite communication device based on a reconfigurable smart surface, characterized in that: It comprises a satellite transceiver device (10) and a RIS device (20); The satellite transceiver device (10) comprises a first main control module (11), a first power supply module (12) connected to the first main control module (11), a first Bluetooth transceiver module (13) and a satellite antenna (14); The RIS device (20) comprises a RIS control board (21) and a RIS antenna board (22) connected to the RIS control board (21); the RIS control board (21) comprises a second main control module (211) and a second power supply module (212) connected to the second main control module (211), a second Bluetooth transceiver module (213), a GPS module (214) and a posture calibration unit (215); the second Bluetooth transceiver module (213) communicates with the first Bluetooth transceiver module (13); an antenna array composed of a plurality of patch antenna units (30) is arranged on the RIS antenna board (22); The satellite transceiver (10) is used to calculate the ephemeris of the star link, and the RIS device (20) is used to receive the satellite wireless signal sent by the satellite transceiver (10) and reflect it to the satellite, or receive the satellite wireless signal sent by the satellite and reflect it to the satellite transceiver (10).

2. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 1, characterized in that: The patch antenna unit (30) comprises a first patch antenna (31), a second patch antenna (32), an H-slot (33), a radio frequency reflection surface (34) stacked in sequence, and a control module (35) connected to the first patch antenna (31) and the second patch antenna (32), and also comprises an insulating layer (36) arranged between two adjacent ones of the first patch antenna (31), the second patch antenna (32), the H-slot (33) and the radio frequency reflection surface (34).

3. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 2, characterized in that: It also includes an antenna isolation layer (37) arranged between the second patch antenna (32) and the H-slot (33).

4. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 1, characterized in that: The first power supply module (12) and / or the second power supply module (212) are configured as POE modules.

5. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 1, characterized in that: The attitude calibration unit (215) comprises an accelerometer, a gyroscope and a magnetometer, and is used to detect the tilt angle.

6. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 1, characterized in that: It also includes a first status indication module (15) connected to the first main control module (11).

7. The near-earth satellite communication device based on a reconfigurable smart surface according to claim 1, characterized in that: It also includes a second status indication module (216) connected to the second main control module (211).

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