CN215897730U - Satellite communication equipment - Google Patents

Abstract

The embodiment of the utility model discloses satellite communication equipment, which comprises a first communication system, a second communication system, a main control module, a power supply module and a man-machine interaction module, wherein the bandwidth of the first communication system is greater than that of the second communication system, and the first communication system and the second communication system respectively respond to different satellites; the first communication system is connected with the first communication end of the main control module, the second communication system is connected with the second communication end of the main control module, the power input end of the main control module is connected with the power module, and the third communication end of the main control module is connected with the human-computer interaction module. According to the technical scheme provided by the embodiment of the utility model, the first communication system and the second communication system with different bandwidths are integrated, and different communication systems can be selected for communication according to actual requirements, so that the respective advantages and the complementary disadvantages of the first communication system and the second communication system are fully exerted, and the safety and the reliability of the satellite communication equipment are improved.

Description

Satellite communication equipment

Technical Field

The embodiment of the utility model relates to the technical field of satellite communication, in particular to satellite communication equipment.

Background

With the rapid development of satellite communication technology, emergency communication means provided by a satellite system are widely applied to scenes of field survival, rescue work and the like.

The satellite communication equipment in the prior art has the advantages of large volume, poor portability and operability, weak environmental adaptability, and incapability of being normally used in certain specific environments, thereby greatly reducing the safety and reliability of the equipment.

SUMMERY OF THE UTILITY MODEL

The embodiment of the utility model provides satellite communication equipment, which aims to improve the safety and reliability of the equipment.

The satellite communication device provided by the embodiment of the utility model comprises: the system comprises a first communication system, a second communication system, a main control module, a power supply module and a man-machine interaction module, wherein the bandwidth of the first communication system is larger than that of the second communication system, and the first communication system and the second communication system respectively respond to different satellites;

the first communication system is connected with the first communication end of the main control module, the second communication system is connected with the second communication end of the main control module, the power input end of the main control module is connected with the power module, and the third communication end of the main control module is connected with the human-computer interaction module.

Optionally, the first communication system includes a radio frequency subsystem, configured to implement data communication between a satellite and a ground station corresponding to the first communication system;

the radio frequency subsystem comprises an antenna feeder network, an uplink radio frequency unit, a low-noise downlink frequency conversion unit and a modem, wherein the uplink radio frequency unit and the low-noise downlink frequency conversion unit are respectively connected with the modem, the modem is connected with the main control module, the uplink radio frequency unit is used for outputting signals sent by the main control module to the antenna feeder network, and the low-noise downlink frequency conversion unit is used for outputting signals transmitted by satellites corresponding to the first communication system to the main control module for data processing.

Optionally, the antenna feed network includes an antenna, a feed source, an orthogonal mode coupler, a transmit-block filter, and a two-way rotary joint;

the feed source is respectively connected with the antenna and the orthogonal mode coupler, the receiving end of the orthogonal mode coupler is connected with the low-noise downlink frequency conversion unit through the transmit-stop filter, and the transmitting end of the orthogonal mode coupler is connected with the uplink radio frequency unit through the double-path rotary joint.

Optionally, the first communication system further comprises a servo subsystem, wherein the servo subsystem comprises a control submodule, a motor, a turntable, an inclinometer and a positioning unit;

the motor is connected with the control submodule to control the rotary table to drive the antenna to rotate; the inclinometer and the positioning unit are respectively connected with the control submodule, and the control submodule is connected with the main control module.

Optionally, the second communication system comprises a satellite communication module and an interface module;

the satellite communication module is connected with the second communication end of the main control module through the interface module.

Optionally, the interface module includes a power supply subunit, and the power supply subunit is connected to the power supply output end of the main control module.

Optionally, the satellite communication module includes a radio frequency transceiver and a power management unit, and the radio frequency transceiver is connected to the interface module through the power management unit.

Optionally, the power module includes a main power key, a first secondary power key and a second secondary power key, the main power key is respectively connected with the power end of the main control module, the first secondary power key and the second secondary power key, the main power key is used for respectively passing through the external power voltage through the main control module, the first secondary power key and the second secondary power key, and the first communication system and the second communication system supply power.

Optionally, the operating frequency of the first communication system is a KU band, a KA band, or a C band, and the operating frequency of the second communication system is an L band.

Optionally, the second communication system includes a Thuraya communication system or a beidou short message module.

According to the satellite communication equipment provided by the embodiment of the utility model, the first communication system and the second communication system with different bandwidths are integrated, and different communication systems can be selected for communication according to actual requirements, so that the respective advantages and complementary defects of the first communication system and the second communication system are fully exerted, and the safety and reliability of the satellite communication equipment are improved.

Drawings

Fig. 1 is a schematic structural diagram of a satellite communication device according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of another satellite communication device according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of an antenna feeder network according to an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a second communication system according to an embodiment of the present invention;

fig. 5 is a schematic diagram of a connection structure of a power module according to an embodiment of the present invention;

fig. 6 is a schematic overall structure diagram of a satellite communication device according to an embodiment of the present invention;

fig. 7 is an electrical schematic diagram of a satellite communication device according to an embodiment of the present invention.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.

Conventional satellite communication equipment generally supports communication in only one frequency band, such as a KU frequency band satellite communication system, and although the KU frequency band satellite communication system has strong communication capability, the disadvantage of the KU frequency band satellite communication system is also very obvious: before each use, accurate satellite alignment is needed, wherein, manual satellite alignment needs professional and experienced personnel to operate, and an automatic satellite alignment system is easy to damage and the equipment is heavy; the communication equipment has large power consumption and serious heating, and is provided with high-power supply equipment when working in the field, so that the portability is poor; the KU frequency band antenna has high rain attenuation coefficient, obvious signal attenuation in rainy weather and low reliability.

In view of the above problem, embodiments of the present invention provide a satellite communication device to improve communication reliability. Fig. 1 is a schematic structural diagram of a satellite communication device according to an embodiment of the present invention, and referring to fig. 1, the satellite communication device according to the embodiment of the present invention includes a first communication system 100, a second communication system 200, a main control module 30, a power module 40, and a human-computer interaction module 50, where a bandwidth of the first communication system 100 is greater than a bandwidth of the second communication system 200, and the first communication system 100 and the second communication system 200 respectively respond to different satellites.

The first communication system 100 is connected to the first communication terminal a1 of the main control module 30, the second communication system 200 is connected to the second communication terminal a2 of the main control module 30, the power input terminal A3 of the main control module 30 is connected to the power module 40, and the third communication terminal a4 of the main control module 30 is connected to the human-computer interaction module 50.

Specifically, the satellite communication device provided by the embodiment of the present invention integrates the first communication system 100 and the second communication system 200 for different bandwidths, where the first communication system 100 establishes a communication connection with the satellite 1, and the second communication system 200 establishes a communication connection with the satellite 2. The power module 40 is used for providing power voltage for the main control module 30, the first communication system 100 and the second communication system 200; the human-computer interaction module 50 is used for implementing interaction between the user terminal and the first communication system 100 and the second communication system 200, such as implementing operations of voice access, data transmission, and the like.

The bandwidth of the communication system may reflect the communication capabilities of the communication system. In the present embodiment, the bandwidth of the first communication system 100 is greater than the bandwidth of the second communication system 200, and therefore, the first communication system 100 has a relatively high communication capability and can communicate broadband data such as video, images, and files; the second communication system 200 uses electromagnetic waves with lower band frequencies for communication, and the communication capability of the second communication system is lower than that of the first communication system 100, but the second communication system 200 has stronger anti-jamming capability and low rain attenuation coefficient, and can ensure the basic communication capability of the satellite communication equipment when the first communication system 100 cannot be used normally.

Illustratively, the first communication system 100 has a KU band and an operating frequency of 12-18 GHz. The first communication system 100 communicates in response to the satellite 1. The wave band of the second communication system 200 is an L-band, the operating frequency thereof is 1-2GHz, and communication is performed in response to the satellite 2, and since the second communication system 200 uses the low-frequency L-band for communication, the anti-interference capability thereof is stronger, and low-rate communication can be performed in a rainy environment, so that the basic communication capability of the communication device is ensured, and the safety and reliability of the device are improved.

According to the satellite communication equipment provided by the embodiment of the utility model, the first communication system and the second communication system with different bandwidths are integrated, and different communication systems can be selected for communication according to actual requirements, so that the respective advantages and complementary defects of the first communication system and the second communication system are fully exerted, and the safety and reliability of the satellite communication equipment are improved.

Fig. 2 is a schematic structural diagram of another satellite communication device according to an embodiment of the present invention, and referring to fig. 1 and fig. 2, the first communication system 100 includes a radio frequency subsystem 110 for implementing data communication between a satellite corresponding to the first communication system 100 and a ground station; the radio frequency subsystem 110 includes an antenna feeder network 111, an uplink radio frequency unit 112, a low-noise downlink frequency conversion unit 113, and a modem 114, where the uplink radio frequency unit 112 and the low-noise downlink frequency conversion unit 113 are respectively connected to the modem 114, the modem 114 is connected to the main control module 30, the uplink radio frequency unit 112 is configured to output a signal sent by the main control module 30 to the antenna feeder network 111, and the low-noise downlink frequency conversion unit 113 is configured to output a signal transmitted by a satellite corresponding to the first communication system 100 to the main control module 30 for data processing.

Specifically, the first communication system 100 implements data communication between the satellite 1 and the ground station by using a radio frequency method. The satellite 1 may be a broadband communication satellite, and the antenna feeder network 111 is used for receiving and transmitting signals. In this embodiment, taking the first communication system 100 as the KU band communication system as an example, the signal receiving process is as follows: the antenna feeder network 111 receives the KU band signal forwarded by the satellite 1, and inputs the received KU band signal to a Low Noise downlink Converter (LNB) 113, the KU band signal is converted into a medium-high band signal by the Low Noise downlink Converter 113 after being filtered, converted, amplified, and the like, and input to the modem 114, and the modem 114 demodulates the received medium-high band signal and then sends the demodulated signal to the main control module 30 for processing. The transmission process of the signal is as follows: the modem 114 receives the signals of the medium-high frequency band sent by the main control module 30 (or the user terminal), demodulates the received signals of the medium-high frequency band, and sends the demodulated signals to the uplink radio frequency unit (Block Up Converter, BUC)112, the uplink radio frequency unit 112 performs filtering, frequency conversion, amplification and other processing on the input signals of the medium-high frequency band, and outputs KU-band signals to the antenna feeder network 111, and the antenna feeder network 111 transmits the KU-band signals to the satellite 1.

Further, fig. 3 is a schematic structural diagram of an antenna feed network according to an embodiment of the present invention, and referring to fig. 3, on the basis of the foregoing technical solution, an antenna feed network 111 includes an antenna 101, a feed source 102, an orthogonal mode coupler 103, a transmit-block filter 104, and a two-way rotary joint 105; the feed source 102 is connected with the antenna 101 and the orthogonal mode coupler 103 respectively, the receiving end of the orthogonal mode coupler 103 is connected with the low-noise downlink frequency conversion unit 113 through the transmit-stop filter 104, and the transmitting end of the orthogonal mode coupler 103 is connected with the uplink radio frequency unit 112 through the double-path rotary joint 105.

Specifically, the antenna 101 is a parabolic offset antenna and is in communication connection with the feed 102. The orthogonal mode coupler 103 is used for realizing dual polarization feeding in a waveguide feeding network, in the signal receiving process, the antenna 101 focuses the KU band signal forwarded by the satellite 1 into the feed source 102 (specifically into a corrugated horn of the feed source 102), couples the KU band signal into the transmit-stop filter 104 through the orthogonal mode coupler 103, and then inputs the KU band signal into the low-noise downlink frequency conversion unit 113. In the process of signal transmission, the KU band signal input by the uplink rf unit 112 at the transmitting end is coupled into the circular waveguide by the orthomode coupler 103, and is radiated out through the ripple horn of the feed source 102. In the present embodiment, the isolation between the input receiving end and the transmitting end of the orthomode coupler 103 is achieved by the dual-path rotary joint 105 and the dual-path rotary joint 105.

With continued reference to fig. 2 and 3, the first communication system 100 further includes a servo subsystem 120, where the servo subsystem 120 includes a control submodule 121, a motor 122, a turntable 123, an inclinometer 124, and a positioning unit 125, and the motor 122 is connected to the control submodule 121 to control the turntable 122 to rotate the antenna 101; the inclinometer 124 and the positioning unit 125 are respectively connected with the control submodule 121, and the control submodule 121 is connected with the main control module 30.

Specifically, the servo subsystem 120 is mainly used for pointing the satellite according to the feedback of the main control module 30 and the rf subsystem 110, wherein the control sub-module 121 is a servo controller. After the device is powered on, each module is initialized, the positioning unit 125 acquires position information of the satellite communication device and angle information of the inclinometer 124, the control submodule 121 calculates a polarization angle and a pitch angle of a target satellite (satellite 1) through an internal software algorithm, and then the control motor 122 drives the turntable 123 to adjust the antenna 101 to the calculated angle, so that coarse satellite alignment of the satellite communication device is realized. Then, the control sub-module 121 performs fine tuning on the polarization angle and the pitch angle of the antenna 101 within a small range according to the received real-time feedback of the signal-to-noise ratio of the modem 114, thereby completing the whole satellite-alignment process. The signal-to-noise ratio of the modem 114 can be calculated according to the signals output by the low-noise down-conversion unit 113 received by the carrier receiver and the beacon receiver (not shown in the figure) in the control sub-module 121.

In the present embodiment, the positioning unit 125 is a GPS/BD module for acquiring the longitude and latitude of the satellite communication device use place to adjust the attitude of the antenna 101.

Of course, in other embodiments, the servo subsystem 120 may further include sensors to acquire data signals of the respective sub-modules.

Optionally, fig. 4 is a schematic structural diagram of a second communication system according to an embodiment of the present invention, and referring to fig. 1 and fig. 4, the second communication system 200 includes a satellite communication module 210 and an interface module 220; the satellite communication module 210 is connected to the second communication terminal a2 of the main control module 30 through the interface module 220.

Further, the interface module 220 includes a power supply subunit 221, and the power supply subunit 221 is connected to the power supply output terminal a5 of the main control module 30. The satellite communication module 210 includes a radio frequency transceiver 201 and a power management unit 202, and the radio frequency transceiver 201 is connected to the interface module 220 through the power management unit 202. The satellite communication module 210 further includes a GPS/BD positioning module, and the radio frequency transceiver 201 and the GPS/BD positioning module are respectively connected to corresponding antennas.

Specifically, the second communication system 200 is a narrow-band satellite communication system, the satellite communication module 210 is configured to implement a satellite communication function and a positioning function, the interface module 220 is connected to the satellite communication module 210, the interface module 220 is integrated with a power supply subunit 221, and the interface module 220 is configured to complete functions of power supply, management, satellite dialing, data transceiving, and the like of the satellite communication module 210.

In this embodiment, the interface module 220 uses a NUC975 serial processor as a main control chip, and the NUC970 serial chip is a system-on-chip with an ARM926EJS as a core, and includes a 16kB I-Cache, a 16kB D-Cache, and an MMU memory management module. The frequency of up to 300MHz is supported, and a rich peripheral interface is provided, and the Device has a serial port, USB fast Host/Device, SDHC, a network interface, I2S audio and other interfaces. And the computer can be started by NAND Flash, SPI and Flash. The interface module 220 adopts an embedded linux operating system, an application program is compiled and developed by using a C language, the connection between the interface module 200 and the satellite communication module 210 through a serial port (such as a TTL serial port) is mainly completed, after the initial power-on, a satellite network access application is carried out by using a PPP dialing function, and communication functions such as satellite network access and TCP connection are completed.

The RF transceiver 201 may be an SM-2700 module, and the SM-2700 module integrates a baseband, an RF transceiver and a power management unit 202, and is equipped with a transmitter and a receiver, and the transceiver operating frequency is an L band, which can complete the communication operation to the satellite 2.

Optionally, fig. 5 is a schematic diagram of a connection structure of a power module according to an embodiment of the present invention, referring to fig. 1 to 5, the power module 40 includes a main power key 43, a first secondary power key 44, and a second secondary power key 45, the main power key 43 is respectively connected to the power end a3 of the main control module 30, the first secondary power key 44, and the second secondary power key 45, and the main power key 30 is configured to supply voltage of the external power source 41 to the first communication system 100 and the second communication system 200 through the main control module 30, the first secondary power key 44, and the second secondary power key 45, respectively.

Specifically, the external power source 41 may be 110-220 VAC power, and the voltage output by the external power source 41 is converted into a voltage matched with the satellite communication device, such as 24VDC, through the adapter 42. The main power key 43 is a main power switch between the external power supply 41 and the satellite communication device, and the first sub power key 44 and the second sub power key 45 are sub power switches between the main power key 43 and the first communication system 100, respectively. Illustratively, the first secondary power key 44 may be used to control a power supply path between the external power source 41 and the motor 122, the modem 114, the beacon, etc. in the first communication system 100, and the second secondary power key 45 may be used to control a power supply path of the upstream radio frequency unit 112.

The power supply of the second communication system 200 is controlled by the control module 30, when the main power key 43 is closed, the whole device is powered on, the user sends a control signal to the main control module 30 through the man-machine interaction module 50, and the main control module 10 controls the external power source 41 to supply power to the second communication system 200 according to the received control signal. Therefore, the user can select a proper communication system for communication according to the actual application scene.

In this embodiment, the human-computer interaction module 50 is developed and completed by using a C language based on an embedded linux system, and is responsible for interaction functions such as system setting, message display, status display, data network interface, and the like. The external interface comprises a WIFI hotspot and two RJ45 network ports for control/service. The user can be connected through equipment such as a PC (personal computer), a mobile phone and the like, and the man-machine interaction interface is accessed through the browser. The equipment such as PC can also be connected through using the net twine, and the guarantee still can normally control equipment when WIFI communication is unstable.

Optionally, fig. 6 is a schematic overall structural diagram of a satellite communication device provided in an embodiment of the present invention, and referring to fig. 1 to 6, the satellite communication device adopts a frame structure with module integration, is light in weight, and can be carried by a single person. The whole waterproof design that adopts of equipment guarantees that equipment can be normal use under overcast and rainy weather. The parabolic antenna is the antenna 101 in the first communication system 100, and a servo driving structure is connected below the parabolic antenna. Two long strip-shaped antenna structures are arranged on two sides of the satellite communication device main body and can correspond to the antenna in the second communication system 200, and the antenna is of a foldable structure.

In the present embodiment, the first communication system 100 is a broadband satellite communication system, and the operating frequency thereof is KU band, KA band or C band. The second communication system 200 is a narrowband satellite communication system, for example, the second communication system 200 may be a Thuraya communication system or a beidou short message module, and the operating frequency thereof is an L-band.

Further, fig. 7 is an electrical schematic diagram of a satellite communication device according to an embodiment of the present invention, and with reference to fig. 1 to 7, a description is given by taking the first communication system 100 as a KU satellite communication system and taking the second communication system 200 as a Thuraya communication system as an example. The adapter 42 is connected to the main power key 43 through an adapter interface 421 provided on the casing of the satellite communication apparatus to connect the external power supply 41 to the apparatus. Different communication systems are selected for communication according to actual requirements, when the first communication system 100 is selected for communication, the first secondary power supply key 44 and the second secondary power supply key 45 are closed, a power supply path of the first communication system 100 is conducted, each module in the servo subsystem 120 is initialized, the positioning unit 125 acquires position information of satellite communication equipment and angle information of the inclinometer 124, the control submodule 121 calculates a polarization angle and a pitch angle of a target satellite (satellite 1) through an internal software algorithm, and then the control motor 122 (the motor 122 is driven through the motor driver 128) drives the rotary table 123 to adjust the antenna 101 to the calculated angle, so that coarse alignment of the satellite communication equipment is achieved. Then, the control sub-module 121 performs fine tuning on the polarization angle and the pitch angle of the antenna 101 within a small range according to the received real-time feedback of the signal-to-noise ratio of the modem 114, thereby completing the whole satellite-alignment process.

After the satellite-to-satellite operation is completed, the signal receiving process of the first communication system 100 is as follows: the antenna feeder network 111 receives the KU band signal forwarded by the satellite 1, and inputs the received KU band signal to the low-noise downlink frequency conversion unit 113, the low-noise downlink frequency conversion unit 113 converts the KU band signal into a medium-high frequency band signal after filtering, frequency conversion, amplification and the like, and inputs the medium-high frequency band signal into the modem 114, and the modem 114 demodulates the received medium-high frequency band signal and then sends the demodulated medium-high frequency band signal to the main control module 30 for processing. The transmission process of the signal is as follows: the modem 114 receives the medium-high frequency band signal sent by the main control module 30 (or the user terminal), demodulates the received medium-high frequency band signal, and sends the demodulated medium-high frequency band signal to the uplink radio frequency unit 112, the uplink radio frequency unit 112 performs filtering, frequency conversion, amplification and other processing on the input medium-high frequency band signal, and outputs a KU band signal to the antenna feeder network 111, and the antenna feeder network 111 transmits the KU band signal to the satellite 1.

When the second communication system 200 is selected for communication, the main control module 30 controls the satellite communication module 210 to be powered on, the satellite communication module 210 is respectively connected with the satellite antenna 230 and the positioning antenna 126, and the satellite communication module 210 completes satellite communication work. For the specific working principle, reference may be made to the description in the above embodiments, which are not repeated herein.

Control net gape 501 and business net gape 502 are two RJ45 net gapes of human-computer interaction module 50 to through using the net twine to connect, ensure when WIFI communication is unstable, still can normally control equipment. The satellite communication device further comprises a switch 60, which is used for realizing the access of IP data, completing the information exchange between the user and the device, such as realizing the access and processing of audio, video and other data.

In an actual field test, compared with a conventional KU communication device, the KU broadband communication system (first communication system) in the satellite communication device provided by the embodiment of the present invention can implement all functions of the conventional KU communication device, and can perform stable broadband satellite communication. Meanwhile, because the equipment is additionally provided with the Thuraya narrowband communication system (the second communication system), the user can meet the actual communication requirement only by using the Thuraya narrowband communication system in various scenes, and because the Thuraya narrowband communication system does not need to operate the satellite, the operations such as self-checking, network access and the like can be automatically completed by electrifying, the operation steps of the equipment are greatly reduced, and the communication function can be realized by quickly accessing the network. The Thuraya narrow-band communication subsystem is extremely low in power consumption, and the field work duration of the equipment is greatly prolonged. When the KU communication system has the conditions of insufficient electric quantity, interference on communication and the like, a user can use the Thuraya narrow-band communication system to ensure the basic communication function, thereby enhancing the practicability and reliability of the equipment.

It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims (10)

1. A satellite communication device, comprising: the system comprises a first communication system, a second communication system, a main control module, a power supply module and a man-machine interaction module, wherein the bandwidth of the first communication system is larger than that of the second communication system, and the first communication system and the second communication system respectively respond to different satellites;

the first communication system is connected with the first communication end of the main control module, the second communication system is connected with the second communication end of the main control module, the power input end of the main control module is connected with the power module, and the third communication end of the main control module is connected with the human-computer interaction module.

2. The satellite communication device according to claim 1, wherein the first communication system includes a radio frequency subsystem for enabling data communication between a satellite corresponding to the first communication system and a ground station;

the radio frequency subsystem comprises an antenna feeder network, an uplink radio frequency unit, a low-noise downlink frequency conversion unit and a modem, wherein the uplink radio frequency unit and the low-noise downlink frequency conversion unit are respectively connected with the modem, the modem is connected with the main control module, the uplink radio frequency unit is used for outputting signals sent by the main control module to the antenna feeder network, and the low-noise downlink frequency conversion unit is used for outputting signals transmitted by satellites corresponding to the first communication system to the main control module for data processing.

3. The satellite communication device of claim 2, wherein the antenna feed network comprises an antenna, a feed, an orthogonal mode coupler, a transmit-block filter, and a two-way rotary joint;

the feed source is respectively connected with the antenna and the orthogonal mode coupler, the receiving end of the orthogonal mode coupler is connected with the low-noise downlink frequency conversion unit through the transmit-stop filter, and the transmitting end of the orthogonal mode coupler is connected with the uplink radio frequency unit through the double-path rotary joint.

4. The satellite communication device of claim 3, wherein the first communication system further comprises a servo subsystem comprising a control sub-module, a motor, a turntable, an inclinometer, and a positioning unit;

the motor is connected with the control submodule to control the rotary table to drive the antenna to rotate; the inclinometer and the positioning unit are respectively connected with the control submodule, and the control submodule is connected with the main control module.

5. The satellite communication device of claim 1, wherein the second communication system comprises a satellite communication module and an interface module;

the satellite communication module is connected with the second communication end of the main control module through the interface module.

6. The satellite communication device of claim 5, wherein the interface module comprises a power supply subunit, the power supply subunit being connected to the power supply output of the master control module.

7. The satellite communication device of claim 5, wherein the satellite communication module includes a radio frequency transceiver and a power management unit, the radio frequency transceiver being connected to the interface module through the power management unit.

8. The satellite communication device according to claim 1, wherein the power module includes a main power key, a first secondary power key, and a second secondary power key, the main power key is connected to the power end of the main control module, the first secondary power key, and the second secondary power key, respectively, and the main power key is configured to supply an external power voltage to the first communication system and the second communication system through the main control module, the first secondary power key, and the second secondary power key, respectively.

9. The satellite communication device of claim 1, wherein the operating frequency of the first communication system is KU band, KA band, or C band, and the operating frequency of the second communication system is L band.

10. The satellite communication apparatus of claim 1, wherein the second communication system comprises a Thuraya communication system or a beidou short message module.

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