CN113572514A - Satellite-borne communication machine and satellite-borne communication system - Google Patents
Satellite-borne communication machine and satellite-borne communication system Download PDFInfo
- Publication number
- CN113572514A CN113572514A CN202110848518.0A CN202110848518A CN113572514A CN 113572514 A CN113572514 A CN 113572514A CN 202110848518 A CN202110848518 A CN 202110848518A CN 113572514 A CN113572514 A CN 113572514A
- Authority
- CN
- China
- Prior art keywords
- unit
- satellite
- radio frequency
- frequency
- uplink
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Mobile Radio Communication Systems (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention discloses a satellite-borne communication machine and a satellite-borne communication system. This satellite-borne communicator includes: the system comprises a radio frequency transceiver module, a digital baseband module and an ARM interface module; the radio frequency transceiver module includes: the radio frequency receiving unit and the radio frequency transmitting unit; the digital baseband module includes: the FPGA unit and the transceiver chip; the radio frequency receiving unit is connected with a first receiving end of the transceiving chip; a first sending end of the transceiving chip is connected with a receiving end of the FPGA unit, and a data end of the FPGA unit is connected with the ARM interface module; and a transmitting end of the FPGA unit is connected with a second receiving end of the transceiver chip, and a second transmitting end of the transceiver chip is connected with the radio frequency transmitting unit. According to the technical scheme, functions of frequency conversion, filtering, gain control and the like of an uplink radio frequency channel and a downlink radio frequency channel are integrated on the transceiver chip, so that the link structure is greatly simplified, the hardware cost, the size and the power consumption are reduced, the function of parameter configuration of the transceiver chip such as the working frequency and the gain is integrated, and the on-orbit configurable function of the satellite-borne communication machine is realized.
Description
Technical Field
The embodiment of the invention relates to the field of satellites, in particular to a satellite-borne communication machine and a satellite-borne communication system.
Background
With the rapid development of the micro-nano satellite technology, the micro-nano satellite is more and more widely applied to the fields of communication, navigation, remote sensing, scientific experiments and the like. The micro-nano satellite is widely applied to satellite-borne communication systems in the fields of communication, navigation, remote sensing, scientific experiments and the like, and is closely related. The satellite-ground or inter-satellite data interaction is realized by using a satellite-borne communication system of the micro-nano satellite, and tasks such as satellite-ground measurement and control of satellite-ground data transmission, satellite-ground communication or inter-satellite relay are completed. Fig. 1 is a schematic structural diagram of a satellite-borne communication device provided in the prior art, and as shown in fig. 1, currently, because a superheterodyne frequency conversion structure and a frequency synthesis technology of frequency doubling phase locking are commonly used in domestic traditional satellite-borne communication devices, a hardware link of the satellite-borne communication device is long and has a complex structure, and for satellite-borne communication devices integrated with different communication systems and functional units, miniaturization of a satellite becomes increasingly difficult.
Disclosure of Invention
In view of this, the invention provides a satellite-borne communication machine and a satellite-borne communication system, which simplify a link structure and reduce hardware cost, volume and power consumption while ensuring an online configurable function of the satellite-borne communication machine.
In a first aspect, an embodiment of the present invention provides a satellite borne communication apparatus, including: the system comprises a radio frequency transceiver module, a digital baseband module and an ARM interface module; wherein, the radio frequency transceiver module includes: the radio frequency receiving unit and the radio frequency transmitting unit; the digital baseband module includes: the FPGA unit and the transceiver chip;
the radio frequency receiving unit is connected with a first receiving end of the transceiver chip; a first sending end of the transceiver chip is connected with a receiving end of the FPGA unit, and a data end of the FPGA unit is connected with the ARM interface module; the transmitting end of the FPGA unit is connected with the second receiving end of the transceiver chip, and the second transmitting end of the transceiver chip is connected with the radio frequency transmitting unit;
converting the received first frequency band signal into a second frequency band signal by using the radio frequency receiving unit, and sending the second frequency band signal to the transceiver chip, so that the transceiver chip converts the second frequency band signal into an uplink zero-frequency signal and sends the uplink zero-frequency signal to the FPGA unit; the FPGA unit is used for demodulating and decoding the uplink zero-frequency signal to obtain uplink remote control data and sending the uplink remote control data to a corresponding satellite computer through the ARM interface module;
the FPGA unit receives downlink telemetering data sent by the satellite computer through the ARM interface module and sends the modulated and coded downlink telemetering data to the transceiver chip; the transceiver chip sends the downlink telemetering data after modulation and coding to the radio frequency sending unit so that the radio frequency sending unit converts the downlink telemetering data after modulation and coding into downlink telemetering data of a first frequency band; and the radio frequency sending unit outputs the downlink telemetry data of the first frequency band to a transmitting antenna.
In a second aspect, an embodiment of the present invention further provides a satellite-borne communication system, including: the system comprises a ground measurement and control center, a cloud server, a satellite ground station and the satellite-borne communication machine in any one of the embodiments; the ground measurement and control center establishes communication connection with the satellite ground station through the cloud server, and the satellite ground station establishes communication connection with the satellite-borne communication machine;
the ground measurement and control center generates an uplink instruction containing satellite identification information and configuration parameters, and sends the uplink instruction to the satellite ground station through the cloud server, so that the satellite ground station sends the uplink instruction to the satellite-borne communication machine; the satellite-borne communication machine controls each module of the satellite-borne communication machine through the SPI interface, refreshes register parameters and achieves the function of on-orbit configuration of the parameters.
The embodiment of the invention discloses a radio frequency transceiver module, a digital baseband module and an ARM interface module; wherein, the radio frequency transceiver module includes: the radio frequency receiving unit and the radio frequency transmitting unit; the digital baseband module includes: the FPGA unit and the transceiver chip; the radio frequency receiving unit is connected with a first receiving end of the transceiving chip; a first sending end of the transceiving chip is connected with a receiving end of the FPGA unit, and a data end of the FPGA unit is connected with the ARM interface module; and a transmitting end of the FPGA unit is connected with a second receiving end of the transceiver chip, and a second transmitting end of the transceiver chip is connected with the radio frequency transmitting unit. According to the technical scheme of the embodiment of the invention, functions of frequency conversion, filtering, gain control and the like of an uplink radio frequency channel and a downlink radio frequency channel are integrated on the transceiver chip, so that the link structure is greatly simplified, the hardware cost, the size and the power consumption are reduced, the function of configuring parameters of the transceiver chip such as the working frequency, the gain and the like is integrated, and the on-orbit configurable function of the satellite-borne communication machine is realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of a satellite-borne communication machine provided in the prior art;
fig. 2 is a block diagram of a satellite-borne communication machine according to an embodiment of the present invention;
FIG. 3 is a block diagram of another satellite-borne communication apparatus according to an embodiment of the present invention;
FIG. 4 is a block diagram of a satellite-borne communication machine according to another embodiment of the invention;
FIG. 5 is a block diagram of a satellite-borne communication apparatus according to another embodiment of the invention;
fig. 6 is a block diagram of a transceiver chip according to an embodiment of the present invention;
fig. 7 is a block diagram of a local oscillation unit according to an embodiment of the present invention;
fig. 8 is a block diagram of a satellite-borne communication system 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 invention and are not limiting of the invention. 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.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. Meanwhile, in the description of the present invention, the terms "first", "second", and the like are used only for distinguishing the description, and are not to be construed as indicating or implying relative importance.
In an embodiment, fig. 2 is a block diagram of a satellite-borne communication device according to an embodiment of the present invention, and this embodiment is applicable to a case of implementing an on-orbit configurable function of a satellite-borne communication device. As shown in fig. 2, the satellite-borne communication apparatus in this embodiment includes: a radio frequency transceiver module 10, a digital baseband module 20 and an arm (advanced RISC machines) interface module 30; the radio frequency transceiver module 10 includes: a radio frequency receiving unit 101 and a radio frequency transmitting unit 102; the digital baseband module 20 includes: a Field Programmable Gate Array (FPGA) unit 201 and a transceiver chip 202;
the radio frequency receiving unit 101 is connected to a first receiving end of the transceiver chip 202; a first sending end of the transceiver chip 202 is connected with a receiving end of the FPGA unit 201, and a data end of the FPGA unit 201 is connected with the ARM interface module 30; a transmitting end of the FPGA unit 201 is connected to a second receiving end of the transceiver chip 202, and a second transmitting end of the transceiver chip 202 is connected to the radio frequency transmitting unit 102;
the radio frequency receiving unit 101 is used for converting the received first frequency band signal into a second frequency band signal, and sending the second frequency band signal to the transceiver chip 202, so that the transceiver chip 202 converts the second frequency band signal into an uplink zero-frequency signal and sends the uplink zero-frequency signal to the FPGA unit 201; the FPGA unit 201 is configured to demodulate and decode the uplink zero-frequency signal to obtain uplink remote control data, and send the uplink remote control data to the corresponding satellite computer 40 through the ARM interface module 30;
the FPGA unit 201 receives downlink telemetry data sent by the satellite computer 40 through the ARM interface module 30, and sends the modulated and encoded downlink telemetry data to the transceiver chip 202; the transceiver chip 202 sends the modulated and coded downlink telemetry data to the radio frequency sending unit 102, so that the radio frequency sending unit 102 converts the modulated and coded downlink telemetry data into downlink telemetry data of a first frequency band; the rf transmitting unit 102 outputs the downlink telemetry data of the first frequency band to the transmitting antenna.
In the embodiment, the radio frequency receiving unit 101 in the satellite based communication machine firstly converts the received first frequency band signal into the second frequency band signal at a time, and directly transmits the second frequency band signal to the transceiver chip 202, the transceiver chip 202 performs zero intermediate frequency conversion on the second frequency band signal to the uplink zero frequency signal, and transmits the uplink zero frequency signal to the FPGA unit 201, so that the FPGA unit 201 demodulates, decodes and decodes the uplink zero frequency signal to obtain uplink injection data, which may also be referred to as uplink remote control data, and outputs the uplink injection data to the satellite computer 40 through the ARM interface module 30. Correspondingly, the FPGA unit 201 receives the downlink telemetry data issued by the satellite computer 40 through the ARM interface module 30, modulates, codes and shapes the downlink telemetry data to obtain the downlink telemetry data after modulation and coding, and forwards the downlink telemetry data after modulation and coding to the transceiver chip 202, and the transceiver chip 202 directly converts the downlink telemetry data after modulation and coding into the downlink telemetry data of the first frequency band through its own frequency conversion unit after receiving the downlink telemetry data after modulation and coding, and directly outputs the downlink telemetry data of the first frequency band to the transmitting antenna through the amplification filter in the radio frequency transmitting unit 102.
In an embodiment, the transceiver chip comprises the following functions: the radio frequency receiving unit has the functions of secondary frequency conversion, intermediate frequency amplification, intermediate frequency filtering, Automatic Gain Control (AGC) Gain Control and AD sampling of an uplink radio frequency channel corresponding to the radio frequency receiving unit; DAC modulation, intermediate frequency primary frequency conversion, intermediate frequency amplification, intermediate frequency filtering and AGC gain control functions of a downlink radio frequency channel corresponding to the radio frequency sending unit.
According to the technical scheme of the embodiment, functions of frequency conversion, filtering, gain control and the like of the uplink radio frequency channel and the downlink radio frequency channel are integrated on the transceiver chip, so that the link structure is greatly simplified, the hardware cost, the size and the power consumption are reduced, the function of parameter configuration of the transceiver chip such as the working frequency, the gain and the like is integrated, and the on-orbit configurable function of the satellite-borne communication machine is realized.
In an embodiment, fig. 3 is a block diagram of another structure of a satellite-borne communication device according to an embodiment of the present invention, and the embodiment further defines the structure of the satellite-borne communication device on the basis of the foregoing embodiment. As shown in fig. 3, the satellite communication device in this embodiment includes: and the power supply module 50 is connected with the ARM interface module 30 and is used for supplying power and controlling power on of each module in the satellite-borne communication machine.
In an embodiment, the rf transceiver module 10 further includes: a local oscillation unit 103; the local oscillation unit 103 includes: a power divider; a first end of the local oscillation unit 103 is connected to the radio frequency receiving unit 101, and a second end of the local oscillation unit 103 is connected to the radio frequency transmitting unit 102; the local oscillation unit 103 provides the local oscillation source to the rf receiving unit 101 and the rf transmitting unit 102 through the power divider.
In an embodiment, the local oscillation unit 103 further includes: a VOC integrated phase locked loop frequency synthesizer. The phase-locked loop frequency synthesizer integrated with the VOC adopts 40MHz as a reference signal, and the FPGA unit 201 controls parameters of an internal register of the phase-locked loop frequency synthesizer to synthesize a local oscillation signal of the radio frequency transceiver module 10. In the embodiment, the FPGA unit 201 controls parameters of an internal register of the phase-locked loop frequency synthesizer to directly synthesize a local oscillation signal required by the radio frequency transceiver module 10, which greatly simplifies a link design, reduces a size and power consumption, and simplifies a peripheral hardware circuit compared with an existing frequency synthesis scheme, and meanwhile, parameters such as output power and output frequency of the frequency synthesizer can be configured on-track through the FPGA unit 201.
In an embodiment, ARM interface module 30 includes: 422 interface 301, Controller Area Network (CAN) bus interface 302, and OC interface 303; the FPAG unit 201 communicates with the satellite computer 40 through the 422 interface 301, the CAN bus interface 302, or the OC interface 303.
ARM interface module 30, further includes: a microcontrol Unit (MCU) control Unit 304; the MCU control unit 304 is configured to receive the uplink remote control data sent by the FPGA unit 201, and send the uplink remote control data to the satellite computer 40 according to an uplink preset format; the MCU control unit 304 is further configured to obtain downlink telemetry data from the satellite computer 40, and transmit the downlink telemetry data to the FPGA unit 201 according to a downlink preset format.
Further, the ARM interface module 30 further includes: a watchdog unit and a clock unit.
In an embodiment, fig. 4 is a block diagram of a structure of another satellite-borne communication apparatus according to an embodiment of the present invention. For example, the communication process of the satellite-borne communication machine will be described by taking the first frequency band as an X frequency band and the second frequency band as an L frequency band.
As shown in fig. 4, the satellite communication device in this embodiment includes: the system comprises a radio frequency receiving unit 101, a radio frequency transmitting unit 102, an FPGA unit 201, a transceiver chip 202, an ARM interface module 30, a satellite computer 40 and a power supply module 50. The rf receiving unit 101 includes: the device comprises a cavity filter, a Low Noise Amplifier (LNA) and a mirror image filter; the radio frequency transmission unit 102 includes: cavity filter, isolator, drive amplifier. It should be noted that the power transistor shown in fig. 4 is not included in the rf transmitting unit 102, and belongs to a component in the power amplifier unit.
In the embodiment, the radio frequency receiving unit 101 of the satellite-borne communication machine firstly converts the received X-band remote control signal to the L-band frequency point at a time to obtain an L-band signal, and then directly inputs the L-band signal to the transceiver chip 202, so that the transceiver chip performs zero-intermediate frequency conversion on the L-band signal to obtain an uplink zero-frequency signal, performs AD sampling, and sends a digital sequence obtained by the sampling to the baseband processing module. Correspondingly, the rf transmitting unit 102 directly converts the intermediate frequency signal output by the transceiver chip 202 to the X frequency band through the frequency converting unit, and outputs the intermediate frequency signal to the transmitting antenna after passing through the amplifying filter. It should be noted that the rf receiving unit 101 and the rf transmitting unit 102 share a local oscillation source, that is, the local oscillation source is divided into two paths by the power divider and respectively provided to the receiving channel corresponding to the rf receiving unit 101 and the transmitting channel corresponding to the rf transmitting unit 102.
In an embodiment, fig. 5 is a block diagram of a structure of another satellite-borne communication apparatus according to an embodiment of the present invention. As shown in fig. 5, in this embodiment, a communication process of the satellite communication device is described by taking an example that the ARM interface module includes 422 interface 301, CAN bus interface 302, and OC interface 303.
The FPGA unit 201 demodulates and decodes the uplink zero-frequency signal and decodes the command to generate uplink injection data, and sends the uplink injection data to the ARM interface module 30, and outputs the uplink injection data through the CAN bus interface 302. Meanwhile, the FPGA unit 201 receives the downlink telemetry data sent by the ARM interface module 30, modulates, codes, and shapes the downlink telemetry data, and sends the modulated, coded, and shaped downlink telemetry data to the transmission channel for radio frequency processing. The MCU control unit realizes communication between the satellite-borne communication machine and the satellite computer 40 through the CAN bus and the 422 bus, transmits uplink injection data to the satellite computer 40, receives downlink telemetering data of the satellite computer 40, and is also responsible for transmitting uplink remote control data of the satellite-borne communication machine to the satellite-borne computer 40 and receiving indirect instructions transmitted by the satellite-borne computer.
The ARM interface module 30 receives the uplink remote control data sent by the FPGA unit, and after interpreting the contents of the frame header, the mode word, and the like, sends the uplink remote control data to the satellite computer for interpretation according to the agreed format. The MCU control unit 304 simultaneously acquires downlink telemetry data from the satellite computer, composes a downlink telemetry frame according to the downlink format requirement, and sends the downlink telemetry frame to the FPGA unit 201 through the serial port.
In an embodiment, fig. 6 is a block diagram of a transceiver chip according to an embodiment of the present invention. As shown in fig. 6, the transceiver chip integrates the functions of secondary frequency conversion, intermediate frequency amplification, intermediate frequency filtering AGC gain control, AD sampling, etc. of the uplink radio frequency channel corresponding to the radio frequency receiving unit, and the functions of DAC modulation, intermediate frequency primary frequency conversion, intermediate frequency amplification, intermediate frequency filtering, gain control, etc. of the downlink channel corresponding to the radio frequency transmitting unit into the transceiver chip. Compared with the existing radio frequency channel scheme, the radio frequency channel scheme has the advantages that the link design is greatly simplified, the volume and the power consumption are reduced, and a peripheral hardware circuit is more simple and more reliable. Meanwhile, parameters such as working frequency, gain and the like of the integrated transceiver chip can be configured on track through the FPGA unit.
In an embodiment, fig. 7 is a block diagram of a local oscillation unit according to an embodiment of the present invention. As shown in fig. 7, the local oscillation unit includes: 40MHz temperature compensation crystal oscillator, an integrated VOC broadband frequency synthesizer and a filter. The broadband frequency synthesizer of the integrated VCO adopts 40MHz as a reference signal, an external FPGA unit controls parameters of a register inside a chip, and local oscillation signals required by an output radio frequency channel are directly synthesized. Compared with the existing frequency synthesis scheme, the link design is greatly simplified, the volume and the power consumption are reduced, and a peripheral hardware circuit is more simple and more reliable. Meanwhile, parameters such as output frequency, output power and the like of the frequency synthesizer chip can be configured on track through the FPGA.
In an embodiment, fig. 8 is a block diagram of a satellite-borne communication system according to an embodiment of the present invention. As shown in fig. 8, the satellite-borne communication system in this embodiment includes: a ground measurement and control center 801, a cloud server 802, a satellite ground station 803 and a satellite-borne communicator 804 according to any one of the above embodiments; the ground measurement and control center 801 establishes communication connection with a satellite ground station 803 through a cloud server 802, and establishes communication connection between the satellite ground station 803 and a satellite-borne communicator 804;
the ground measurement and control center 801 generates an uplink instruction containing satellite identification information and configuration parameters, and sends the uplink instruction to the satellite ground station 803 through the cloud server 802, so that the satellite ground station 803 sends the uplink instruction to the satellite-borne communication machine 804; the satellite-borne communication machine 804 controls each module of the satellite-borne communication machine through the SPI interface, refreshes register parameters and achieves the function of on-orbit configuration of the parameters. After the satellite-borne communication machine 804 completes the configuration of the parameters, downlink telemetry data is generated and sent to the satellite ground station 803, so that the satellite ground station 803 forwards the downlink telemetry data to the ground measurement and control center 801 through the cloud server 802.
The satellite-borne communication system in the embodiment not only simplifies the link structure and reduces the hardware cost, the volume and the power consumption while ensuring the function of the satellite-borne communication machine, but also enables the satellite-borne communication machine to update and configure parameters such as a working frequency point, link gain, an ADC (analog to digital converter) sampling clock and modulation mode, a code rate and the like on track.
It should be noted that, in the embodiment of the satellite borne communication machine, the included units and modules are only divided according to functional logic, but are not limited to the above division as long as the corresponding functions can be realized; in addition, specific names of the functional units are only for convenience of distinguishing from each other, and are not used for limiting the protection scope of the present invention.
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 illustrated 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 invention. 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 space-borne communicator, comprising: the system comprises a radio frequency transceiver module, a digital baseband module and an ARM interface module; wherein, the radio frequency transceiver module includes: the radio frequency receiving unit and the radio frequency transmitting unit; the digital baseband module includes: the FPGA unit and the transceiver chip are arranged on the field programmable gate array;
the radio frequency receiving unit is connected with a first receiving end of the transceiver chip; a first sending end of the transceiver chip is connected with a receiving end of the FPGA unit, and a data end of the FPGA unit is connected with the ARM interface module; the transmitting end of the FPGA unit is connected with the second receiving end of the transceiver chip, and the second transmitting end of the transceiver chip is connected with the radio frequency transmitting unit;
converting the received first frequency band signal into a second frequency band signal by using the radio frequency receiving unit, and sending the second frequency band signal to the transceiver chip, so that the transceiver chip converts the second frequency band signal into an uplink zero-frequency signal and sends the uplink zero-frequency signal to the FPGA unit; the FPGA unit is used for demodulating and decoding the uplink zero-frequency signal to obtain uplink remote control data and sending the uplink remote control data to a corresponding satellite computer through the ARM interface module;
the FPGA unit receives downlink telemetering data sent by the satellite computer through the ARM interface module and sends the modulated and coded downlink telemetering data to the transceiver chip; the transceiver chip sends the downlink telemetering data after modulation and coding to the radio frequency sending unit so that the radio frequency sending unit converts the downlink telemetering data after modulation and coding into downlink telemetering data of a first frequency band; and the radio frequency sending unit outputs the downlink telemetry data of the first frequency band to a transmitting antenna.
2. The on-board communication machine according to claim 1, further comprising: and the power supply module is connected with the ARM interface module and is used for supplying power and controlling power on of each module in the satellite-borne communication machine.
3. The on-board communication machine according to claim 1 or 2, wherein the radio frequency transceiver module further comprises: a local oscillation unit; the local oscillation unit includes: a power divider;
the first end of the local oscillator unit is connected with the radio frequency receiving unit, and the second end of the local oscillator unit is connected with the radio frequency transmitting unit; and the local oscillation unit provides a local oscillation source to the radio frequency receiving unit and the radio frequency sending unit through the power divider.
4. The on-board communication machine according to claim 1 or 2, wherein the ARM interface module comprises: 422 interface, controller area network CAN bus interface and OC interface;
the FPAG unit communicates with the satellite computer through the 422 interface, the CAN bus interface or the OC interface.
5. The on-board communication machine of claim 4, wherein the ARM interface module further comprises: a Micro Control Unit (MCU) control unit;
the MCU control unit is used for receiving uplink remote control data sent by the FPGA unit and sending the uplink remote control data to the satellite computer according to an uplink preset format; the MCU control unit is also used for acquiring downlink telemetering data from the satellite computer and sending the downlink telemetering data to the FPGA unit according to a downlink preset format.
6. The on-board communication machine of claim 4, wherein the ARM interface module further comprises: a watchdog unit and a clock unit.
7. The on-board communication machine according to claim 1 or 2, characterized in that said transceiver chip comprises the following functions: the radio frequency receiving unit has the functions of secondary frequency conversion, intermediate frequency amplification, intermediate frequency filtering, Automatic Gain Control (AGC) gain control and analog-to-digital (AD) sampling of an uplink radio frequency channel corresponding to the radio frequency receiving unit; DAC modulation, intermediate frequency primary frequency conversion, intermediate frequency amplification, intermediate frequency filtering and AGC gain control functions of a downlink radio frequency channel corresponding to the radio frequency sending unit.
8. The satellite-borne communication machine according to claim 3, wherein the local oscillation unit further comprises: a VOC integrated phase locked loop frequency synthesizer.
9. The on-board communication machine according to claim 8, wherein the VOC-integrated pll frequency synthesizer uses 40MHz as a reference signal, and the FPGA unit controls internal register parameters of the pll frequency synthesizer to synthesize the local oscillator signal of the rf transceiver module.
10. A satellite-borne communication system, comprising: a ground measurement and control center, a cloud server, a satellite ground station and the satellite-borne communication machine according to any one of claims 1 to 9; the ground measurement and control center establishes communication connection with the satellite ground station through the cloud server, and the satellite ground station establishes communication connection with the satellite-borne communication machine;
the ground measurement and control center generates an uplink instruction containing satellite identification information and configuration parameters, and sends the uplink instruction to the satellite ground station through the cloud server, so that the satellite ground station sends the uplink instruction to the satellite-borne communication machine; the satellite-borne communication machine controls each module of the satellite-borne communication machine through the SPI interface, refreshes register parameters and achieves the function of on-orbit configuration of the parameters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110848518.0A CN113572514A (en) | 2021-07-27 | 2021-07-27 | Satellite-borne communication machine and satellite-borne communication system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110848518.0A CN113572514A (en) | 2021-07-27 | 2021-07-27 | Satellite-borne communication machine and satellite-borne communication system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113572514A true CN113572514A (en) | 2021-10-29 |
Family
ID=78167756
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110848518.0A Pending CN113572514A (en) | 2021-07-27 | 2021-07-27 | Satellite-borne communication machine and satellite-borne communication system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113572514A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115865182A (en) * | 2023-03-01 | 2023-03-28 | 中国科学院国家空间科学中心 | Satellite-borne high-speed multiplexing modulator based on domestic components |
| CN116743241A (en) * | 2023-08-16 | 2023-09-12 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011054225A1 (en) * | 2009-11-09 | 2011-05-12 | 上海华测导航技术有限公司 | Baseband circuit structure for realizing dual-frequency global positioning system (gps) satellite signal receiver and method thereof |
| CN109450519A (en) * | 2018-10-30 | 2019-03-08 | 航天东方红卫星有限公司 | A kind of spaceborne total digitalization USB answering machine |
| CN110266349A (en) * | 2019-07-11 | 2019-09-20 | 上海航天测控通信研究所 | A kind of Small Universal double frequency continuous wave answering machine |
| CN111800187A (en) * | 2020-07-07 | 2020-10-20 | 成都天奥信息科技有限公司 | Satellite ground communication circuit based on AD9364 radio frequency chip |
| CN213484869U (en) * | 2020-09-30 | 2021-06-18 | 北京航宇星通科技有限公司 | Satellite communication data link transceiver module |
-
2021
- 2021-07-27 CN CN202110848518.0A patent/CN113572514A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011054225A1 (en) * | 2009-11-09 | 2011-05-12 | 上海华测导航技术有限公司 | Baseband circuit structure for realizing dual-frequency global positioning system (gps) satellite signal receiver and method thereof |
| CN109450519A (en) * | 2018-10-30 | 2019-03-08 | 航天东方红卫星有限公司 | A kind of spaceborne total digitalization USB answering machine |
| CN110266349A (en) * | 2019-07-11 | 2019-09-20 | 上海航天测控通信研究所 | A kind of Small Universal double frequency continuous wave answering machine |
| CN111800187A (en) * | 2020-07-07 | 2020-10-20 | 成都天奥信息科技有限公司 | Satellite ground communication circuit based on AD9364 radio frequency chip |
| CN213484869U (en) * | 2020-09-30 | 2021-06-18 | 北京航宇星通科技有限公司 | Satellite communication data link transceiver module |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115865182A (en) * | 2023-03-01 | 2023-03-28 | 中国科学院国家空间科学中心 | Satellite-borne high-speed multiplexing modulator based on domestic components |
| CN115865182B (en) * | 2023-03-01 | 2023-05-16 | 中国科学院国家空间科学中心 | Satellite-borne high-speed multiplexing modulator based on domestic components |
| CN116743241A (en) * | 2023-08-16 | 2023-09-12 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
| CN116743241B (en) * | 2023-08-16 | 2023-10-13 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113572514A (en) | Satellite-borne communication machine and satellite-borne communication system | |
| KR920005507B1 (en) | Vehicel loading equipment of automatic vehicle chasing system | |
| US6366620B1 (en) | VSAT system | |
| CN103166670B (en) | Radio frequency transceiver of Beidou satellite navigation and positioning system | |
| CN102739278B (en) | 2.4G wireless transceiver chip with an intermediate frequency of 1MHz | |
| US7979034B2 (en) | Architecture for RFID tag reader/writer | |
| CN101783701A (en) | Radio-frequency receiver of Beidou I navigation system | |
| CN106506018A (en) | A kind of digital AIS receiver systems that is directly sampled based on radio frequency | |
| CN103944631A (en) | Miniature satellite-borne X-band data transmission launcher based on SIP (system in package) technology | |
| WO2006096029A1 (en) | Apparatus for processing a radio frequency signal for an automobile based terminal | |
| EP0679301A1 (en) | A method for minimizing a phase error of a transmitter | |
| CN102540203A (en) | Radio frequency receiver of number-one Beidou satellite navigation system | |
| CN112910544A (en) | On-orbit configurable satellite-borne L/S frequency band data broadcast distribution system | |
| CN110365364B (en) | Radio frequency channel device and satellite transponder comprising same | |
| CN115632675B (en) | Multi-module wireless signal processing system and method based on FPGA | |
| JPH1093469A (en) | Frequency generator for radio communication equipment and frequency conversion method | |
| CN116418361A (en) | Radio frequency transceiver chip and radio frequency transceiver device | |
| US8781524B2 (en) | Wireless communication device | |
| CN203233411U (en) | Radio frequency transceiver for Beidou satellite navigation system | |
| US6622009B1 (en) | Radiotelephone transmitter/receiver | |
| CN212211006U (en) | Satellite electronic system of micro/nano satellite | |
| CN201600457U (en) | Radio-frequency receiver of beidou-I satellite navigation system | |
| CN206402228U (en) | A kind of modulation-demodulation device, trunk desk and the Solution of Vehicles Radio of modulus mixing | |
| CN214281377U (en) | Small satellite communication module based on radio frequency agile transceiver | |
| CN219372427U (en) | Transceiver and communication device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211029 |
|
| RJ01 | Rejection of invention patent application after publication |