CN110474674B - Load data interface device for satellite communication - Google Patents
Load data interface device for satellite communication Download PDFInfo
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- CN110474674B CN110474674B CN201910792508.2A CN201910792508A CN110474674B CN 110474674 B CN110474674 B CN 110474674B CN 201910792508 A CN201910792508 A CN 201910792508A CN 110474674 B CN110474674 B CN 110474674B
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- 230000006854 communication Effects 0.000 title claims abstract description 31
- 238000004891 communication Methods 0.000 title claims abstract description 31
- 230000005540 biological transmission Effects 0.000 claims abstract description 27
- 238000001228 spectrum Methods 0.000 claims abstract description 24
- 238000006243 chemical reaction Methods 0.000 claims abstract description 6
- 238000005070 sampling Methods 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 230000003993 interaction Effects 0.000 abstract description 4
- 230000007175 bidirectional communication Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 6
- 239000000306 component Substances 0.000 description 3
- 238000013480 data collection Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000008358 core component Substances 0.000 description 1
- 238000013524 data verification Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005562 fading Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
Classifications
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- 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
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- 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
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/06—Notations for structuring of protocol data, e.g. abstract syntax notation one [ASN.1]
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/26—Special purpose or proprietary protocols or architectures
-
- 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
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- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Computer Security & Cryptography (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Computing Systems (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention provides a load data interface device for satellite communication, which comprises a control unit, a demodulation module, a modulation module, a spectrum channel analysis module and a radio frequency unit, wherein the control unit is used for receiving a signal from a satellite; the control unit receives CAN bus level signals to be coded and serial bus level signals sent by the CAN bus and the serial bus, sends the CAN bus level signals and the serial bus level signals to the modulation module, receives demodulated CAN bus level signals and serial bus level signals sent by the demodulation module, and sends the CAN bus level signals and the serial bus level signals outwards through the CAN bus and the serial bus; the modulation module carries out modulation coding and voltage conversion on the CAN bus level signal to be coded and the serial bus level signal; the demodulation module demodulates the signal to be demodulated. The load data interface device for satellite communication provided by the invention has a wide application range, and can be used for realizing information interaction among loads, satellite systems and data transmission systems and communication among loads, ground data centers and terminals.
Description
Technical Field
The invention relates to the technical field of satellite communication, in particular to a load data interface device for satellite communication.
Background
With the continuous development of electronic technology and computer technology, the complexity of spaceflight tasks is improved, and the load data interface forms of the spaceborne equipment are more and more diversified. The CAN signal interface, the RS-485 signal interface and the RS-422 signal interface are widely applied to the satellite-borne equipment. The load data interface of the satellite can realize the mutual data transmission among the load component, the satellite service system and the data transmission system, and also relates to the data communication between the satellite and the ground receiving bus.
The load component is a communication module on the satellite, and is used as a communication system for satellite data acquisition to acquire and receive information scattered in the satellite and transmit the information to a corresponding mechanism. The satellite system is used for inter-satellite communication, including coordination of inter-satellite time service, synchronization, location, messages, etc. when used in networking of multiple satellites. The data transmission system module is a core component of the satellite platform and is used for information transmission between the satellite and the ground station. The data transmission system mainly comprises an antenna system, a transmitter, a large dynamic AGC receiver, a signal processor and other main functional components.
However, the current technology lacks specifications and standards for the implementation of hardware devices, interface protocols and frame structures for mutual coordination of information interaction among loads, star systems and data transmission systems. In order to simplify the internal circuit structure of the satellite and reduce the design cost, so that the satellite integrated electronic system achieves high integration and comprehensiveness, fully realizes resource sharing and information fusion, and needs to design a high-efficiency load data interface device.
Disclosure of Invention
Therefore, the main purpose of the present invention is to provide a load data interface device for satellite communication, which has a wide application range, can be used for realizing information interaction among loads, satellite systems and data transmission systems, and communication among loads, ground data centers and terminals, and can be compatible with various signal interfaces, and has the advantages of low cost, high reliability, high expansibility, etc.
The invention adopts the technical scheme that the load data interface device for satellite communication comprises a control unit, a demodulation module, a modulation module, a spectrum channel analysis module and a radio frequency unit;
the control unit receives CAN bus level signals to be coded and serial bus level signals sent by the CAN bus and the serial bus, sends the CAN bus level signals and the serial bus level signals to the modulation module, receives demodulated CAN bus level signals and serial bus level signals sent by the demodulation module, and sends the CAN bus level signals and the serial bus level signals outwards through the CAN bus and the serial bus;
the modulation module carries out modulation coding and voltage conversion on the CAN bus level signal to be coded and the serial port bus level signal, and sends the CAN bus level signal to be coded and the serial port bus level signal to the radio frequency unit for sending;
the radio frequency unit receives the signals after modulation coding and voltage conversion and sends the signals outwards, and the radio frequency unit also receives the signals to be demodulated externally and sends the signals to the demodulation module;
the demodulation module demodulates the signal to be demodulated, generates a demodulated CAN bus level signal and a serial port bus level signal, sends the signals to the control unit, and sends sampling data to the spectrum channel analysis module;
and the spectrum channel analysis module receives the issued sampling data from the demodulation module through the synchronous clock interface, performs spectrum detection and channel analysis, and then sends an analysis result to the control unit through a serial bus.
The load data interface is used for realizing the communication of the load, the satellite system and the data transmission system, realizes the data compatibility of the CAN bus and the serial port bus by adopting the programmable control unit and the modulation module and the demodulation module, modulates and codes the signal to be coded received by the control unit by the modulation module, and transmits the signal to be demodulated received by the radio frequency unit to the control unit for signal processing by demodulating the radio frequency unit, thereby realizing the CAN communication of the load and the satellite system and the serial port communication of the data transmission system.
The control unit controls the transmitting channel and the receiving channel of the modulation module and the demodulation module respectively;
the channel control includes control of frequency and spreading code.
By the above, the control unit controls the frequency and spread spectrum code flow and data transmission respectively by the demodulation module and the modulation module, so that the demodulation module and the modulation module select the frequency and spread spectrum code to demodulate or modulate according to the program steps.
Further improved, the control unit is connected with the radio frequency unit through a serial peripheral interface, so that the frequency control of the intermediate frequency integrated module of the radio frequency unit is realized.
The frequency synthesizer module is used for generating the frequency signal sent by the radio frequency unit, and the frequency parameter is controlled by the control unit through the serial peripheral interface.
Wherein the control unit includes, but is not limited to: an FPGA chip, a DSP microprocessor or an MCU processor.
By the above, the related control functions of the signal processing and control unit are realized by adopting a programmable FPGA chip, a DSP microprocessor or an MCU processor.
The control unit realizes bidirectional communication with the star system through the CAN bus; the control unit realizes bidirectional communication with the data transmission system through an asynchronous serial bus.
Therefore, the load data interface device CAN realize the compatibility of the CAN bus and the serial port bus, so that the load is in bidirectional communication with the star system through the CAN bus and in bidirectional communication with the data transmission system through the asynchronous serial port bus.
Drawings
FIG. 1 is a schematic diagram of a satellite data collection system according to the present invention;
FIG. 2 is a schematic diagram of a payload data interface device for satellite communications according to the present invention;
FIG. 3 is a diagram of an interface protocol for communicating a payload with a data transmission system according to the present invention.
Detailed Description
A specific embodiment of the load data interface device for satellite communication according to the present invention will be described in detail with reference to fig. 1 to 3.
Fig. 1 is a schematic diagram of a satellite data collection system, where a satellite Data Collection System (DCS) includes a load 100, a satellite system 200, and a data transmission system 300, the satellite system 200 is responsible for data transmission among a plurality of satellites, and the data transmission system 300 is responsible for data transmission among satellites and output of measurement and control data. The load 100 is in bidirectional communication with the star system 200 through the CAN bus, in bidirectional communication with the data transmission system 300 through the asynchronous serial bus, and the star system 200 is in bidirectional communication with the data transmission system 300 through the CAN bus;
fig. 2 is a schematic diagram of a load data interface device for satellite communication, where it can be seen that the load data interface device for satellite communication provided by the present invention includes a control unit 101, a modulation module 102, a demodulation module 103, a spectrum channel analysis module 104, a radio frequency unit 105, and a serial bus for communication;
the control unit 101 may be implemented by programmable devices such as an FPGA chip, a DSP microprocessor, or an MCU processor, and bidirectional communication with the star system 200 is implemented through a CAN bus, and bidirectional communication with the data transmission system 300 is implemented through an asynchronous serial bus. The control unit 101 receives a CAN bus level signal to be encoded sent by the star system 200 and a serial bus level signal to be encoded sent by the data transmission system 300, and sends the CAN bus level signal to be encoded and the serial bus level signal to the modulation module 102 through a serial bus UART according to a pre-stored CAN bus control protocol and a serial bus control protocol;
the modulation module 102 is configured by the control unit 101 to set a transmitting channel thereof, wherein parameters set by the control unit include frequency, spread spectrum code and the like, and the modulation module 102 performs modulation coding and voltage conversion after receiving the CAN bus level signal to be coded and the serial port bus level signal, generates a high-frequency signal and sends the high-frequency signal to the radio frequency unit 105;
the radio frequency unit 105 includes a frequency synthesizer (frequency synthesizer), the frequency of which is controlled by the control unit 101 through the serial peripheral interface (SP 1 interface), and the radio frequency unit 105 sends out the received high-frequency signal according to the set frequency; in addition, the radio frequency unit 105 receives an external signal to be demodulated and sends the external signal to the demodulation module 103;
the demodulation module 103 sets a receiving channel of the control unit 101, the demodulation module 103 demodulates a signal to be demodulated, generates a CAN bus level signal and a serial bus level signal, sends the CAN bus level signal and the serial bus level signal to the control unit 101 through a serial bus UART, and simultaneously sends sampling data to the spectrum channel analysis module 104 through a synchronous clock interface;
the spectrum channel analysis module 104 performs spectrum detection on the sampled data sent by the demodulation module 103, detects whether a signal exists in a communication frequency band, performs channel analysis at the same time, analyzes the signal intensity in the communication frequency band, analyzes parameters such as channel fading, interference and the like, and sends the analysis result to the control unit 101 through a corresponding channel of a serial bus UART;
the control unit 101 sends the received demodulated CAN bus level signal and serial port bus level signal to the star service system 200 and the data transmission system 300 respectively through the CAN bus and the serial port bus according to a pre-stored CAN bus control protocol and a serial port bus control protocol.
In the embodiment of the invention, the serial port bus can be realized by serial port communication lines without data verification, 8-bit data bit, 1-bit stop bit and baud rate 19200.
Fig. 3 is a schematic diagram of an interface protocol for communication between a payload and a data transmission system according to the present invention, in this embodiment, the definition of a frame header, a frame type, a frame length and frame data is as follows:
frame header: occupy 4B bytes, fixed padding to 0xFAF30020;
frame type: occupying 4B bytes, and filling 0x00 for the frame being a data frame; the frame is spectrum data and is filled with 0x01 representation;
frame length: used for representing the length of the following frame data and occupying 2B bytes;
frame data: for filling data, when the frame type is a data frame, 26B bytes are occupied if the frame data is 208 bits, and 114B bytes are occupied if the frame data is 912 bits; when the frame type is spectrum data, the spectrum data occupies 512B bytes.
Compared with the existing data interface, the invention has the following advantages:
1. the application range is wide, and the method is used for information interaction among loads, stars and data transmission systems and communication among loads, ground data centers and terminals;
2. the implementation cost is low, and the reliability is higher due to the adoption of a mature device;
3. the method has high expansibility, and can conveniently increase the number of channels due to the adoption of a soft core (control unit) control mode, thereby having good expansibility.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (5)
1. The load data interface device for satellite communication is characterized by comprising a control unit, a demodulation module, a modulation module, a spectrum channel analysis module and a radio frequency unit;
the control unit respectively carries out transmitting channel control and receiving channel control on the modulation module and the demodulation module, wherein the channel control comprises control of frequency and spread spectrum code, the control unit receives CAN bus level signals to be coded and serial bus level signals sent by a CAN bus and a serial bus and sends the CAN bus level signals to the modulation module, and also receives demodulated CAN bus level signals and serial bus level signals sent by the demodulation module and sends the CAN bus level signals and the serial bus level signals outwards through the CAN bus and the serial bus;
the modulation module carries out modulation coding and voltage conversion on the CAN bus level signal to be coded and the serial port bus level signal, and sends the CAN bus level signal to be coded and the serial port bus level signal to the radio frequency unit for sending;
the radio frequency unit receives the signals after modulation coding and voltage conversion and sends the signals outwards, and the radio frequency unit also receives the signals to be demodulated externally and sends the signals to the demodulation module;
the demodulation module demodulates the signal to be demodulated, generates a demodulated CAN bus level signal and a serial port bus level signal, sends the signals to the control unit, and sends sampling data to the spectrum channel analysis module;
the spectrum channel analysis module receives the issued sampling data from the demodulation module through a synchronous clock interface, performs spectrum detection and channel analysis, and then sends an analysis result to the control unit through a serial bus;
the control unit realizes the two-way communication with the star system through the CAN bus and realizes the two-way communication with the data transmission system through the asynchronous serial bus.
2. The apparatus of claim 1, wherein the control unit is connected to the radio frequency unit through a serial peripheral interface to control the frequency of the intermediate frequency synthesizer module of the radio frequency unit.
3. The apparatus of claim 1, wherein the control unit includes, but is not limited to: an FPGA chip, a DSP microprocessor or an MCU processor.
4. The apparatus of claim 1, wherein the demodulation module, the modulation module, and the spectrum channel analysis module are implemented with the control unit by using the following serial communication lines:
there is no data check, 8 bits of data, 1 bit stop bit, baud rate 19200.
5. The apparatus of claim 1, wherein the control unit communicates with the data transmission system using the following format frames:
frame header: occupy 4B bytes, fixed padding to 0xFAF30020;
frame type: occupying 4B bytes, and filling 0x00 for the frame being a data frame; filling 0x01 for spectrum data;
frame length: used for representing the length of the following frame data and occupying 2B bytes;
frame data: for filling data, when the frame type is a data frame, 26B bytes are occupied if the frame data is 208 bits, and 114B bytes are occupied if the frame data is 912 bits; when the frame type is spectrum data, the spectrum data occupies 512B bytes.
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| CN201910792508.2A CN110474674B (en) | 2019-08-26 | 2019-08-26 | Load data interface device for satellite communication |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910792508.2A CN110474674B (en) | 2019-08-26 | 2019-08-26 | Load data interface device for satellite communication |
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| CN110474674A CN110474674A (en) | 2019-11-19 |
| CN110474674B true CN110474674B (en) | 2024-03-22 |
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|---|---|---|---|---|
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| CN203554492U (en) * | 2013-09-25 | 2014-04-16 | 上海微小卫星工程中心 | Controller LAN bus intelligent interface device and satellite |
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| CN207603634U (en) * | 2017-12-29 | 2018-07-10 | 西安思丹德信息技术有限公司 | A kind of data-link synthetical baseband plate number passes device |
| CN109981499A (en) * | 2019-03-29 | 2019-07-05 | 西安思丹德信息技术有限公司 | A kind of synthetical baseband data link system and data transmission method |
-
2019
- 2019-08-26 CN CN201910792508.2A patent/CN110474674B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR19980059165A (en) * | 1996-12-31 | 1998-10-07 | 유기범 | Data link inspection method of satellite communication system and channel modem for satellite communication system |
| CN102333057A (en) * | 2011-05-25 | 2012-01-25 | 北京航空航天大学 | Micro/nano satellite measure and control communication integral transmitting and receiving system and realization method thereof |
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