CN114070386A - Satellite-borne Ethernet communication system - Google Patents
Satellite-borne Ethernet communication system Download PDFInfo
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- CN114070386A CN114070386A CN202210046343.6A CN202210046343A CN114070386A CN 114070386 A CN114070386 A CN 114070386A CN 202210046343 A CN202210046343 A CN 202210046343A CN 114070386 A CN114070386 A CN 114070386A
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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
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B11/00—Communication cables or conductors
- H01B11/02—Cables with twisted pairs or quads
- H01B11/06—Cables with twisted pairs or quads with means for reducing effects of electromagnetic or electrostatic disturbances, e.g. screens
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Abstract
The application provides a satellite-borne Ethernet communication system, belongs to satellite technology field, and this system includes: the system comprises a house keeping computer and subsystems which are in communication connection with the house keeping computer through Ethernet; the satellite affair computer and the computer of each subsystem comprise a satellite-borne Ethernet communication device; the satellite-borne Ethernet communication device comprises: the FPGA chip is used for receiving, transmitting and processing data; the Ethernet communication chip is connected with the FPGA chip and used for combining first data sent by the FPGA chip into a sending sequence to be sent to the router and combining second data sent by the router into a receiving sequence to be transmitted to the FPGA chip. Through the Ethernet communication connection mode, the data bandwidth can be expanded, and the maximum data bandwidth can reach 1Gbps (transmission rate unit, one gigabit per second). Meanwhile, the hardware topology structure can be simplified, so that physical wiring in the satellite-borne Ethernet communication system is simpler.
Description
Technical Field
The application relates to the technical field of satellites, in particular to a satellite-borne Ethernet communication system.
Background
In a space-borne system of a spacecraft, currently, commonly used communication connection modes include a serial port communication mode, a bus communication mode, and a mode of data transmission through an LVDS (Low Voltage Differential Signaling) interface.
Since different subsystems in the on-board system may be configured with different communication interfaces, a relatively high hardware resource requirement is imposed on a core processing unit (such as an on-board computer in the on-board system). Meanwhile, the complexity of the satellite-borne system in physical connection can be increased by adopting the existing communication connection mode, and the increasing bandwidth requirement of the satellite-borne system cannot be met.
Disclosure of Invention
An object of the embodiments of the present invention is to provide a satellite-borne ethernet communication system, so as to reduce the complexity of the physical connection of the satellite-borne ethernet communication system and expand the data bandwidth.
The invention is realized by the following steps:
in a first aspect, an embodiment of the present application provides a satellite-borne ethernet communication system, including: the system comprises a house affair computer and subsystems which are in communication connection with the house affair computer through Ethernet; the satellite affair computer and the computer of each subsystem comprise a satellite-borne Ethernet communication device; the satellite-borne Ethernet communication device comprises: the FPGA chip is used for receiving, transmitting and processing data; the Ethernet communication chip is connected with the FPGA chip and used for combining first data sent by the FPGA chip into a sending sequence to be sent to the router and combining second data sent by the router into a receiving sequence to be transmitted to the FPGA chip.
In the embodiment of the application, the satellite computers and the computers in the subsystems are provided with the satellite-borne Ethernet communication devices, so that the satellite computers and the subsystems can be in communication connection through the Ethernet. Through the Ethernet communication connection mode, the data bandwidth can be expanded, and the maximum data bandwidth can reach 1Gbps (transmission rate unit, one gigabit per second). In addition, because the connection mode between the satellite computer and each subsystem is unified, the hardware topology structure can be simplified, and the physical wiring in the satellite-borne Ethernet communication system is simpler.
With reference to the technical solution provided by the first aspect, in some possible implementation manners, the apparatus further includes: a high-speed connector; the high-speed connector is connected with the Ethernet communication chip and is also used for being connected with the router.
In the embodiment of the application, the circuits in the satellite borne Ethernet communication system can be further managed through the uniform high-speed connector, so that the physical wiring of the whole satellite borne Ethernet communication system is simpler to a certain extent. Meanwhile, high-speed signal transmission can be further ensured through the high-speed connector.
With reference to the technical solution provided by the first aspect, in some possible implementations, the high-speed connector is a nine-core trapezoidal connector; the nine-core trapezoidal connector comprises a nine-core trapezoidal connector body, wherein a first wire core, a second wire core, a third wire core, a fourth wire core and a fifth wire core which are sequentially arranged are arranged close to the lower bottom edge of the nine-core trapezoidal connector body; a sixth wire core, a seventh wire core, an eighth wire core and a ninth wire core which are sequentially arranged are arranged close to the upper bottom edge of the nine-core trapezoidal connector; the first wire core, the second wire core, the sixth wire core and the seventh wire core are used for sending the sending sequence to the router; the fourth wire core, the fifth wire core, the eighth wire core and the ninth wire core are used for receiving second data sent by the router.
In the embodiment of the application, the high-speed connector is specifically a nine-core trapezoidal connector so as to adapt to the vibration mechanical environment and the irradiation environment of space application.
With reference to the technical solution provided by the first aspect, in some possible implementation manners, the satellite-borne ethernet communication device further includes an interface protection circuit; the interface protection circuit is respectively connected with the high-speed connector and the Ethernet communication chip.
In the embodiment of the present application, the interface protection circuit may be used for ESD (Electrostatic Discharge) and EMI (Electromagnetic Interference) protection, such as common mode rejection and lightning stroke protection. The optical fiber cable can also be used as physical isolation between the inside of an internal PCB (Printed Circuit Board) and the cable when signals are introduced, and can also be used for bridging and communicating effective information.
With reference to the technical solution provided by the first aspect, in some possible implementation manners, the ethernet communication chip is a three-speed ethernet PHY chip.
With reference to the technical solution provided by the first aspect, in some possible implementations, the house keeping computer and the computers of each of the subsystems each include a unified energy interface; the energy interface is used for connecting an energy subsystem.
In the embodiment of the application, the physical line of the whole satellite-borne Ethernet communication system can be further simplified through the unified energy interface.
With reference to the technical solution provided by the first aspect, in some possible implementation manners, the house keeping computer and each of the subsystems each include a main computer and a backup computer.
In the embodiment of the application, the data safety can be effectively protected through the backup computer, and the normal work of the subsystem can be ensured when the main computer fails through the backup computer.
With reference to the technical solution provided by the first aspect, in some possible implementations, the subsystems are also communicatively connected through an ethernet.
In the embodiment of the application, since the satellite computer and the computer of each subsystem comprise the satellite-borne ethernet communication device, the subsystems are also in communication connection through the ethernet. By the method, interconnection and intercommunication among all the subsystems can be realized, each subsystem can initiate or receive a task request, and connection links among the satellite-borne Ethernet communication systems are enriched.
In some possible implementation manners, the subsystem includes at least one of a measurement and transmission subsystem, an attitude control subsystem, a thermal control subsystem, an energy subsystem, and a load subsystem.
With reference to the technical solution provided by the first aspect, in some possible implementation manners, the satellite-borne ethernet communication device is connected to the router through a shielded cable; the shielding cable shields the cable core through two shielding layers, and the inside of the shielding cable is filled with fillers.
In the embodiment of the application, the transmission performance under the environment of electromagnetic interference and the like is enhanced by the double-layer shielding layer. And the looseness of the inner wire core is prevented through the filler, so that the use reliability of the shielding cable is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a block diagram of a satellite-borne system connected through an RS422 serial port according to the prior art.
Fig. 2 is a block diagram of a first satellite-borne ethernet communication system according to an embodiment of the present disclosure.
Fig. 3 is a block diagram of a first satellite-borne ethernet communication device according to an embodiment of the present disclosure.
Fig. 4 is a block diagram of a second satellite-borne ethernet communication device according to an embodiment of the present disclosure.
Fig. 5 is a schematic structural diagram of a nine-core trapezoidal connector according to an embodiment of the present application.
Fig. 6 is a cross-sectional view of a shielded cable provided in an embodiment of the present application, the cross-sectional view being taken along a vertical direction of extension.
Fig. 7 is a block diagram of a second satellite-borne ethernet communication system according to an embodiment of the present application.
Fig. 8 is a block diagram of a third satellite-borne ethernet communication system according to an embodiment of the present disclosure.
Icon: 1-a first wire core; 2-a second wire core; 3-a third wire core; 4-a fourth wire core; 5-a fifth wire core; 6-sixth wire core; 7-a seventh wire core; 8-eighth wire core; 9-ninth wire core; 10-satellite-borne ethernet communication system; 101-a house keeping computer; 102-a subsystem; 20-a satellite-borne ethernet communication device; 201-FPGA chip; 2011-ARM chip; 2012-ethernet interface module; 202-an ethernet communication chip; 203-high speed connector; 204-interface guard circuitry.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
In a space-borne system of a spacecraft, currently, commonly adopted communication connection modes include a serial port communication mode, a bus communication mode and a mode of data transmission through an LVDS interface.
Referring to fig. 1, fig. 1 shows a communication connection method through an RS422 serial port adopted by a current satellite based system. The RS422 serial port connection can only realize point-to-point communication connection between the satellite computer and each subsystem, and the method has more hardware resource usage, and the computer in each subsystem needs 4 signal wires to be connected with the satellite computer, which also puts higher hardware resource requirements on the satellite computer and increases the complexity of the physical connection of the whole satellite system.
And the serial communication of data is realized by using a pair of differential lines in a bus communication mode, the data transmission bandwidth is effective, the bandwidth generally does not exceed 1Mbps (transmission rate unit, megabit per second), and the complexity of the physical connection of the whole satellite-borne system is increased to a certain extent by using the bus communication mode.
If the subsystem is in communication connection with the housekeeping computer by using the LVDS interface, for example, the measurement and transmission subsystem in the subsystem is in communication connection with the housekeeping computer by using the LVDS interface, the housekeeping computer needs a plurality of channels to be connected to the measurement and transmission subsystem under a multi-load architecture, and the interfaces of the measurement and transmission subsystem cannot be increased infinitely. The increased number of interfaces in the transmission subsystem will increase the design difficulty and cost of the system.
And since different subsystems may be configured with different communication interfaces, this also puts higher hardware resource requirements on the core processing unit (such as an on-board computer in an on-board system).
It can be seen that the complexity of the physical connection of the satellite-borne system is increased during the configuration of the current communication connection mode, and the increasing bandwidth requirement of the satellite-borne system cannot be met. In view of the above problems, the present inventors have made extensive studies and studies to provide the following examples to solve the above problems.
Referring to fig. 2, an embodiment of the present invention provides a satellite-borne ethernet communication system 10, which includes a satellite computer 101 and subsystems 102 communicatively connected to the satellite computer 101 via an ethernet.
The star computer 101 is a core device in the satellite-borne ethernet communication system 10, and is mainly used for completing tasks such as satellite control, star management, data processing, and the like.
While subsystems 102 communicatively coupled to the star computer 101 via ethernet are used to implement different business functions. In the embodiment of the present application, subsystem 102 may be at least one of a measurement and transmission subsystem, an attitude control subsystem, a thermal control subsystem, an energy subsystem, and a load subsystem. Of course, subsystems of the on-board ethernet communication system 10 may include a measurement subsystem, an attitude control subsystem, a thermal control subsystem, an energy subsystem, and a load subsystem.
As the subsystems 102 are well known in the art, they will not be described in detail herein.
Referring to fig. 3, in the embodiment of the present application, the star computer 101 and each subsystem 102 are respectively provided with a satellite-borne ethernet communication device 20, so as to implement ethernet communication connection between the star computer 101 and each subsystem 102.
The satellite-borne ethernet communication device 20 includes an FPGA chip 201 and an ethernet communication chip 202.
The FPGA chip 201 is connected to the ethernet communication chip 202.
The FPGA chip 201 is also connected to a main controller of the device. In an exemplary embodiment, the FPGA chip 201 is further connected to a main controller of the star computer 101, such as a Central Processing Unit (CPU) of the star computer 101, of the satellite-based ethernet communication device 20 disposed on the star computer 101. The FPGA chip 201 of the satellite-borne ethernet communication device 20 disposed on the computer of the subsystem 102 is further connected to the main controller of the computer. The FPGA chip 201 is specifically used for receiving, transmitting, and processing data. The processing of data includes, but is not limited to, caching of data, protocol stack processing, and application layer task scheduling.
In the embodiment of the present application, the model of the FPGA chip 201 may be M2S 090T.
The ethernet communication chip 202 is configured to combine the first data sent by the FPGA chip 201 into a sending sequence and send the sending sequence to the router, and combine the second data sent by the router into a receiving sequence and transmit the receiving sequence to the FPGA chip 201.
Specifically, when the ethernet communication chip 202 receives the first data sent by the FPGA chip 201, the first data may be encoded according to a physical layer encoding rule, filtered, and combined to form a sending sequence, and then the ethernet communication chip 202 sends the sending sequence to the router. When the ethernet communication chip 202 receives the second data returned by the router, the second data may be filtered, demodulated, and the like to form a receiving sequence, and then the ethernet communication chip 202 transmits the receiving sequence to the FPGA chip 201.
It should be noted that the ethernet communication chip 202 is a communication chip for implementing physical layer connection. In the embodiment of the present application, the ethernet communication chip 202 is a Physical Layer (PHY) chip, and the specific type of the PHY chip may be 88E 1340S. The high-speed signal transmission can be realized through the Ethernet communication chip 202 with the model and the FPGA chip 201 with the model of M2S090T, and three transmission rates of 1000/100/10Mbps are simultaneously supported.
As can be seen, since the satellite-borne ethernet communication device 20 is disposed in both the satellite computer 101 and the computers in each subsystem 102, the satellite computer 101 and each subsystem 102 can be communicatively connected through ethernet. Through the Ethernet communication connection mode, the data bandwidth can be expanded, and the maximum data bandwidth can reach 1Gbps (transmission rate unit, one gigabit per second). In addition, since the connection mode between the star computer 101 and each subsystem 102 is unified, the hardware topology architecture can be simplified, and the physical routing in the satellite-borne ethernet communication system 10 is simpler.
Referring to fig. 4, as an embodiment, the FPGA chip 201 may specifically include an ARM (Advanced RISC Machines) chip 2011 and an ethernet interface module 2012.
The ARM chip 2011 is configured with an application program and a protocol stack in advance, and the ARM chip 2011 is mainly used for receiving, sending, and processing data. The processing of data includes, but is not limited to, caching of data, protocol stack processing, and application layer task scheduling. Ethernet interface module 2012 acts as a connection bridge to connect ARM chip 2011 to ethernet communication chip 202. When the ethernet communication chip 202 is a three-speed ethernet PHY chip, the ethernet interface module 2012 is an ethernet PHY IP _ Core.
The ethernet interface module 2012 is configured with a First Input First Output (FIFO), a receiving FIFO, a Media Access Control Address (MAC) sending module, a MAC receiving module, and an interface.
It should be explained that a FIFO is an address area for data buffering. The MAC sending module is used for data sending and is a medium intervention layer. The MAC receiving module is used for receiving data, which is also a media intervention layer. The interface is used to physically connect with ethernet communication chip 202.
When external data is received through the satellite-borne ethernet communication device 20, the transmission path of the data is: the ethernet communication chip 202-interface-MAC sending module-sending FIFO-ARM chip 2011.
When data is sent out through the satellite-borne ethernet communication device 20, the transmission path of the data is: ARM chip 2011-receive FIFO-MAC receive module-interface-ethernet communication chip 202.
With continued reference to fig. 4, the on-board ethernet communication device 20 may optionally further include a high-speed connector 203.
High-speed connector 203 is connected to ethernet communication chip 202. The high speed connector 203 is also used to connect with a router.
The circuits in the satellite borne ethernet communication system 10 can be further managed through the unified high speed connector 203, so that the physical routing of the whole satellite borne ethernet communication system 10 is more concise to a certain extent. Meanwhile, high-speed signal transmission can be further ensured through the high-speed connector 203.
To accommodate the vibrational mechanical environment and the radiation environment of space applications, the high-speed connector 203 may employ a nine-core (9 pin) trapezoidal connector.
Referring to fig. 5, the nine-core trapezoidal connector includes nine cores.
The lower bottom edge (namely the lower bottom edge of the trapezoid) close to the nine-core trapezoidal connector is provided with a first wire core 1, a second wire core 2, a third wire core 3, a fourth wire core 4 and a fifth wire core 5 which are sequentially arranged. A sixth wire core 6, a seventh wire core 7, an eighth wire core 8 and a ninth wire core 9 which are sequentially arranged are arranged near the upper bottom edge (namely the lower bottom edge of the trapezoid) of the nine-core trapezoid-shaped connector.
In the nine-core ladder connector, data transmission is performed using eight cores, wherein the first core 1, the second core 2, the sixth core 6, and the seventh core 7 are used to transmit data, and the fourth core 4, the fifth core 5, the eighth core 8, and the ninth core 9 are used to receive data. And the third core 3 is used for the connection of an internal shielded wire.
Specifically, the first wire core 1, the second wire core 2, the sixth wire core 6 and the seventh wire core 7 are used for sending the sending sequence to the router. The fourth wire core 4, the fifth wire core 5, the eighth wire core 8 and the ninth wire core 9 are used for receiving second data sent by the router.
Of course, in other embodiments, the first wire core 1, the second wire core 2, the sixth wire core 6 and the seventh wire core 7 may be used for receiving data, and the fourth wire core 4, the fifth wire core 5, the eighth wire core 8 and the ninth wire core 9 may be used for transmitting data, which is not limited in this application.
It can be seen that, when the nine-core ladder-shaped connector is disposed in each satellite-borne ethernet communication device 20, the computer carrying the nine-core ladder-shaped connector can communicate with other computers only through an eight-core ethernet cable. The hardware topology structure of the computer carrying the nine-core trapezoidal connector is further simplified by the method, so that the wiring is simpler.
In the embodiment of the present application, the satellite-borne ethernet communication device 20 is connected to the router through a shielded cable.
When the ethernet-on-board communication device 20 includes the high-speed connector 203, the shielded cable is used to connect the high-speed connector 203 with the router.
The shielding cable provided by the embodiment of the application shields the wire cores through the double-layer shielding layer, and the inside of the shielding cable is filled with fillers, so that each wire core is stable. The transmission performance under the environment of electromagnetic interference and the like is enhanced by the double-layer shielding layer. And the looseness of the inner wire core is prevented through the filler, so that the use reliability of the shielding cable is improved.
Further, when the high-speed connector 203 is a nine-core trapezoidal connector, a shielded cable as shown in fig. 6 is used to connect the nine-core trapezoidal connector and the router. Fig. 6 shows a twisted pair shielded cable.
The twisted pair shielding cable takes every two cores as a group to form a twisted pair. There are four sets of twisted pairs in a twisted pair shielded cable. The core is formed by providing an insulating layer outside the conductor. And the twisted pair internal shielding layer and the twisted pair protective layer are sequentially arranged outside each group of twisted pairs. The inside of the shielding layer inside the twisted pair is filled with filler to ensure the stability of the twisted pair. And a bundling layer, an external shielding layer and an external protective layer are sequentially arranged outside the whole formed by the four groups of twisted pairs. The inside of the binding layer is filled with fillers to ensure the stability of the four groups of twisted pairs.
With continued reference to fig. 4, the on-board ethernet communication device 20 may further include an interface protection circuit 204.
The interface protection circuit 204 is connected to the high-speed connector 203 and the ethernet communication chip 202, respectively.
The interface protection circuit 204 can be used for ESD (Electrostatic Discharge) and EMI (Electromagnetic Interference) protection, such as common mode rejection and lightning strike protection. The optical fiber cable can also be used as physical isolation between the inside of an internal PCB (Printed Circuit Board) and the cable when signals are introduced, and can also be used for bridging and communicating effective information.
In a specific circuit structure, the interface protection circuit 204 may be implemented by an isolation transformer or an optical coupler, which is not limited in this application.
When external data is received through the satellite-borne ethernet communication device 20, the transmission path of the data is: the router-high-speed connector 203-the interface protection circuit 204-the ethernet communication chip 202-the interface-the MAC sending module-the sending FIFO-the ARM chip 2011.
When data is sent out through the satellite-borne ethernet communication device 20, the transmission path of the data is: ARM chip 2011-receive FIFO-MAC receive module-interface-Ethernet communication chip 202-interface protection circuit 204-high speed connector 203-router.
To further simplify the physical circuitry, in the present embodiment, in on-board ethernet communication system 10, both the star computer 101 and the computers of each subsystem 102 include a unified power interface. The energy interface is used for connecting the energy subsystem.
Specifically, according to the power supply pressure and power capacity of the star computer 101 and each subsystem 102, a proper energy source line is adapted, and then the energy source interfaces of the star computer 101 and the subsystems 102 are connected with the energy subsystems through the energy source line.
Referring to fig. 7, the satellite-borne ethernet communication system 10 includes two connection channels, one of which is an energy transmission channel and the other is an ethernet data transmission channel. In the satellite-borne ethernet communication system 10, the satellite computer 101 and the computer of each subsystem 102 are connected to the router through the satellite-borne ethernet communication device 20, so as to form an ethernet data transmission channel, so that the data in the subsystem 102 can be transmitted to the satellite computer 101 through the ethernet data transmission channel. The house keeping computer 101 and each subsystem 102 that needs to supply energy are connected to the energy subsystem through an energy line, so as to form an energy transmission channel, so that the energy subsystem supplies energy to other subsystems 102 and the house keeping computer 101.
It should be noted that the number of computers in each subsystem 102 is not limited in this application, for example, each subsystem 102 may include only one computer. Each subsystem 102 includes a computer that establishes an ethernet communication connection with the star computer 101.
In another embodiment, each subsystem includes a main computer and a backup computer, and the backup computer can effectively protect data security and can ensure the normal operation of the subsystem when the main computer fails. Wherein, the main computer and the backup computer both comprise the satellite-borne Ethernet communication device in the embodiment. In the embodiment of the application, both the main computer and the backup computer can be used for establishing Ethernet communication connection with the star computer. By the method, when the main computer in the subsystem is abnormal, the subsystem can be switched to the backup computer to carry out data transmission with the house keeping computer.
In addition, the primary computer and the backup computer in the subsystem may also include a unified power interface for connecting the power subsystem. Meanwhile, the house keeping computer 101 may also include a house keeping main computer and a house keeping backup computer; the house keeping host computer and the house keeping backup computer can also comprise a uniform energy interface to connect with the energy subsystem. Of course, it is also starting to set a uniform power interface for all computers.
Referring to fig. 8, the measurement and transmission subsystem includes a measurement and transmission main computer and a measurement and transmission backup computer; the attitude control subsystem comprises a measurement and transmission main computer and a measurement and transmission backup computer; the thermal control subsystem comprises a thermal control main computer and a thermal control backup computer; the energy subsystem comprises an energy main computer and an energy backup computer; the load subsystem comprises a load main computer and a load backup computer; the house keeping computer includes house keeping main computer and house keeping back computer.
The main computer and the backup computer can be connected to the Ethernet data transmission channel and can supply energy through the energy transmission channel.
In addition, because the computers in each subsystem are connected to the router through the satellite-borne Ethernet communication device, the subsystems can be connected in a communication mode through the Ethernet. By the method, interconnection and intercommunication among all the subsystems can be realized, each subsystem can initiate or receive a task request, and connection links among the satellite-borne Ethernet communication systems are enriched.
In addition, the ethernet communication method adopted in the embodiment of the present application realizes interconnection and interworking between any two devices and the characteristic of efficiently coordinating low latency through a TCP (Transmission Control Protocol), an IP (Internet Protocol) and a Powerlink (an open source real-time communication technology) communication Protocol. In the embodiment of the application, the identification of each computer of the subsystem is carried out through the MAC (Access Control Address), the media access Control address) address and the IP address, so that the computers work on the basis of the fast Ethernet IEEE802.3 standard in a unified way, the computer protocol standard is unified, and the compatibility and the expansibility of equipment are realized. The System may be built by using an OSI (Open System Interconnect) model, which is not limited in this application.
In summary, since the satellite-borne ethernet communication device 20 is provided in both the satellite computer 101 and the computers in the subsystems 102, the satellite computer 101 and the subsystems 102 can be communicatively connected by ethernet. Through the Ethernet communication connection mode, the data bandwidth can be expanded, and the maximum data bandwidth can reach 1Gbps (transmission rate unit, one gigabit per second). In addition, since the connection mode between the star computer 101 and each subsystem 102 is unified, the hardware topology architecture can be simplified, and the physical routing in the satellite-borne ethernet communication system 10 is simpler.
The functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. A satellite-borne ethernet communication system, comprising: the system comprises a house affair computer and subsystems which are in communication connection with the house affair computer through Ethernet;
the satellite affair computer and the computer of each subsystem comprise a satellite-borne Ethernet communication device;
the satellite-borne Ethernet communication device comprises:
the FPGA chip is used for receiving, transmitting and processing data;
the Ethernet communication chip is connected with the FPGA chip and used for combining first data sent by the FPGA chip into a sending sequence to be sent to the router and combining second data sent by the router into a receiving sequence to be transmitted to the FPGA chip.
2. The on-board ethernet communication system according to claim 1, wherein said on-board ethernet communication device further comprises: a high-speed connector;
the high-speed connector is connected with the Ethernet communication chip and is also used for being connected with the router.
3. An on-board ethernet communication system according to claim 2, wherein said high speed connector is a nine-core trapezoidal connector;
the nine-core trapezoidal connector comprises a nine-core trapezoidal connector body, wherein a first wire core, a second wire core, a third wire core, a fourth wire core and a fifth wire core which are sequentially arranged are arranged close to the lower bottom edge of the nine-core trapezoidal connector body; a sixth wire core, a seventh wire core, an eighth wire core and a ninth wire core which are sequentially arranged are arranged close to the upper bottom edge of the nine-core trapezoidal connector;
the first wire core, the second wire core, the sixth wire core and the seventh wire core are used for sending the sending sequence to the router; the fourth wire core, the fifth wire core, the eighth wire core and the ninth wire core are used for receiving second data sent by the router.
4. The on-board ethernet communication system according to claim 2, wherein said on-board ethernet communication device further comprises an interface protection circuit;
the interface protection circuit is respectively connected with the high-speed connector and the Ethernet communication chip.
5. The on-board ethernet communication system according to claim 1, wherein said ethernet communication chip is a three-speed ethernet PHY chip.
6. A system as claimed in claim 1, wherein said satellite computers and the computers of each of said subsystems comprise a unified power interface; the energy interface is used for connecting an energy subsystem.
7. A system as claimed in claim 1, wherein said satellite computer and each of said subsystems comprise a primary computer and a backup computer.
8. An on-board ethernet communication system according to claim 1, wherein said subsystems are also communicatively connected via ethernet.
9. The on-board ethernet communication system according to claim 1, wherein said subsystem comprises at least one of a measurement subsystem, an attitude control subsystem, a thermal control subsystem, an energy subsystem, and a load subsystem.
10. The on-board ethernet communication system according to claim 1, wherein said on-board ethernet communication device is connected to said router by a shielded cable;
the shielding cable shields the cable core through two shielding layers, and the inside of the shielding cable is filled with fillers.
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| CN202210046343.6A CN114070386B (en) | 2022-01-17 | 2022-01-17 | Satellite-borne Ethernet communication system |
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| CN115514410A (en) * | 2022-11-24 | 2022-12-23 | 成都国星宇航科技股份有限公司 | Remote sensing satellite data transmission system based on Ethernet |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030236916A1 (en) * | 2002-04-23 | 2003-12-25 | Adcox Timothy D. | Media access control address translation for a fiber to the home system |
| CN102594683A (en) * | 2012-02-17 | 2012-07-18 | 黑龙江省电力有限公司 | Special network switching method and equipment with synchronous digital hierarchy (SDH) network accurate clock synchronization function |
| CN106919153A (en) * | 2017-01-12 | 2017-07-04 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Electronic equipment on satellite Integrated system management and control framework |
| CN106936491A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | Satellite-carried wireless information system |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
| CN208796075U (en) * | 2018-10-23 | 2019-04-26 | 成都瑞特森科技有限公司 | A kind of wide-band linearity isolation collector |
| CN208881780U (en) * | 2018-07-25 | 2019-05-21 | 成都飞机工业（集团）有限责任公司 | A kind of anti-skid brake system (ABS) on-Line Monitor Device |
| CN110138442A (en) * | 2019-05-23 | 2019-08-16 | 上海微小卫星工程中心 | Floor synthetic test macro and method for satellite data transmission |
| CN110138440A (en) * | 2019-04-30 | 2019-08-16 | 中国空间技术研究院 | Space intelligent aircraft cloud side cooperative information processing framework |
| CN110417780A (en) * | 2019-07-30 | 2019-11-05 | 哈尔滨工业大学 | Customize the multi-channel high-speed data interface conversion module of Data Transport Protocol |
| CN110824508A (en) * | 2019-11-27 | 2020-02-21 | 中国科学院微小卫星创新研究院 | Reconfigurable navigation satellite simulator |
| CN111917453A (en) * | 2020-07-15 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Satellite integrated electronic system |
| CN212659070U (en) * | 2020-08-20 | 2021-03-05 | 深圳市绿联科技有限公司 | Adapter |
| CN214384910U (en) * | 2021-01-27 | 2021-10-12 | 上海赫千电子科技有限公司 | Synchronous transmission system of vehicle-mounted star-shaped ring network |
-
2022
- 2022-01-17 CN CN202210046343.6A patent/CN114070386B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030236916A1 (en) * | 2002-04-23 | 2003-12-25 | Adcox Timothy D. | Media access control address translation for a fiber to the home system |
| CN102594683A (en) * | 2012-02-17 | 2012-07-18 | 黑龙江省电力有限公司 | Special network switching method and equipment with synchronous digital hierarchy (SDH) network accurate clock synchronization function |
| CN106936491A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | Satellite-carried wireless information system |
| CN106919153A (en) * | 2017-01-12 | 2017-07-04 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Electronic equipment on satellite Integrated system management and control framework |
| CN208881780U (en) * | 2018-07-25 | 2019-05-21 | 成都飞机工业（集团）有限责任公司 | A kind of anti-skid brake system (ABS) on-Line Monitor Device |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
| CN208796075U (en) * | 2018-10-23 | 2019-04-26 | 成都瑞特森科技有限公司 | A kind of wide-band linearity isolation collector |
| CN110138440A (en) * | 2019-04-30 | 2019-08-16 | 中国空间技术研究院 | Space intelligent aircraft cloud side cooperative information processing framework |
| CN110138442A (en) * | 2019-05-23 | 2019-08-16 | 上海微小卫星工程中心 | Floor synthetic test macro and method for satellite data transmission |
| CN110417780A (en) * | 2019-07-30 | 2019-11-05 | 哈尔滨工业大学 | Customize the multi-channel high-speed data interface conversion module of Data Transport Protocol |
| CN110824508A (en) * | 2019-11-27 | 2020-02-21 | 中国科学院微小卫星创新研究院 | Reconfigurable navigation satellite simulator |
| CN111917453A (en) * | 2020-07-15 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Satellite integrated electronic system |
| CN212659070U (en) * | 2020-08-20 | 2021-03-05 | 深圳市绿联科技有限公司 | Adapter |
| CN214384910U (en) * | 2021-01-27 | 2021-10-12 | 上海赫千电子科技有限公司 | Synchronous transmission system of vehicle-mounted star-shaped ring network |
Non-Patent Citations (2)
| Title |
|---|
| PAUL C. HADDOCK: "Integrated Communications and Navigation Module", 《2012 IEEE INTERNATIONAL CARNAHAN CONFERENCE ON SECURITY TECHNOLOGY (ICCST)》 * |
| 田雪: "星上网络化通用服务单元设计与实现", 《中国优秀硕士学位论文全文数据库-信息科技辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115514410A (en) * | 2022-11-24 | 2022-12-23 | 成都国星宇航科技股份有限公司 | Remote sensing satellite data transmission system based on Ethernet |
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| CN114070386B (en) | 2022-04-26 |
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