CN114466040A - Spacecraft integrated biplane network system - Google Patents
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- H04L41/06—Management of faults, events, alarms or notifications
- H04L41/0654—Management of faults, events, alarms or notifications using network fault recovery
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Abstract
The invention provides a spacecraft integrated biplane network system, which consists of a control plane network system and a data plane network system, wherein the control plane network system consists of control plane switching equipment, data plane switching equipment, a control plane network node end, a data plane network node end, a biplane network node end and a host function end. The control plane network system and the data plane network system adopt star type, switching type and full duplex network architectures, and support single redundancy, double redundancy, triple redundancy symmetrical network architectures and multi-hop transmission. The control plane network system realizes the transmission of working state, health state, remote measuring service, remote control service, task control service and low-speed load remote sensing data among various host machine function ends in the spacecraft. The invention provides a design idea of 'unified inside and outside and one network to the end', provides a fusion design of a satellite borne network and an equipment network, and constructs an integrated and flat network system of a spacecraft.
Description
Technical Field
The invention relates to the technical field of satellite-borne electronic equipment, in particular to an integrated biplane network system of a spacecraft.
Background
Information transfer between the satellite-borne electronic devices is realized through special interconnection technology. A large amount of resources need to be consumed in traditional discrete signal interfaces and point-to-point communication, interconnection cost is relieved to a certain extent due to the introduction of a field bus technology, and a physical layer and link layer transmission system suitable for a space environment is established. However, in the face of the demands of satellite intellectualization and networking, the transmission barriers brought by heterogeneous field buses hinder the intra-satellite data sharing from moving to a higher stage, and the protocol conversion overhead is increased sharply due to the complication of intra-satellite, inter-satellite and satellite-ground links, so that the problem that the current satellite network needs to be solved urgently is solved. Some satellites adopt SpaceWire, Ethernet, wireless transmission and other technologies to construct high and low speed hybrid networks, and partially solve the problem of standardized interconnection and intercommunication, but on the level of the whole satellite and the level of a system architecture, the connection relationship, types and quantity are still complex and diverse, the problems of long links, inconsistent time delay, different bandwidths, poor fault tolerance, fault propagation, protocol barriers and the like are serious, and the physical basis and the information basis of the satellite-borne network are very weak.
Patent document No. CN112333071A discloses a communication method and system based on multiple bus network architectures, where the multiple bus network architectures include: a plurality of control terminals, switching bridges and network slaves; the NC node of the network controller in each control end sends a command frame to the NT node of the network terminal in the control end, the NT node receives the command frame and judges whether the command frame belongs to the node, if so, corresponding operation is carried out according to the command frame, otherwise, the command frame is sent to the switching network bridge through the ONU port of the optical network unit; the switching bridge forwards the command frame to the NT node corresponding to the command frame in the network slave through the optical line terminal OLT port.
The patent document with the publication number of CN108768754A discloses a high-reliability fault-tolerant system based on a bus network, wherein the fault-tolerant system comprises an analog IO control module, an interface and exchange module, an airborne flight control and comprehensive calculation module, a high-performance processing module, a digital IO control module, a router module and a corresponding dual-redundancy isomorphic module, the 6 modules and the corresponding dual-redundancy isomorphic module form 4 network connections to realize dual-redundancy hot backup, and the improvement of the fault-tolerant capability of the dual-redundancy system is realized by using a spaceWire interconnection bus architecture and a dual-ring topology structure.
A reconfigurable satellite-borne electronic system is disclosed in patent document CN 106411571A. The invention replaces the original shared bus network or point-to-point connection with the exchange network, takes the network and the information as the core, and improves the reliability of the system through the redundancy design. In the reconfigurable satellite-borne electronic system, each device carries out data interaction through a satellite-borne network switch; the satellite-borne network switch consists of a load switch and a platform switch, and the platform switch is connected with the load switch through a load network interface; the equipment related to the load in the satellite-borne electronic system is connected with the load switch, and the platform equipment in the satellite-borne electronic system is connected with the platform switch.
The invention discloses a 1553B bus network simulation system suitable for a spacecraft system in patent document with publication number CN101977133A, which belongs to the field of aerospace and computer simulation, and comprises a 1553B bus, an Ethernet, a bus network tester, a bus terminal tester, a digital fluorescence oscilloscope, a bus separation switch, a simulation terminal, a bus system performance evaluation computer and a bus interface control file configuration calculation, wherein the bus system performance evaluation computer is used for simulating and analyzing information transmission and system operation of an actual spacecraft bus system.
Other publications also propose spacecraft bus networks constructed based on MIL-STD-1553B, CAN, SpaceWire, time triggered Ethernet, AFDX and other technologies. The system design scheme has certain help in the aspects of reducing information interaction barriers, reducing complexity of connection relations among equipment, improving information sharing capability and fault tolerance capability and the like, but the following problems generally exist:
1. generally, optimization is performed on a certain characteristic of a spacecraft network, for example, reliability is improved by improving redundancy or cross redundancy, and data transmission efficiency is improved by designing a plurality of sub-networks;
2. generally, a spacecraft is designed for certain type of data transmission, for example, a network is designed for high-speed load data, but the spacecraft cannot be well compatible with low-speed control data transmission with higher real-time and certainty requirements;
3. there is no fundamental reduction in spacecraft attachment. Under the condition that the number, types and frequency of information interaction of the current spacecraft are increased sharply, barriers for information interaction of various devices in the satellite need to be opened, a flattened connection relation is constructed, and the cost caused by the interconnection barriers is reduced to the maximum extent.
Therefore, a technical solution is needed to improve the above technical problems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an integrated biplane network system for a spacecraft.
The spacecraft integrated biplane network system provided by the invention comprises a control plane switching device, a data plane switching device, a control plane network node end, a data plane network node end, a biplane network node end and a host function end, wherein the control plane switching device, the data plane switching device, the control plane network node end, the data plane network node end, the biplane network node end and the host function end form a control plane network system and a data plane network system;
the control plane switching equipment comprises a control plane switch in an independent single machine form and a plugboard type control plane switching module in a non-independent single machine form; the data plane switching equipment comprises a data plane switch in an independent single machine form and a plugboard type data plane switching module in a non-independent single machine form;
the control plane network node end is connected with the control plane switching equipment through a physical link to receive and transmit data; the data plane network node end is connected with the data plane switching equipment through a physical link to receive and transmit data; and the biplane network node end is respectively connected with the control plane switching equipment and the data plane switching equipment through physical links to receive and transmit data.
Preferably, the host functional end is an abstract description of an electronic single machine or module for realizing specific functions of the spacecraft; the host function end and the control plane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is accessed into the control plane network system through the control plane network node end; the host function end and the data plane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is accessed into the data plane network system through the data plane network node end; the host function end and the biplane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is respectively accessed to the control plane network system and the data plane network system through the biplane network node end;
the control plane switching equipment configures a data plane network node end and accesses a data plane network system through the data plane network node end; the data plane switching equipment is configured with a control plane network node end, and is accessed to a control plane network system through the control plane network node end; if the host function end is configured with a biplane network node end and has the functions of receiving, transmitting and processing data of the control plane and the data plane, the host function end completes bidirectional protocol bridging of the control plane and the data plane.
Preferably, the control plane network system and the data plane network system adopt star, switched and full-duplex network architectures.
Preferably, the control plane switching device, the data plane switching device, the control plane network node end, the data plane network node end and the bi-plane network node end of the control plane network system and the data plane network system support a single-redundancy, dual-redundancy and tri-redundancy symmetrical network architecture.
Preferably, the control plane switching device and the data plane switching device of the control plane network system and the data plane network system support multi-hop transmission.
Preferably, the control plane network system transmits the working state, the health state, the telemetering service, the remote control service, the task control service and the low-speed load remote sensing data among various host function terminals in the spacecraft.
Preferably, the data plane network system transmits high-speed load remote sensing data among various host function terminals in the existing spacecraft.
Preferably, if the control plane network system or the data plane network system is of a single redundant network architecture, the control plane switching device is connected to other control plane switching devices, and the data plane switching device is connected to other data plane switching devices.
Preferably, if the control plane network system or the data plane network system is a dual redundant network architecture, each control plane switching device or each data plane switching device has two independent backups; the first parts of all the control plane switching devices are connected according to the topology, and the second parts of all the control plane switching devices are connected according to the same topology relation; the first shares of all data plane switching devices are connected according to topology and the second shares of all data plane switching devices are connected according to the same topology.
Preferably, if the control plane network system or the data plane network system is a triple redundant network architecture, each control plane switching device or each data plane switching device has three independent backups; the first shares of all the control plane switching devices are connected according to the topology, and the second shares and the third shares of all the control plane switching devices are connected according to the same topology relation; the first shares of all the data plane switching devices are connected according to the topology, and the second shares and the third shares of all the data plane switching devices are connected according to the same topology relation.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention provides a control plane network and a data plane network, which meet the transmission requirements of various types of satellite-borne data on the same physical link, and compared with the traditional point-to-point and bus connection modes, the invention reduces the connection types and the number and reduces the data transmission resource overhead;
2. the invention realizes the integration design of the satellite-borne network and the equipment network from the aspect of cross-domain development of network technology, realizes direct access to the equipment module level through the exchange module, reduces the protocol conversion overhead in the data transmission process, improves the real-time performance and the reliability of data transmission, and realizes the flat network interconnection of 'internal and external unification and one network to the end';
3. the invention provides bidirectional protocol bridging between a control plane network and a data plane network, realizes data interconnection and intercommunication between different networks, and can further improve the network reliability by cross-plane degradation backup transmission when a network fails;
4. the control plane network and the data plane network provided by the invention are suitable for single redundancy, double redundancy and triple redundancy network architectures and multi-hop transmission, are flexible in topological relation connection mode, and can meet the requirements of different network transmission reliability and network scale.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a functional block diagram of an integrated biplane network system for a spacecraft of the present invention;
FIG. 2a is a schematic diagram of a single redundant connection of a control plane network system according to the present invention;
FIG. 2b is a schematic diagram of dual redundant connections of the control plane network system according to the present invention;
FIG. 2c is a schematic diagram of triple-redundant connection in the control plane network system according to the present invention;
FIG. 3a is a schematic diagram of a single redundant connection of a data plane network system according to the present invention;
FIG. 3b is a schematic diagram of dual redundant connections of the data plane network system according to the present invention;
FIG. 3c is a schematic diagram of triple redundant connections in the data plane network system according to the present invention;
fig. 4 is a diagram of an implementation manner of the spacecraft integrated biplane network system of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Aiming at the requirements of intelligent and networking development of satellites on high reliability, high bandwidth and high real-time satellite-borne data transmission, the invention analyzes the uniformity of the internal connection of satellite-borne electronic equipment and the connection design among equipment from the perspective of cross-domain development of network technology, provides a design idea of 'internal and external unification and one-network-to-the-end', constructs a flat connection relation, realizes cross-domain seamless sharing of data and forms an integrated network interconnection system.
The invention aims to provide an integrated biplane network system of a spacecraft, and provides a fusion design of a satellite-borne network and an equipment network, wherein an external network realizes direct access to an equipment module level through a switching module, the connection form of network links is normalized, the connection types are reduced, and integrated and flattened network interconnection is realized.
For further detailed description of the present invention, a functional block diagram of a spacecraft integrated biplane network system designed by the present invention is shown in fig. 1.
The spacecraft integrated double-plane network system is formed by a control plane network system and a data plane network system which are formed by control plane switching equipment, data plane switching equipment, a control plane network node end, a data plane network node end, a double-plane network node end, a host function end and other types of products.
The control plane switching equipment comprises a control plane switch in an independent single machine form and a plugboard type control plane switching module in a non-independent single machine form; the data plane switching equipment comprises a data plane switch in an independent single machine form and a plugboard type data plane switching module in a non-independent single machine form.
The control plane network node end is connected with the control plane switching equipment through a physical link to receive and transmit data; the data plane network node end is connected with the data plane switching equipment through a physical link to receive and transmit data; the biplane network node end is respectively connected with the control plane switching equipment and the data plane switching equipment through physical links to receive and transmit data.
The host function end is the abstract description of an electronic single machine or module for realizing the specific function of the spacecraft; the host function end and the control plane network node end can be combined to form various terminal single machines or modules of the spacecraft, and the host function end is accessed to the control plane network system through the control plane network node end to realize the specific function of the spacecraft; the host function end can also be combined with the data plane network node end to form various terminal single machines or modules of the spacecraft, and the host function end is connected into the data plane network system through the data plane network node end to realize the specific function of the spacecraft; the host function end can also be combined with the biplane network node end to form various terminal single machines or modules of the spacecraft, and the host function end is respectively accessed to the control plane network system and the data plane network system through the biplane network node end to realize the specific function of the spacecraft.
In order to realize message transmission between a control plane network system and a data plane network system, there are two implementation modes, one is to perform protocol bridging at a switching device, and the other is to perform protocol bridging at a node end. The control plane switching equipment can configure a data plane network node end and access a data plane network system through the data plane network node end; the data plane switching device can also configure a control plane network node end, and access the control plane network system through the control plane network node end. If the host function end is configured with a biplane network node end and has the functions of receiving, transmitting and processing data of the control plane and the data plane, the host function end completes the bidirectional protocol bridging of the control plane and the data plane.
The control plane network system and the data plane network system adopt star, switched and full duplex network architectures. The control plane network system realizes the transmission of information such as working state, health state, remote measurement service, remote control service, task control service, low-speed load remote sensing data and the like among various host function terminals in the spacecraft. The data plane network system realizes the transmission of high-speed load remote sensing data and other large data volume messages among various host functional ends in the spacecraft.
The control plane switching equipment, the data plane switching equipment, the control plane network node end, the data plane network node end and the double-plane network node end of the control plane network system and the data plane network system support a single-redundancy, double-redundancy and triple-redundancy symmetrical network architecture and multi-hop transmission. If the control plane network system or the data plane network system is of a single redundant network architecture, the control plane switching device is connected to other control plane switching devices, as shown in fig. 2(a), the control plane switching device 1 is connected to the control plane switching device 2; the data plane switching device is connected with other data plane switching devices, as shown in fig. 3(a), the data plane switching device 1 is connected with the data plane switching device 2.
If the control plane network system or the data plane network system is a dual redundant network architecture, each control plane switching device or data plane switching device has two independent backups; as shown in fig. 2(B), the control plane switching device 1-a and the control plane switching device 1-B backup each other, the control plane switching device 2-a and the control plane switching device 2-B backup each other, the control plane switching device 1-a is connected to the control plane switching device 2-a, and the control plane switching device 1-B is connected to the control plane switching device 2-B; as shown in fig. 3(B), the data plane switching device 1-a and the data plane switching device 1-B backup each other, the data plane switching device 2-a and the data plane switching device 2-B backup each other, the data plane switching device 1-a is connected to the data plane switching device 2-a, and the data plane switching device 1-B is connected to the data plane switching device 2-B.
If the control plane network system or the data plane network system is a triple redundant network architecture, each control plane switching device or data plane switching device has three independent backups; as shown in fig. 2(C), the control plane switching device 1-a, the control plane switching device 1-B and the control plane switching device 1-C are backed up with each other, the control plane switching device 2-a, the control plane switching device 2-B and the control plane switching device 2-C are backed up with each other, the control plane switching device 1-a is connected to the control plane switching device 2-a, the control plane switching device 1-B is connected to the control plane switching device 2-B, and the control plane switching device 1-C is connected to the control plane switching device 2-C; as shown in fig. 3(C), the data plane switching device 1-a, the data plane switching device 1-B, and the data plane switching device 1-C backup each other, the data plane switching device 2-a, the data plane switching device 2-B, and the data plane switching device 2-C backup each other, the data plane switching device 1-a is connected to the data plane switching device 2-a, the data plane switching device 1-B is connected to the data plane switching device 2-B, and the data plane switching device 1-C is connected to the data plane switching device 2-C.
In this example, the control plane network system uses time triggered ethernet, and the data plane network system uses RapidIO, as shown in fig. 4. The time-triggered Ethernet switch A and the time-triggered Ethernet switch B are control plane switches in an independent single machine form, and the two switches are a dual-redundancy network architecture which is a backup. The RapidIO switch A, RapidIO switch B is a data plane switch in an independent stand-alone form, and the two switches are a dual-redundancy network architecture which is a backup of each other. The switching modules in the integrated management unit, the data storage unit, the data processing unit A and the data processing unit B are plugboard type control plane switching modules in a non-independent single machine form. The integrated management unit is A, B main and standby in the whole machine, the exchange module A and the exchange module B are mutually backups, the data processing unit A and the data processing unit B are A, B main and standby between the whole machines, and the exchange modules in the single machine are mutually backups. The data storage unit is backups-free. Thus, the control plane is 3 hops and the data plane is 1 hop in this example.
The responder 1, the responder 2, the navigation receiver, the inter-satellite terminal, the satellite sensor 1, the satellite sensor 2, the flywheel and the gyroscope are various terminal single-machine products formed by combining a host function end and a control plane network node end. The function modules in the integrated management unit, the data storage unit, the data processing unit A and the data processing unit B are various module products formed by combining a host function end and a control plane network node end. The data compression unit 1, the data preprocessing unit 1, the load system 1, the data compression unit 2, the data preprocessing unit 2 and the load system 2 are various terminal single-machine products formed by combining a host function end and a data plane network node end. The data transmitter and the relay transmitter are various terminal single-machine products formed by combining a host function end and a biplane network node end.
The invention provides a fusion design of a satellite-borne network and an equipment network, an external network realizes direct access to an equipment module level through an exchange module, the connection form of a network link is normalized, the connection type is reduced, and integrated and flattened network interconnection is realized; from the perspective of cross-domain development of network technology, the unity of internal connection of the satellite-borne electronic equipment and connection design between the equipment is analyzed, a design idea of 'unified inside and outside and one network to the bottom' is provided, a flat connection relation is constructed, cross-domain seamless sharing of data is achieved, and an integrated network interconnection system is formed.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A spacecraft integrated biplane network system is characterized by comprising control plane switching equipment, data plane switching equipment, a control plane network node end, a data plane network node end, a biplane network node end and a host function end, wherein the control plane switching equipment, the data plane switching equipment, the control plane network node end, the data plane network node end, the biplane network node end and the host function end form a control plane network system and a data plane network system;
the control plane switching equipment comprises a control plane switch in an independent single machine form and a plugboard type control plane switching module in a non-independent single machine form; the data plane switching equipment comprises a data plane switch in an independent single machine form and a plugboard type data plane switching module in a non-independent single machine form;
the control plane network node end is connected with the control plane switching equipment through a physical link to receive and transmit data; the data plane network node end is connected with the data plane switching equipment through a physical link to receive and transmit data; and the biplane network node end is respectively connected with the control plane switching equipment and the data plane switching equipment through physical links to receive and transmit data.
2. A spacecraft-integrated biplane network system according to claim 1, wherein the host functional side is an abstract description of an electronic standalone or module implementing a specific function of a spacecraft; the host function end and the control plane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is accessed into the control plane network system through the control plane network node end; the host function end and the data plane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is connected into the data plane network system through the data plane network node end; the host function end and the biplane network node end are combined to form various terminal single machines or modules of the spacecraft, and the host function end is respectively accessed to the control plane network system and the data plane network system through the biplane network node end;
the control plane switching equipment configures a data plane network node end and accesses a data plane network system through the data plane network node end; the data plane switching equipment is configured with a control plane network node end and is accessed into a control plane network system through the control plane network node end; if the host function end is configured with a biplane network node end and has the functions of receiving, transmitting and processing data of the control plane and the data plane, the host function end completes bidirectional protocol bridging of the control plane and the data plane.
3. A spacecraft-integrated biplane network system according to claim 1, wherein the control plane network system and data plane network system employ a star, switched, full-duplex network architecture.
4. A spacecraft integrated biplane network system according to claim 1, wherein the control plane switching devices, data plane switching devices, control plane network node ends, data plane network node ends and biplane network node ends of the control plane network system and data plane network system support a single-redundancy, double-redundancy, triple-redundancy symmetric network architecture.
5. A spacecraft integrated biplane network system according to claim 1, wherein control plane switching devices and data plane switching devices of the control plane network system and data plane network system support multi-hop transmission.
6. A spacecraft-integrated biplane network system according to claim 1, wherein the control plane network system performs transmission of operating state, health state, telemetry service, remote control service, task control service, and low-speed load remote sensing data among various host function terminals in a spacecraft.
7. A spacecraft integrated biplane network system according to claim 1, wherein the data plane network system is used for transmitting high-speed load remote sensing data between various host function terminals in the existing spacecraft.
8. A spacecraft integrated biplane network system according to claim 4, wherein if the control plane network system or the data plane network system is of a single redundant network architecture, the control plane switching device is connected to other control plane switching devices, and the data plane switching device is connected to other data plane switching devices.
9. A spacecraft integrated biplane network system according to claim 4, wherein if the control plane network system or the data plane network system is a dual redundant network architecture, each control plane switching device or data plane switching device has two independent backups with each other; the first parts of all the control plane switching devices are connected according to the topology, and the second parts of all the control plane switching devices are connected according to the same topology relation; the first shares of all data plane switching devices are connected according to topology and the second shares of all data plane switching devices are connected according to the same topology.
10. A spacecraft integrated biplane network system according to claim 4, wherein if the control plane network system or the data plane network system is a triple redundant network architecture, each control plane switching device or data plane switching device has three independent backups with each other; the first shares of all the control plane switching devices are connected according to the topology, and the second shares and the third shares of all the control plane switching devices are connected according to the same topology relation; the first shares of all the data plane switching devices are connected according to the topology, and the second shares and the third shares of all the data plane switching devices are connected according to the same topology relation.
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