CN108173587B - Space station space technology test information management system based on network communication - Google Patents
Space station space technology test information management system based on network communication Download PDFInfo
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- CN108173587B CN108173587B CN201711412171.5A CN201711412171A CN108173587B CN 108173587 B CN108173587 B CN 108173587B CN 201711412171 A CN201711412171 A CN 201711412171A CN 108173587 B CN108173587 B CN 108173587B
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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
- H04B7/155—Ground-based stations
- H04B7/15528—Control of operation parameters of a relay station to exploit the physical medium
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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
- H04B7/18502—Airborne stations
- H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
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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
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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
- H04B7/18517—Transmission equipment in earth stations
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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
- H04B7/18523—Satellite systems for providing broadcast service to terrestrial stations, i.e. broadcast satellite service
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40006—Architecture of a communication node
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40267—Bus for use in transportation systems
- H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
Abstract
The invention relates to a space station space technology test information management system based on network communication, which aims at the high-capacity and high-speed downlink requirements of each test load of a space station, realizes an information scheme and a communication protocol for carrying out communication transmission by utilizing various data such as remote measurement, instructions, broadcasting and programs in a network communication mode, is the first application of the network communication technology on a spacecraft, and has wide popularization and application prospects.
Description
Technical Field
The invention relates to a space station aerospace technology test information management system based on network communication, and belongs to the technical field of space station engineering aerospace technology tests.
Background
The space station aerospace technology test is a new aerospace technology test carried out on a space station platform by utilizing a platform and space environment resources. Aiming at the transmission requirements of high-capacity and high-speed data communication of various novel test loads and the purpose of reducing the bus resource consumption of a test system, the traditional bus communication technology cannot meet the communication requirements of an on-orbit test of a space station aerospace technology test, and a novel communication scheme needs to be designed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a space station space technology test information management system based on network communication, which can meet the downlink requirements of large capacity and high speed of each test load of a space station and effectively improve the network communication efficiency of the space station.
The invention adopts the following technical scheme for solving the technical problems: the invention designs a space station space technology test information management system based on network communication, which comprises a cargo ship, a ground system of the cargo ship, a space-based system and a ground system, wherein the space-based system comprises a space station space-based system and a space-based system; wherein, the cargo ship comprises a load management unit and a network switch; the ground system of the cargo ship comprises a master control device and a measurement and control device; the space-based system comprises a device A and each device B; the ground system comprises a ground flight control support system, an equipment A self-checking device and each equipment B self-checking device; in the space-based system, each B device is communicated with the A device in a signal acquisition line or network communication mode; in the ground system, the equipment A self-checking device and each equipment B self-checking device are respectively communicated with the ground flight control support system in a network communication mode; a device in the space-based system is communicated with a load management unit in the cargo ship through a bus communication mode, and simultaneously, the A device is communicated with a network switch in the cargo ship through a network communication mode; the master control equipment and the measurement and control equipment in the ground system of the freight ship are respectively communicated with the ground flight control support system in the ground system in a network communication mode; the load management unit in the freight airship is communicated with the master control equipment in the ground system of the freight airship; the network switch in the freight ship is communicated with the measurement and control equipment in the ground system of the freight ship.
As a preferred technical scheme of the invention: the space station space technology test information management system adopts two mutually independent data transmission channels aiming at the transmission of each data: a measurement and control data channel and a service data channel; the measurement and control data channel is mainly used for transmitting control instructions, telemetering data, an upper note program and broadcast information from superior cargo ship/A equipment; the service data channel is mainly used for transmitting test data and equipment state data generated or transmitted by the A equipment/B equipment in the test process.
As a preferred technical scheme of the invention: the device A and each device B are respectively and automatically designed with a cache region, wherein the size of the cache region of the device B can at least store complete data of 2 minimum test periods; the buffer area of the device A is allocated to the device B according to the size of 5GB of each device B, the device B preferentially uses the buffer area of the device A in a first-in first-out mode in the test process, once the pre-allocated storage threshold value is reached, the device A sends a data transmission forbidding command to enable the device B not to receive data any more, and the data is reported to the ground through telemetering data, and at the moment, the device B needs to buffer the data automatically.
As a preferred technical scheme of the invention: the device A and each device B support breakpoint continuous transmission.
As a preferred technical scheme of the invention: in the space-based system, each B device is communicated with the A device through an RS422 acquisition signal line or a network communication mode.
As a preferred technical scheme of the invention: the bus communication mode is a 1553B bus communication mode.
As a preferred technical scheme of the invention: the network switch is an Ethernet switch, and the network communication mode is an Ethernet communication mode.
Compared with the prior art, the space station aerospace technology test information management system based on network communication has the following technical effects: the space station space technology test information management system based on network communication, which is designed by the invention, aims at the downlink requirements of large capacity and high speed of each test load of the space station, realizes an information scheme and a communication protocol for carrying out communication transmission on various data such as remote measurement, instructions, broadcasting, programs and the like by utilizing the Ethernet, is the first application of the Ethernet communication technology on a spacecraft, and has wide popularization and application prospects.
Drawings
FIG. 1 is an architecture diagram of a space station aerospace technology test information management system based on network communication according to the present invention;
FIG. 2 is a system configuration and network, RT terminal configuration of the space based system of the present invention;
FIG. 3 is a communication hierarchy of measurement and control data channels according to the present invention;
FIG. 4 is a schematic diagram of uplink and downlink packet/unpacking of a measurement and control data channel in the present invention;
FIG. 5 is a communication hierarchy of traffic data channels in the present invention;
fig. 6 is a schematic diagram of downlink packetization/depacketization of a traffic data channel in the present invention.
Detailed Description
The following description will explain embodiments of the present invention in further detail with reference to the accompanying drawings.
As shown in fig. 1, the invention relates to a space station space technology test information management system based on network communication, which comprises a cargo ship, a cargo ship ground system, a space-based system and a ground system; wherein, the cargo ship comprises a load management unit and an Ethernet switch; the ground system of the cargo ship comprises a master control device and a measurement and control device; the space-based system comprises a device A and each device B, and the specific space-based system is shown in figure 2; the ground system comprises a ground flight control support system, an equipment A self-checking device and each equipment B self-checking device; in the antenna-based system, each B device is communicated with the A device in a RS422 acquisition signal line or Ethernet communication mode; in the ground system, the equipment A self-checking device and each equipment B self-checking device are respectively communicated with the ground flight control support system in an Ethernet communication mode; a device in the space-based system is communicated with a load management unit in a cargo ship through a 1553B bus communication mode, and simultaneously, the A device is communicated with a network switch in the cargo ship through an Ethernet communication mode; the general control equipment and the measurement and control equipment in the ground system of the freight ship are respectively communicated with the ground flight control support system in the ground system in an Ethernet communication mode; the load management unit in the freight airship is communicated with the master control equipment in the ground system of the freight airship; the network switch in the freight ship is communicated with the measurement and control equipment in the ground system of the freight ship.
The invention relates to a space station space technology test information management system based on network communication, which adopts two mutually independent data transmission channels for the transmission of each data: a measurement and control data channel and a service data channel; the measurement and control data channel is mainly used for transmitting control instructions, telemetering data, an upper note program and broadcast information from superior cargo ship/A equipment; the service data channel is mainly used for transmitting test data and equipment state data generated or transmitted by the A equipment/B equipment in the test process. The device A and each device B are respectively designed with a cache region, wherein the size of the cache region of the device B can store at least 2 complete data of the minimum test period; the buffer area of the device A is allocated to the device B according to the size of 5GB of each device B, the device B preferentially uses the buffer area of the device A in a first-in first-out mode in the test process, once the pre-allocated storage threshold value is reached, the device A sends a data transmission forbidding command to enable the device B not to receive data any more, and the data is reported to the ground through telemetering data, and at the moment, the device B needs to buffer the data automatically.
The data reliability design is specified, and the device A and each device B support breakpoint continuous transmission in view of uncertainty of information channels between the heaven and the earth and between a cargo ship platform and a TZ-1 task system; in addition, as a network transport layer protocol (UDP) adopted by data downlink has no reliability guarantee mechanisms such as confirmation, congestion, disorder and the like, the independence of information is fully considered when B equipment is proposed to design a service data packet, the information association degree between the packet and the packet is reduced as much as possible, and the effective test data can be conveniently obtained to the maximum extent.
The space station space technology test information management system based on network communication that this patent designed, in practical application, to the B equipment that has a plurality of sub-test tasks, need to possess two kinds of states at least: a wait state and a test state. The waiting state refers to a state without a test task which is firstly entered after the equipment is powered on; the test state refers to the working state of the equipment performing the test task. For a B-device with multiple test sub-loads, as long as there is one sub-load performing the test task, it is in the test state. The current state of the B device needs to be reported to the ground in real time through 1553B.
Each information device (including a device A and a device B) is required to respond to the real-time detection of the working process and the health state of each information device (including the number of actual downlink total service data packets, all 1553B telemetering data which can be displayed in each detection device) and periodically downloads the data to the ground through a service channel to automatically analyze in real time.
Management of time distribution: the a device will periodically receive the current time broadcast by the cargo ship over the 1553B bus. The device A needs to correct the clock of the device A at a certain period, and with 10s as one period, the real-time of the device A is distributed to the device B through a broadcast message, and the maximum time deviation received by the device B does not exceed 1 s.
For the information interconnection in the space station space technology test information management system based on network communication, the device a and the device B (except B2) are in information interconnection through ethernet, and the device a and the cargo ship (i.e. the load management unit and the ethernet switch of the cargo ship) are in information interconnection through 1553B and ethernet respectively, as shown in fig. 2.
Information interconnection is carried out between the cargo ship and the equipment A through 1553B and an Ethernet (UDP), and an RT address, an IP address and a UDP port number are respectively allocated:
the cargo ship provides a 2-way information interface:
1553B bus BC terminal;
and secondly, accessing the gateway to the Ethernet, wherein the IP address is 172.22.8.1/20 (only a gateway is made, the gateway is not the destination address of the UDP data packet, the destination address is the IP address of the GCSS, the default is 172.18.0.134, the port is 55001, and the gateway can be set by the ground).
The a device provides a 2-way information interface:
1553B bus RT end, RT address is 4;
② the Ethernet access terminal, IP address is 172.22.9.128/20, UDP port number is 5000.
Device A and device BXThe (X ═ 1,3,4,5) devices exchange information through the ethernet (TCP), and allocate IP addresses and TCP port numbers (ANY represents an arbitrary port number) respectively:
the a device provides a 2-way information interface:
measuring and controlling interface, IP address is 10.0.0.100/24, TCP port number is 290;
② a service interface, the IP address is 10.0.0.100/24, and the TCP port number is 310.
Each BXThe equipment respectively provides 2 paths of information interfaces:
measuring and controlling an interface, wherein the IP address is 10.0.0.10X/24, and the TCP port number is ANY;
and the IP address is 10.0.0.10X/24 and the TCP port number is ANY.
Data transmission mechanism
In order to ensure the consistency of data, when the data is sent between the devices, the sequence of byte data is arranged according to the high-order byte at the low address and the low-order byte at the high address; the information checking mode is uniformly defined as accumulating and summing according to bytes, and taking 2 bytes at the bottom as a checking code.
The communication hierarchy and the packet packing/unpacking mechanism of the measurement and control data channel are shown in fig. 3 and 4, respectively.
Fig. 5 and 6 show the communication hierarchy of the service data channel and the packet packaging/unpacking mechanism, respectively.
The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (6)
1. A space station space technology test information management system based on network communication is characterized in that: the system comprises a cargo ship, a cargo ship ground system, a space-based system and a ground system; wherein, the cargo ship comprises a load management unit and an Ethernet switch; the ground system of the cargo ship comprises a master control device and a measurement and control device; the space-based system comprises a device A and each device B; the ground system comprises a ground flight control support system, an equipment A self-checking device and each equipment B self-checking device; in the space-based system, each B device is communicated with the A device in a signal acquisition line or Ethernet communication mode respectively; in the ground system, the equipment A self-checking device and each equipment B self-checking device are respectively communicated with the ground flight control support system in an Ethernet communication mode; the device A in the space-based system is communicated with a load management unit in the cargo ship through a bus communication mode, and simultaneously, the device A is communicated with an Ethernet switch in the cargo ship through an Ethernet communication mode; the general control equipment and the measurement and control equipment in the ground system of the freight ship are respectively communicated with the ground flight control support system in the ground system in an Ethernet communication mode; the load management unit in the freight airship is communicated with the master control equipment in the ground system of the freight airship; the Ethernet switch in the freight ship is communicated with the measurement and control equipment in the ground system of the freight ship.
2. The space station aerospace technology test information management system based on network communication of claim 1, wherein: the space station space technology test information management system adopts two mutually independent data transmission channels aiming at the transmission of each data: a measurement and control data channel and a service data channel; the measurement and control data channel is mainly used for transmitting control instructions, telemetering data, an upper note program and broadcast information from a superior cargo ship or A equipment; the service data channel is mainly used for transmitting test data and equipment state data generated or transmitted by the equipment A or the equipment B in the test process.
3. The space station aerospace technology test information management system based on network communication of claim 1, wherein: the device A and each device B are respectively and automatically designed with a cache region, wherein the size of the cache region of the device B can at least store complete data of 2 minimum test periods; the buffer area of the device A is allocated to the device B according to the size of 5GB of each device B, the device B preferentially uses the buffer area of the device A in a first-in first-out mode in the test process, once the pre-allocated storage threshold value is reached, the device A sends a data transmission forbidding command to enable the device B not to receive data any more, and the data is reported to the ground through telemetering data, and at the moment, the device B needs to buffer the data automatically.
4. The space station aerospace technology test information management system based on network communication of claim 1, wherein: the device A and each device B support breakpoint continuous transmission.
5. The space station aerospace technology test information management system based on network communication of claim 1, wherein: in the space-based system, each B device is communicated with the A device through an RS422 acquisition signal line or an Ethernet communication mode.
6. The space station aerospace technology test information management system based on network communication of claim 1, wherein: the bus communication mode is a 1553B bus communication mode.
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| CN110808893A (en) * | 2019-11-04 | 2020-02-18 | 北京空间技术研制试验中心 | 1553B bus data remote interactive communication method for spacecraft standard |
| CN112363481B (en) * | 2020-10-26 | 2022-02-22 | 中国商用飞机有限责任公司 | Post-flight self-inspection control device and control method of fly-by-wire flight control system |
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| CN106341176B (en) * | 2016-09-20 | 2019-03-19 | 西安戴森电子技术有限公司 | A kind of multiservice system based on multi-service ADS-B combined floor station owner's machine equipment |
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