CN108400811B - Spacelab information system based on advanced onboard processing method - Google Patents
Spacelab information system based on advanced onboard processing method Download PDFInfo
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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
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Abstract
The present invention relates to a kind of spacelab information systems based on advanced onboard processing method, comprising: the data information system based on 1553B bus realizes telemetering, instruction and communication function；High speed data transmission system based on AOS realizes the transmission of high-speed data.Spacelab information system according to the present invention based on advanced onboard processing method can support manned spacecraft to complete all in-orbit functions.
Description
Technical field
The present invention relates to spacecraft electric fields, are related to a kind of design more particularly to one of manned spacecraft information system
Manned spacecraft information system of the kind based on advanced onboard processing method.
Background technique
With the continuous development of space technology, the tasks of science of spacecraft flight is increasingly heavy, and data volume is increasing,
TG-1 spacelab data source category is more, and bus data amount is big, has a variety of output channels, is embodied in:
1) data of spacelab transmission include engineering telemetering, number pipe telemetering, image speech, scientific experimentation data, answer
Use system data.
2) data source of spacelab includes 2 sets of 1553B buses totally 26 terminals, 1 set of docking 1553B bus totally 2
Terminal, 1 set of 1394 bus totally 5 terminals, the direct high-speed hardware interface (LVDS) of occupant, speech (RS422) etc..
3) 3 sets of total 600kbps of 1553B bus data amount of spacelab, 1394 bus data amounts reach 46Mbps.
4) to S data rate 2kbps, back S data rate 768kbps × 2, forward direction Ka data rate before spacelab
3.2Mbps, back Ka maximum data rate 144Mbps, while can adapt to the data transmission of basic, normal, high three kinds of rates.
Data format and transmission rate described above from different data sources are different, domestic other any spacecrafts
All without such numerous data sources and so complicated bus architecture, these designs to data multiplexing, storage
Bring difficulty.
Summary of the invention
The purpose of the present invention is to solve the above problem, provides a kind of support manned spacecraft and completes that institute is functional to be based on
The spacelab information system of advanced onboard processing method.
To achieve the above object, the present invention provides a kind of spacelab information based on advanced onboard processing method
System characterized by comprising
Based on the data information system of 1553B bus, telemetering, instruction and communication function are realized；
High speed data transmission system based on AOS realizes the transmission of high-speed data.
According to an aspect of the present invention, the information system realizes data using AOS data system and pseudo channel
Scheduling controlling.
According to an aspect of the present invention, the data information system based on 1553B bus includes: central processing list
Member, RTU, mass storage and high-speed data multiplexer, data converter；
Mass storage is for storing telemetry, delayed telemetry data, test data and medical data；
High-speed data multiplexer receives the real-time telemetry data of CTU, the delayed telemetry number of mass storage for multiple connection
According to and voice data, distribute corresponding pseudo channel for different types of data, be scheduled according to the priority of setting.
According to an aspect of the present invention, the high speed data transmission system based on AOS includes:
Link terminal equipment, comprising: relaying comprehensive unit, Ka transmitting-receiving subassembly and relay antenna；
High-speed communication processor completes back platform telemetry data, in-orbit test data, occupant's telemetry, picture number
According to, the tidal data recovering of voice data, mass storage delay data, by the formatting and scheduling of transmission frame, channel coding,
It the processing such as synchronizes, forms uniform data and stream the link terminal equipment transmission；And before link terminal equipment reception
To data, including telecommand, data, speech and image are injected, after communication process and branch, by respective output interface
It sends out.
According to an aspect of the present invention, the Ka transmitting-receiving subassembly includes:
Ka channel is relayed, the transmitted in both directions of high-speed data is completed；
The transmitted in both directions of the high-speed data includes: fl transmission telecommand, injection data and 2 tunnel high-speeds words
Sound, 1 tunnel high-speed image and sound accompaniment；And
Data, 2 road high quality speech, 2 road high quality graphics and the companion of back transmission number pipe high-speed data multiplexer multiple connection
Sound, delay data and payload data.
According to an aspect of the present invention, the relaying Ka channel forward-going data rate is 3.2Mbps, back transmission
The maximum rate of data is 144Mbps；
In the high speed data transmission system based on AOS, the high-speed communication processor receives the relaying Ka letter
6 pseudo channels are distributed when the forward data in road；
The high-speed communication processor distributes 8 pseudo channels when receiving the back data of the relaying Ka channel.
According to an aspect of the present invention, the data information system based on 1553B bus, which uses, meets AOS standard
Number pipe telemetry protocol；
The data structure that several pipe telemetry protocols use includes:
EPDU is wrapped in source, is formed by packaging protocol data unit by certain format to different type telemetry；
Multichannel protocol Data Unit MPDU is combined multiple source bag datas by certain format, so that multiple sources are wrapped
Share a pseudo channel transmission；
Bit stream protocol Data Unit BPDU, is made of top guide and data field；
Virtual channel data unit member VCDU is made of leading head, data field and tailer sequence；
Channel Access Data Unit unit CADU, is made of virtual channel data unit member VCDU and synchronous code.
According to an aspect of the present invention, the multichannel protocol Data Unit MPDU by multichannel protocol Data Unit top guide and
Multichannel protocol Data Unit packet domain is constituted；
First top guide pointer in the multichannel protocol Data Unit top guide is pointing directly at rising for first source packet EPDU
Beginning position；
Multichannel protocol Data Unit packet domain first character section is the first byte that the packet header EPDU is wrapped in the source.
According to an aspect of the present invention, the data field of the virtual channel data unit member VCDU is the multichannel agreement number
According to unit MPDU and the bit stream protocol Data Unit BPDU；
The length of the virtual channel data unit member VCDU is 882 bytes；
The data format of the virtual channel data unit member VCDU includes:
The space flight that the VCDU and the mass storage of the high-speed data multiplexer output are exported by 20M interface
Device delayed telemetry and airship delayed telemetry VCDU；
The crew subsystem 1M data and load data VCDU that the mass storage is exported by 20M interface.
According to an aspect of the present invention, in the data information system based on 1553B bus, in observing and controlling area,
The high-speed data multiplexer receives spacecraft and airship real-time telemetry data, 32K voice data and mass storage pass through
The delayed telemetry data of frame are taken out, pseudo channel is distributed for different types of data, is scheduled according to the priority of setting, used
Dynamic Scheduling Strategy makes the pseudo channel timesharing occupy a physical channel, by under the channel 768Kbps and the channel 2Mbps
Row；
Outside observing and controlling area, the high-speed test (HST) data of the mass storage multiple connection delayed telemetry data and burst are carried out
Partitioned storage, and realize the mode put when writing enters behind observing and controlling area by passing under 20Mbps access, the massive store
Device distributes 6 pseudo channels.
Manned spacecraft information system according to the present invention, its advantages are the following aspects:
1) manned spacecraft (such as tiangong-1) information system applies China manned spacecraft CCSDS recommendation for the first time
Advanced Orbiting Systems (AOS) realize that manned spacecraft platform data, load data share bandwidth, unified management, bandwidth benefit for the first time
With rate close to 100%.
2) by using the data system of Advanced Orbiting Systems in manned spacecraft information system, data source is solved
With external interface huge number, process demand is complicated, and the big problem of data throughout realizes platform telemetry data, image, words
Sound data, the 7 class data such as two-way payload real time data, mass storage data, interconnection network data reliably input, efficiently
Transmission, and guarantee the requirement of the time delay of image, voice data.
3) by using virtual signal transmission strategy and dynamic dispatching control strategy, meet manned spacecraft in entire task
All users in period guarantee that each input channel can share output bandwidth to data transfer demands, improve channel benefit
With rate, forward data rate 3.2Mbps is realized, the transmitted in both directions of back maximum data rate 144Mbps can adapt to simultaneously
The data of basic, normal, high three kinds of rates are transmitted, the needs of special duty during meeting in orbit.
Effectively to transmit Various types of data, spacelab is using the part in the Advanced Orbiting Systems (AOS) of CCSDS suggestion
The design of traffic criteria development number pipe telemetering.Meanwhile to solve that the data volume of relay transmission is big and channel is limited and various numbers
According to the different problem of priority, spacelab carries out downlink using the related business of Advanced Orbiting Systems (AOS) that CCSDS suggests
Communicating link data priority design.
Advanced Orbiting Systems (AOS) are international space data system Advisory Boards (CCSDS) specifically for multi-user, height
The space manned spacecraft of rate complexity and a kind of data processing proposed and transmission system, the manned spacecrafts such as international space station
It is all made of AOS system, China's target flight needs to handle and transmit a large amount of, multi-user high-speed data, using AOS body
System may be implemented to carry out dynamic dispatching and multiplexing to user data, form uniform data stream, guarantee high efficiency, the usury of channel
With rate, guarantee the data transmission of high quality.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 schematically shows a kind of data information system based on 1553B bus of embodiment according to the present invention
Composed structure and spacecraft telemetry source figure；
Fig. 2 indicates a kind of manned spacecraft of embodiment according to the present invention based on the high speed data transmission system of AOS
The schematic diagram of forward direction information flow；
Fig. 3 indicates a kind of manned spacecraft of embodiment according to the present invention based on the high speed data transmission system of AOS
The schematic diagram of back information flow；
Fig. 4 schematically shows the data structure diagram of packet EPDU in source according to the present invention.
Specific embodiment
The description of this specification embodiment should be combined with corresponding attached drawing, and attached drawing should be used as the one of complete specification
Part.In the accompanying drawings, the shape of embodiment or thickness can expand, and to simplify or facilitate mark.Furthermore it is respectively tied in attached drawing
The part of structure will be to describe to be illustrated respectively, it is notable that attached to be not shown in the figure or be not illustrated by text
Element is the form known to a person of ordinary skill in the art in technical field.
The description of embodiments herein, any reference in relation to direction and orientation, is merely for convenience of describing, and cannot manage
Solution is any restrictions to the scope of the present invention.It can be related to the combination of feature below for the explanation of preferred embodiment,
These features may be individually present or combine presence, and the present invention is not defined in preferred embodiment particularly.The present invention
Range be defined by the claims.
Spacelab information system be spacelab information collection, conversion, processing, transmission, display, storage it is all
Function soft and hardware set provides support for autonomous operation, the emergency operating of spacecraft, and during spacecrafts rendezvous with airship into
Row information communication, supports spacecrafts rendezvous.
According to the requirement of engineering totality, spacelab information system information type includes engineering telemetering, number pipe telemetering, words
The contents such as sound, video, test data, instruction, injection data.Information system is using 1553B bus data information system as boat
The total line generalization achievement unit of its device divides telemetering, instruction, communication function, is passed using link terminal equipment, USB response machine equipment and S number
Equipment constitutes day-ground information transmission system and realizes information transmission；It is real using the data system and pseudo channel of Advanced Orbiting Systems
Existing scheduling controlling, i.e., realize the scheduling controlling of data between 1553B bus data information system and day-ground information transmission system
Strategy.
Above system is engineering overall system, the summation including ground and space-orbit information system.And in the present invention,
Mainly illustrate the information system of space-orbit manned spacecraft.It is described as follows:
Spacelab information system according to the present invention based on advanced onboard processing method includes: to be based on
The data information system of 1553B bus and high speed data transmission system based on AOS.In the present invention, based on 1553B bus
Data information system can be realized telemetering, instruction and communication function.The biography of high-speed data is realized based on day-ground information transmission system
It is defeated.
In the present invention, spacelab information system realizes the scheduling of data using AOS data system and pseudo channel
Control, i.e. tune of the realization data in the data information system based on 1553B bus and the high speed data transmission system based on AOS
Degree control.
Fig. 1 schematically shows a kind of data information system based on 1553B bus of embodiment according to the present invention
Composed structure and spacecraft telemetry source figure.As shown in Figure 1, the data information system based on 1553B bus includes: centre
Manage unit, RTU, mass storage and high-speed data multiplexer.As shown in Figure 1, in the present embodiment, in observing and controlling area,
The telemetry of each subsystem and the data of other middle low speed are sent supreme by two sets of 1553B buses after being acquired and organized by CTU
Fast data multiplexing device；Outside observing and controlling area, delay data is sent by two sets of 1553B buses to large capacity after being acquired and organized by CTU
Memory.
Outside observing and controlling area, mass storage receives spacecraft delayed telemetry data, the test data, medicine that CTU is sent
It checks data, this three data is stored；In observing and controlling area, mass storage sends out storing data by LVDS interface
It send to high speed data multiplexing device.
High-speed data multiplexer receives the delayed telemetry of the real-time telemetry data of CTU, mass storage in observing and controlling area
Data and voice data distribute corresponding pseudo channel for different types of data, are scheduled according to the priority of setting.When
When input data rate is added up to less than output speed, led at a high speed by output combining data after high-speed data multiplexer buffering to observing and controlling
Believe processor downlink；Real-time Delay telemetry and speech are also combined by high-speed data multiplexer, and output stream presses 768Kbps
Pass through observing and controlling S data set downlink.
In the present invention, manned spacecraft high speed data transmission system uses the data system of Advanced Orbiting Systems.According to
One embodiment of the present invention, the high speed data transmission system based on AOS include: link terminal equipment and high-speed communication processing
Device.Link terminal equipment includes relaying comprehensive unit, Ka transmitting-receiving subassembly and relay antenna.In the present embodiment, to lead at a high speed
Believe that processor is that core realizes that the back collection neutralization of high-speed data is preceding to distribution and AOS communication protocol processes.Ka transmitting-receiving subassembly
Complete the transmitted in both directions of high-speed data.
In the present embodiment, high-speed communication processor is the core equipment of high speed data transfer, high-speed communication processor
Complete back platform telemetry data, in-orbit test data, occupant's telemetry, image data, voice data, mass storage
The tidal data recovering of delay data handles with scheduling, channel coding, synchronous etc. by the formatting of transmission frame, forms uniform data
Stream the link terminal equipment transmission；And forward data, including telecommand, injection are received from the link terminal equipment
Data (running parameter, text file, audio files), speech and image, after communication process and branch, by respective
Output interface is sent to specific user.
Fig. 2 and Fig. 3 indicates a kind of manned spacecraft of embodiment according to the present invention based on the high speed data transfer of AOS
The schematic diagram of system forward information flow and back information flow.
A kind of embodiment according to the present invention, Ka transmitting-receiving subassembly include for completing in the transmitted in both directions of high-speed data
After Ka channel.As shown in Figures 2 and 3, in the present embodiment, the transmitted in both directions of high-speed data includes: to be sent to remote control demodulation
The fl transmission telecommand of device, the injection data for being sent to instrument controller and 2 tunnel high-speed speeches, 1 tunnel high-speed figure
Picture and sound accompaniment；And data, the 2 road high quality speech, 2 road high quality graphics of back transmission number pipe high-speed data multiplexer multiple connection
And sound accompaniment, delay data and payload data.
In the present embodiment, relaying Ka channel forward-going data rate is 3.2Mbps, and back transmits the maximum of data
Rate is 144Mbps, while can adapt to the data transmission of low, medium and high three kinds of rates.
In the present embodiment, it is mentioned in high-speed communication processor by R-S (255,223) coding, the method to interweave
Transmission performance of the senior middle school after Ka channel.High-speed communication processor virtual channel schedule process uses static priority and poll plan
Slightly, i.e., priority being divided according to importance, scheduler module queue high to priority first is inquired, and for same preferential
Poll rule query is then pressed in the queue of grade.High-speed communication processor is also equipped with preferential by data injection mode change input channel
The ability of grade, the needs of special duty during meeting in orbit.
A kind of embodiment according to the present invention, the data information system based on 1553B bus, which uses, meets AOS standard
Number pipe telemetry protocol.The data structure that number pipe telemetry protocol uses includes: source packet EPDU, multichannel protocol Data Unit MPDU, position
Stream protocol data cell BPDU, virtual channel data unit member VCDU and Channel Access Data Unit unit CADU.
In the present embodiment, packet EPDU in source is the different type telemetry generated to each subsystem of spacelab
Packaging protocol data unit is formed by by certain format.Each terminal telemetry that number pipe CTU will be acquired by 1553B bus
Classifying packing is carried out according to terminal address and terminal subaddressing.One bus termination is corresponding with one or more source packet EPDU, source
The content of packet EPDU is decided in its sole discretion by each subsystem, and number pipe CTU is responsible for acquire the source data come according to the source standard CC SDS packet lattice
Formula is packed, the secondary top guide including leading head and 6 bytes plus 6 bytes.For some parameters of several pipe softwares itself,
It is packaged respectively according to different classes of.The data structure that EPDU is wrapped in source is as shown in Figure 4.
In the present embodiment, multichannel protocol Data Unit MPDU is that multiple sources are wrapped using the data format of the following table 1
EPDU data are combined, so that multiple sources packet EPDU shares a pseudo channel transmission.
Multichannel protocol Data Unit MPDU is made of multichannel protocol Data Unit top guide and multichannel protocol Data Unit packet domain.
Including multichannel protocol Data Unit top guide and multichannel protocol Data Unit packet domain.In the present embodiment, multichannel protocol data
The data format of unit MPDU such as the following table 1:
Table 1
In the present embodiment, the first top guide pointer in multichannel protocol Data Unit top guide is pointing directly at first source packet
The initial position of EPDU can distinguish each independent source according to the mark that packet length in EPDU is wrapped in source and wrap EPDU.If
Multichannel protocol Data Unit packet domain first character section is exactly first byte in the packet header Yuan Bao, then first top guide pointer is 0.
If not including the packet header Yuan Bao in multichannel protocol Data Unit, first top guide pointer field is set as complete 1, i.e.,
“11111111111”。
It if not including any effective user data in multichannel protocol Data Unit, that is, only include filling bag, that
First top guide pointer field is set as " 11111111110 ".
If the top guide of a source packet EPDU is in two multichannel protocol Data Units, (EPDU is wrapped in divided source
Divide in multichannel protocol Data Unit (x) and multichannel protocol Data Unit (x+1)), if source packet EPDU is multichannel agreement number
EPDU is wrapped according to first source of unit (x), then the first top guide pointer field of multichannel protocol Data Unit (x) is directed toward this source packet
EPDU first address.EPDU is wrapped if not first source of multichannel protocol Data Unit (x), then multichannel protocol Data Unit (x
+ 1) first top guide pointer is directed toward the packet header the latter Yuan Bao of the source of being divided packet EPDU.
In the present embodiment, bit stream protocol Data Unit BPDU, is made of top guide and data field.For by indeterminate boundary
Serial code bit string be divided into several short data blocks, be put into pseudo channel cell data area.
In the present embodiment, in spacelab application, virtual channel data unit member VCDU format is by dominating head, number
It is constituted according to domain and tailer sequence.The data field of virtual channel data unit member VCDU is multichannel protocol Data Unit MPDU and bit stream agreement
Data cell BPDU.
In the present embodiment, virtual channel data unit member VCDU length be 882 bytes, data format altogether there are two types of:
The target manned space flight that the VCDU and mass storage of high-speed data multiplexer output are exported by 20M interface
Device platform delayed telemetry and airship delayed telemetry VCDU, data format such as the following table 2:
Table 2
The occupant 1M data and load data VCDU, data format that mass storage is exported by 20M interface are as follows
Table 3:
Table 3
A kind of spacelab embodiment according to the present invention, for the data information system based on 1553B bus into
The design of line number pipe telemetering virtual channel allocation.In the present embodiment, high-speed data multiplexer and mass storage are as number
According to center, it is respectively completed multiple connection and store tasks.In observing and controlling area, high-speed data multiplexer receives spacecraft and hands over spacecraft
Airship real-time telemetry data, 32K voice data and the mass storage that can be docked are not by the delayed telemetry data of pumping frame
The data of same type distribute 6 pseudo channels, are scheduled according to the priority of setting, make multiple void using Dynamic Scheduling Strategy
Quasi- channel timesharing occupies a physical channel, passes through the channel 768Kbps and the channel 2Mbps downlink.Outside observing and controlling area, large capacity is deposited
The high-speed test (HST) data of reservoir multiple connection delayed telemetry data and burst carry out partitioned storage, and realize the side put when writing
Formula enters behind observing and controlling area by passing under 20Mbps access.
The wherein virtual channel allocation of high-speed data multiplexer such as following table 4, the virtual channel allocation of mass storage
Such as following table 5:
Table 4
Table 5
A kind of embodiment according to the present invention carries out high-speed data biography for the high speed data transmission system based on AOS
Defeated virtual channel allocation design.In the present embodiment, high-speed communication processor is responsible for as high speed data transmission system core
The collection of spacecraft high speed back data neutralizes the distribution of forward data, supports platform telemetry data, image, voice data, two-way
Payload real time data, mass storage data, totally 7 circuit-switched data backs transmit interconnection network data.Effectively to guarantee height
The reliable quick transmission of priority data guarantees the validity of spacecraft telemetry and world face-to-face communication, high-speed communication
Processor uses virtual signal scheduling strategy, and virtual channel schedule process is combined using static priority and polling dispatching strategy
Scheduling method.
High-speed communication processor receives the forward data of relaying Ka channel, data type, virtual channel allocation such as the following table 6:
| Wire data type | Pseudo channel | Rate | |
| Telecommand data | VC1 | ≤2Kbit/s | |
| Data injection | VC2 | ≤2Mbit/s | |
| Image and sound accompaniment | VC3 | 768Kbit/s | |
| Speech | VC4 | 192K bit/s | |
| Dedicated speech | VC5 | 192K bit/s | |
| Idle frame | VC6 | ? |
Table 6
As shown in Table 6,6 virtual letters are distributed when high-speed communication processor receives the forward data of relaying Ka channel
Road.
Data type, virtual channel allocation, priority such as the following table 7 of high-speed communication processor back data:
Table 7
As shown in Table 7,8 virtual letters are distributed when high-speed communication processor receives the back data of relaying Ka channel
Road.
Above-mentioned setting according to the present invention, its advantages are the following aspects:
1) manned spacecraft (such as tiangong-1) information system applies China manned spacecraft CCSDS recommendation for the first time
Advanced Orbiting Systems (AOS) realize that manned spacecraft platform data, load data share bandwidth, unified management, bandwidth benefit for the first time
With rate close to 100%.
2) by using the data system of Advanced Orbiting Systems in manned spacecraft information system, data source is solved
With external interface huge number, process demand is complicated, and the big problem of data throughout realizes platform telemetry data, image, words
Sound data, the 7 class data such as two-way payload real time data, mass storage data, interconnection network data reliably input, efficiently
Transmission, and guarantee the requirement of the time delay of image, voice data.
3) by using virtual signal transmission strategy and dynamic dispatching control strategy, meet manned spacecraft in entire task
All users in period guarantee that each input channel can share output bandwidth to data transfer demands, improve channel benefit
With rate, forward data rate 3.2Mbps is realized, the transmitted in both directions of back maximum data rate 144Mbps can adapt to simultaneously
The data of basic, normal, high three kinds of rates are transmitted, the needs of special duty during meeting in orbit.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (11)
1. a kind of spacelab information system based on advanced onboard processing method characterized by comprising
Based on the data information system of 1553B bus, telemetering, instruction and communication function are realized；
High speed data transmission system based on AOS realizes the transmission of high-speed data；
The high speed data transmission system based on AOS includes:
Link terminal equipment, comprising: relaying comprehensive unit, Ka transmitting-receiving subassembly and relay antenna；
High-speed communication processor completes back platform telemetry data, in-orbit test data, occupant's telemetry, image data, words
The tidal data recovering of sound data, mass storage delay data, by formatting and the scheduling of transmission frame, channel coding and synchronous
Processing forms uniform data and streams the link terminal equipment transmission；And forward data is received from the link terminal equipment,
Including telecommand, data are injected, speech and image are sent out after communication process and branch by respective output interface；
The data information system based on 1553B bus includes: central processing unit, RTU, mass storage and high speed number
According to multiplexer, data converter；
Mass storage is for storing telemetry, delayed telemetry data, test data and medical data；
High-speed data multiplexer for multiple connection receive the real-time telemetry data of CTU, the delayed telemetry data of mass storage and
Voice data distributes corresponding pseudo channel for different types of data, is scheduled according to the priority of setting；
In the data information system based on 1553B bus, in observing and controlling area, the high-speed data multiplexer receives space flight
Device and airship real-time telemetry data, 32K voice data and mass storage are inhomogeneity by the delayed telemetry data of pumping frame
The data of type distribute pseudo channel, are scheduled according to the priority of setting, make the pseudo channel using Dynamic Scheduling Strategy
Timesharing occupies a physical channel, and by the channel 768Kbps and the channel 2Mbps downlink, wherein the design of Dynamic Scheduling Strategy is adopted
With static priority and polling schemas, i.e., divide priority according to importance, scheduler module queue high to priority first into
Row inquiry, and poll rule query is then pressed for the queue of same priority, while being also equipped with and changing by data injection mode
The ability of input channel priority；
Outside observing and controlling area, the high-speed test (HST) data of the mass storage multiple connection delayed telemetry data and burst carry out subregion
Storage, and realizes the mode put when writing, and enters behind observing and controlling area by passing under 20Mbps access, the mass storage point
With 6 pseudo channels.
2. the spacelab information system according to claim 1 based on advanced onboard processing method, feature
It is, the information system realizes the scheduling controlling of data using AOS data system and pseudo channel.
3. the spacelab information system according to claim 1 based on advanced onboard processing method, feature
It is, the Ka transmitting-receiving subassembly includes:
Ka channel is relayed, the transmitted in both directions of high-speed data is completed；
The transmitted in both directions of the high-speed data includes: fl transmission telecommand, injection data and 2 tunnel high-speed speeches, 1 tunnel
High-speed image and sound accompaniment；And
Data, 2 road high quality speech, 2 road high quality graphics and the sound accompaniment of back transmission number pipe high-speed data multiplexer multiple connection are prolonged
When data and payload data.
4. the spacelab information system according to claim 3 based on advanced onboard processing method, feature
It is, the relaying Ka channel forward-going data rate is 3.2Mbps, and the maximum rate that back transmits data is 144Mbps.
5. the spacelab information system according to claim 1 based on advanced onboard processing method, feature
It is, the data information system based on 1553B bus is using the number pipe telemetry protocol for meeting AOS standard；
The data structure that several pipe telemetry protocols use includes:
EPDU is wrapped in source, is formed by packaging protocol data unit by certain format to different type telemetry；
Multichannel protocol Data Unit MPDU is combined multiple source bag datas by certain format, so that multiple source Bao Gongyong
One pseudo channel transmission；
Bit stream protocol Data Unit BPDU, is made of top guide and data field；
Virtual channel data unit member VCDU is made of leading head, data field and tailer sequence；
Channel Access Data Unit unit CADU, is made of virtual channel data unit member VCDU and synchronous code.
6. the spacelab information system according to claim 5 based on advanced onboard processing method, feature
It is, the multichannel protocol Data Unit MPDU is by multichannel protocol Data Unit top guide and multichannel protocol Data Unit packet domain structure
At.
7. the spacelab information system according to claim 6 based on advanced onboard processing method, feature
It is, the first top guide pointer in the multichannel protocol Data Unit top guide is pointing directly at the start bit of first source packet EPDU
It sets；
Multichannel protocol Data Unit packet domain first character section is the first byte that the packet header EPDU is wrapped in the source.
8. the spacelab information system according to claim 5 based on advanced onboard processing method, feature
It is, the data field of the virtual channel data unit member VCDU is the multichannel protocol Data Unit MPDU and the bit stream agreement
Data cell BPDU.
9. the spacelab information system according to claim 5 based on advanced onboard processing method, feature
It is, the length of the virtual channel data unit member VCDU is 882 bytes.
10. the spacelab information system according to claim 5 based on advanced onboard processing method, feature
It is, the data format of the virtual channel data unit member VCDU includes:
The VCDU and the mass storage of the high-speed data multiplexer output are prolonged by the spacecraft that 20M interface exports
When telemetering and airship delayed telemetry VCDU；
The crew subsystem 1M data and load data VCDU that the mass storage is exported by 20M interface.
11. the spacelab information system according to claim 4 based on advanced onboard processing method, feature
It is, in the high speed data transmission system based on AOS, the high-speed communication processor receives the relaying Ka channel
6 pseudo channels are distributed when forward data；
The high-speed communication processor distributes 8 pseudo channels when receiving the back data of the relaying Ka channel.
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| CN110535561B (en) * | 2019-08-15 | 2022-04-12 | 北京空间飞行器总体设计部 | Spacecraft telemetry data transmission implementation method based on two-way linked list |
| CN110391840B (en) * | 2019-09-17 | 2019-12-17 | 中国人民解放军国防科技大学 | Method and system for judging abnormality of telemetry parameters of sun synchronous orbit satellite |
| CN111025995A (en) * | 2019-12-26 | 2020-04-17 | 北京空间技术研制试验中心 | Space manipulator teleoperation communication system based on space-based relay communication |
| CN113177009B (en) * | 2021-05-24 | 2022-10-21 | 上海航天计算机技术研究所 | Multi-interface multiplexing method and system for deep space probe |
| CN115801101B (en) * | 2022-11-07 | 2023-06-20 | 银河航天(北京)通信技术有限公司 | Telemetry scheduling method, device and storage medium based on virtual channel time slot |
| CN115801100B (en) * | 2022-11-07 | 2023-07-28 | 银河航天(北京)通信技术有限公司 | Remote control-based method for remotely measuring and scheduling channel number apparatus and storage medium |
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