CN205792659U - A kind of APS redundant system based on SpaceWire bus - Google Patents
A kind of APS redundant system based on SpaceWire bus Download PDFInfo
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- CN205792659U CN205792659U CN201620582236.5U CN201620582236U CN205792659U CN 205792659 U CN205792659 U CN 205792659U CN 201620582236 U CN201620582236 U CN 201620582236U CN 205792659 U CN205792659 U CN 205792659U
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Abstract
This utility model relates to a kind of APS redundant system based on SpaceWire bus, by computer, PC bus, SpaceWire node 1, SpaceWire bus node 2, and executor's composition.Computer is connected with SpaceWire bus node 1 by PC bus, is connected by the bus cable of two groups of bidirectional transmit-receives between bus node 1 and node 2, and SpaceWire bus node 2 is connected with executor.Node 1 and node 2 are each configured with APS automatic switching device.This utility model is on the premise of meeting SpaceWire bus protocol; additionally exploitation design is with the SpaceWire bus node of redundancy feature; use automatic-protecting switching device; two the most active and standby SpaceWire node contacts are got up; realize the master-slave redundancy switch function of SpaceWire bus, substantially increase the reliability of SpaceWire bus transfer.
Description
Technical field
A kind of APS redundant system based on SpaceWire bus of the present utility model, belongs to space communication technical field,
It is specifically related to a kind of APS based on SpaceWire bus (Auto-Protection Switch) APS redundancy skill
Art.
Background technology
SpaceWire bus is jointly to be formulated a kind of brand-new of proposition by European Space Agency, European Space company and academia
(2Mb/s～400Mb/s), point-to-point, the serial bus network of full duplex at a high speed.Bus standard is devoted to spacecraft payload
System data and the process of the information of control, with satisfied following high-performance high speed data transfer as target, it is provided that a kind of unified use
Connect the architecture of sensor, data processing unit, mass storage.SpaceWire bus has good electromagnetism
Compatibility feature, strengthens the function of online error detection and the aspect such as recovery, troubleshooting and protection and time broadcast simultaneously.
Above-mentioned advantage makes SpaceWire bus show one's talent in numerous space flight buses, is got more and more both at home and abroad
Scientific research organization pay close attention to, and start will be maybe multiple space mission service.In recent years, SpaceWire bus successively ESA,
The launch mission of NASA and JAXA is able to successful Application.SpaceWire bus is made by China's No. four meteorological satellite plans of wind and cloud
For key network.
To field permanently effective, that reliability service has particular/special requirement, redundancy is one of important fault-toleranr technique, is to improve
Complete machine and a kind of significant design technology of system reliability.SpaceWire standard includes physical layer, signals layer, character layer, exchange
Layer, packet level and Internet six layers.Physical layer the most therein, signals layer and character layer are corresponding to the thing of osi model
Reason layer, and switching layer, covering and Internet are corresponding to the link layer of osi model.In SpaceWire specification, and it is not provided with
Close redundancy scheme.Realize this mechanism and have a lot of method, but there is no a kind of referred to as SpaceWire specification.
Utility model content
The purpose of this utility model is to provide a kind of APS redundant system based on SpaceWire bus, to improve
SpaceWire bus reliability is target, studies the redundancy of its transmission link, communication protocol, key equipment etc.,
According to SpaceWire bus protocol feature, in conjunction with existing redundancy, a kind of automatic-protecting switching device (APS) is proposed, will
Two the most active and standby SpaceWire node contacts get up to realize the master-slave redundancy switch function of SpaceWire bus, significantly carry
The high reliability of SpaceWire bus transfer.
For solving above-mentioned technical problem, this utility model by the following technical solutions:
The APS redundant system of a kind of SpaceWire bus, by the APS device of SpaceWire bus node, it is achieved be
The redundancy of system, it is ensured that the reliability of bus transfer.SpaceWire bus redundancy checking system by computer, PC bus,
SpaceWire node 1, SpaceWire bus node 2, and executor's composition.Computer passes through PC bus and SpaceWire
Bus node 1 is connected, and is connected by the bus cable of two groups of bidirectional transmit-receives, SpaceWire between bus node 1 and node 2
Bus node 2 is connected with executor.Node 1 and node 2 are each configured with APS automatic switching device.Under normal operation,
Only have main receipts, master sends out antenna efficiency, and standby receipts does not works with preparation, and when main receipts or a main link break down, APS device ensures
System automatically switches to standby receipts and on preparation link, it is ensured that the normal communication of equipment room.
A kind of APS redundant system based on SpaceWire bus, on the premise of meeting SpaceWire bus protocol, separately
Outer exploitation design is with the SpaceWire bus node of redundancy feature.Use automatic-protecting switching device, by the most active and standby two
Individual SpaceWire node contacts gets up, it is achieved the master-slave redundancy switch function of SpaceWire bus.Concrete redundancy approach bag
Include following steps:
Step S1: after data communication based on SpaceWire bus starts, APS automatic-protecting switching device is started working；
The SpaceWire node module that two independent is connected by step S2:APS module, and APS module constantly detects two
The duty of the most active and standby individual SpaceWire node；
Step S3:APS module detects that host node link breaks down (LOS-A:Loss of Signal for Node
A), time, APS module utilizes far-end life indication (RDI-B:Remote Defect Indicator for Node B) to lead to
Crossing secondary node chain road direction opposite end and send switching request numeric data code, the standby receiver module of opposite end receives this switching request numeric data code
After, produce changeover signal to the APS module of opposite end, APS module receive after immediately by the bus switch of opposite end to standby
In SpaceWire bus, simultaneously opposite end standby sending module send switch confirmation numeric data code to local terminal secondary node, local terminal is standby
Receiving with node after switching confirmation numeric data code, produce local changeover signal to local APS module, local terminal APS is immediately by local
Bus switch, in standby SpaceWire bus, completes redundancy protecting and switches.
Wherein, under normal operation, only host node antenna efficiency, secondary node link does not works, and works as main node
When link breaks down, APS device automatically switches on secondary node link, it is ensured that the communication of equipment room is normal.
Wherein, under normal operation, APS module constantly detects the work of two SpaceWire nodes the most active and standby
State；When detecting that link breaks down, APS module can be with SpaceWire node receiving and transmitting data signals, intercommunication,
Complete the switching of bus, it is achieved function of redundancy protection.
A kind of APS redundant system based on SpaceWire bus of this utility model, its advantage and effect are: meeting
On the premise of SpaceWire bus protocol, additionally exploitation design is with the SpaceWire bus node of redundancy feature, uses certainly
Two the most active and standby SpaceWire node contacts are got up by dynamic pretection switch device, it is achieved SpaceWire bus active and standby
Redundancy inversion function, substantially increases the reliability of SpaceWire bus transfer.
Accompanying drawing explanation
Fig. 1 SpaceWire bus redundancy checking system principle.
The SpaceWire bus board of Fig. 2 band APS APS function.
Fig. 3 APS switches the main downstream main reception link that is sent in upstream of operation principle schematic diagram and breaks down.
Fig. 4 APS switches the main upstream main reception link that is sent in downstream of operation principle schematic diagram and breaks down.
Fig. 5 APS switches the two-way link of operation principle schematic diagram and breaks down.
Main fault in Fig. 6 bus redundancy checking system backbone.
Main receipts fault in Fig. 7 bus redundancy checking system backbone.
Main receipts and main simultaneous faults in Fig. 8 bus redundancy checking system backbone.
Detailed description of the invention
Elaborating embodiment of the present utility model below in conjunction with the accompanying drawings, the present embodiment is with this utility model technical side
Implement premised on case, give detailed embodiment and concrete operating process, but protection domain of the present utility model
It is not limited to following embodiment.
Traditional SpaceWire bus board (carrying two independent SpaceWire nodes) two node IP conducts of instantiation
The dual pathways.Each node IP comprises following submodule: HCI (HCI), transmitter are (with Credit-Counter mould
Block), receptor (with OutstandingCounter module), interface host state machine (FSM), receive FIFO, send FIFO, time
Between code module.Transmitter is used for carrying out Data-Strobe (data-filtering) and encoding and send data, it can send from
The data of main frame or timing code.Receptor has been used for the decoding effort of DS coding and has been sent by the data sequence solved
To host computer system.The FIFO of receptor is used as buffering and speeds match.SpaceWire bus is responsible for by SpaceWire controller
All runnings, including initialization, normal operation and fault processing.Two passages share a pll clock unit.Host computer system is passed through
Pci bus interface depositor each to node is written and read, it is achieved the Monitoring and Controlling of Link State is transmitted with data.
Whole SOC(system on a chip) comprises 5 clock sources altogether: reference clock CLK_BASE, super as 850ns, 6.4us, 12.8us
Time intervalometer baseline；Through the high speed global clock gclk that PLL frequency multiplication obtains, it is used for coordinating each module synchronization of whole chip
Work, i.e. judges the level state of other clocks, then performs corresponding actions, for preventing because of pulsewidth problem at each gclk rising edge
The same action of repeated trigger, it is also possible to pin the jumping of other clocks along carrying out logical judgment again with gclk；Internal logic divides
The transmitter clock tclk obtained, configurable to realize transmission baud rate；DS decodes the receiver clock rclk obtained, in order to right
D_in signal carries out sampling and obtains valid data；The synchronised clock LCLK of HCI.Data exchange between different clock-domains uses reads
The asynchronous FIFO writing clock independence realizes.The reading clock sending FIFO is tclk, and writing clock is LCLK；Receive FIFO writes clock
For rclk, reading clock is LCLK.
Based on SpaceWire bus protocol, in conjunction with existing redundancy, traditional SpaceWire bus board (sets
In respect of two SpaceWire bus nodes), the automatic-protecting switching device (APS) in design this utility model.By one
The SpaceWire node module that two independent is connected by APS module.
A kind of SpaceWire bus redundancy checking system of the present utility model, as shown in Figures 1 and 2, passes through
The APS device of SpaceWire bus node, it is achieved the redundancy of system, it is ensured that the reliability of bus transfer.SpaceWire bus
Redundant validation system is by computer, PC bus, SpaceWire node 1, SpaceWire bus node 2, and executor's composition.
Computer is connected with SpaceWire bus node 1 by PC bus, by two groups of two-way receipts between bus node 1 and node 2
The bus cable sent out connects, and SpaceWire bus node 2 is connected with executor.Node 1 and node 2 are each configured with APS certainly
Dynamic changeover apparatus.
APS automatic switching device constantly detects the duty of two SpaceWire bus nodes the most active and standby, works as inspection
Measure host node link break down (LOS-A:Loss of Signal for Node A) time, APS module utilizes far-end to lose
Effect indication signal (RDI-B:Remote Defect Indicator for Node B) is sent out by secondary node chain road direction opposite end
Go out switching request numeric data code, after the standby receiver module of opposite end receives this switching request numeric data code, produce changeover signal to opposite end
APS module, APS module receive after immediately by the bus switch of opposite end to standby SpaceWire bus, opposite end is standby simultaneously
With sending module send switch confirmation numeric data code to local terminal secondary node, local terminal secondary node receive switch confirmation numeric data code after,
Produce local changeover signal to local APS module, local terminal APS immediately by local bus switch to standby SpaceWire bus
On, complete a redundancy protecting and switch.
Assuming to send fault as Fig. 3 middle and upper reaches master is sent to the main reception in downstream link, the link that in figure, red X marks is sent out
Send fault, the order of digitized representation reversed process in figure.
The link that upstream host node is sent between the host node reception in downstream breaks down；
After downstream host node detects this link failure, downstream slave node sends life indication；
Downstream slave node sends switching request numeric data code to upstream slave node；
Upstream slave node receives and sends changeover signal after switching request numeric data code to upstream APS module, and APS module is by upstream
Bus is switched to slave node from host node.
Upstream slave node sends switches confirmation numeric data code to downstream slave node；
Downstream slave node receives to produce after switching confirmation numeric data code switches confirmation signal to the APS module in downstream, APS module
Downstream bus being switched to slave node from host node, complete an APS and switch, upstream and downstream website begin through standby joint
Point carries out data transmission.
Assuming to send fault as Fig. 4 middle and lower reaches master is sent to the main reception in upstream link, the link that in figure, red X marks is sent out
Send fault, the order of digitized representation reversed process in figure.
The link that downstream host node is sent between the host node reception of upstream breaks down；
After upstream host node detects this link failure, upstream slave node sends life indication；
Upstream slave node sends switching request numeric data code to downstream slave node；
Downstream slave node receives and sends changeover signal after switching request numeric data code to downstream APS module, and APS module is by downstream
Bus is switched to slave node from host node.
Downstream slave node sends switches confirmation numeric data code to upstream slave node；
Upstream slave node receives to produce after switching confirmation numeric data code switches confirmation signal to the APS module of upstream, APS module
Upstream bus being switched to slave node from host node, complete an APS and switch, upstream and downstream website begin through standby joint
Point carries out data transmission.
Two-way link between assuming such as Fig. 5 middle and upper reaches host node to downstream host node sends fault simultaneously, such as X red in figure
Shown in labelling, in figure, numeral and letter represent the order of a direction link switchover process respectively.
Upstream host node to the two-way link between the host node of downstream break down simultaneously time, its each unidirectional switching process and figure
3 is consistent with Fig. 4.(4) (f) unlike Wei Yi and (6) (d) step.(4) (f) and (6) (d) step are provided with and switch mutually
Lock circuit, is used for preventing two-way link from repeating to switch.
When APS automatic switching device is applied to system in Fig. 1, working condition such as Fig. 6, shown in 7,8.
When normally working, primary link is connected, and reserve link does not works, and breaks down when main in primary link, and its redundancy is fallen
Process of changing is consistent with Fig. 3, switches rear executor and remains to keep normally working.
When receipts main in primary link break down, and its redundancy inversion process is consistent with Fig. 4, switch rear executor and remain to just keep
Often work.
When, in primary link, when main receipts break down with main, its redundancy inversion process is consistent with Fig. 5, holds after switching simultaneously
Row device remains to normally work.
Claims (1)
1. an APS redundant system based on SpaceWire bus, is characterised by: it be by computer, PC bus,
SpaceWire bus node 1, SpaceWire bus node 2, and executor's composition；Computer by PC bus with
SpaceWire bus node 1 is connected, between bus node 1 and bus node 2 by the bus cable of two groups of bidirectional transmit-receives even
Connecing, SpaceWire bus node 2 is connected with executor；Node 1 and node 2 are each configured with APS automatic switching device.
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| CN201620582236.5U CN205792659U (en) | 2016-06-15 | 2016-06-15 | A kind of APS redundant system based on SpaceWire bus |
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| CN201620582236.5U CN205792659U (en) | 2016-06-15 | 2016-06-15 | A kind of APS redundant system based on SpaceWire bus |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106100954A (en) * | 2016-06-15 | 2016-11-09 | 北京航空航天大学 | A kind of APS redundancy approach based on SpaceWire bus |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106100954A (en) * | 2016-06-15 | 2016-11-09 | 北京航空航天大学 | A kind of APS redundancy approach based on SpaceWire bus |
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