CN115065444A - On-orbit dual-redundancy data processing method of satellite-borne management and control computer - Google Patents
On-orbit dual-redundancy data processing method of satellite-borne management and control computer Download PDFInfo
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- CN115065444A CN115065444A CN202210603504.7A CN202210603504A CN115065444A CN 115065444 A CN115065444 A CN 115065444A CN 202210603504 A CN202210603504 A CN 202210603504A CN 115065444 A CN115065444 A CN 115065444A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/22—Arrangements for detecting or preventing errors in the information received using redundant apparatus to increase reliability
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/22—Parsing or analysis of headers
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04Q—SELECTING
- H04Q11/00—Selecting arrangements for multiplex systems
- H04Q11/0001—Selecting arrangements for multiplex systems using optical switching
- H04Q11/0062—Network aspects
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04Q—SELECTING
- H04Q11/00—Selecting arrangements for multiplex systems
- H04Q11/0001—Selecting arrangements for multiplex systems using optical switching
- H04Q11/0062—Network aspects
- H04Q2011/0079—Operation or maintenance aspects
- H04Q2011/0081—Fault tolerance; Redundancy; Recovery; Reconfigurability
Abstract
The invention discloses an on-orbit dual-redundancy data processing method of a satellite-borne management and control computer, which is characterized in that a load system is arranged, the satellite-borne management and control computer adopts two hot standby interfaces to be respectively connected into switches, data fusion processing is carried out on received data by adopting a first-come-first-get principle, if the data of two channels are verified correctly, a fastest-arriving data packet is selected to be processed or distributed to a next-stage data processing unit, and meanwhile, the satellite-borne management and control computer respectively sends engineering data, application data, display parameters, return messages and other data to two switches FC through two optical ports. The method for fusion processing of on-orbit dual-redundancy data is beneficial to greatly improving the reliability of data exchange between the satellite-borne management and control computer of the load system and an external platform.
Description
Technical Field
The invention relates to the technical field of combined aircrafts, in particular to an on-orbit dual-redundancy data processing method for a satellite-borne management and control computer.
Background
In the combined aircraft load system, data exchange with an external platform is completed by a satellite-borne management and control computer, and the data exchange comprises downloading of engineering data and application data of loads; remote control instructions, uplink data uploading and platform time position attitude information broadcasting. As the only core node for external information interaction, the reliability of external data interaction of the satellite-borne management and control computer plays a decisive role in the success of the whole load task.
When the satellite-borne management and control computer in the prior art is implemented, a design mode of binding a main link logic design and a standby link logic design with an external FC-AE-1553 link is generally adopted, namely two paths of hot standby receive data simultaneously, and one path of FC-AE-1553 data is fixedly selected for use. However, if the primary FC-AE-1553 link is interrupted or fails (for example, an NC end, a switch or a link is abnormal or fails) due to an external reason, the load system cannot normally complete a data exchange task with an external platform, and the satellite-borne supervisory control computer must be notified to activate a backup link by an uplink instruction of the ground operation control system, the whole switching process passes through a large sky-ground closed loop and a long link, and the satellite receives and executes an instruction to complete the primary-standby switching from the acquisition of fault information, the downloading of the fault information and the uplink instruction, so that the whole operation requires at least tens of seconds or even longer, which seriously affects the normal execution of the task.
Disclosure of Invention
The invention mainly aims to provide an on-orbit dual-redundancy data processing method for a satellite-borne management and control computer, and aims to solve the technical problems that the data communication reliability of the existing satellite-borne management and control computer is low, and the time consumed for executing the switching of a main communication link and a standby communication link is long when the existing satellite-borne management and control computer is interrupted or fails.
In order to achieve the above object, the present invention provides an on-orbit dual-redundancy data processing method for a satellite-borne management and control computer, wherein the satellite-borne management and control computer is connected to a first switch through a first optical interface and is connected to a second switch through a second optical interface, and the method comprises the following steps:
upon receiving the data:
s11: the satellite-borne management and control computer simultaneously obtains first data sent by a first switch through a first optical interface and obtains second data sent by a second switch through a second optical interface;
s12: if the first data and the second data are received at the same time, the satellite-borne control computer takes the data information received first in the first data and the second data as the data to be processed;
s13: if only the first data or the second data is received, taking the received first data or the received second data as data to be processed;
when data is transmitted:
s21: the satellite-borne control computer detects the communication states of a first link formed by the first optical interface and the first switch, and a second link formed by the second optical interface and the second switch;
s22: if the communication states of the first link and the second link meet the sending condition, the satellite-borne control computer sends the data to be processed to the first optical interface and the second optical interface simultaneously;
s23: and if only the communication state of the first link or only the communication state of the second link meets the sending condition, the satellite-borne management and control computer sends the data to be processed to the first optical interface or the second optical interface.
Optionally, the step S12 specifically includes:
s121: if the first data and the second data are received simultaneously, reading and comparing the first data and the second data;
s122: and taking correct non-repeated frame data in the first data and the second data as data to be processed, and discarding error frame data and/or repeated frame data in the first data and the second data.
Optionally, step S121 specifically includes:
s1211: extracting feature information in the received first data and second data;
s1212: and performing table building and query on the first data and the second data in a first-come-first-serve mode according to the characteristic information so as to judge whether the received first data or the received second data are repeated frame data or error frame data.
Optionally, in step S1211, the feature information includes: a source address ID, a destination address ID, a transmit exchange ID, a receive exchange ID, a sequence ID, and a sequence count.
Optionally, in step S22, the sending condition is that the count value of the number of frames for sending the first data or the second data is smaller than the count value of the allowed sending of the buffer in the link.
Optionally, the satellite-borne management and control computer includes an FPGA data processing unit and a subordinate data processing unit, the FPGA data processing unit is connected to the first optical port and the second optical port, and the subordinate data processing unit is connected to the FPGA data processing unit.
Optionally, when receiving the first data or the second data, the satellite-borne management computer sends the first data or the second data to the FPGA data processing unit, and the FPGA data processing unit performs first communication protocol layer processing and second communication protocol layer processing on the first data or the second data, and sends the processed data to the lower-level data processing unit after the processing.
Optionally, the first communication protocol layer is an encoding layer and is configured to perform serial-to-parallel conversion, and the second communication protocol layer is a signal protocol layer and is configured to define a transmission mechanism of a fiber channel.
The invention provides an on-orbit dual-redundancy data processing method of a satellite-borne management and control computer, which is characterized in that the method comprises the steps of setting a load system satellite-borne management and control computer, respectively accessing two hot standby interfaces (a main channel and a standby channel) into a switch, carrying out data fusion processing on received data by adopting a first-come-first-get principle, if data of the two channels are correctly verified, selecting a data packet which arrives fastest to process or distribute a next-stage data processing unit, and simultaneously, the satellite-borne management and control computer respectively sends engineering data, application data, display parameters, return messages, FC-2 layer protocols and other data to two FC switches through two optical ports. The method for fusion processing of on-orbit dual-redundancy data is beneficial to greatly improving the reliability of data exchange between the satellite-borne management and control computer of the load system and an external platform.
Drawings
Fig. 1 is a schematic flow chart of an on-orbit dual-redundancy data processing method of a satellite-borne management and control computer according to an embodiment of the present invention;
FIG. 2 is a diagram of dual redundant access FC-AE-1553 bus of a satellite-borne management control computer according to an embodiment of the present invention.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
At present, in the related technical field, the existing satellite-borne management and control computer has low data communication reliability, and when interruption or failure occurs, it takes long time to execute the switching of the main and standby communication links.
In order to solve the problem, the invention provides various embodiments of an on-orbit dual-redundancy data processing method of a satellite-borne management and control computer. The on-orbit dual-redundancy data processing method of the satellite-borne management control computer provided by the invention is characterized in that the satellite-borne management control computer is provided with a load system, two hot standby interfaces (a main channel and a standby channel) are respectively accessed into a switch, data fusion processing is carried out on received data by adopting a principle of first-come-first-obtained, if data of the two channels are correctly verified, a fastest-arriving data packet is selected for processing or distributing to a next-stage data processing unit, and meanwhile, the satellite-borne management control computer respectively sends engineering data, application data, display parameters, return messages and other data to two FC switches through two optical ports. The method for fusion processing of on-orbit dual-redundancy data is beneficial to greatly improving the reliability of data exchange between the satellite-borne management and control computer of the load system and an external platform.
The embodiment of the invention provides an on-orbit double-redundancy data processing method of a satellite-borne management and control computer, and referring to fig. 1, fig. 1 is a flow diagram of the on-orbit double-redundancy data processing method embodiment of the satellite-borne management and control computer.
In this embodiment, the on-orbit dual-redundancy data processing method for the satellite-borne management and control computer comprises the following steps:
upon receiving the data:
s11: the satellite-borne management control computer simultaneously acquires first data sent by a first switch through a first optical interface and acquires second data sent by a second switch through a second optical interface;
s12: if the first data and the second data are received simultaneously, the satellite-borne control computer takes the data information received first in the first data and the second data as the data to be processed;
s13: if only the first data or the second data is received, taking the received first data or the received second data as data to be processed;
when data is transmitted:
s21: the satellite-borne control computer detects the communication states of a first link formed by the first optical interface and the first switch, and a second link formed by the second optical interface and the second switch;
s22: if the communication states of the first link and the second link meet the sending condition, the satellite-borne control computer sends the data to be processed to the first optical interface and the second optical interface simultaneously;
s23: and if only the communication state of the first link or only the communication state of the second link meets the sending condition, the satellite-borne management and control computer sends the data to be processed to the first optical interface or the second optical interface.
In this embodiment, as shown in fig. 2, a satellite-borne management control computer (FC-AE-1553NT end) module provides 2 FC-AE-1553 optical interfaces, and establishes a data path with a platform information host (FC-AE-1553NC end) by accessing an FC-AE-1553 bus switch, so as to realize analysis, processing and forwarding of FC-AE-1553 protocol data and complete 1588 clock synchronization based on an FC protocol.
Specifically, double FC-AE-1553 optical ports in the satellite-borne pipe control computer are simultaneously sent into one FPGA, and network communication protocols of FC-1, FC-2 and FC-AE-1553NT layers are realized in the FPGA. The FC-1 layer is a coding layer, serial-parallel conversion is realized on serial data, and then data information is sent to the FC-2 layer for processing. The FC-2 layer is a signal protocol layer, defines a transmission mechanism of a fiber channel, comprises a frame format, a service type, credit management among nodes and the like, and sends data information to a lower data processing unit for processing after the transmission mechanism is completed. The specific protocol algorithm of the FC-1 layer and the FC-2 layer is not the focus of the invention, and is not detailed here.
After receiving the two FC-AE-1553 data paths, the FPGA data processing unit realizes double redundancy channel judgment through a redundancy judgment mechanism by a first-come-first-obtained processing principle, so as to realize double redundancy data fusion processing. Wherein:
the fusion processing method of the dual redundant received data comprises the following steps: the two FC-AE-1553 interface links are in a normal connection state, data received by the two FC-AE-1553 receiving modules are read and compared, table building and query are carried out according to characteristic information (source address identification, destination address identification, sending exchange ID, receiving exchange ID, sequence counting and the like) extracted from frames received by the FC-AE-1553 modules in a first-come first-serve mode, correct non-repeated frames are distributed to a next-level data processing unit, characteristic information of the correct non-repeated frames is recorded, and repeated frames or error frames are discarded. If only one path of interface link of FC-AE-1553 is in normal connection state, the data of the path is distributed to the next stage data processing unit as correct data. Detailed data message types and distribution processing are shown in table 1.
Table 1 shows the message reception situation of FC-AE-1553
The fusion processing method of the dual redundancy sending data comprises the following steps:
and selecting non-transmission, single-channel transmission or dual-channel transmission according to the establishment and disconnection conditions of the FC-AE-1553 link. Under the normal condition, the default selection is to send the double-channel, and whether the link is sent or not is controlled according to the value of the actual frame sending count, and under the redundant sending mode, the data can be sent only when the actual frame sending count is smaller than the allowed frame sending count through the two ports. When one channel link is blocked, the blocked channel is abandoned, and only the normal channel is selected to send data. The detailed data message type transmission process is shown in table 2.
Table 2 shows the message sending situation of FC-AE-1553
The embodiment provides an on-orbit dual-redundancy data processing method for a satellite-borne management and control computer, which solves the problem that the satellite-borne management and control computer cannot normally exchange information with the outside and can complete data exchange only by completing main-standby switching through an upper injection instruction of a ground transportation and control system when an external main FC-AE-1553 link (an NC (numerical control) end, a switch or a link) is interrupted or fails by performing autonomous information fusion judgment on two paths of FC-AE-1553 data by using a dual-redundancy information fusion processing method, and greatly improves the reliability of the satellite-borne management and control computer.
The above are only preferred embodiments of the invention, and not intended to limit the scope of the invention, and all equivalent structures or equivalent flow transformations that may be applied to the present specification and drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the invention.
Claims (8)
1. An on-orbit dual-redundancy data processing method of a satellite-borne management and control computer is characterized in that the satellite-borne management and control computer is connected with a first switch through a first optical interface and connected with a second switch through a second optical interface, and the method comprises the following steps:
upon receiving the data:
s11: the satellite-borne management and control computer simultaneously obtains first data sent by a first switch through a first optical interface and obtains second data sent by a second switch through a second optical interface;
s12: if the first data and the second data are received at the same time, the satellite-borne control computer takes the data information received first in the first data and the second data as the data to be processed;
s13: if only the first data or the second data is received, taking the received first data or the received second data as data to be processed;
when data is transmitted:
s21: the satellite-borne control computer detects the communication states of a first link formed by the first optical interface and the first switch, a second link formed by the second optical interface and the second switch;
s22: if the communication states of the first link and the second link meet the sending condition, the satellite-borne control computer sends the data to be processed to the first optical interface and the second optical interface simultaneously;
s23: and if only the communication state of the first link or only the communication state of the second link meets the sending condition, the satellite-borne management and control computer sends the data to be processed to the first optical interface or the second optical interface.
2. The on-orbit dual-redundancy data processing method of the satellite-borne management and control computer according to claim 1, wherein the step S12 specifically comprises:
s121: if the first data and the second data are received simultaneously, reading and comparing the first data and the second data;
s122: and taking correct non-repeated frame data in the first data and the second data as data to be processed, and discarding error frame data and/or repeated frame data in the first data and the second data.
3. The on-orbit dual-redundancy data processing method of the satellite-borne management and control computer according to claim 2, wherein the step S121 specifically comprises:
s1211: extracting characteristic information in the received first data and second data;
s1212: and performing table building and query on the first data and the second data in a first-come-first-serve mode according to the characteristic information so as to judge whether the received first data or the received second data are repeated frame data or error frame data.
4. The on-orbit dual-redundancy data processing method of a satellite-borne control computer according to claim 3, wherein in the step S1211, the characteristic information includes: a source address ID, a destination address ID, a transmit exchange ID, a receive exchange ID, a sequence ID, and a sequence count.
5. The on-board dual redundancy data processing method of a satellite-borne control computer according to claim 1, wherein in step S22, the sending condition is that the count value of the number of frames for sending the first data or the second data is smaller than the count value of the allowed sending of the buffer in the link.
6. The on-orbit dual-redundancy data processing method of the on-board star-based management control computer according to claim 1, wherein the on-board star-based management control computer comprises an FPGA data processing unit and a lower data processing unit, the FPGA data processing unit is connected with the first optical port and the second optical port, and the lower data processing unit is connected with the FPGA data processing unit.
7. The on-orbit dual-redundancy data processing method of the satellite-borne management computer according to claim 6, wherein the satellite-borne management computer sends the first data or the second data to the FPGA data processing unit when receiving the first data or the second data, the FPGA data processing unit performs a first communication protocol layer process and a second communication protocol layer process on the first data or the second data, and sends the processed data to a lower data processing unit after the processes.
8. The on-orbit dual-redundancy data processing method of a satellite-borne management computer according to claim 7, wherein the first communication protocol layer is a coding layer for serial-parallel conversion processing, and the second communication protocol layer is a signal protocol layer for defining a transmission mechanism of a fiber channel.
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