CN113938450B - Avionics system communication fault processing method, avionics system communication fault processing device, computer equipment and medium - Google Patents
Avionics system communication fault processing method, avionics system communication fault processing device, computer equipment and medium Download PDFInfo
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- CN113938450B CN113938450B CN202111020828.XA CN202111020828A CN113938450B CN 113938450 B CN113938450 B CN 113938450B CN 202111020828 A CN202111020828 A CN 202111020828A CN 113938450 B CN113938450 B CN 113938450B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L49/00—Packet switching elements
- H04L49/55—Prevention, detection or correction of errors
- H04L49/555—Error detection
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L49/00—Packet switching elements
- H04L49/55—Prevention, detection or correction of errors
- H04L49/557—Error correction, e.g. fault recovery or fault tolerance
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Abstract
The application relates to a communication fault processing method and device for an avionics system. The device comprises: the first AFDX switch receives first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, and the first to-be-detected data sent by the second AFDX switch is sent to the second AFDX switch by the first AFDX terminal; if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty; if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty. The device can accurately position the communication link with faults when the communication link is faulty, so that technicians can process the communication link with faults in time, and data loss is avoided.
Description
Technical Field
The present application relates to the field of avionics technologies, and in particular, to a method, an apparatus, a computer device, and a medium for processing communication faults of an avionics system.
Background
With the development of avionics technology, the avionics system communication network is more and more complex, because of the number of communication terminals and large communication data, once communication faults occur, if the communication link with the fault cannot be accurately found, the faults are difficult to quickly and accurately locate, and the data loss can be caused, so that the operation of the avionics system is affected. Therefore, there is a need to quickly and accurately locate the fault location and reduce communication data loss.
In the prior art, data interaction is performed between AFDX terminals through an AFDX switch, and whether a communication link between the AFDX terminal and a certain AFDX switch connected with the AFDX terminal is in fault is judged according to data received by the AFDX terminal.
However, when a communication link between two AFDX terminals fails, only a failure of a certain communication link between two AFDX terminals can be determined, but it cannot be determined whether the failed communication link is a communication link between one of the AFDX terminals and the AFDX switch or a communication link between the AFDX switch and another one of the AFDX terminals, and when more than one communication link fails at the same time, a loss of communication data may occur.
Disclosure of Invention
In view of the foregoing, it is desirable to provide an avionics system communication failure processing method, apparatus, computer device, and medium that accurately locates a failed communication link when an AFDX communication link fails, and reduces loss of communication data. The maintenance efficiency and the operation efficiency of the avionics system are improved, and the reliability of the communication network of the avionics system is further enhanced.
A method of avionics system communication fault handling, the method comprising: the method comprises the steps that a first AFDX switch receives first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch; if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty; and if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
In one embodiment, the method further comprises: the first AFDX switch receives second to-be-detected data sent by at least one of a second AFDX terminal and a second AFDX switch, wherein the second to-be-detected data sent by the second AFDX switch is the second to-be-detected data sent by the second AFDX terminal to the second AFDX switch; if the second data to be detected sent by the second AFDX switch is received and the second data to be detected sent by the second AFDX terminal is not received, judging that a communication link between the first AFDX switch and the second AFDX terminal is faulty; and if the second data to be detected sent by the second AFDX terminal is received and the second data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the second AFDX terminal is faulty.
In one embodiment, the method further comprises: after receiving data to be detected, checking the data to be detected, wherein the data to be detected is the first data to be detected or the second data to be detected; and if the data to be detected is in error checking, judging that a communication link between the sending end of the data to be detected and the first AFDX switch is faulty.
In one embodiment, the method further comprises: and if the data to be detected is checked to be correct, judging that a communication link between the sending end of the data to be detected and the first AFDX switch is normal.
In one embodiment, the method further comprises: when data to be transmitted needs to be sent to the first AFDX terminal, if a communication link between the first AFDX switch and the first AFDX terminal is normal, the data to be transmitted is sent to the first AFDX terminal; and if the communication link between the first AFDX switch and the first AFDX terminal is failed and the communication link between the second AFDX switch and the first AFDX terminal is normal, sending the data to be transmitted to the second AFDX switch so that the second AFDX switch sends the data to be transmitted to the first AFDX terminal.
In one embodiment, the method further comprises: and when the communication link between the first AFDX switch and the first AFDX terminal is failed and the communication link between the second AFDX switch and the first AFDX terminal is normal, sending data to be transmitted to the first AFDX terminal through the second AFDX switch.
In one embodiment, the first AFDX switch and the second AFDX switch have the same structure, and the first AFDX switch and the second AFDX switch implement the same function.
An avionics system communication fault handling device, the device comprising:
the data receiving module is used for receiving first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch;
the fault judging module is used for judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty when the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received; and when the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
A computer device comprising a memory storing a computer program and a processor which when executing the computer program performs the steps of:
the method comprises the steps that a first AFDX switch receives first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch;
if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty;
and if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
A computer readable storage medium having stored thereon a computer program which when executed by a processor performs the steps of:
the method comprises the steps that a first AFDX switch receives first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch;
if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty;
and if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
The avionics system communication fault processing method, the avionics system communication fault processing device, the computer equipment and the medium. Receiving, by the first AFDX switch, first data to be detected sent by at least one of the first AFDX terminal and the second AFDX switch, the first data to be detected sent by the second AFDX switch being the first data to be detected sent by the first AFDX terminal to the second AFDX switch. Therefore, by adding a communication link between the first AFDX switch and the second AFDX switch, data exchange can be carried out between the first AFDX switch and the second AFDX switch, the first AFDX switch can receive data sent by the first AFDX terminal and data sent by the second AFDX switch, and when the communication link fails, whether the communication link between the first AFDX switch and the first AFDX terminal fails or not can be judged according to the data respectively received from the second AFDX switch and the first AFDX terminal, and fault location can be accurately carried out. If the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty; if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty. Therefore, when the data sent to the AFDX terminal can not be received, the communication link between the AFDX switch and the AFDX terminal can be determined to be faulty according to the data sent to other AFDX switches by the AFDX terminal, and further, technicians can process the faulty communication link in time.
When communication links between a plurality of AFDX terminals and an AFDX switch are simultaneously failed in the avionics system communication network, a new communication link can be still established through another AFDX switch. And when the communication link between the AFDX terminal and any AFDX switch has no fault, the AFDX terminal can send data to other AFDX terminals or receive data sent by other AFDX terminals. The stability of data transmission of the avionics system communication network is higher, and data loss is avoided.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments or the conventional techniques of the present application, the drawings required for the descriptions of the embodiments or the conventional techniques will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to the drawings without inventive effort for those skilled in the art.
FIG. 1 is a flow diagram of a method of handling avionics system communication faults, in one embodiment;
FIG. 2 is a flow chart of a method of handling communication faults of an avionics system in accordance with another embodiment;
FIG. 3 is a flow chart of a method of determining communication failure of an avionics system in one embodiment;
FIG. 4 is a schematic diagram of an avionics system communications network in one embodiment;
FIG. 5 is a schematic diagram of an avionics system communication fault handling device in one embodiment;
fig. 6 is an internal structural diagram of a computer device in one embodiment.
Reference numerals illustrate: 10-first AFDX switch, 20-second AFDX switch, 30-first AFDX terminal, 40-second AFDX terminal.
Detailed Description
In order that the application may be readily understood, a more complete description of the application will be rendered by reference to the appended drawings. Embodiments of the application are illustrated in the accompanying drawings. This application may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.
It will be understood that the terms first, second, etc. as used herein may be used to describe various elements, but these elements are not limited by these terms. These terms are only used to distinguish one element from another element.
It will be understood that when an element is referred to as being "connected" to another element, it can be directly connected to the other element or be connected to the other element through intervening elements. Further, "connection" in the following embodiments should be understood as "electrical connection", "communication connection", and the like if there is transmission of electrical signals or data between objects to be connected.
As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," and/or the like, specify the presence of stated features, integers, steps, operations, elements, components, or groups thereof, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, or groups thereof.
As described in the background art, in the avionics full duplex switched ethernet (AFDX) aviation communication network in the prior art, when the AFDX switch does not receive data sent by the AFDX terminal, it cannot be determined whether the AFDX terminal does not send data, or whether a communication link between the AFDX switch and the AFDX terminal fails, and the problem that the communication link with the failure cannot be accurately located; there is also a problem in that data cannot be continuously transmitted when a part of the communication link fails. The inventor researches find that the reason for the problem is that in the traditional technology, a communication link is not arranged between two AFDX switches, so that data exchange cannot be performed between the two AFDX switches, the two AFDX switches cannot compare received data, and a fault link cannot be accurately positioned; and cannot maintain data transfer by forwarding data between two AFDX exchanges when part of the communication link fails.
Based on the reasons, the application provides a communication fault processing method of an avionics system, which can accurately locate a communication link with faults and still maintain data transmission when part of the communication links are faulty.
In one embodiment, as shown in fig. 1, there is provided an avionics system communication fault handling method, the method comprising:
step S100, the first AFDX switch receives first data to be detected sent by at least one of the first AFDX terminal and the second AFDX switch.
Specifically, the first data to be detected sent by the second AFDX switch is the first data to be detected sent by the first AFDX terminal to the second AFDX switch.
Step S110, if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, determining that the communication link between the first AFDX switch and the first AFDX terminal is faulty.
Step S120, if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, determining that the communication link between the second AFDX switch and the first AFDX terminal is faulty.
Specifically, the AFDX communication network is used as a new generation avionics network transmission technology, has the characteristics of large networking scale and strong flexibility, and is suitable for interconnection of avionics systems of large and medium-sized airplanes. The AFDX network consists of an AFDX terminal, an AFDX switch and a communication cable. The AFDX terminal is an important component of an AFDX network, is applied to each device of an avionics system AFDX communication network, provides a unified interface connected with an AFDX switch for different devices in the network, and realizes a safe and reliable data transmission function among the devices in the AFDX communication network.
In this embodiment, the first to-be-detected data sent by at least one of the first AFDX terminal and the second AFDX switch is received by the first AFDX switch, and the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch. Therefore, by adding a communication link between the first AFDX switch and the second AFDX switch, data exchange can be carried out between the first AFDX switch and the second AFDX switch, the first AFDX switch can receive data sent by the first AFDX terminal and data sent by the second AFDX switch, and when the communication link fails, whether the communication link between the first AFDX switch and the first AFDX terminal fails can be judged according to the data respectively received from the second AFDX switch and the first AFDX terminal. If the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty; if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty. Therefore, when the data sent to the AFDX terminal can not be received, the communication link between the AFDX switch and the AFDX terminal can be determined to be faulty according to the data sent to other AFDX switches by the AFDX terminal, and further, technicians can process the faulty communication link in time.
In one embodiment, as shown in fig. 2, the avionics system communication fault handling method further includes:
step S200, the first AFDX switch receives second data to be detected sent by at least one of the second AFDX terminal and the second AFDX switch.
Specifically, the second data to be detected sent by the second AFDX switch is the second data to be detected sent by the second AFDX terminal to the second AFDX switch.
Step S210, if the second data to be detected sent by the second AFDX switch is received and the second data to be detected sent by the second AFDX terminal is not received, determining that the communication link between the first AFDX switch and the second AFDX terminal is faulty.
Step S220, if the second data to be detected sent by the second AFDX terminal is received and the second data to be detected sent by the second AFDX switch is not received, determining that the communication link between the second AFDX switch and the second AFDX terminal is faulty.
Specifically, the avionics system AFDX communication network comprises a plurality of AFDX terminals, each AFDX terminal is respectively connected with the first AFDX switch and the second AFDX switch, and when data are transmitted, the data are simultaneously transmitted to the first AFDX switch and the second AFDX switch.
In this embodiment, the first AFDX switch receives the data to be detected sent by the second AFDX terminal and the second AFDX switch respectively, if the data sent by the second AFDX terminal is received but the data sent by the second AFDX switch is not received, the communication link between the second AFDX switch and the second AFDX terminal is determined to be faulty, and if the data sent by the second AFDX switch is received but the data sent by the second AFDX terminal is not received, the communication link between the first AFDX switch and the second AFDX terminal is determined to be faulty. The AFDX switch may first determine, according to the received data of the AFDX terminal and the other AFDX switch, whether the AFDX terminal does not send data, or whether the communication link fails, and then determine whether the communication link that fails is a communication link between the first AFDX switch and the first AFDX terminal, or a communication link between the second AFDX switch and the first AFDX terminal. Therefore, when the communication link fails, the failed communication link can be accurately positioned. The same mode is also applicable to communication systems of a plurality of AFDX terminals, and whether communication links between each AFDX terminal and each AFDX switch are faulty or not can be judged respectively, so that when the communication links are faulty, the faulty communication links can be positioned accurately, and technicians can process the faulty communication links timely.
In one embodiment, as shown in fig. 3, the avionics system communication fault handling method further includes:
step S300, after receiving the data to be detected, checking the data to be detected.
Step S310, if the data to be detected has an error, determining that the communication link between the sending end of the data to be detected and the first AFDX switch is faulty.
Step S320, if the data to be detected is checked correctly, it is determined that the communication link between the sending end of the data to be detected and the first AFDX switch is normal.
Illustratively, the data to be detected includes a CRC (cyclic redundancy check) check code, which can be used to check the data to be detected. If the data to be detected which cannot pass the verification is compared with the data to be detected which can pass the verification after being respectively decoded, the numerical values of the data to be detected are found to be different. Therefore, according to the value after decoding the data to be detected, it can be determined whether the data to be detected passes the check.
Illustratively, the communication link failure includes at least one of a communication link failure, a communication port failure, a shielding layer failure.
Illustratively, the first AFDX switch is configured identically to the second AFDX switch, and the first AFDX switch performs the same function as the second AFDX switch. The role functions of the second AFDX exchange and the first AFDX exchange can be interchanged.
In this embodiment, by checking the received data to be detected, whether a communication link between the sending end of the data to be detected and the first AFDX switch is faulty or not is judged, and when the communication link between the sending end of the data to be detected and the first AFDX switch is faulty, the data to be detected may not be received; it is also possible that the received data to be detected is disturbed or incomplete, which may lead to a verification error. By checking the data to be detected in different modes, faults of different types of communication links can be rapidly judged.
In one embodiment, the avionics system communication fault handling method further comprises:
step S400, when the data to be transmitted needs to be sent to the first AFDX terminal, if the communication link between the first AFDX switch and the first AFDX terminal is normal, the data to be transmitted is sent to the first AFDX terminal.
Step S410, if the communication link between the first AFDX switch and the first AFDX terminal is failed and the communication link between the second AFDX switch and the first AFDX terminal is normal, the data to be transmitted is sent to the second AFDX switch, so that the second AFDX switch sends the data to be transmitted to the first AFDX terminal.
Step S420, when the communication link between the first AFDX switch and the first AFDX terminal is faulty and the communication link between the second AFDX switch and the first AFDX terminal is normal, sending data to be transmitted to the first AFDX terminal through the second AFDX switch.
Specifically, as shown in FIG. 4, the avionics system communication network includes a first AFDX switch 10, a second AFDX switch 20, and a plurality of AFDX terminals. The first AFDX switch 10 is connected with all the AFDX terminals through communication links A1, A2 and … … An respectively, the second AFDX switch 20 is connected with all the AFDX terminals through communication links B1, B2 and … … Bn respectively, and the first AFDX switch 10 is connected with the second AFDX switch 20 through a communication link S.
For example, the communication link for data transmission between the first AFDX terminal 30 and the second AFDX terminal 40 comprises: first AFDX termination 30→a1→first AFDX exchange 10→a2→second AFDX termination 40. Or the first AFDX terminal 30→b1→the second AFDX switch 20→b2→the second AFDX terminal 40.
If the communication link A1 fails, the first AFDX exchange 10 may receive the data to be detected sent by the second AFDX exchange 20, but cannot receive the data to be detected sent by the first AFDX terminal 30, so that the communication link A1 can be quickly located, and the failure of the communication link A1 is identified.
If the communication links A1 and B2 fail, the AFDX exchange can identify that A1 and B2 fail and change the transmission of the communication link maintenance data, where the communication link of the data transmission between the first AFDX terminal 30 and the second AFDX terminal 40 is: first AFDX terminal 30→B1→second AFDX exchange 20→first AFDX exchange 10→A2→second AFDX terminal 40.
In particular, the above-described method of reconstructing a communication link is applicable to all communication links in an avionics system communication network. When more than two AFDX terminals exist in the avionics system communication network and communication links between the AFDX terminals and the AFDX switch have faults at the same time, the AFDX terminals can send data to other AFDX switches through other communication links without faults, so that the data can be directly forwarded to the target AFDX terminals through the other AFDX switches; or forwarding the data to the AFDX exchange with the communication link fault between the AFDX exchange and the AFDX terminal through another AFDX exchange, and forwarding the data to the target AFDX terminal through the original AFDX exchange. Therefore, through the data interaction between the two AFDX switches, the communication link is flexibly changed, when a plurality of communication links fail, a new communication link is reconstructed according to the rest normal communication link and the data forwarding between the two AFDX switches, the data communication between different AFDX terminals is maintained, and the loss of data is avoided.
If the communication link A1 fails, the first AFDX exchange may identify the A1 failure, thereby modifying the subsequent communication link, where the communication link for data transmission between the first AFDX terminal 30 and the second AFDX terminal 40 is: first AFDX terminal 30→b1→second AFDX switch 20→b2→second AFDX terminal 40.
Specifically, if only one communication link between an AFDX exchange and one AFDX terminal fails, the subsequent data transmission discards the failed communication link. I.e. when only one communication link fails, the communication link is not required to be maintained through data forwarding between the AFDX exchanges, but the data interaction between the AFDX terminal and other AFDX terminals is realized directly through another AFDX exchange.
Specifically, when the original communication link B2 between the second AFDX terminal and the second AFDX terminal also fails (A1 is also in a failure state), the communication system in the present application can reconstruct the communication network, and the communication between the first AFDX terminal and the second AFDX terminal is restored through the connection of the first AFDX terminal, the second AFDX switch, the first AFDX switch, and the second AFDX terminal.
In this embodiment, when data to be transmitted needs to be sent to an AFDX terminal, it is first determined whether a communication link between an AFDX switch that sends data and the AFDX terminal that receives data is faulty, and if the communication link is normal, the data to be transmitted is sent to the AFDX terminal. If the communication link is faulty and the communication link between the second AFDX switch and the AFDX terminal is normal, the data to be transmitted is sent to the second AFDX switch, and then the second AFDX switch sends the data to be transmitted to the AFDX terminal. Thus, when communication links between a plurality of AFDX terminals and an AFDX switch are simultaneously failed in the avionics system communication network, a new communication link can be still established through another AFDX switch. And when the communication link between the AFDX terminal and any AFDX switch has no fault, the AFDX terminal can send data to other AFDX terminals or receive data sent by other AFDX terminals. If only one communication link between the AFDX switch and the AFDX terminal fails, the data forwarding is directly performed through the other AFDX switch. The stability of data transmission of the avionics system communication network is higher.
It should be understood that, although the steps in the flowcharts of fig. 1-3 are shown in order as indicated by the arrows, these steps are not necessarily performed in order as indicated by the arrows. The steps are not strictly limited to the order of execution unless explicitly recited herein, and the steps may be executed in other orders. Moreover, at least a portion of the steps of fig. 1-3 may include multiple steps or stages that are not necessarily performed at the same time, but may be performed at different times, nor does the order in which the steps or stages are performed necessarily occur sequentially, but may be performed alternately or alternately with other steps or at least a portion of the steps or stages in other steps.
In one embodiment, as shown in fig. 5, there is provided an avionics system communication failure handling device, comprising: a data receiving module 901 and a fault judging module 902, wherein:
the data receiving module is used for receiving first data to be detected sent by at least one of the first AFDX terminal and the second AFDX switch. The first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch.
The fault judging module is used for judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty when the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received; and when the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
For specific limitations on the avionics system communication fault handling apparatus, reference may be made to the limitations of avionics system communication fault handling methods hereinabove, and no further description is given herein. The modules in the avionics system communication fault handling device may be implemented in whole or in part in software, hardware, and combinations thereof. The above modules may be embedded in hardware or may be independent of a processor in the computer device, or may be stored in software in a memory in the computer device, so that the processor may call and execute operations corresponding to the above modules. It should be noted that, in the embodiment of the present application, the division of the modules is schematic, which is merely a logic function division, and other division manners may be implemented in actual implementation.
In one embodiment, a computer device is provided, the internal structure of which may be as shown in FIG. 6. The computer device includes a processor, a memory, and a network interface connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, computer programs, and a database. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage media. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program when executed by the processor implements a method for processing communication faults of an avionics system.
It will be appreciated by those skilled in the art that the structure shown in FIG. 6 is merely a block diagram of some of the structures associated with the present inventive arrangements and is not limiting of the computer device to which the present inventive arrangements may be applied, and that a particular computer device may include more or fewer components than shown, or may combine some of the components, or have a different arrangement of components.
In one embodiment, a computer device is provided, comprising a memory and a processor, the memory having stored therein a computer program, the processor implementing the steps of the method embodiments described above when the computer program is executed.
In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored which, when executed by a processor, implements the steps of the method embodiments described above.
Those skilled in the art will appreciate that implementing all or part of the above-described methods in accordance with the embodiments may be accomplished by way of a computer program stored on a non-transitory computer readable storage medium, which when executed may comprise the steps of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in embodiments provided herein may include at least one of non-volatile and volatile memory. The nonvolatile Memory may include Read-Only Memory (ROM), magnetic tape, floppy disk, flash Memory, optical Memory, or the like. Volatile memory can include random access memory (Random Access Memory, RAM) or external cache memory. By way of illustration, and not limitation, RAM can be in the form of a variety of forms, such as static random access memory (Static Random Access Memory, SRAM) or dynamic random access memory (Dynamic Random Access Memory, DRAM), and the like.
In the description of the present specification, reference to the terms "some embodiments," "other embodiments," "desired embodiments," and the like, means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, schematic descriptions of the above terms do not necessarily refer to the same embodiment or example.
The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The foregoing examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.
Claims (10)
1. A method for processing communication faults of an avionics system, the method comprising:
the method comprises the steps that a first AFDX switch receives first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch;
if the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received, judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty;
and if the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
2. The method according to claim 1, wherein the method further comprises:
the first AFDX switch receives second to-be-detected data sent by at least one of a second AFDX terminal and a second AFDX switch, wherein the second to-be-detected data sent by the second AFDX switch is the second to-be-detected data sent by the second AFDX terminal to the second AFDX switch;
if the second data to be detected sent by the second AFDX switch is received and the second data to be detected sent by the second AFDX terminal is not received, judging that a communication link between the first AFDX switch and the second AFDX terminal is faulty;
and if the second data to be detected sent by the second AFDX terminal is received and the second data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the second AFDX terminal is faulty.
3. The method according to claim 2, wherein the method further comprises:
after receiving data to be detected, checking the data to be detected, wherein the data to be detected is the first data to be detected or the second data to be detected;
and if the data to be detected is in error checking, judging that a communication link between the sending end of the data to be detected and the first AFDX switch is faulty.
4. A method according to claim 3, characterized in that the method further comprises:
and if the data to be detected is checked to be correct, judging that a communication link between the sending end of the data to be detected and the first AFDX switch is normal.
5. The method according to claim 4, wherein the method further comprises:
when data to be transmitted needs to be sent to the first AFDX terminal, if a communication link between the first AFDX switch and the first AFDX terminal is normal, the data to be transmitted is sent to the first AFDX terminal;
and if the communication link between the first AFDX switch and the first AFDX terminal is failed and the communication link between the second AFDX switch and the first AFDX terminal is normal, sending the data to be transmitted to the second AFDX switch so that the second AFDX switch sends the data to be transmitted to the first AFDX terminal.
6. The method according to claim 4, wherein the method further comprises:
and when the communication link between the first AFDX switch and the first AFDX terminal is failed and the communication link between the second AFDX switch and the first AFDX terminal is normal, sending data to be transmitted to the first AFDX terminal through the second AFDX switch.
7. The method of any of claims 1 to 6, wherein the first AFDX switch is configured identically to the second AFDX switch, and wherein the first AFDX switch performs the same function as the second AFDX switch.
8. An avionics system communication fault handling device, the device comprising:
the data receiving module is used for receiving first to-be-detected data sent by at least one of a first AFDX terminal and a second AFDX switch, wherein the first to-be-detected data sent by the second AFDX switch is the first to-be-detected data sent by the first AFDX terminal to the second AFDX switch;
the fault judging module is used for judging that a communication link between the first AFDX switch and the first AFDX terminal is faulty when the first data to be detected sent by the second AFDX switch is received and the first data to be detected sent by the first AFDX terminal is not received; and when the first data to be detected sent by the first AFDX terminal is received and the first data to be detected sent by the second AFDX switch is not received, judging that a communication link between the second AFDX switch and the first AFDX terminal is faulty.
9. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that the processor implements the steps of the method of any of claims 1 to 7 when the computer program is executed.
10. A computer readable storage medium, on which a computer program is stored, characterized in that the computer program, when being executed by a processor, implements the steps of the method of any of claims 1 to 7.
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