CN114679373B - Avionics system fault prediction method, device, computer equipment and medium - Google Patents

Avionics system fault prediction method, device, computer equipment and medium Download PDF

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Publication number
CN114679373B
CN114679373B CN202210128750.1A CN202210128750A CN114679373B CN 114679373 B CN114679373 B CN 114679373B CN 202210128750 A CN202210128750 A CN 202210128750A CN 114679373 B CN114679373 B CN 114679373B
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afdx
communication link
signal
time difference
terminal
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CN114679373A (en
Inventor
刘俊斌
周振威
黄云
路国光
时林林
何世烈
孟苓辉
俞鹏飞
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China Electronic Product Reliability and Environmental Testing Research Institute
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China Electronic Product Reliability and Environmental Testing Research Institute
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L41/00—Arrangements for maintenance, administration or management of data switching networks, e.g. of packet switching networks
    • H04L41/06—Management of faults, events, alarms or notifications
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L41/00—Arrangements for maintenance, administration or management of data switching networks, e.g. of packet switching networks
    • H04L41/14—Network analysis or design
    • H04L41/147—Network analysis or design for predicting network behaviour
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L43/00—Arrangements for monitoring or testing data switching networks
    • H04L43/08—Monitoring or testing based on specific metrics, e.g. QoS, energy consumption or environmental parameters
    • H04L43/0852—Delays
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L43/00—Arrangements for monitoring or testing data switching networks
    • H04L43/16—Threshold monitoring
    • 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
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L12/00—Data switching networks
    • H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
    • H04L12/40—Bus networks

Abstract

The application relates to a method, a device, computer equipment and a medium for predicting avionics system faults. The method comprises the following steps: receiving a first signal sent by a first AFDX switch, wherein the first signal is a first signal sent to the first AFDX switch by a first AFDX terminal, receiving a second signal sent by a second AFDX switch, and the second signal is a second signal sent to the second AFDX switch by the first AFDX terminal, acquiring a time difference value of the first signal and the second signal, and judging whether a communication link is about to fail according to the time difference value. The method can accurately predict the occurrence of the fault of the communication link before the occurrence of the fault of the communication link, is convenient for technicians to process the communication link which is about to be in fault in time, ensures higher stability of data transmission of the communication network of the avionics system, and avoids data loss.

Description

Avionics system fault prediction method, device, computer equipment and medium
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 predicting an avionics system failure.
Background
The AFDX (Avionics Full Duplex Switched Ethernet Network, avionics full duplex communication ethernet switched) bus is a standard definition based electronic and protocol specification (IEEE 802.3 and ARINC 664Part 7) that is used in avionics systems for data exchange between on-board aircraft avionics subsystems. It provides a star topology of up to 24 end systems that allows connection redundancy to guarantee bandwidth and quality of service. The AFDX 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 exchanger and a communication link.
The communication link is an important component of the AFDX network, is applied between every two devices of the avionics system AFDX network, provides a channel connected with an AFDX switch for different devices in the network, and realizes the safe and reliable data transmission function between the devices in the AFDX network. However, when the AFDX network works, the communication link is easy to break down, which may cause data loss and affect the operation of the avionics system, so that the AFDX network has poor working performance. The conventional technology provides a fault detection method of a communication link, but the fault detection method can only be detected after the communication link fails, so that the conventional AFDX network has the defect that the communication link fails can not be accurately predicted.
Disclosure of Invention
Based on the above, it is necessary to provide a method, a device, a computer device and a medium for predicting the failure of an avionics system, aiming at the problem that the failure of a communication link cannot be accurately predicted in the conventional AFDX network.
A method of avionics system fault prediction, the method comprising:
receiving a first signal sent by a first AFDX switch, wherein the first signal is sent to the first AFDX switch by a first AFDX terminal;
receiving a second signal sent by a second AFDX switch, wherein the second signal is sent to the second AFDX switch by a first AFDX terminal;
acquiring a time difference value of receiving the first signal and receiving the second signal;
and judging whether the communication link is about to fail according to the time difference value.
In one embodiment, the determining whether the communication link is about to fail according to the time difference value includes: and when the time difference value is larger than a preset time difference threshold value, judging that the communication link is about to break down.
In one embodiment, when the time difference value is greater than a preset time difference threshold, the determining that the communication link is about to fail includes: and when the time difference value is larger than a preset time difference threshold value, judging that the communication link with the transmission delay is about to fail.
In one embodiment, after determining whether the communication link is about to fail according to the time difference value, the method further includes: and after judging that the communication link is about to fail, carrying out alarm prompt.
In one embodiment, the first signal and the second signal are simultaneously emitted by the first AFDX terminal.
In one embodiment, the configuration difference value of the first AFDX switch and the second AFDX switch is within an allowable error range.
In one embodiment, the communication link comprises a first communication link between the first AFDX switch and the first AFDX terminal and a second communication link between the second AFDX switch and the first AFDX terminal, the configuration difference values of the first communication link and the second communication link being within a tolerance range.
An avionics system fault prediction apparatus, the apparatus comprising:
the first signal receiving module is used for receiving a first signal sent by a first AFDX switch, wherein the first signal is sent to the first AFDX switch by a first AFDX terminal;
the second signal receiving module is used for receiving a second signal sent by a second AFDX switch, wherein the second signal is sent to the second AFDX switch by the first AFDX terminal;
the data processing module is used for acquiring a time difference value of receiving the first signal and the second signal;
and the fault prediction module is used for judging whether the communication link is about to break down according to the time difference value.
A computer device comprising a memory storing a computer program and a processor implementing the steps described above when the processor executes the computer program.
A computer readable storage medium having stored thereon a computer program which when executed by a processor performs the above steps.
According to the avionics system fault prediction method, the avionics system fault prediction device, the computer equipment and the medium, through receiving a first signal sent by a first AFDX switch, the first signal is the first signal sent by a first AFDX terminal to the first AFDX switch, receiving a second signal sent by a second AFDX switch, the second signal is the second signal sent by the first AFDX terminal to the second AFDX switch, acquiring a time difference value of the first signal and the second signal, and judging whether a communication link is about to be faulty or not according to the time difference value. The AFDX network compares the signal receiving time from different communication links through redundancy, and accurately predicts that the communication link fails before the communication link fails, so that technicians can process the communication link which is about to fail in time, 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 chart of a method of predicting a failure of an avionics system in one embodiment;
FIG. 2 is a schematic diagram of an avionics system network in one embodiment;
FIG. 3 is a flow diagram of a method of communication link failure prediction in one embodiment;
FIG. 4 is a flow diagram of communication link failure prediction determination conditions in one embodiment;
FIG. 5 is a schematic diagram of a communication link transmitting signals in one embodiment;
FIG. 6 is a schematic diagram of a communication link transmission signal in one embodiment;
FIG. 7 is a diagram of waveforms of data at a transmitting end and a receiving end of a communication link according to one embodiment;
FIG. 8 is a flow chart of a method of warning an avionics system in one embodiment;
FIG. 9 is a schematic diagram of an avionics system predicting device in one embodiment;
fig. 10 is an internal structural view of a computer device in one embodiment.
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.
In one embodiment, as shown in fig. 1, the application provides a method for predicting a failure of an avionics system, wherein the avionics system comprises an avionics system (AFDX) terminal, an AFDX switch and a communication link, the AFDX terminal is an important component of an AFDX network, different devices of the AFDX network can communicate with a transmitting signal through the AFDX terminal, the AFDX switch is a relay device in the AFDX network, the signals from the different AFDX terminals are uniformly received and transmitted, and the communication link is a channel for connecting the AFDX terminal and the AFDX switch in the AFDX network. The AFDX terminal, the AFDX switch and the communication link realize the safe and reliable data transmission function among all devices in the AFDX network. The avionics system fault prediction method may be performed by an AFDX terminal in the avionics system. The method comprises the following steps:
step S100, receiving a first signal sent by a first AFDX switch.
In particular, the first signal transmitted by the first AFDX switch may be received by a second AFDX terminal in the avionics system. The first signal sent by the first AFDX switch is the first signal sent by the first AFDX terminal to the first AFDX switch. The first AFDX terminal is connected with the first AFDX switch, and the first AFDX switch is connected with the second AFDX terminal. The first signal is sent out by the first AFDX terminal and then reaches the second AFDX terminal through the first AFDX switch.
Step S200, receiving a second signal sent by a second AFDX switch.
In particular, the second signal transmitted by the second AFDX-switch may be received by a second AFDX terminal in the avionics system. The second signal sent by the second AFDX switch is the second signal sent by the first AFDX terminal to the second AFDX switch. The first AFDX terminal is connected with a second AFDX switch, and the second AFDX switch is connected with the second AFDX terminal. The second signal is sent out by the first AFDX terminal and then reaches the second AFDX terminal through the second AFDX switch.
Step S300, obtaining a time difference value between receiving the first signal and receiving the second signal.
Specifically, because the communication links for transmitting the first signal and the second signal are different, when there is an abnormal communication link, the working states of the different communication links may be different, and the time for receiving the first signal and the second signal may be different, and at this time, a time difference value may exist between the time for receiving the first signal and the time for receiving the second signal, where the time difference value is generally the difference between the two times, and may represent the sequence of receiving the first signal and the second signal. The time difference value is used as an evaluation index, so that the working state of the communication link can be intuitively judged.
Step S400, judging whether the communication link is about to fail according to the time difference value.
After the time difference value is obtained, the time interval between the reception of the first signal and the reception of the second signal can be judged according to the time difference value. Determining whether the communication link is about to fail according to the time difference value may be: when the time difference value is larger, the time interval between the first signal and the second signal is considered longer, and the communication link is judged to work abnormally, so that faults are about to occur. At the moment, the early warning can be given to the staff, so that the staff can check and process in time, and the influence of the communication link fault on the avionics system is reduced.
The AFDX network compares the signal receiving time from different communication links in a redundancy mode, and accurately predicts that the communication link fails before the communication link fails, so that technicians can process the communication link which is about to fail in time, the stability of data transmission of the avionics system communication network is higher, and data loss is avoided.
Further, in the avionics system, the number of AFDX terminals is not unique, and typically two or more AFDX terminals are configured with different values within an allowable error range. Exemplary, the AFDX communication module structures of the first AFDX terminal and the second AFDX terminal are the same, and the AFDX communication functions realized by the first AFDX terminal and the second AFDX terminal are also the same.
The number of AFDX exchanges is not unique, and is usually two or more, and the configuration difference value of each AFDX exchange is within the allowable error range. Illustratively, the first AFDX switch and the second AFDX switch have the same structure, the functions implemented by the first AFDX switch and the second AFDX switch are also the same, and the role functions of the second AFDX switch and the first AFDX switch can be interchanged. Through the redundancy backup of the AFDX switches with the same structure, configuration and function, the signal bandwidth and the signal transmission capacity of the AFDX network can be ensured, and the reliability of the prediction result of the impending failure of the communication link can be enhanced.
The number of communication links is not unique, and in particular, since the number of AFDX terminals and AFDX exchanges in the AFDX network is not unique, a person skilled in the art can determine the number of AFDX terminals and AFDX exchanges. The communication link may include a first communication link between the first AFDX switch and the first AFDX terminal and a second communication link between the second AFDX switch and the first AFDX terminal, and may further include a third communication link between the first AFDX switch and the second AFDX terminal and a fourth communication link between the second AFDX switch and the second AFDX terminal.
Illustratively, the avionics system includes An AFDX network, which includes a plurality of AFDX terminals and two AFDX exchanges, as shown in fig. 2, a first AFDX exchange 10 is connected to a first AFDX terminal 30, a second AFDX terminal 40, … … and An nth AFDX terminal through a first communication link A1, a third communication link A2, … … An, respectively, and a second AFDX exchange 20 is connected to a first AFDX terminal 30, a second AFDX terminal 40, … … and An nth AFDX terminal through a second communication link B1, a fourth communication link B2, … … Bn, respectively.
The line of data transmission between the first AFDX terminal 30 and the second AFDX terminal 40 comprises: first AFDX terminal 30→first communication link a1→first AFDX switch 10→third communication link a2→second AFDX terminal 40, or first AFDX terminal 30→second communication link b1→second AFDX switch 20→fourth communication link b2→second AFDX terminal 40.
The above method of constructing a communication link is applicable to all communication links in an avionics system communication network. When a communication link in the avionics system communication network is about to fail, each AFDX terminal can determine the time difference value of signals from different communication links and sent by the same AFDX terminal.
The cause of the failure of the communication link is numerous, including but not limited to, variations in electrical parameters of the communication link such as line impedance, parasitic inductance, and parasitic capacitance. Taking the example that the line impedance changes to cause the communication link to fail, as the working time of the communication link increases, the surface layer of the metal wire inside the communication link is oxidized, so that the impedance of the communication link increases, the speed of the communication link for transmitting signals is reduced after the impedance increases, and when the impedance further increases, the waveform of the signals transmitted by the communication link can not be identified, and the communication link fails at the moment.
The method for judging whether the communication link is about to fail according to the time difference value is not unique, the time difference value can be compared with preset judging conditions, and data related to the preset judging conditions can be stored in each AFDX terminal in advance, so that the method is convenient to call. The relationship between the time difference value and the working state of the communication link can be learned by arranging an artificial intelligence algorithm module in the AFDX terminal to obtain a prediction result. By taking the example that the AFDX terminal receives the time difference value data of the signals sent by the same AFDX terminal from different communication links, the time difference value data of the communication link transmission signals with the working time length reaching the fault standard can be used as a neural network prediction training set, and the accuracy of a neural network prediction model can be verified according to the time difference value data of the transmission signals of another communication link (with the working time length not being unique), so that the degree of automation can be greatly improved. It will be appreciated that in other embodiments, other methods of learning the received test results may be used to obtain the predicted results, as long as those skilled in the art recognize this as being possible.
In one embodiment, as shown in FIG. 3, step S400 includes step S410.
In step S410, when the time difference value is greater than the preset time difference threshold, it is determined that the communication link is about to fail.
After receiving the first signal and the second signal, the second AFDX terminal 40 calculates a time difference value between the first signal and the second signal, and compares the time difference value with a preset determination condition. The preset determination condition is not unique, in this embodiment, the preset determination condition is a preset time difference threshold, and when the calculated time difference value is greater than the preset time difference threshold, it is determined that a communication link transmitting the first signal and the second signal is about to have a fault in the communication link. It is understood that the preset time difference threshold value is not unique, and can be adjusted according to actual requirements, so long as the person skilled in the art considers that the adjustment can be achieved.
In one embodiment, as shown in FIG. 4, step S410 includes step S420.
In step S420, when the time difference value is greater than the preset time difference threshold, it is determined that the communication link with the transmission delay is about to fail.
Specifically, as shown in fig. 6, the process of transmitting signals from the first AFDX terminal 30 to the second AFDX terminal 40 through two lines is shown, further, as shown in fig. 7, the communication link for transmitting the first signal includes a first resistor 301, a first parasitic capacitor 302 and a first parasitic inductor 303, the communication link in the second signal transmission line includes a second resistor 401, a second parasitic capacitor 402 and a second parasitic inductor 403, and electrical parameters such as line impedance, parasitic inductance and parasitic capacitance of the communication link may change with the working time. Taking line impedance as an example, on a communication link transmitting a first signal, as the operation time of the communication link increases, the surface layer of the metal line inside the communication link is oxidized, and the resistivity of the metal line inside the communication link decreases, thereby increasing the impedance of the communication link. An RC circuit is formed between the first resistor 301 and the first parasitic capacitor 302 in the communication link, where the voltage value across the first parasitic capacitor is:
wherein U is 0 For the input voltage of the first AFDX terminal 30, e is a base of natural logarithm, R is a resistance value of the first resistor 301, C is a capacitance value of the first parasitic capacitor 302, the product RC is a time constant of the RC circuit, and τ is represented by τ, where the magnitude of τ reflects the progress speed of the circuit transition stage.
As can be seen from the formula (1), when the resistance of the first resistor 301 increases, the time constant τ of the RC circuit increases, the voltage value at the two ends of the first parasitic capacitor 302 changes slowly, so that the edge of the transmitted signal slows down, the edge of the signal jumps slowly, and the receiving end of the AFDX terminal can only identify the high-level signal, that is, the receiving end of the AFDX terminal can identify the signal only after waiting until the signal voltage is higher than a certain value, so that the time of receiving the signal by the receiving end of the AFDX terminal can be delayed.
As shown in fig. 7, the first AFDX terminal 30 sends data to the second AFDX terminal 40 through two lines, and if the impedance of the communication link for transmitting the second signal is relatively high and the communication link for transmitting the first signal is all normal, the receiving ends of different signals on the second AFDX terminal 40 receive low-level signals at the same time at time t0, at this time, the second AFDX terminal 40 cannot recognize the low-level signals, and as the communication link for transmitting the first signal works normally, the voltage waveform received by the first signal receiving end of the second AFDX terminal is relatively steep and reaches high-level signals at time t1, i.e. the second AFDX terminal 40 starts to receive the first signals at time t 1. The impedance of the communication link for transmitting the second signal is larger, the voltage waveform received by the first signal receiving end of the second AFDX terminal is relatively gentle and reaches a high level signal at the time T2, that is, the second AFDX terminal 40 starts to receive the first signal at the time T2, and the time interval between the time T2 and the time T1 is the time difference T between the first signal and the second signal received by the second AFDX terminal 40, so that a person skilled in the art can set a time difference threshold according to the actual situation, so long as the person skilled in the art considers that the implementation can be achieved. The time difference value between the first signal and the second signal received by the second AFDX terminal 40 is used as an evaluation index, so that the calculation is simple and convenient, the workload of the AFDX terminal can be reduced, and the communication link which is about to be failed can be efficiently and quickly judged.
Illustratively, when the first communication link A1 or the third communication link A2 is about to fail, the second AFDX terminal 40 receives the second signal sent by the second AFDX switch 20 first, and after a period of time greater than the time difference threshold, the second AFDX terminal 40 receives the first signal sent by the first AFDX switch 10, so that the first communication link A1 or the third communication link A2 is about to fail can be quickly identified. When the second communication link B1 or the fourth communication link B2 is about to fail, the second AFDX terminal 40 receives the first signal sent by the first AFDX switch 10 first, and after a time length greater than the time difference threshold, the second AFDX terminal 40 receives the second signal sent by the second AFDX switch 20, so that the failure of the second communication link B1 or the fourth communication link B2 can be quickly identified. When the first communication link A1, the second communication link B1, the third communication link A2 and the fourth communication link B2 all work normally, the second AFDX terminal 40 receives the first signal sent by the first AFDX switch 10 and the second signal sent by the second AFDX switch 20 sequentially, and the time interval is less than or equal to the time length of a time difference threshold.
In one embodiment, as shown in fig. 8, after step S400, the avionics system fault prediction method further includes step S500.
Step S500: and after judging that the communication link is about to fail, carrying out alarm prompt.
Specifically, the device for performing the alarm prompting is not unique, and the second AFDX terminal 40 may perform the alarm after determining that the communication link is about to fail according to the time difference value, or may send an alarm signal to an external alarm device through a communication mode such as a 4G network, etc., and the external alarm device receives the alarm signal and then alarms. For example, after the AFDX terminal determines that the communication link is about to fail according to the time difference value, the wireless 4G communication module with the SIM card inserted inside the second AFDX terminal 40 sends the alarm signal to the remote alarm, so as to realize remote alarm. The specific mode of alarming is not unique, and can adopt an acoustic alarm or an optical alarm, and the alarm mode can be set according to actual requirements. For example, when the second AFDX terminal 40 adopts an acoustic alarm, the second AFDX terminal 40 alarms by emitting an alarm sound after determining that the communication link is about to fail. Furthermore, the type of the sound alarm is not unique, the alarm effect is good by continuously or intermittently sending out the alarm sound with larger volume, or the sound alarm can be played as voice, and different alarm voices are played according to the about to be faulty of different communication links, so that the alarm content is rich.
When the second AFDX terminal 40 adopts the optical alarm, the second AFDX terminal 40 alarms by sending out an alarm light wave after judging that the communication link is about to fail. Furthermore, the type of the optical alarm is not unique, obvious laser can be continuously or intermittently emitted, the alarm effect is good, or the optical alarm can be strobe light, and light waves with different frequencies can be emitted according to the impending faults of different communication links so as to rapidly convey fault information. It will be appreciated that in other embodiments, the second AFDX terminal 40 may also take other forms of alerting, as long as it is deemed to be possible by a person skilled in the art.
In one embodiment, the first signal and the second signal are simultaneously issued by the first AFDX terminal 30. The time required to affect the transmission of the first and second signals to the second AFDX terminal 40 is only related to the operational state of the communication link, and the influence on the reliability of the prediction result due to the difference of the initial times of the transmitted signals is reduced to a certain extent.
In one embodiment, the communication links include a first communication link A1 between the first AFDX switch 10 and the first AFDX terminal 30 and a second communication link B1 between the second AFDX switch 20 and the first AFDX terminal 30, the configuration difference values of the first communication link A1 and the second communication link B1 being within the allowable error range. Specifically, the configuration difference value of the first communication link A1 and the second communication link B1 within the allowable error range means that the chip types and the cable lengths of the first communication link A1 and the second communication link B1 are the same, the initial resistance values and other electrical parameters of the first communication link A1 and the second communication link B1 are the same, the functions implemented by the first communication link A1 and the second communication link B1 are the same, and the role functions of the first communication link A1 and the second communication link B1 can be interchanged. In an expandable manner, when the avionics system further includes other communication links, such as a third communication link A2 between the first AFDX switch 10 and the second AFDX terminal 40 and a fourth communication link B2 between the second AFDX switch 20 and the second AFDX terminal 40, the configuration difference values of the respective communication links are within the allowable error range. By means of the communication link, the reliability of the prediction result of the impending failure of the communication link can be enhanced.
For a better understanding of the above embodiments, a detailed explanation is provided below in connection with a specific embodiment. In one embodiment, the avionics system includes a plurality of AFDX terminals and two AFDX switches, as shown in fig. 2, the first AFDX switch 10 is connected to the first AFDX terminal 30, the second AFDX terminal 40, the … … nth AFDX terminal through a first communication link A1, a third communication link A2, … … An, and the second AFDX switch 20 is connected to the first AFDX terminal 30, the second AFDX terminal 40, … … nth AFDX terminal through a second communication link B1, a fourth communication link B2, … … Bn.
The first AFDX exchange 10 has the same structure as the second AFDX exchange 20, the functions realized by the first AFDX exchange 10 and the second AFDX exchange 20 are also the same, and the role functions of the second AFDX exchange 20 and the first AFDX exchange 10 can be interchanged.
The configuration difference values of the first AFDX terminal 30, the second AFDX terminal 40 and the rest of the AFDX terminals in the avionics system are within the allowable error range, the structures of the AFDX communication modules in the AFDX terminals are the same, and the AFDX communication functions realized by the AFDX terminals are also the same.
The chip types and the cable lengths of the communication modules in the first communication link A1, the second communication link B1, the third communication link A2, the fourth communication link B2 and the rest communication links in the avionics system are the same, the initial resistance values and other electrical parameters of the communication links are the same, the functions realized by the communication links are the same, and the role functions of the communication links can be interchanged.
The first signal and the second signal are sent by the first AFDX terminal 30 at the same time, and the transmission process of the first signal is as follows: first AFDX terminal 30→first communication link a1→first AFDX switch 10→third communication link a2→second AFDX terminal 40. The transmission process of the second signal is as follows: first AFDX terminal 30→second communication link b1→second AFDX switch 20→fourth communication link b2→second AFDX terminal 40.
After the second AFDX terminal 40 receives the first signal and the second signal, calculates a time difference value of the received first signal and the second signal, and then compares the time difference value with a preset determination condition, in this embodiment, the preset determination condition is a preset time difference threshold T, and when the calculated time difference value is beyond the time difference threshold T, it is determined that a communication link transmitting the first signal and the second signal is about to fail.
In this embodiment, the second AFDX terminal 40 receives the second signal sent by the second AFDX switch 20 first, and after a time length greater than the time difference threshold T, the second AFDX terminal 40 receives the first signal sent by the first AFDX switch 10, and at this time, it can be predicted that the first communication link A1 or the third communication link A2 will fail.
After determining that the first communication link A1 or the third communication link A2 is about to fail, the second AFDX terminal 40 sends an alarm signal to the control center to inform a technician that the first communication link A1 or the third communication link A2 is about to fail, so that the technician can process the communication link about to fail in real time, the stability of data transmission of the avionics system communication network is higher, and data loss is avoided.
According to the avionics system fault prediction method, the first signal sent by the first AFDX switch is received, the first signal is the first signal sent to the first AFDX switch by the first AFDX terminal, the second signal sent by the second AFDX switch is received, the second signal sent to the second AFDX switch by the first AFDX terminal is obtained, the time difference value of the first signal and the second signal is received is obtained, and whether a communication link is about to be broken down is judged according to the time difference value. The AFDX network compares the signal receiving time from different communication links through redundancy, and accurately predicts that the communication link fails before the communication link fails, so that technicians can process the communication link which is about to fail in time, the stability of data transmission of the avionics system communication network is higher, and data loss is avoided.
In one embodiment, as shown in fig. 9, there is provided an avionics system fault handling apparatus comprising: a first signal receiving module 101, a second signal receiving module 102, a data processing module 103, and a failure prediction module 104, wherein:
a first signal receiving module 101, configured to receive a first signal sent by a first AFDX switch, where the first signal is a first signal sent by a first AFDX terminal to the first AFDX switch;
a second signal receiving module 102, configured to receive a second signal sent by a second AFDX switch, where the second signal is a second signal sent by the first AFDX terminal to the second AFDX switch;
a data processing module 103, configured to obtain a time difference value between receiving the first signal and receiving the second signal;
the failure prediction module 104 is configured to determine whether the communication link is about to fail according to the time difference value.
For specific limitations on the avionics system fault prediction device, reference may be made to the limitations of the avionics system fault prediction method hereinabove, and will not be described in detail herein. The modules in the avionics system fault prediction device may be implemented in whole or in part by 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 also provided, the internal structure of which may be as shown in FIG. 10. 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 a processor implements a method of predicting an avionics system failure.
It will be appreciated by those skilled in the art that the structure shown in FIG. 10 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 may be accomplished by way of a computer program, which may be stored on a non-transitory computer readable storage medium, that 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 predicting a failure of an avionics system, the method comprising the steps of:
receiving a first signal sent by a first AFDX switch, wherein the first signal is sent to the first AFDX switch by a first AFDX terminal;
receiving a second signal sent by a second AFDX switch, wherein the second signal is sent to the second AFDX switch by a first AFDX terminal;
acquiring a time difference value of receiving the first signal and receiving the second signal;
and judging whether the communication link is about to fail according to the time difference value.
2. The avionics system fault prediction method according to claim 1, wherein determining whether a communication link is about to fail based on the time difference value comprises:
and when the time difference value is larger than a preset time difference threshold value, judging that the communication link is about to break down.
3. The avionics system fault prediction method according to claim 2, wherein determining that the communication link is about to fail when the time difference value is greater than a preset time difference threshold comprises:
and when the time difference value is larger than a preset time difference threshold value, judging that the communication link with the transmission delay is about to fail.
4. The avionics system fault prediction method according to claim 1, wherein after determining whether a communication link is about to fail according to the time difference value, further comprising:
and after judging that the communication link is about to fail, carrying out alarm prompt.
5. The avionics system fault prediction method of claim 1, wherein the first signal and the second signal are issued simultaneously by the first AFDX terminal.
6. The avionics system fault prediction method of claim 1, wherein a configuration difference value of the first AFDX switch and the second AFDX switch is within an allowable error range.
7. The avionics system fault prediction method of claim 1, wherein the communication link comprises a first communication link between the first AFDX switch and the first AFDX terminal and a second communication link between the second AFDX switch and the first AFDX terminal, the configuration difference values of the first communication link and the second communication link being within a tolerance.
8. An avionics system fault prediction apparatus, the apparatus comprising:
the first signal receiving module is used for receiving a first signal sent by a first AFDX switch, wherein the first signal is sent to the first AFDX switch by a first AFDX terminal;
the second signal receiving module is used for receiving a second signal sent by a second AFDX switch, wherein the second signal is sent to the second AFDX switch by the first AFDX terminal;
the data processing module is used for acquiring a time difference value of receiving the first signal and the second signal;
and the fault prediction module is used for judging whether the communication link is about to break down according to the time difference value.
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 having a computer program stored thereon, characterized in that,
the computer program implementing the steps of the method of any of claims 1 to 7 when executed by a processor.
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