CN115964247A - Non-bus signal fault injection equipment and method applied to integrated avionics system - Google Patents
Non-bus signal fault injection equipment and method applied to integrated avionics system Download PDFInfo
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- CN115964247A CN115964247A CN202211662865.5A CN202211662865A CN115964247A CN 115964247 A CN115964247 A CN 115964247A CN 202211662865 A CN202211662865 A CN 202211662865A CN 115964247 A CN115964247 A CN 115964247A
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Abstract
The invention relates to the technical field of fault injection of a comprehensive avionics system, in particular to non-bus signal fault injection equipment and a method applied to the comprehensive avionics system, wherein the fault injection equipment comprises an equipment main body, a main control computer, a fault injection assembly, a signal monitoring assembly and a signal conditioning and converting assembly, wherein the main control computer, the fault injection assembly, the signal monitoring assembly and the signal conditioning and converting assembly are arranged in the equipment main body; the main control computer is in communication connection with the fault injection assembly, the signal monitoring assembly and the signal conditioning and converting assembly through Ethernet interfaces; the fault injection assembly is connected with the main control computer and the signal conditioning conversion assembly; the signal monitoring assembly is connected with the main control computer, the fault injection assembly and the signal conditioning and converting assembly. The invention realizes the injection of non-bus signals of the integrated avionics system and the injection and recurrence of cross-linking faults caused by failure of the non-bus signals, and effectively improves the precision and efficiency of fault location and diagnosis of the integrated avionics system.
Description
Technical Field
The invention relates to the technical field of fault injection of a comprehensive avionics system, in particular to non-bus signal fault injection equipment and a non-bus signal fault injection method applied to the comprehensive avionics system.
Background
With the continuous improvement of the integration degree of the avionics system, the cross-linking between the internal subsystems is more complex, and the difficulty in locating the generated cross-linking fault is higher and higher. In order to improve the diagnosis and recurrence capacity of the cross-linking fault of the comprehensive avionics system, the research on the fault injection technology is particularly important.
The integrated avionics system has various signal types, including FC optical fiber signals, 1553B bus signals and non-bus signals (RS-429 signals, RS-422 signals, analog quantity signals, discrete quantity signals and the like). At present, the application of the fault injection technology in the integrated avionics system mainly focuses on the stages of design and functional verification, and mainly is fault injection realized from a 1553B bus layer, and no related research case exists at the fault diagnosis and recurrence layer. In fact, the injection of the FC fiber signal and the 1553B bus signal depends on relatively independent fault injection equipment and a complete signal interface definition, and the injection of the non-bus signal has no systematic complete fault injection equipment and method in the field of the fault injection of the avionics system due to the large difference of signal types.
Disclosure of Invention
Aiming at the technical problem, the invention provides non-bus signal fault injection equipment and a non-bus signal fault injection method applied to a comprehensive avionics system.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the non-bus signal fault injection equipment applied to the comprehensive avionics system comprises an equipment main body, a main control computer, a fault injection assembly, a signal monitoring assembly and a signal conditioning and converting assembly, wherein the main control computer, the fault injection assembly, the signal monitoring assembly and the signal conditioning and converting assembly are arranged in the equipment main body;
the main control computer is in communication connection with the fault injection assembly, the signal monitoring assembly and the signal conditioning and converting assembly through Ethernet interfaces and is used for realizing the unified management of configuration information of each assembly;
the fault injection component is connected with the main control computer and the signal conditioning and converting component and is used for configuring and generating HB6096, RS422, discrete quantity, analog quantity and synchronizer quantity non-bus signals;
the signal monitoring component is connected with the main control computer, the fault injection component and the signal conditioning and converting component and is used for monitoring and analyzing the non-bus interface communication data of the integrated avionics system;
the signal conditioning and converting assembly is connected with the main control computer, the fault injection assembly and the signal monitoring assembly and is used for conditioning and switching signals of the comprehensive avionic system and non-bus injection signals.
Preferably, the fault injection assembly comprises a fault injection assembly box, a fault injection assembly controller arranged in the fault injection assembly box, an ARINC429 communication module, a serial communication module, a discrete quantity module, an analog voltage and current output module and a 2CH excitation/synchronizer module.
Preferably, the fault injection assembly box body is in butt joint with the comprehensive avionics system and the signal conditioning conversion assembly through an aviation plug connector, and the fault injection assembly controller is in communication connection with the main control computer.
Preferably, the signal monitoring assembly comprises a monitoring assembly box body, a monitoring assembly controller arranged in the monitoring assembly box body, a PXI synchronization module, an HB6096 interface card, a carrier card, an RS-422 bus interface card, a discrete quantity interface card and an analog quantity interface card.
Preferably, the monitoring component box body is in butt joint with the comprehensive avionics system, the fault injection component box body and the signal conditioning conversion component through an air insertion connector, and the monitoring component controller is in communication connection with the main control computer.
Preferably, the signal conditioning conversion assembly comprises a conditioning assembly box body, a signal conditioning conversion controller and a matrix switch.
Preferably, the conditioning component box body is in butt joint with the comprehensive avionics system, the fault injection component box body and the signal monitoring component box body through an aviation plug connector, and the signal conditioning conversion controller is in communication connection with the main control computer.
The non-bus signal fault injection method applied to the integrated avionics system utilizes non-bus signal fault injection equipment applied to the integrated avionics system, and comprises the following specific steps of:
step one, combining a cross-linking fault phenomenon to determine a fault signal injection requirement;
step two, configuring a module in the fault injection assembly through a main control computer, and outputting a required non-bus signal;
step three, the signal monitoring component monitors whether the output non-bus signal meets the requirement, and if not, the non-bus signal is fed back to the main control computer to reconfigure parameters; if the requirements are met, the next step is carried out;
the signal monitoring component judges whether the equipment is accessed to a signal on a real machine of the integrated avionics system again, if the equipment is not accessed to the signal, the injected signal is output to the integrated avionics system, and fault injection is executed; if the real signal is accessed, the signal conditioning and converting component is controlled to disconnect the real signal and output an injection signal to the avionic system, and fault injection is executed;
monitoring the injection signal received by the integrated avionics system and the output accuracy of the next-stage signal by the signal monitoring assembly, and finishing the fault injection process if the output signal is accurate and the fault is reproduced; and if the inaccurate fault of the output signal does not reappear, feeding back to the main control computer to execute the step (two) -the step (five) again.
The beneficial effects of the invention are:
compared with the prior art, the method and the device realize the injection of the non-bus signals of the integrated avionics system and the injection and the recurrence of the cross-linking faults caused by the failure of the non-bus signals, and effectively improve the precision and the efficiency of fault positioning and diagnosis of the integrated avionics system.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a schematic view of the external structure of the apparatus of the present invention;
FIG. 2 is a block diagram of the components of the present invention;
FIG. 3 is a block diagram of the components of the fault injection assembly of the present invention;
FIG. 4 is a block diagram of the signal monitoring components of the present invention;
FIG. 5 is a block diagram of the signal conditioning converter assembly of the present invention;
FIG. 6 is a flow chart of a method of the present invention.
In the figure: 1. an apparatus main body; 101. a main control computer; 102. a fault injection assembly; 103. a signal monitoring component; 104. and a signal conditioning and converting component.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained in the following with the accompanying drawings and the embodiments.
As shown in fig. 1 and fig. 2, the non-bus signal fault injection device applied to the integrated avionics system includes a device body 1, a main control computer 101, a fault injection module 102, a signal monitoring module 103, and a signal conditioning and converting module 104. The main control computer 101, the fault injection component 102, the signal monitoring component 103 and the signal conditioning and converting component 104 are correspondingly arranged in the equipment main body 1.
As a further improvement of this embodiment, the main control computer 101 is in communication connection with the fault injection component 102, the signal monitoring component 103, and the signal conditioning and converting component 104 through an ethernet interface, and realizes unified management of configuration information of each component by scheduling board card configuration software and customizing application software of each component.
The fault injection component 102 is configured to generate HB6096, RS422, discrete magnitude, analog magnitude, synchronizer magnitude non-bus signals.
As shown in fig. 3, the fault injection assembly 102 includes a fault injection assembly box, a fault injection assembly controller disposed in the fault injection assembly box, an ARINC429 communication module, a serial communication module, a discrete magnitude module, an analog voltage and current output module, and a 2CH excitation/synchronizer module.
The fault injection assembly box body is mainly used for converting a board card interface into an aerial plug interface and realizing butt joint with an onboard cable and a signal conditioning conversion assembly 104 of the integrated avionics system through aerial plug; the fault injection component controller is mainly used for being in communication connection with the main control computer 101; the ARINC429 communication module is mainly used for configuration and generation of HB6096 signals; the serial port communication module is mainly used for configuration and generation of RS-422 signals; the discrete magnitude module is mainly used for configuring and generating discrete magnitude signals, and the analog voltage and current output module is mainly used for configuring and generating analog magnitude signals; the 2CH excitation/synchronizer module is mainly used for configuration and generation of synchronizer and frequency quantities.
The signal monitoring component 103 is used for monitoring and analyzing the non-bus interface communication data of the integrated avionics system.
As shown in fig. 4, the signal monitoring component 103 includes a monitoring component box, a monitoring component controller disposed in the monitoring component box, a PXI synchronization module, an HB6096 interface card, a carrier card, an RS-422 bus interface card, a discrete quantity interface card, and an analog quantity interface card.
The monitoring component box body is mainly used for converting a board card interface into an aerial plug interface and realizing butt joint with an onboard cable, a fault injection component box body and a signal conditioning and converting component 104 of the integrated avionics system through aerial plug; the monitoring component controller is mainly used for being in communication connection with the main control computer 101; the PXI synchronization module is mainly used for synchronizing PXI system time through IRIG-B; the card carrier is mainly used for converting a PXI interface into a PMC interface; the HB6096 interface card is mainly used for communication test of HB6096 signals; the RS-422 bus interface card is mainly used for communication test of RS-422 signals; the discrete magnitude interface card is mainly used for communication configuration of discrete magnitude signals; the analog quantity interface card is mainly used for communication configuration of analog quantity signals.
The signal conditioning and converting component 104 is used for conditioning and switching the integrated avionics system signal and the non-bus injection signal.
As shown in fig. 5, the signal conditioning converter assembly 104 includes a conditioning assembly box, a signal conditioning converter controller, and a matrix switch.
The conditioning component box body is in butt joint with a cable on the comprehensive avionic system machine, a fault injection component box body and a signal monitoring component box body through an aviation plug connector; the signal conditioning conversion controller is mainly used for being in communication connection with a main control computer 101; the matrix switch is mainly used for switching non-bus signals and non-bus injection signals of the integrated avionics system.
As shown in fig. 6, the non-bus signal fault injection method applied to the integrated avionics system utilizes the above non-bus signal fault injection device applied to the integrated avionics system, and includes the following specific steps:
and (I) combining the cross-linking fault phenomenon to determine the fault signal injection requirement.
And (II) configuring a module in the fault injection assembly 102 through the main control computer 101, and outputting a required non-bus signal.
Step (III), the signal monitoring component 103 monitors whether the output non-bus signal meets the requirement, and if not, the output non-bus signal is fed back to the main control computer 101 to reconfigure parameters; if the requirement is met, the next step is carried out.
Step (four), the signal monitoring component 103 judges whether the equipment is accessed to a signal on a real machine of the integrated avionics system again, and if the real signal is not accessed, the injected signal is output to the integrated avionics system to execute fault injection; if the real signal is accessed, the control signal conditioning and converting component 104 outputs the injection signal to the avionics system after disconnecting the real signal, and executes fault injection.
Step (five), the signal monitoring component 103 monitors the injection signal received by the integrated avionics system and the output accuracy of the next-stage signal thereof, and if the output signal is accurate and the fault is reproduced, the fault injection process is ended; and if the inaccurate fault of the output signal does not reappear, feeding back to the main control computer 101 to execute the step (two) -the step (five) again.
The foregoing shows and describes the general principles, principal features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. Be applied to non-bus signal fault injection equipment among comprehensive avionics system, its characterized in that: the device comprises a device body (1), a main control computer (101) arranged in the device body (1), a fault injection assembly (102), a signal monitoring assembly (103) and a signal conditioning and converting assembly (104);
the main control computer (101) is in communication connection with the fault injection component (102), the signal monitoring component (103) and the signal conditioning and converting component (104) through an Ethernet interface and is used for realizing the unified management of configuration information of each component;
the fault injection component (102) is connected with the main control computer (101) and the signal conditioning and converting component (104) and is used for configuring and generating HB6096, RS422, discrete quantity, analog quantity and synchronizer quantity non-bus signals;
the signal monitoring component (103) is connected with the main control computer (101), the fault injection component (102) and the signal conditioning conversion component (104) and is used for monitoring and analyzing the non-bus interface communication data of the integrated avionics system;
the signal conditioning and converting component (104) is connected with the main control computer (101), the fault injection component (102) and the signal monitoring component (103) and is used for conditioning and switching signals of the comprehensive avionics system and non-bus injection signals.
2. The non-bus signal fault injection device applied to the integrated avionics system according to claim 1, wherein: the fault injection assembly (102) comprises a fault injection assembly box body, a fault injection assembly controller arranged in the fault injection assembly box body, an ARINC429 communication module, a serial port communication module, a discrete magnitude module, an analog voltage and current output module and a 2CH excitation/synchronizer module.
3. The non-bus signal fault injection device applied to the integrated avionics system according to claim 2, wherein: the fault injection assembly box body is in butt joint with the integrated avionics system and the signal conditioning and converting assembly (104) through an aerial plug connector, and the fault injection assembly controller is in communication connection with the main control computer (101).
4. The non-bus signal fault injection device applied to the integrated avionics system according to claim 2, characterized in that: the signal monitoring assembly (103) comprises a monitoring assembly box body, a monitoring assembly controller, a PXI synchronization module, an HB6096 interface card, a carrier card, an RS-422 bus interface card, a discrete quantity interface card and an analog quantity interface card, wherein the monitoring assembly controller, the PXI synchronization module, the HB6096 interface card, the carrier card, the RS-422 bus interface card, the discrete quantity interface card and the analog quantity interface card are arranged in the monitoring assembly box body.
5. The non-bus signal fault injection device applied to the integrated avionics system according to claim 4, characterized in that: the monitoring component box body is in butt joint with the comprehensive avionics system, the fault injection component box body and the signal conditioning conversion component (104) through an aviation plug connector, and the monitoring component controller is in communication connection with the main control computer (101).
6. The non-bus signal fault injection device applied to the integrated avionics system according to claim 4, characterized in that: the signal conditioning conversion assembly (104) comprises a conditioning assembly box body, a signal conditioning conversion controller and a matrix switch.
7. The non-bus signal fault injection device applied to the integrated avionics system according to claim 6, wherein: the conditioning component box body is in butt joint with the comprehensive avionics system, the fault injection component box body and the signal monitoring component box body through an aviation plug connector, and the signal conditioning conversion controller is in communication connection with the main control computer (101).
8. The non-bus signal fault injection method applied to the comprehensive avionics system is characterized by comprising the following steps of: the non-bus signal fault injection equipment applied to the integrated avionics system, which is disclosed by any one of claims 1 to 7, comprises the following specific steps:
step one, combining a cross-linking fault phenomenon to determine a fault signal injection requirement;
step two, configuring a module in the fault injection assembly (102) through a main control computer (101) and outputting a required non-bus signal;
step three, the signal monitoring component (103) monitors whether the output non-bus signal meets the requirement, if not, the output non-bus signal is fed back to the main control computer (101) to reconfigure parameters; if the requirements are met, the next step is carried out;
step four, the signal monitoring component (103) judges whether the equipment is accessed to a signal on a real machine of the integrated avionics system again, if the real signal is not accessed, the injected signal is output to the integrated avionics system, and fault injection is executed; if the real signal is accessed, the signal conditioning and converting component (104) is controlled to disconnect the real signal and then output an injection signal to the avionic system to execute fault injection;
step five, a signal monitoring component (103) monitors an injection signal received by the integrated avionics system and the output accuracy of a next-stage signal thereof, and if the output signal is accurate and the fault is reproduced, the fault injection process is ended; and if the inaccurate fault of the output signal does not reappear, feeding back to the main control computer (101) to execute the step (two) to the step (five) again.
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| CN202211662865.5A CN115964247A (en) | 2022-12-23 | 2022-12-23 | Non-bus signal fault injection equipment and method applied to integrated avionics system |
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| CN202211662865.5A CN115964247A (en) | 2022-12-23 | 2022-12-23 | Non-bus signal fault injection equipment and method applied to integrated avionics system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118068767A (en) * | 2024-04-19 | 2024-05-24 | 中国民航大学 | Automatic acquisition and injection device and method for G1000 avionics system data |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118068767A (en) * | 2024-04-19 | 2024-05-24 | 中国民航大学 | Automatic acquisition and injection device and method for G1000 avionics system data |
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