CN113867172B - Avionics system fault simulation verification platform and method - Google Patents

Abstract

The application relates to a fault simulation verification platform and method for an avionics system. The device comprises: the detection device is used for sending an interference signal to an input port of the target functional module and acquiring an actual feedback signal and a fault detection condition which are output by the target functional module after receiving the interference signal; the processor is used for judging that the performance to be verified of the target functional module meets the standard when the actual feedback signal and the fault detection condition corresponding to the interference signal are the same as the standard feedback signal and the fault detection condition corresponding to the interference signal; when the actual feedback signal and the fault detection condition corresponding to the interference signal are different from the standard feedback signal and the fault detection condition corresponding to the interference signal, judging that the performance to be verified of the target functional module does not reach the standard. Through the device, various interference signals possibly received by each function of the avionics system in the actual working process can be simulated, and then the fault diagnosis performance of each functional module can be verified.

Description

Avionics system fault simulation verification platform and method

technical field

The present application relates to the technical field of avionics, in particular to an avionics system failure simulation verification platform and method.

Background technique

With the development of avionics technology, the avionics system is becoming more and more advanced. Various electronic equipment of the aircraft are closely related to the avionics system. The performance of the avionics system determines the various performances of the aircraft. The fault diagnosis relationship of the avionics system to the reliability of the avionics system. Therefore, it is necessary to carry out fault simulation verification on the avionics system to ensure the reliable operation of the aircraft.

In the traditional technology, software simulation is combined with the actual operation of the aircraft to perform fault simulation verification on the avionics system.

However, it is inefficient to verify the fault diagnosis technology of the avionics system during the actual operation of the aircraft, and it is impossible to fully verify the performance of the fault diagnosis technology of the avionics system. At the same time, due to the large number of equipment in the avionics system and the complexity of various interference signals, there is a large gap between the software simulation technology and the actual operation of the avionics system.

Contents of the invention

Based on this, it is necessary to address the above technical problems and provide an avionics system failure simulation verification platform and method capable of simulating various interference signals to simulate and verify the real functional modules of the aircraft's avionics system.

An avionics system fault simulation verification platform, the avionics system includes a plurality of functional modules, the functional modules include at least one signal input port and at least one signal output port, the avionics system fault simulation verification platform includes: A device for sending an interference signal whose performance is to be verified to at least one signal input port of the target function module, and obtaining an actual feedback signal output by the target function module from at least one signal output port after receiving the interference signal, so The target function module is at least one of the plurality of function modules; a processor is configured to determine the target when the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal. The performance to be verified of the functional module meets the standard; when the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module does not meet the standard.

In one of the embodiments, the detection device includes: a signal excitation module, the input end of which is connected to the processor, for receiving the first instruction sent by the processor, and outputting the performance to be verified according to the first instruction The interference signal of the first matrix switch, the input terminal is connected to the output terminal of the signal excitation module, the output terminal is connected to the multiple signal input ports of the multiple functional modules, and the control terminal is connected to the processor; the The first matrix switch is used to receive the second instruction sent by the processor, and according to the second instruction, connect the output terminal of the signal excitation module with at least one signal input port of the target function module, so as to connect The interference signal is sent to at least one signal input port of the target function module.

In one of the embodiments, the detection device includes: a second matrix switch, the input terminal is connected to a plurality of signal output ports of the plurality of functional modules, and the control terminal is connected to the processor; the second matrix switch It is used to receive the third instruction sent by the processor, and according to the third instruction, connect at least one signal output port of the target function module with the output end of the second matrix switch; the signal acquisition module, input terminal is connected to the output terminal of the second matrix switch, the output terminal is connected to the processor, and is used to collect the actual feedback signal output by at least one signal output port of the target function module, and the collected actual feedback signal sent to the processor.

In one embodiment, the plurality of functional modules include at least one of an IMA processing module, a display module, a power supply module, an AFDX network switch, a flight management computer, a navigation computer, a radar module, and an entertainment module.

In one of the embodiments, at least one signal input port of the target function module includes multiple signal input ports with the same label in the functional modules, signal input ports with different labels in the multiple functional modules, one of the Any one of the signal input ports with different labels in the functional modules; the interference signals received by each of the signal input ports are the same or different.

In one embodiment, the interference signal includes at least one of a sine wave, a square wave, a sawtooth wave, and a random noise signal, and the voltage, current, and frequency of the interference signal can be adjusted.

In one of the embodiments, the processor is respectively connected to each of the functional modules, and is used to read the fault conditions of the functional modules.

In one of the embodiments, the working state of the functional module after receiving the interference signal includes one of the following modes: the functional module works normally; the functional module fails, and the output of the actual feedback The signal is the same as the standard feedback signal corresponding to the fault; the functional module fails, but the actual feedback signal output is different from the standard feedback signal corresponding to the fault; the functional module cannot work normally at all, but after restarting Functional; the functional module is completely non-functional and cannot be recovered.

In one of the embodiments, the processor is further configured to perform feature extraction on the actual feedback signal to obtain at least one signal feature, wherein the signal feature includes the amplitude and mean square of the actual feedback signal At least one of root, skewness, variance, maximum value, minimum value, frequency amplitude, envelope spectrum, power spectrum, frequency band energy, standard deviation, Crest factor, kurtosis, peak-to-peak value.

An avionics system failure simulation verification method, the method comprising:

Sending an interference signal whose performance is to be verified to at least one signal input port of the target function module, and obtaining an actual feedback signal output by the target function module from at least one signal output port after receiving the interference signal, the avionics system It includes a plurality of functional modules, the functional modules include a plurality of signal input ports and a plurality of signal output ports, and the target functional module is at least one of the plurality of functional modules;

If the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module meets the standard;

If the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module does not meet the standard.

The above avionics system failure simulation verification platform and method, by sending an interference signal to be verified performance to at least one signal input port of a target function module in a plurality of functional modules of the avionics system, and obtaining the target function module when receiving the interference signal Finally, the actual feedback signal output from at least one signal output port, and then compare the actual feedback signal with the standard feedback signal corresponding to the emitted interference signal, and when the actual feedback signal is the same as the standard feedback signal, it is determined that the performance of the target function module to be verified is up to standard ; When the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance of the target function module to be verified is not up to the standard. By selecting different functional modules, signal input ports and interference signals, various interference signals that each functional module of the avionics system may encounter in practice can be simulated. In this way, the avionics system is not installed on the aircraft, and each functional module can also show the response in various actual scenarios, which can ensure the accuracy of the avionics system fault diagnosis technology and reliability inspection results. Therefore, before the avionics system is installed on the aircraft, it is possible to quickly detect whether the various performances of the various functional modules of the avionics system are up to standard, and it is not necessary to wait for the aircraft to meet the actual situation before the inspection, which improves the inspection effect and can be simulated Compared with software simulation, the test results of various interference signals that various functional modules of the avionics system may encounter in practice are more comprehensive. Improve the reliability of the avionics system and reduce the cost of maintenance.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application or the conventional technology, the following will briefly introduce the accompanying drawings that need to be used in the description of the embodiments or the traditional technology. Obviously, the accompanying drawings in the following description are only the present invention For some embodiments of the application, those skilled in the art can also obtain other drawings based on these drawings without creative work.

Fig. 1 is the structural representation of avionics system failure simulation verification platform in an embodiment;

Fig. 2 is the structural representation of avionics system failure simulation verification platform in another embodiment;

Fig. 3 is a schematic flowchart of a method for simulating and verifying a fault of an avionics system in an embodiment.

Explanation of reference signs: 1-aviation system, 2-functional module, 10-detection device, 20-processor, 11-signal excitation module, 12-first matrix switch, 13-second matrix switch, 14-signal acquisition module.

Detailed ways

In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the relevant drawings. Embodiments of the application are given in the drawings. However, the present application can be embodied in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of this application more thorough and comprehensive.

Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terms used herein in the specification of the application are only for the purpose of describing specific embodiments, and are not intended to limit the application.

It can be understood that the terms "first", "second" and the like used in this application may be used to describe various elements herein, but these elements are not limited by these terms. These terms are only used to distinguish one element from another element.

It should be noted that when an element is considered to be "connected" to another element, it may be directly connected to the other element, or connected to the other element through an intervening element. In addition, "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 the connected objects.

When used herein, the singular forms "a", "an" and "the/the" may also include the plural forms unless the context clearly dictates otherwise. It should also be understood that the terms "comprising/comprising" or "having" etc. specify the presence of stated features, integers, steps, operations, components, parts or combinations thereof, but do not exclude the presence or addition of one or more The possibility of other features, integers, steps, operations, components, parts or combinations thereof.

As mentioned in the background technology, when performing simulation verification on the avionics system in the prior art, it is necessary to test the avionics system of the aircraft on the actual aircraft, and for the functional modules in the avionics system in the face of small probability occurrence The various situations that may occur when the signal is interfered cannot be fully detected. The inventors have found that the reason for this problem is that there is currently a lack of a method that can simulate the various functional modules of the real aircraft's avionics system. Various interference signals, so as to be able to verify the fault simulation verification platform of the performance of various functional modules in the face of various interference signals.

Based on the above reasons, the present invention provides an avionics system failure simulation verification platform and method capable of simulating various interference signals to simulate and verify the real functional modules of the aircraft avionics system.

In one embodiment, as shown in FIG. 1 , an avionics system failure simulation verification platform is provided. The avionics system 1 includes a plurality of functional modules 2, and the functional modules 2 include at least one signal input port and at least one signal output port. , the device includes: a detection device 10 and a processor 20. The detection device 10 is used to send an interference signal whose performance is to be verified to at least one signal input port of the target functional module, and obtain an actual feedback signal output by the target functional module from at least one signal output port after receiving the interference signal, and the target functional module It is at least one of the plurality of functional modules 2. The processor 20 is configured to determine that the performance of the target functional module is up to standard when the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal; when the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal When the signals are different, it is determined that the performance to be verified of the target functional module is not up to standard.

In this embodiment, by sending an interference signal whose performance is to be verified to at least one signal input port of a target function module in a plurality of functional modules of the avionics system, and obtaining the target function module from at least one signal after receiving the interference signal The actual feedback signal output by the output port, and then compare the actual feedback signal with the standard feedback signal corresponding to the transmitted interference signal. When the actual feedback signal is the same as the standard feedback signal, it is determined that the performance of the target functional module is up to standard; When the actual feedback signal of the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance of the target function module to be verified is not up to the standard. By selecting different functional modules, signal input ports and interference signals, various interference signals that each functional module of the avionics system may encounter in practice can be simulated. In this way, the avionics system is not installed on the aircraft, and each functional module can also show the response in various actual scenarios, which can ensure the accuracy of the performance test results. Therefore, before the avionics system is installed on the aircraft, it is possible to check whether the various performances of the various functional modules of the avionics system are up to standard, and it is not necessary to wait for the actual situation of the aircraft to be inspected, which improves the effect of the inspection, and can simulate the avionics The various interference signals that each functional module of the system may encounter in practice are more comprehensive than those simulated by software. Improve the reliability of the avionics system and reduce the cost of maintenance.

Exemplarily, the processor 20 may be a central processing unit (Central Processing Unit, CPU), and may also be other general-purpose processors, a digital signal processor (Digital Signal Processor, DSP), an application specific integrated circuit (Application Specific Integrated Circuit, ASIC) , one of off-the-shelf programmable gate arrays (Field-Programmable Gate Array, FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, and the like. A general purpose processor can be a microprocessor or any conventional processor.

Exemplarily, the functional module 2 includes at least one of an IMA processing module, a display module, a power supply module, an AFDX network switch, a flight management computer, a navigation computer, a radar module, and an entertainment module.

Exemplarily, at least one signal input port of the functional module 2 includes signal input ports with the same label in multiple functional modules 2, signal input ports with different labels in multiple functional modules 2, and signal input ports with different labels in one functional module 2. Any one of the ports; the interference signals received by each signal input port are the same or different.

Exemplarily, at least one signal output port of the functional module 2 includes signal output ports with the same label in multiple functional modules 2, signal output ports with different labels in multiple functional modules 2, and signal output ports with different labels in one functional module 2. any kind of mouth. The interference signals received by each signal output port are the same or different.

Specifically, each signal input port and each signal output port of each functional module are labeled in order from left to right according to the actual positions of the signal input ports and signal output ports on the functional module, so as to facilitate Distinguish different signal input ports and different signal output ports of the functional modules. In addition, they can also be labeled according to different types or corresponding functions of the signal input ports and signal output ports of each functional module. The specific labeling method is not fixed. It only needs to be able to distinguish different signal input ports and different signal output ports of the functional modules.

Exemplarily, the interference signal includes at least one of a sine wave, a square wave, a sawtooth wave, and a random noise signal, and the voltage, current, and frequency of the interference signal can be adjusted.

Specifically, the processor 20 is respectively connected to each functional module 2, and is used to read the fault condition of the functional module 2, and can detect the fault of the functional module.

Specifically, the interference signal is used to simulate various real situations that each functional module may encounter during operation. For example, during the actual flight of an aircraft, electromagnetic interference may be encountered, and electromagnetic interference may appear in any position of any functional module of the avionics system, so the interference signal in this application can be sent to each component of the avionics system. The different signal input ports of the functional modules can better simulate the real situation of the actual aircraft encountering electromagnetic interference. Or, during the actual flight of the aircraft, a lightning strike may be encountered, and the lightning strike will generate a surge signal, which may cause a high voltage and large current at the power input terminal of the avionics system, so the interference signal in this application can also be The high-voltage and high-current signal sent to the power input terminal of the avionics system is used to simulate the real situation of the aircraft encountering lightning strikes during actual flight.

Specifically, after the functional module 2 receives different frequencies, different amplitudes, and different types of interference signals, the working state of the functional module will be affected by the interference signal and change. The working state of the functional module includes one of the following methods: function Module 2 works normally; Function module 2 fails, and the actual output feedback signal is the same as the standard feedback signal corresponding to the failure; Function module 2 fails, but the actual output feedback signal is different from the standard feedback signal corresponding to the failure; Function module 2 It doesn't work at all, but it works after restarting; function module 2 doesn't work at all, and it can't be recovered.

Exemplarily, the relationship between functional modules, interference signals and verification results is shown in the following table.

Table 1. Response comparison table corresponding to interference signal strength and functional modules:

In one embodiment, as shown in FIG. 2 , the detection device 10 includes: a signal excitation module 11 and a first matrix switch 12 . The signal excitation module 11 is connected to the processor 20 at the input end, and is used for receiving the first instruction sent by the processor 20, and outputting the interference signal of the performance to be verified according to the first instruction. The first matrix switch 12, the input end is connected with the output end of the signal excitation module 11, the output end is connected with a plurality of signal input ports of a plurality of functional modules 2, and the control end is connected with the processor 20; the first matrix switch 12 is used for receiving The second instruction sent by the processor 20, and according to the second instruction, the output end of the signal excitation module 11 is communicated with at least one signal input port of the target function module, so as to send the interference signal to at least one signal input port of the target function module .

In this embodiment, through the signal excitation module, various interference signals can be sent to each functional module according to the instructions of the processor, corresponding to the various interferences that each functional module may receive during the actual flight of the aircraft. Signals, so that various interference signals that the functional modules may encounter during actual use can be simulated, and various performances to be verified of the functional modules can be verified. The first matrix switch can connect the output end of the signal excitation module with at least one signal input port of the functional module according to the instructions of the processor, so that the interference signal sent by the signal excitation module can reach any signal input port of the functional module, thereby It can verify the situation after different signal input ports of different functional modules receive interference signals.

Exemplarily, the signal excitation module 11 may be an AWG5200 arbitrary waveform generator of Tektronix, or a PXI-6363/PXI-5422 signal generator board of NI.

Exemplarily, the first matrix switch 12 may be a PXI-2532B matrix switch board of National Instruments.

In one embodiment, as shown in FIG. 2 , the detection device 10 includes: a second matrix switch 13 and a signal acquisition module 14 . The second matrix switch 13, the input end is connected with a plurality of signal output ports of a plurality of functional modules 2, and the control end is connected with the processor 20; the second matrix switch 13 is used to receive the third instruction sent by the processor 20, and according to the first Three instructions, collecting the actual feedback signal output by at least one signal output port of the target function module. The signal acquisition module 14 has an input end connected to the output end of the second matrix switch 13 and an output end connected to the processor 20 , for sending the collected actual feedback signal to the processor 20 .

In this embodiment, through the second matrix switch, the actual feedback signal output by at least one signal output port of the functional module can be collected according to the instruction of the processor, so that the signal output by any signal output port of any functional module can be obtained. . The actual feedback signal collected is sent to the processor through the signal collection module, so that feedback signals output by different signal output ports of different functional modules can be obtained. Furthermore, different performances to be verified of different functional modules can be verified.

Specifically, a fault diagnosis model is preset in the processor, including standard feedback signals corresponding to various interference signals and corresponding fault results, and the actual feedback signals corresponding to the interference signals can be compared and analyzed with the corresponding standard feedback signals.

Exemplarily, the second matrix switch 13 may be a PXI-2532B matrix switch board of National Instruments.

Exemplarily, the signal acquisition module 14 can be the PXI-6363 oscilloscope module of NI Company, or the PXI-5922 oscilloscope module, or use ADC (analog to digital converter, analog to digital converter), MCU (Microcontroller Unit, micro control unit) , FPGA (Field Programmable Gate Array, Field Programmable Logic Gate Array) combined module capable of collecting signals.

Specifically, when different interference signals are input to different signal input ports of different functional modules, different feedback signals and different faults will be generated. There is not a one-to-one correspondence between interference signals, feedback signals, and faults, and multiple signal inputs may The input of the same or different interference signals will generate a feedback signal and fault, and it is also possible that a signal input port input interference signal will generate multiple feedback signals and multiple faults, or different signal input ports may input the same/different interference signals Will produce the same feedback signal, fault.

For example, different locations where the CPU module can input interference signals include power supply terminals and data signal input terminals. When the power supply terminal of the CPU module receives an interference signal, the entire CPU module may fail to work, and when the data signal input terminal of the CPU module receives an interference signal, it may cause a certain data error, while other parts can still work normally . Therefore, the same interference signal input to different positions of the same module may produce different effects.

Specifically, different signal input ports and different signal output ports of a functional module represent different network points of the functional module. For example, there are thousands of network points inside the IMA processing module, and different signal input ports and different signal output ports are the Different network points inside.

Exemplarily, when the performance to be verified is a fault diagnosis algorithm or model, the voltage, current, and frequency of the interference signal can be adjusted. In this way, the working state of the function module can be controlled according to the algorithm to be verified, so that the function module works under the working conditions corresponding to the algorithm to be verified, and then it is detected whether the actual feedback signal output by the function module is the same as the standard feedback signal corresponding to the algorithm/model to be verified , to realize the verification of whether the algorithm/model to be verified is correct.

For example, when verifying the fault diagnosis model of the processor module, if a sine wave with a frequency of 1kHz and a voltage of 2V is input to the CPU chip clock pin of the processor module, the CPU will not work normally under this condition, and all output ports The voltage is 0V. If it is detected that all output port voltages of the functional module are 0V, it is determined that the fault diagnosis function to be verified is correct. If it is detected that the output voltage of the functional module is not 0V or there are other signal outputs, it is determined that the fault diagnosis function to be verified is wrong. Stop injecting the interference signal to the CPU chip clock pin of the processor module, restart the processor module, if the processor module can work normally, then judge that the processor module is qualified, otherwise judge that the reliability of the processor module is unqualified.

In one embodiment, the processor 20 is further configured to perform feature extraction on the actual feedback signal to obtain at least one signal feature, wherein the signal feature includes the amplitude, root mean square, skewness, variance, At least one of maximum value, minimum value, frequency amplitude, envelope spectrum, power spectrum, frequency band energy, standard deviation, Crest factor, kurtosis, and peak-to-peak value.

Specifically, feature extraction is to select the signal features that best represent the state of the system, such as a vibration signal, including amplitude, root mean square, skewness, variance, maximum value, minimum value, frequency amplitude, envelope spectrum , power spectrum, frequency band energy, etc. dozens of characteristic parameters, as well as electrical signals, speed, temperature, etc.; and different fault modes can be reflected in different characteristic parameters (combinations), this step is to select the most relevant fault Combination of characteristic parameters. Once a fault occurs or is forming, these characteristic parameter combinations will "change" to a certain extent. Condition monitoring is usually configured together with feature extraction. Poor monitoring, etc. Similarly, there are many feature extraction methods. Users can configure specific feature extraction methods according to specific needs, or configure multiple feature extraction methods in parallel at one time for comparison or fusion. The most relevant feature parameters, for example, when the user is doing PHM configuration of a new object that he does not understand, he needs to explore and compare, select the optimal feature extraction method through parallel connection, or the user understands the failure mechanism of the hardware device to be tested, Once you know which feature parameters to extract, you can configure multiple feature extraction methods in parallel to obtain feature parameters in various aspects for subsequent processing to obtain results at different levels and jointly support the final result.

In this embodiment, by extracting the features of the actual feedback signal and recording the signal features, the actual feedback signals sent by the functional modules after receiving different interference signals can be counted, which is convenient for analyzing the verification results of the functional modules and facilitating Display the corresponding feedback signal when the functional module receives different interference signals. It enables the staff to obtain various performances of the functional modules.

In one embodiment, as shown in FIG. 3 , a method for simulation and verification of a fault in an avionics system is provided, the method comprising:

Step S100, sending an interference signal whose performance is to be verified to at least one signal input port of the target functional module, and obtaining an actual feedback signal output by the target functional module from at least one signal output port after receiving the interference signal. The avionics system includes multiple functional modules, the functional modules include multiple signal input ports and multiple signal output ports, and the target functional module is at least one of the multiple functional modules.

Specifically, the fault condition of the target functional module is also obtained, and according to whether the actual feedback signal output by the target functional module corresponds to the actual fault of the target functional module, it is judged whether the fault handling of the functional module is qualified.

Step S110, if the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal, then it is determined that the performance to be verified of the target functional module meets the standard.

Step S120, if the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module does not meet the standard.

In this embodiment, by sending an interference signal whose performance is to be verified to at least one signal input port of a target function module in a plurality of functional modules of the avionics system, and obtaining the target function module from at least one signal after receiving the interference signal The actual feedback signal output by the output port and the actual fault of the target function module, and then compare the actual feedback signal with the standard feedback signal and standard fault corresponding to the emitted interference signal, when the actual feedback signal is the same as the standard feedback signal and standard fault, Determine that the performance to be verified of the target functional module is up to the standard; when the actual feedback signal corresponding to the interference signal is different from the standard feedback signal or standard fault corresponding to the interference signal, it is determined that the performance to be verified of the target functional module is not up to the standard. In this way, it can be detected whether the various performances of each module of the avionics system are up to standard, and the avionics system uses real avionics system modules, so that the results of the simulation verification are the same as the real results, so that when it is necessary to verify the performance of the avionics system, it is not necessary to It is necessary to go to the actual aircraft for verification, but use the system of this application for verification, which improves the efficiency of verification, makes it more convenient to simulate and verify the avionics system, improves the reliability of the avionics system, and reduces maintenance costs. .

It should be understood that although the various steps in the flow chart of FIG. 3 are displayed sequentially as indicated by the arrows, these steps are not necessarily executed sequentially in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order restriction on the execution of these steps, and these steps can be executed in other orders. Moreover, at least some of the steps in FIG. 3 may include multiple steps or stages. These steps or stages are not necessarily executed at the same time, but may be executed at different times. The execution sequence of these steps or stages is also It is not necessarily performed sequentially, but may be performed alternately or alternately with other steps or at least a part of steps or stages in other steps.

Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above-mentioned embodiments can be completed by instructing related hardware through computer programs, and the computer programs can be stored in a non-volatile computer-readable memory In the medium, when the computer program is executed, it may include the processes of the embodiments of the above-mentioned methods. Wherein, any references to memory, storage, database or other media used in the various embodiments provided in the present application may include at least one of non-volatile memory and volatile memory. The non-volatile memory may include read-only memory (Read-Only Memory, ROM), magnetic tape, floppy disk, flash memory or optical memory, and the like. Volatile memory may include random access memory (Random Access Memory, RAM) or external cache memory. By way of illustration and not limitation, RAM can be in various forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM).

In the description of this specification, descriptions referring to the terms "some embodiments", "other embodiments", "ideal embodiments" and the like mean that specific features, structures, materials, or characteristics described in connection with the embodiments or examples are included in this specification. In at least one embodiment or example of the invention. 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 can be combined arbitrarily. To make the description concise, all possible combinations of the technical features in the above embodiments are not described. However, as long as there is no contradiction in the combination of these technical features, they should be It is considered to be within the range described in this specification.

The above-mentioned embodiments only represent several implementation modes of the present application, and the description thereof is relatively specific and detailed, but it should not be construed as limiting the scope of the patent for the invention. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the scope of protection of the patent application should be based on the appended claims.

Claims (10)

1. A kind of avionics system failure simulation verification platform, it is characterized in that, described avionics system (1) comprises a plurality of functional modules (2), and described functional module (2) comprises at least one signal input port and at least one signal Output port, described avionics system failure simulation verification platform includes processor (20), also includes: A signal excitation module (11), the input end of which is connected to the processor (20), is used to receive the first instruction sent by the processor (20), and output an interference signal of performance to be verified according to the first instruction; The first matrix switch (12), the input end is connected to the output end of the signal excitation module (11), the output end is connected to a plurality of signal input ports of the plurality of functional modules (2), and the control end is connected to the processing The device (20) is connected; the first matrix switch (12) is used to receive the second instruction sent by the processor (20), and according to the second instruction, the output of the signal excitation module (11) The terminal communicates with at least one signal input port of the target functional module, so as to send the interference signal to at least one signal input port of the target functional module; The second matrix switch (13), the input terminal is connected with a plurality of signal output ports of the described plurality of functional modules (2), and the control terminal is connected with the processor (20); the second matrix switch (13) is used receiving the third instruction sent by the processor (20), and according to the third instruction, connecting at least one signal output port of the target function module with the output end of the second matrix switch (13); Signal acquisition module (14), input end is connected with the output end of described second matrix switch (13), and output end is connected with described processor (20), is used to collect at least one signal output port of described target function module output the actual feedback signal, and send the collected actual feedback signal to the processor (20); A fault diagnosis model is preset in the processor (20), wherein the fault diagnosis model includes correspondences between various interference signals and standard feedback signals; The processor (20) is configured to determine a corresponding standard feedback signal according to the interference signal and the fault diagnosis model, when the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal At the same time, determine that the performance to be verified of the target functional module is up to standard; when the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, determine the performance to be verified of the target functional module Not up to standard, the performance to be verified includes fault diagnosis performance. 2. avionics system fault simulation verification platform according to claim 1, is characterized in that, described multiple functional modules (2) comprise IMA processing module, display module, power supply module, AFDX network switchboard, flight management computer, navigation At least one of computer, radar module and entertainment module. 3. avionics system fault simulation verification platform according to claim 1, is characterized in that, at least one signal input port of described target function module comprises the identical signal input port of label in a plurality of described function modules (2), Any one of signal input ports with different labels in multiple functional modules (2), and signal input ports with different labels in one functional module (2); the interference signals received by each of the signal input ports are the same or different . 4. avionics system fault simulation verification platform according to claim 1, is characterized in that, described interference signal comprises at least one in sine wave, square wave, sawtooth wave, random noise signal, the voltage of described interference signal , Current and frequency can be adjusted. 5. avionics system fault simulation verification platform according to claim 1, is characterized in that, described processor (20) is connected with each described function module (2) respectively, is used for reading described function module (2) ) failure conditions. 6. avionics system failure simulation verification platform according to claim 1, is characterized in that, the working state after described functional module (2) receives described interference signal comprises a kind of in the following ways: The functional module (2) works normally; The functional module (2) fails, and the actual feedback signal output is the same as the standard feedback signal corresponding to the failure; The functional module (2) fails, but the actual feedback signal output is different from the standard feedback signal corresponding to the failure; The functional module (2) cannot work normally at all, but can work normally after restarting; The functional module (2) cannot work normally at all and cannot be restored. 7. The avionics system failure simulation verification platform according to claim 6, characterized in that, the processor (20) is also used for failing to reach a fault detection threshold when the strength of the interference signal, and the functional module (2) In the case of normal operation, it is determined that the functional module (2) meets the requirements. 8. The avionics system failure simulation and verification platform according to claim 6, wherein the processor (20) is also used for failing to reach a fault detection threshold when the strength of the interference signal, and the functional module (2) When a fault is detected, it is determined that the functional module (2) has detected a fault by mistake. 9. avionics system fault simulation verification platform according to claim 1, is characterized in that, described processor (20) is also used for, Performing feature extraction on the actual feedback signal to obtain at least one signal feature, wherein the signal feature includes the amplitude, root mean square, skewness, variance, maximum value, minimum value, and frequency of the actual feedback signal At least one of amplitude, envelope spectrum, power spectrum, band energy, standard deviation, Crest factor, kurtosis, and peak-to-peak value. 10. An avionics system failure simulation verification method, characterized in that it is applied to the avionics system failure simulation verification platform as claimed in any one of claims 1-9, said method comprising: Sending an interference signal whose performance is to be verified to at least one signal input port of the target function module, and obtaining an actual feedback signal output by the target function module from at least one signal output port after receiving the interference signal, the avionics system It includes a plurality of functional modules, the functional modules include a plurality of signal input ports and a plurality of signal output ports, and the target functional module is at least one of the plurality of functional modules; If the actual feedback signal corresponding to the interference signal is the same as the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module meets the standard; If the actual feedback signal corresponding to the interference signal is different from the standard feedback signal corresponding to the interference signal, it is determined that the performance to be verified of the target functional module is not up to standard, and the performance to be verified includes fault diagnosis performance.