Aviation disconnection test system and method based on switch array virtualization reconstruction

Abstract

The invention discloses an aviation disconnection test system and method based on switch array virtualization reconstruction. The hardware circuit module comprises PXI equipment, a signal adapter and a signal tester; a case connection card, a single-pole single-throw switch card and a matrix switch card are integrated in the PXI equipment; the PXI equipment is connected with the control card of the server module through the case connection card; all test signals needing to be subjected to wire breaking, measurement and fly wire testing enter from the signal adapter, flow through the corresponding single-pole single-throw switch cards, then are connected to column wires of the matrix switch card in parallel and then are output from the signal adapter; the signal tester is connected to a row line of a matrix switch card in the PXI equipment through the signal adapter; and the server module is also respectively connected with the signal tester and the master control module. According to the invention, the reutilization of hardware resources is realized, the test efficiency is improved, the limitation of test sites is broken through, and remote test control is realized.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aviation test technology, and particularly relates to an aviation disconnection test system and method based on switch array virtualization reconstruction. BACKGROUND

[0002] In the field of aviation test, the aviation disconnection test system is a key infrastructure, mainly used for aircraft system test, airborne equipment verification and ground test bench construction. The aviation disconnection test system mainly includes the following functions:

[0003] 1) Fault injection and safety isolation, by manually plugging in and out the disconnection block, artificially creating fault scenarios such as disconnection, short circuit, signal interference, verifying the fault tolerance of the aircraft system;

[0004] 2) Signal excitation and measurement, connecting the test equipment (such as digital multimeter, signal generator) with airborne equipment through standardized interface, realizing signal characteristic test and command simulation of resistance, voltage, etc.

[0005] The traditional aviation disconnection test system adopts standard structure design and modular layout, and multiple sets of disconnection blocks are installed side by side on the front panel of the box body, as shown in FIG. Figure 1 The aviation connector is installed on the rear panel of the box body, and connected with the airborne equipment through the aviation test cable.

[0006] The traditional aviation disconnection test system has the following defects:

[0007] 1) Special customization, different airborne equipment (measured object) needs to develop different disconnection test systems due to different signal quantity, signal type and signal definition;

[0008] 2) Low test efficiency, the test personnel need to manually plug in and out the disconnection block, and measure resistance, voltage, etc. with a digital multimeter, and because the number of signals to be measured is large, the repeated operation of plugging in and out the disconnection block will consume a lot of test time;

[0009] 3) Limited use location, the test personnel must operate in front of the disconnection test system, which cannot meet the needs of some high-risk test projects and hazardous test environment. SUMMARY

[0010] The purpose of the present application is to provide an aviation disconnection test system and method based on switch array virtualization reconstruction. The present application realizes the reusability of hardware resources, improves the test efficiency, breaks the test location restriction, and realizes remote test control.

[0011] The technical scheme of the present application is: an aviation broken line test system based on switch array virtualization reconstruction, comprising: a hardware circuit module, a server module, and a master control module; the hardware circuit module comprises a PXI device, a signal adapter, and a signal tester; the PXI device is integrated with a case connection card, a single-pole single-throw switch card, and a matrix switch card; the PXI device is connected with the control card of the server module through the case connection card; each test signal that needs to be tested for broken line, measurement, and flying line is input from the signal adapter, flows through the corresponding single-pole single-throw switch card, and then is connected in parallel to the column line of the matrix switch card, and then is output from the signal adapter; the signal tester is connected to the row line of the matrix switch card in the PXI device through the signal adapter; the server module is also connected with the signal tester and the master control module.

[0012] In the foregoing aviation broken line test system based on switch array virtualization reconstruction, the server module is used to receive the instructions of the master control module, control the on / off of the corresponding switches in the PXI device, and control the working mode of the signal tester, and upload the test results to the master control module.

[0013] In the foregoing aviation broken line test system based on switch array virtualization reconstruction, after the server module defines all the hardware resources as a “resource ICD” file, the server module receives the instructions sent by the master control module and controls the specific hardware based on the “resource ICD” file.

[0014] In the foregoing aviation broken line test system based on switch array virtualization reconstruction, the master control module adopts a platform design and a single-client architecture, and in the technical implementation, a.NET-based technical architecture is adopted, which contains an architecture supporting business management and data processing and display.

[0015] In the foregoing aviation broken line test system based on switch array virtualization reconstruction, the master control module comprises the following functional units:

[0016] A main interface automatic generation unit: the signal name of the test signal and the switch array resource corresponding to the signal are described through a configuration file, and then the main interface is automatically generated based on the configuration file;

[0017] An operation mode switching unit: three operation modes are designed: viewing, broken line, and lead line; in the viewing mode, the signal name, the bound switch number, and the card number of the selected broken line block on the main interface can be viewed; in the broken line mode, the selected broken line block is disconnected, and the selected broken line block is restored again; in the lead line mode, the selected broken line block is connected to the high end and the low end of the signal tester through the shortcut keys;

[0018] An instrument control unit: used for integrating the function of the digital meter in the control panel.

[0019] The aforementioned aviation break-line test system based on switch array virtualization reconstruction, the master control end module further comprises the following functional units:

[0020] An impedance calibration unit is configured to calibrate a signal line that needs to be tested for impedance and save the impedance value on the device line to a configuration file.

[0021] A safety assurance unit is configured to ensure that only one switch on the row line of the matrix switch card is closed to prevent signal short circuit.

[0022] A fast search unit is configured to search for the break-line block to be operated through the signal name.

[0023] A test method based on the aforementioned aviation break-line test system based on switch array virtualization reconstruction is provided, in which two single-pole single-throw switches are connected in series between the high-end loop and the low-end loop of the test signal, the common end of the two switches on the high-end loop is connected to one column line of the matrix switch card, and the common end of the two switches on the low-end loop is connected to another column line. Correspondingly, the high end and the low end of the signal tester are connected to two row lines of the matrix switch card. In the initial state, all switches on the high-end loop and the low-end loop are closed, and all matrix switches are disconnected. When the test signal is measured, the single-pole single-throw switches between the high-end loop inlet end and the corresponding common end and between the low-end loop inlet end and the corresponding common end are closed, the single-pole single-throw switches between the high-end loop outlet end and the corresponding common end and between the low-end loop outlet end and the corresponding common end are disconnected, and the row line of the matrix switch card connected to the signal tester and the matrix switch at the intersection of the column line of the matrix switch card connected to the high-end loop and the low-end loop are closed. Finally, the high end and the low end of the test signal are connected to the high end and the low end of the signal tester, respectively, and the measurement range of the signal tester is switched by the master control end module, and the test result is read.

[0024] In the test method of the aforementioned aviation break-line test system based on switch array virtualization reconstruction, the disconnection method of the single-pole single-throw switch is as follows: the operating mode switching unit is switched to the break-line mode; the single-pole single-throw switch indicated by the break-line block corresponding to the high end and the low end of the test signal on the main interface is switched to the disconnected state.

[0025] In the test method of the aforementioned aviation break-line test system based on switch array virtualization reconstruction, the closing method of the matrix switch card is as follows: the operating mode switching unit is switched to the lead-in mode; the break-line block corresponding to the high end and the low end of the test signal is selected on the main interface, and the high end and the low end of the selected signal tester are connected through the shortcut keys.

[0026] In the test method of the aforementioned aviation break-line test system based on switch array virtualization reconstruction, the measurement range of the signal tester is switched as follows: the test function option of the signal tester is selected in the instrument control unit of the main interface for testing.

[0027] The application has the advantages that in the application, the tester can remotely perform the test through the master module, and the needs of some high-risk test projects and hazardous test environments can be met.

[0028] The application realizes the reconfiguration of the virtual break test system through the platform design of the master module, and has strong adaptability and expansibility.

[0029] The application improves the test efficiency, the test result is more accurate, and the safety of the airborne product and the test equipment is ensured.

[0030] In summary, the application realizes the reusability of the hardware resources, improves the test efficiency, breaks the test location restriction, and realizes the remote test control. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 It is a schematic diagram of an aviation break test system;

[0032] Figure 2 It is a hardware composition wiring diagram of a virtual break test system;

[0033] Figure 3 It is a hardware circuit module wiring design;

[0034] Figure 4 It is a system architecture diagram

[0035] Figure 5 It is a master module interface schematic diagram;

[0036] Figure 6 It is a master module search function schematic diagram;

[0037] Figure 7 It is a master module configuration file schematic diagram;

[0038] Figure 8 It is another hardware circuit module wiring design. DETAILED DESCRIPTION

[0039] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0040] Embodiment 1: An aviation break test system based on switch array virtualization reconfiguration, referring to Figures 1-8The system includes: a hardware circuit module, a server module, and a main control module. The hardware circuit module includes a PXI device, a signal adapter, and a signal tester. The PXI device integrates a chassis connection card, a single-pole single-throw switch card, and a matrix switch card. The PXI device connects to the control card of the server module via the chassis connection card. Test signals requiring disconnection, measurement, or flying wire testing enter through the signal adapter, flow through the corresponding single-pole single-throw switch card, are then connected in parallel to the column lines of the matrix switch card, and are output from the signal adapter. The signal tester connects to the row lines of the matrix switch card in the PXI device via the signal adapter. The server module is also connected to both the signal tester and the main control module. Specifically, the signal tester can be a digital multimeter. The aforementioned server module is used to receive instructions from the main control module, control the corresponding switches in the PXI device to be turned on / off, and control the working mode of the signal tester, and upload the test results to the main control module.

[0041] The aforementioned server module is used to receive instructions from the main control module, control the corresponding switches in the PXI device to be turned on / off, and control the working mode of the signal tester, and upload the test results to the main control module.

[0042] The aforementioned server module defines all hardware resources as "resource ICD" files, then receives instructions sent by the master control module via TCP / IP protocol, and controls specific hardware based on the "resource ICD" files. (See [link to relevant documentation]). Figure 4 This design eliminates the need for the main control unit to directly operate hardware such as matrix switch cards and digital multimeters, and it no longer needs to be deployed near the hardware system. Test personnel can conduct tests remotely through the main control unit module, meeting the needs of some high-risk test projects and tests in hazardous environments.

[0043] The aforementioned main control module adopts a platform-based design and a single-client architecture. Technically, it utilizes a .NET-based architecture, including structures supporting business management and data processing display. This method offers excellent operability and visualization, satisfying the operational habits of testers operating the disconnection test system and simplifying operation to the greatest extent possible. The main interface is as follows: Figure 5 As shown.

[0044] The aforementioned main control module includes the following functional units:

[0045] The main interface is automatically generated by describing the signal name and corresponding switch array resources of the test signal through a configuration file. The main interface is then automatically generated based on this configuration file. The number, color, and signal definition of the disconnection blocks on the main interface can all be modified through the configuration file. The main interface can be zoomed in and out and dragged in any direction, maximizing the replication of the layout design of a realistic disconnection test system. Through this platform-based design, the virtual disconnection test system becomes reconfigurable, possessing strong adaptability and scalability.

[0046] The operation mode switching unit is designed with three operation modes: viewing, disconnecting and leading. In the viewing mode, selecting the disconnecting block on the main interface can view the signal name, bound switch number and card number of the disconnecting block. In the disconnecting mode, selecting the disconnecting block can disconnect the disconnecting block, and selecting the disconnecting block again can restore it. In the leading mode, selecting the disconnecting block and using the shortcut keys F1 and F2 can connect the high end and the low end of the signal tester, respectively. The all-disconnect and all-pass functions are designed, and the test personnel can disconnect all the disconnecting blocks at one click, test the signals on the left side or the right side of the disconnecting blocks, and close all the disconnecting blocks at one click after the test, thereby improving the test efficiency.

[0047] The instrument control unit is used to integrate the function of the multimeter in the control panel, including resistance, direct current voltage, alternating current voltage, frequency and current test, and the test results are displayed on the interface intuitively.

[0048] In addition to the basic functions, the master control module also includes the following functional units to ensure the safety, accuracy and efficiency of the test:

[0049] The impedance calibration unit is used to calibrate the signal line that needs to be tested for impedance and save the impedance value on the device line to the configuration file.

[0050] Since the switch is added to the test line, an additional impedance value is introduced. To solve this problem, the signal line that needs to be tested for impedance is calibrated before the device is put into use, and the impedance value on the device line is saved to the configuration file. The system will subtract the corresponding calibration impedance from the test result when testing the signal resistance each time, so as to obtain the real resistance value of the airborne device and the cable, making the test result more accurate.

[0051] The safety guarantee unit is used to ensure that only one switch on the row line of the matrix switch card can be closed to prevent signal short circuit. When measuring resistance with a digital multimeter, it is necessary to ensure that the finished product is not powered on, otherwise the digital multimeter or the airborne device may be burned out. When switching to resistance measurement on the system, the system will pop up a prompt to remind the test personnel to ensure that there is no power on. This function ensures the safety of the airborne product and the test equipment.

[0052] The fast search unit is used to search for the disconnecting block to be operated through the signal name. In order to efficiently and quickly select the disconnecting block to be operated, a search function is designed, which can search for the disconnecting block according to the signal name. After selecting the signal name, the corresponding disconnecting block will be automatically displayed in the center and highlighted, as shown in FIG. 8, thereby improving the test efficiency. Figure 6

[0053] The test method of the aforementioned aviation disconnecting test system based on virtualization reconstruction of the switch array is characterized in that,

[0054] ​In the high-end loop and low-end loop of the test signal, two single-pole single-throw switches are connected in series, the common end of the two switches in the high-end loop is connected to a column line of the matrix switch card, and the common end of the two switches in the low-end loop is connected to another column line; correspondingly, the high end and the low end of the signal tester are connected to two row lines of the matrix switch card; in the initial state, all the switches in the high-end loop and the low-end loop are closed, and all the matrix switches are disconnected; when the test signal is input, the single-pole single-throw switches between the input end and the corresponding common end in the high-end loop and the low-end loop are closed, the single-pole single-throw switches between the output end and the corresponding common end in the high-end loop and the low-end loop are disconnected, and the row line of the matrix switch card connected to the signal tester and the matrix switch at the intersection of the column line connected to the high-end loop and the low-end loop are closed; finally, the high end and the low end of the test signal input are connected to the high end and the low end of the signal tester respectively, and the measurement gear of the signal tester is switched through the main control module, and the test result is read.

[0055] The disconnection method of the single-pole single-throw switch is as follows: the disconnection mode is switched through the operation mode switching unit; the single-pole single-throw switch marked by the disconnection block corresponding to the high end and the low end of the test signal is switched to the disconnected state by clicking on the disconnection block in the main interface.

[0056] The closing method of the matrix switch card is as follows: the lead-in mode is switched through the operation mode switching unit; the high end and the low end of the signal tester selected in the main interface are connected through the shortcut keys.

[0057] The measurement gear of the signal tester is switched as follows: the test function option of the signal tester is selected in the instrument control unit of the main interface for testing.

[0058] Taking the pilot control interface unit of the flight control system as an example, the specific implementation steps are as follows.

[0059] Firstly, according to the test requirements, the signal connection and circuit diagram of the disconnection test system are designed to realize the operations of disconnection, measurement and lead-in on the disconnection test system without affecting the original signal loop, and the virtual disconnection test system signal connection relationship is as shown in Figure 3 Two single-pole single-throw switches are connected in series between the signal loops, and the two switches are connected in parallel to the column line of the matrix switch card, and the high end and the low end of the digital multimeter are connected to the row line of the matrix switch card. Under normal circumstances, the switches in the signal loop are in the closed state, and all the matrix switches are in the disconnected state, which will not affect the signal loop. When the signal input needs to be measured, the single-pole single-throw switches between the input end and the corresponding common end in the high-end loop and the low-end loop are closed Figure 3the switches COM1 and COM3 in the signal in, and simultaneously open the switches COM2 and COM4, and then close the matrix switches R0C0 and R1C1, and finally realize that the high end and the low end of the signal in are connected to the high end and the low end of the digital multimeter, and then switch the measurement range of the digital multimeter through the main interface, and read the test result. If it is required to measure the signal out, the switches COM2 and COM4 in the signal out are closed, and the switches COM1 and COM3 are opened, and then the matrix switches R0C0 and R1C1 are closed, and on this basis, the switches COM1 and COM3 are closed, so that the voltage or resistance on the signal loop can be directly measured. Figure 3 the switches COM1 and COM3 in the signal in, and simultaneously open the switches COM2 and COM4, and then close the matrix switches R0C0 and R1C1, and finally realize that the high end and the low end of the signal in are connected to the high end and the low end of the digital multimeter, and then switch the measurement range of the digital multimeter through the main interface, and read the test result. If it is required to measure the signal out, the switches COM2 and COM4 in the signal out are closed, and the switches COM1 and COM3 are opened, and then the matrix switches R0C0 and R1C1 are closed, and on this basis, the switches COM1 and COM3 are closed, so that the voltage or resistance on the signal loop can be directly measured.

[0060] After the hardware circuit module circuit design is completed, the main control end module configuration file design is completed according to the signal wiring relationship, as shown in Figure 7 each row represents a disconnect block on the main interface, and the finished pin part defines the connector code, pin number and signal name of the finished product, and the switch array resource part defines the single-pole single-throw switch and matrix switch connected on the signal line. The configuration file designed is imported into the main control end module, and the main interface is automatically generated.

[0061] As shown in Figure 6 , the signal test and fault injection can be performed.

[0062] Figure 3 Only a typical reference hardware circuit module wiring design is provided, and according to the actual test requirements and the number of hardware resources, the design can also be simplified, such as testing only the signal in, the switches COM1 and COM3 can be removed, and testing only the signal out, the switches COM2 and COM4 can be removed. In addition, if the matrix switch hardware resources are many and the single-pole single-throw switch resources are few, the wiring design in Figure 8 can also be referred to.

[0063] For different types of signals, attention should be paid to the selection of the switch card. According to the typical signal current size of the flight control system, it can be divided into:

[0064] 1) Single-pole single-throw low-power switch for realizing signal disconnection with current less than or equal to 1A;

[0065] 2) Single-pole single-throw high-power switch for realizing signal disconnection with current greater than 1A and less than or equal to 5A;

[0066] 3) Small-power single-line matrix switch for realizing signal measurement with current less than or equal to 1A;

[0067] 4) Large-power single-line matrix switch for realizing signal measurement with current less than or equal to 5A;

[0068] Multiplexing matrix switch for realizing signal flying wire with current less than or equal to 1A.

[0069] The above merely describes specific embodiments of the present application, and the detailed description of the present application is not exhaustive of the conventional technology. However, the protection scope of the present application is not limited to this, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered by the protection scope of the present application. The protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aviation wire breakage testing system based on switch array virtualization reconstruction, characterized in that, include: Hardware circuit module, server module, main control module; the hardware circuit module includes PXI device, signal adapter, and signal tester; The PXI device integrates a chassis connection card, a single-pole single-throw switch card, and a matrix switch card. The PXI device connects to the control card of the server module via the chassis connection card. Test signals requiring disconnection, measurement, and flying wire testing enter through the signal adapter, flow through the corresponding single-pole single-throw switch card, are then connected in parallel to the column lines of the matrix switch card, and are output from the signal adapter. The signal tester connects to the row lines of the matrix switch card in the PXI device via the signal adapter. The server module also connects to the signal tester and the main control module.

2. The aviation wire breakage test system based on switch array virtualization reconstruction according to claim 1, characterized in that, The server module receives instructions from the main control module, controls the corresponding switches in the PXI device to be on / off, and controls the working mode of the signal tester, and uploads the test results to the main control module.

3. The aviation wire breakage test system based on switch array virtualization reconstruction according to claim 2, characterized in that, After defining all hardware resources as "resource ICD" files, the server module receives instructions sent by the master control module and controls the specific hardware based on the "resource ICD" files.

4. The aviation wire breakage test system based on switch array virtualization reconstruction according to claim 2, characterized in that, The main control module adopts a platform-based design and a single-client architecture. In terms of technical implementation, it adopts a .NET-based technical architecture, which includes an architecture that supports business management and data processing and display.

5. The aviation wire breakage test system based on switch array virtualization reconstruction according to claim 1, characterized in that, The main control module includes the following functional units: Automatic main interface generation unit: The main interface is automatically generated based on the configuration file, which describes the signal name of the test signal and the corresponding switch array resources. Operating mode switching unit: It is designed with three operating modes: view, disconnect, and lead. In view mode, selecting the disconnect block on the main interface can display its signal name, the bound switch number and card number; in disconnect mode, selecting the interrupt block will disconnect the disconnect block, and selecting it again will restore it; in lead mode, after selecting the interrupt block, the high end and low end of the signal tester can be connected respectively through shortcut keys. Instrument control unit: Used to integrate digital meter functions into the control panel.

6. The aviation wire breakage test system based on switch array virtualization reconstruction according to claim 5, characterized in that, The main control module also includes the following functional units: The impedance calibration unit is used to calibrate the signal lines that need to be impedance tested and save the impedance values ​​on the equipment lines to the configuration file. The safety protection unit is used to ensure that only one switch can be closed on a row line of the matrix switch card to prevent signal short circuits. The fast search unit is used to search for the disconnected block to be operated by signal name.

7. A test method for an aviation wire breakage test system based on switch array virtualization reconstruction as described in any one of claims 1-6, characterized in that, Two single-pole single-throw (SPS) switches are connected in series between the high-end and low-end circuits of the test signal. The common terminal of the two switches on the high-end circuit is connected to one column line of the matrix switch card, and the common terminal of the two switches on the low-end circuit is connected to the other column line. Correspondingly, the high and low ends of the signal tester are connected to the two row lines of the matrix switch card. In the initial state, all switches on the high and low end circuits are closed, and all matrix switches are open. When measuring the test signal input, the SPS switches between the high-end circuit input terminal and the corresponding common terminal, and between the low-end circuit input terminal and the corresponding common terminal are closed. The SPS switches between the high-end circuit output terminal and the corresponding common terminal, and between the low-end circuit output terminal and the corresponding common terminal are opened. Then, the matrix switches at the intersection of the row line of the matrix switch card connected to the signal tester and the column line of the matrix switch card connected to the high and low end circuits are closed. Finally, the high and low ends of the test signal input are connected to the high and low ends of the signal tester, respectively. The measurement range of the signal tester is then switched through the main control module, and the test results are read.

8. The test method for the aviation wire breakage test system based on switch array virtualization reconstruction according to claim 7, characterized in that, The method for disconnecting a single-pole single-throw switch is as follows: switch to the disconnect mode by operating the mode switching unit; on the main interface, click the disconnect block corresponding to the high or low end of the test signal to switch the single-pole single-throw switch to the disconnect state.

9. The test method for the aviation wire breakage test system based on switch array virtualization reconstruction according to claim 7, characterized in that, The closing method of the matrix switch card is as follows: switch to the lead wire mode by operating the mode switching unit; select the disconnection block corresponding to the high and low ends of the test signal on the main interface, and connect the selected signal tester to the high and low ends respectively by using the shortcut keys.

10. The test method for the aviation wire breakage test system based on switch array virtualization reconstruction according to claim 7, characterized in that, The measurement range switching of the signal tester is as follows: Select the test function option of the signal tester in the instrument control unit on the main interface to perform the test.

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