Rapid troubleshooting test equipment for aircraft control assembly

Abstract

The utility model provides an aircraft control assembly rapid troubleshooting test device, comprising a test host computer and a test circuit board, the test host computer sends a test control instruction to the test circuit board, and the test circuit board outputs a discrete signal for the test of a to-be-tested device to the to-be-tested device after receiving the test control instruction. And after the to-be-tested device receives the test discrete signal, test feedback information is transmitted to the test circuit board, and the test circuit board sends the test feedback information to the test upper computer, so that the test upper computer processes the test feedback information to judge whether the function of the to-be-tested device is normal or not. Compared with a traditional test bench test method, the method has the advantages that functions which cannot be realized by a traditional test bench can be realized by using existing software and hardware, the time for completing the test of a single aircraft control assembly is shorter, the test efficiency is higher, a more efficient and effective test program is realized, and the overall quality and reliability of the aircraft control assembly are improved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft fault testing, in particular to a rapid troubleshooting test device for an aircraft control component. Background Art

[0002] Most of the existing tests on aircraft control components need to be performed using original test equipment. During the repair process of aircraft control components, they need to be functionally tested using a test bench to confirm whether their functions are normal. The testing of aircraft control components is usually completed on semiconductor test equipment, which leads to a lack of testing resources for aircraft control components. In addition, the testing steps of existing test equipment are cumbersome, the testing methods are complicated, and potential faults of aircraft control components cannot be detected well. Utility Model Content

[0003] In view of the above technical problems, the technical solution adopted by the utility model is:

[0004] According to one aspect of the present application, there is provided an aircraft control component rapid troubleshooting test device, comprising:

[0005] A test circuit board, used for outputting a discrete signal to the device under test for testing the device under test, and receiving test feedback information returned by the device under test; the device under test is an aircraft control component that needs to be tested;

[0006] The test host computer is used to send test control instructions to the test circuit board and process the test feedback information sent by the test circuit board;

[0007] The test circuit board is communicatively connected with the test host computer and the device under test respectively. When receiving the test control instruction sent by the test host computer, the test circuit board outputs a test discrete signal to the device under test, and sends the test feedback information returned by the device under test to the test host computer, so that the test host computer processes the test feedback information.

[0008] In an exemplary embodiment of the present application, an optocoupler chip and a relay assembly are provided on the test circuit board, and both the optocoupler chip and the relay assembly are communicatively connected to the device under test, and the optocoupler chip and the relay assembly are used to output test discrete signals to the main power supply, auxiliary power supply, and front panel power supply of the device under test.

[0009] In an exemplary embodiment of the present application, the model of the optocoupler chip is AQ215.

[0010] In an exemplary embodiment of the present application, the relay assembly includes a plurality of relays, and the model of each relay is ER134DM4-26B.

[0011] In an exemplary embodiment of the present application, a resistor network and a single-chip microcomputer sampling module are also provided on the test circuit board. The resistor network and the single-chip microcomputer sampling module are both communicatively connected to the device under test. The resistor network and the single-chip microcomputer sampling module are used to collect the test feedback analog signal sent by the device under test and convert the test feedback analog signal into a test feedback digital signal.

[0012] In an exemplary embodiment of the present application, the single-chip microcomputer sampling module is a 10-bit-AD sampling module.

[0013] In an exemplary embodiment of the present application, a communication module is also provided on the test circuit board, and the communication module is communicatively connected to the test host computer and the single-chip microcomputer sampling module. The communication module is used to send the test feedback digital signal to the test host computer and receive the test control instructions sent by the test host computer.

[0014] In an exemplary embodiment of the present application, the signal communication protocol of the communication module is the RS232 communication protocol.

[0015] In an exemplary embodiment of the present application, the test circuit board is also connected to a switching power supply, and the switching power supply is used to convert 220V AC power into 28V DC power for testing the test circuit board.

[0016] In an exemplary embodiment of the present application, the test circuit board and the switching power supply are both connected to a static inverter, which is used to convert the 28V DC power output by the switching power supply into AC power with a frequency of 400 Hz and a voltage of 5V to power the test circuit board.

[0017] The utility model has at least the following beneficial effects:

[0018] The utility model relates to a rapid troubleshooting test device for an aircraft control component. A test host computer sends a test control instruction to a test circuit board. After receiving the test control instruction, the test circuit board outputs a discrete signal for testing the device under test to the device under test. After receiving the test discrete signal, the device under test transmits test feedback information to the test circuit board. The test circuit board sends the test feedback information to the test host computer, so that the test host computer processes the test feedback information to determine whether the function of the device under test is normal. Therefore, in order to solve the problem of insufficient testing resources for aircraft control components, the aircraft control component rapid troubleshooting test equipment of the utility model provides a dedicated aircraft control component testing environment, and realizes the functional detection of aircraft control components by utilizing the combination of single-chip microcomputer software and hardware. Compared with the traditional test bench testing method, the existing software and hardware can be utilized to realize functions that the traditional test bench cannot realize, so the developability and replicability are strong. Since the maintenance of traditional test equipment requires regular self-testing, the utility model reduces the potential maintenance cost from the design, so the maintenance cost is lower, and the time to complete a single aircraft control component test is shorter, and the testing efficiency is higher, so as to realize a more efficient and effective testing procedure, improve the overall quality and reliability of aircraft control components, and ensure their safe and effective application in modern aviation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 A component connection block diagram of an aircraft control component rapid troubleshooting test device provided in an embodiment of the utility model. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the utility model.

[0022] A rapid troubleshooting test device for aircraft control components, such as Figure 1 As shown, it includes a test circuit board, a test host computer, a switching power supply, a static converter and a device under test, and the device under test is an aircraft control component that needs to be tested.

[0023] The test circuit board is used to output discrete signals for testing the device under test according to the test control instructions sent by the test host computer, and to receive test feedback information returned by the device under test and send the test feedback information to the test host computer. The test feedback information is the data signal of the device under test that needs to be tested.

[0024] The test host computer is used to send test control instructions to the test circuit board and process the test feedback information sent by the test circuit board to obtain the functional test results of the device under test, wherein the method for processing the test feedback information can adopt the existing test method.

[0025] The test circuit board is also connected to a switching power supply, which is used to convert 220V alternating current into 28V direct current for testing the test circuit board.

[0026] The test circuit board and the switching power supply are both connected to a static converter, which is used to convert the 28V DC power output by the switching power supply into an AC power with a frequency of 400 Hz and a voltage of 5V to power the test circuit board.

[0027] The test circuit board is respectively connected to the test host computer, the device under test, the switching power supply, and the static converter for communication. When receiving the test control instruction sent by the test host computer, the test circuit board outputs a test discrete signal to the device under test. After receiving the test discrete signal, the device under test will send a test feedback signal corresponding to the test data type to the test circuit board according to the test data type included in the test discrete signal. The test circuit board then sends the test feedback signal to the test host computer. The test host computer processes the test feedback signal to determine whether the test feedback signal meets the condition standard for normal function, so as to determine whether the function of the device under test is normal.

[0028] Among them, the test circuit board is provided with an optocoupler chip, a relay assembly, a resistor network, a single-chip microcomputer sampling module and a communication module. The optocoupler chip and the relay assembly are both connected to the device under test in communication, and the optocoupler chip and the relay assembly are used to output test discrete signals to the main power supply, auxiliary power supply and front panel power supply of the device under test; the resistor network and the single-chip microcomputer sampling module are both connected to the device under test in communication, and the resistor network and the single-chip microcomputer sampling module are used to collect the test feedback analog signal sent by the device under test, and convert the test feedback analog signal into a test feedback digital signal; the communication module is connected to the test host computer and the single-chip microcomputer sampling module in communication, and the communication module is used to send the test feedback digital signal to the test host computer, and receive the test control instruction sent by the test host computer. In a feasible embodiment, the model of the optocoupler chip is AQ215, the relay assembly includes a plurality of relays, each of which is ER134DM4-26B, the single-chip microcomputer sampling module is a 10bit-AD sampling module, and the signal communication protocol of the communication module is the RS232 communication protocol.

[0029] The utility model relates to a rapid troubleshooting test device for an aircraft control component. A test host computer sends a test control instruction to a test circuit board. After receiving the test control instruction, the test circuit board outputs a discrete signal for testing the device under test to the device under test. After receiving the test discrete signal, the device under test transmits test feedback information to the test circuit board. The test circuit board sends the test feedback information to the test host computer, so that the test host computer processes the test feedback information to determine whether the function of the device under test is normal. Therefore, in order to solve the problem of insufficient testing resources for aircraft control components, the aircraft control component rapid troubleshooting test equipment of the utility model provides a dedicated aircraft control component testing environment, and realizes the functional detection of aircraft control components by utilizing the combination of single-chip microcomputer software and hardware. Compared with the traditional test bench testing method, the existing software and hardware can be utilized to realize functions that the traditional test bench cannot realize, so the developability and replicability are strong. Since the maintenance of traditional test equipment requires regular self-testing, the utility model reduces the potential maintenance cost from the design, so the maintenance cost is lower, and the time to complete a single aircraft control component test is shorter, and the testing efficiency is higher, so as to realize a more efficient and effective testing procedure, improve the overall quality and reliability of aircraft control components, and ensure their safe and effective application in modern aviation.

[0030] The above is only a specific implementation of the utility model, but the protection scope of the utility model is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the utility model should be included in the protection scope of the utility model. Therefore, the protection scope of the utility model should be based on the protection scope of the claims.

Claims

1. A rapid troubleshooting test device for aircraft control components, characterized in that: include: A test circuit board, used for outputting a discrete signal for testing the device under test to the device under test, and receiving test feedback information returned by the device under test; The device under test is an aircraft control component that needs to be tested; A test host computer, used to send a test control instruction to the test circuit board, and process the test feedback information sent by the test circuit board; The test circuit board is communicatively connected with the test host computer and the device under test respectively. When receiving the test control instruction sent by the test host computer, the test circuit board outputs a test discrete signal to the device under test, and sends the test feedback information returned by the device under test to the test host computer, so that the test host computer processes the test feedback information.

2. The aircraft control component rapid troubleshooting test equipment according to claim 1, characterized in that: The test circuit board is provided with an optocoupler chip and a relay assembly, both of which are communicatively connected with the device under test, and are used to output test discrete signals to the main power supply, auxiliary power supply, and front panel power supply of the device under test.

3. The aircraft control component rapid troubleshooting test equipment according to claim 2, characterized in that: The model of the optocoupler chip is AQ215.

4. The aircraft control component rapid troubleshooting test equipment according to claim 3, characterized in that: The relay assembly includes a plurality of relays, and the model of each relay is ER134DM4-26B.

5. The aircraft control component rapid troubleshooting test equipment according to claim 4, characterized in that: The test circuit board is also provided with a resistor network and a single-chip microcomputer sampling module, both of which are communicatively connected with the device under test, and are used to collect the test feedback analog signal sent by the device under test, and convert the test feedback analog signal into a test feedback digital signal.

6. The aircraft control component rapid troubleshooting test equipment according to claim 5, characterized in that: The single chip microcomputer sampling module is a 10bit-AD sampling module.

7. The aircraft control component rapid troubleshooting test equipment according to claim 6, characterized in that: The test circuit board is also provided with a communication module, which is communicatively connected with the test host computer and the single-chip microcomputer sampling module, and is used to send the test feedback digital signal to the test host computer and receive the test control instruction sent by the test host computer.

8. The aircraft control component rapid troubleshooting test equipment according to claim 7, characterized in that: The signal communication protocol of the communication module is the RS232 communication protocol.

9. The aircraft control component rapid troubleshooting test equipment according to claim 8, characterized in that: The test circuit board is also connected to a switching power supply, and the switching power supply is used to convert 220V alternating current into 28V direct current for use in testing the test circuit board.

10. The aircraft control component rapid troubleshooting test equipment according to claim 9, characterized in that: The test circuit board and the switching power supply are both connected to a static converter, and the static converter is used to convert the 28V direct current output by the switching power supply into alternating current with a frequency of 400 Hz and a voltage of 5V to power the test circuit board.

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