Aircraft electronic component power interruption test system and method

Abstract

The invention discloses an airplane electronic component power supply interruption test system and method. The system comprises an STM32 main control module, an AC interruption control module, a DC interruption control module, an RS485 display module, an EC11 coding module, an adjustable load module and a power supply module. The method comprises the following steps: setting a parameter requirement; constructing an aircraft electronic component power interruption test system; compiling a bottom interruption test code; debugging a hardware circuit and a software code; and commissioning and debugging the whole machine. The system and the method provided by the invention can realize high-precision interruption test and lightning stroke test of an alternating-current or direct-current power supply of dozens of milliseconds, also can carry out high-voltage lightning stroke test on electronic components, and meet test requirements and application requirements.

Description

Technical Field

[0001] The invention relates to a test device and method for aircraft electronic components, in particular to a power interruption test system and method for aircraft electronic components. Background Art

[0002] ATC / TACS (Air Traffic Control / Traffic Alert and Collision Avoidance System) is an electronic component control panel system for Airbus single-aisle (A319 / A320 / A321 series) and long-range (A330 / A340 series) aircraft. Its main function is to remotely control the ATC (Air Traffic Control) transponder. According to the manual requirements of this component, interruption test and lightning strike test are required for this type of parts, but the original test equipment does not realize this part of the test function, resulting in the inability to fully test and verify this type of component.

[0003] Existing testing methods rely on manual labor, are time-consuming, and lack accuracy.

[0004] Therefore, there is an urgent need for a power supply interruption test system for interruption tests and lightning strike tests of aircraft electronic components based on the test specifications and requirements of interruption tests and lightning strike tests, as well as the needs of interruption tests and lightning strike tests of other aircraft electronic components, to achieve high-precision interruption of AC or DC power supply for interruption tests of more than ten milliseconds, and to perform high-voltage lightning tests on electronic components. Summary of the invention

[0005] The object of the present invention is to provide an aircraft electronic component power interruption test system and method, which can realize high-precision interruption test and lightning strike test analysis according to aircraft electronic component power interruption test requirements.

[0006] A first object of the present invention is to provide an aircraft electronic component power interruption test system, comprising:

[0007] STM32 main control module, AC interrupt control module, DC interrupt control module, RS485 display module, EC11 encoding module, adjustable load module and power supply module.

[0008] The STM32 main control module is connected to the RS485 display module, the AC interruption control module and the DC interruption control module; the AC interruption control module and the DC interruption control module are respectively connected to the electronic components of the tested aircraft;

[0009] The STM32 main control module adopts an ARM processor, and the STM32 main control module is connected to an external PC software programming module for writing the main control program; the ARM processor's chip internal registers, interrupt services, and dynamic scanning algorithms are used for writing. The ARM processor mainly collects EC11 coded signals, performs data calculation and analysis on the collected data, outputs to the RS485 display screen to display high-precision time, and controls the output AC interruption test and DC interruption test.

[0010] The power module is connected to the RS485 display module, the STM32 main control module, the AC interrupt control module, and the DC interrupt control module and supplies power;

[0011] The power module receives an input voltage from a +220VDC interface and generates +28VDC, +12VDC, and +5VDC DC voltage outputs, and is used to supply the RS485 display module, the DC interrupt control module, and the STM32 main control module with the output voltages +28VDC, +12VDC, and +5VDC respectively when the interrupt test is working;

[0012] The AC interrupt control module and the DC interrupt control module receive IO control signals from the STM32 main control module, and can perform interruption tests and lightning tests on aircraft electronic components in a very short time at the millisecond level. The test signals meet all test requirements of the aircraft to ensure a complete interruption test.

[0013] The RS485 display module receives the AB signal from the 485 port of the STM32 main control module, and displays the test results of the 0 to 10 second millisecond time change set by the EC11 encoding circuit. After this time is ensured to be precise and accurate, the electronic components can be interrupted and lightning tested.

[0014] After the EC11 encoding module is manually set to the required time for the test, it is input to the STM32 main control module through A, B, and KEY signals, and the main control module processes and calculates the setting to control the precise time of the interrupt test.

[0015] The adjustable load module is composed of 4 series high-power precision circuits with a setting range of 0-9999ohm. The adjustable load module inputs the load to the input end of the DC interruption control module to simulate the load and current parameter requirements of the DC interruption test.

[0016] The external PC software programming module is an EC11 encoding module.

[0017] The aircraft electronic component under test is an air traffic control / traffic alert and collision avoidance system (TAC / TACS).

[0018] The STM32 main control module controls the output of AC interrupt control or DC interrupt control output control signals to perform interruption test and lightning test on the electronic components to be tested.

[0019] The system of the present invention further comprises a voltage and current protection circuit when applied to high AC voltage operation.

[0020] Another object of the present invention is to provide a method for testing power interruption of aircraft electronic components, comprising the following steps:

[0021] S1: First, set the parameter requirements according to the interruption test requirements of the aircraft electronic components to be tested; this is the preliminary research stage of the power interruption test equipment;

[0022] S2: Select the peripherals and CPU required for the test, build the aircraft electronic component power interruption test system, and make the test system load test requirements and accuracy;

[0023] S3: Write low-level interrupt test code;

[0024] S4: Hardware circuit debugging and software code debugging;

[0025] S5: Test run and debug the whole machine to achieve final stability.

[0026] Compared with the prior art, the present invention can achieve high-precision interruption of AC or DC power supply within tens of milliseconds for interruption testing and lightning strike testing, and can also perform high-voltage lightning testing on electronic components, meeting testing requirements and application needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] Figure 1 It is a functional module diagram of the aircraft electronic component power interruption test system of the present invention;

[0029] Figure 2 It is a working principle diagram of the aircraft electronic component power interruption test system of the present invention;

[0030] Figure 3 It is a schematic diagram of a power module circuit in the aircraft electronic component power interruption test system of the present invention;

[0031] Figure 4 It is a schematic diagram of the STM32 main control circuit in the aircraft electronic component power interruption test system of the present invention;

[0032] Figure 5 It is a schematic diagram of a DC / AC interruption test circuit in the aircraft electronic component power interruption test system of the present invention;

[0033] Figure 6 It is a schematic diagram of the RS485 display circuit in the aircraft electronic component power interruption test system of the present invention;

[0034] Figure 7 It is a schematic diagram of the EC11 coding circuit in the aircraft electronic component power interruption test system of the present invention;

[0035] Figure 8 The present invention is a schematic diagram of an adjustable load circuit in the aircraft electronic component power interruption test system. DETAILED DESCRIPTION

[0036] like Figure 1 and Figure 2 The aircraft electronic component power interruption test system shown in the figure includes: STM32 main control module, AC interruption control module, DC interruption control module, RS485 display module, EC11 encoding module, adjustable load module and power supply module.

[0037] The STM32 main control module is connected to the RS485 display module, the AC interruption control module and the DC interruption control module; the AC interruption control module and the DC interruption control module are respectively connected to the electronic components of the tested aircraft; the electronic components of the tested aircraft are the air traffic control / traffic alert and collision avoidance system (TAC / TACS).

[0038] like Figure 4 As shown, the STM32 main control module adopts an ARM processor, and the STM32 main control module is connected to an external PC software programming module for writing the main control program; the chip internal registers, interrupt services, and dynamic scanning algorithms of the ARM processor are used for writing. The ARM processor mainly collects EC11 coded signals, performs data calculation and analysis on the collected data, outputs to the RS485 display screen to display high-precision time, and controls the output AC interruption test and DC interruption test. The external PC software programming module is an EC11 coding module. The output AC interruption control or DC interruption control output control signal is controlled by the STM32 main control module to perform interruption test and lightning test of the electronic components to be tested.

[0039] ARM processor uses ST (STMicroelectronics) based on Cortex TM-M3 as the core of the STM32F1 series of high-performance microcontrollers, with up to 1MB of Flash, 72MHz high-speed performance makes digital signal controller applications and rapid product development to a new level, improve the execution speed of control algorithms and code efficiency, using its multiple AHB bus matrix and multi-channel DMA, the program uses IO ports to control the DC interrupt control module and AC interrupt control module to test aircraft electronic components, read the EC11 code setting signal after the output signal to the RS485 data bus to the RS485 display to display millisecond time, to achieve accurate interrupt test and lightning test.

[0040] The power module is connected to the RS485 display module, the STM32 main control module, the AC interrupt control module, and the DC interrupt control module to supply power;

[0041] like Figure 3 As shown, the power module receives the input voltage from the +220VDC interface and generates +28VDC, +12VDC, and +5VDC DC voltage outputs. When the interrupt test is working, the output voltages +28VDC, +12VDC, and +5VDC are respectively supplied to the RS485 display module, the DC interrupt control module, and the STM32 main control module;

[0042] like Figure 5 As shown, the AC interrupt control module and the DC interrupt control module receive IO control signals from the STM32 main control module, and can perform interruption tests and lightning tests on aircraft electronic components in a very short time at the millisecond level. The test signals meet all test requirements of the aircraft to ensure a complete interruption test.

[0043] like Figure 6 As shown, the RS485 display module receives the AB signal from the 485 port of the STM32 main control module and displays the test results of the 0 to 10 second millisecond time change set by the EC11 encoding circuit. After this time is ensured to be precise and accurate, the electronic components can be interrupted and lightning tested.

[0044] like Figure 7 As shown in the figure, after the EC11 encoding module is manually set with the test required time, it is input to the STM32 main control module through the A, B, and KEY signals, and the main control module processes and calculates the setting to control the precise time of the interrupt test. Figure 8 As shown, the adjustable load module is composed of 4 series high-power precision circuits, and the adjustable load module can be set in the range of 0-9999 ohms. The adjustable load module inputs the load to the input end of the DC interruption control module to simulate the load and current parameter requirements of the DC interruption test.

[0045] The system of the present invention further comprises a voltage and current protection circuit when applied to high AC voltage operation.

[0046] The method for performing power interruption testing on aircraft electronic components using the above system comprises the following steps:

[0047] S1: First, set the parameter requirements according to the interruption test requirements of the aircraft electronic components to be tested; this is the preliminary research stage of the power interruption test equipment;

[0048] S2: Select the peripherals and CPU required for the test, build the aircraft electronic component power interruption test system, and make the test system load test requirements and accuracy;

[0049] S3: Write low-level interrupt test code;

[0050] S4: Hardware circuit debugging and software code debugging;

[0051] S5: Test run and debug the whole machine to achieve final stability.

[0052] The system and method of the present invention are applied to testing aircraft electronic components, and can achieve high-precision interruption of AC or DC power supply for more than ten milliseconds to perform interruption testing and lightning strike testing, and can also perform high-voltage lightning testing on electronic components, meeting testing requirements and application needs.

[0053] The implementation methods of the present invention are not limited to these. Based on the above basic technical concept of the present invention, various other modifications, replacements or changes made to the contents of the present invention in accordance with common technical knowledge and customary means in the field all fall within the scope of protection of the present invention.

Claims

1. Aircraft electronic component power interruption test system, characterized by: The system includes: STM32 main control module, AC interrupt control module, DC interrupt control module, RS485 display module, EC11 encoding module, adjustable load module and power supply module; The STM32 main control module is connected to the RS485 display module, the AC interruption control module and the DC interruption control module; the AC interruption control module and the DC interruption control module are respectively connected to the electronic components of the tested aircraft; The STM32 main control module adopts an ARM processor, and the STM32 main control module is connected to an external PC software programming module for writing a main control program; the chip internal registers, interrupt services, and dynamic scanning algorithms of the ARM processor are used for writing; The power module is connected to the RS485 display module, the STM32 main control module, the AC interrupt control module, and the DC interrupt control module and supplies power; The AC interrupt control module and the DC interrupt control module receive IO control signals from the STM32 main control module; The RS485 display module receives the AB signal from the 485 port of the STM32 main control module, and displays the test result of the 0 to 10 second millisecond time change set by the EC11 encoding circuit; After the EC11 encoding module is manually set to the required time for the test, it is input to the STM32 main control module through A, B, and KEY signals, and the main control module processes and calculates the setting to control the precise time of the interrupt test.

2. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The ARM processor collects EC11 coded signals, performs data calculation and analysis on the collected data, outputs the high-precision time numerically to the RS485 display screen, and controls the output of AC interruption test and DC interruption test.

3. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The power supply module receives an input voltage from a +220VDC interface and generates +28VDC, +12VDC, and +5VDC DC voltage outputs. When the interrupt test is working, the output voltages +28VDC, +12VDC, and +5VDC are respectively supplied to the RS485 display module, the DC interrupt control module, and the STM32 main control module.

4. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The adjustable load module is composed of 4 series high-power precision circuits with a setting range of 0-9999ohm. The adjustable load module inputs the load to the input end of the DC interruption control module to simulate the load and current parameter requirements of the DC interruption test.

5. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The external PC software programming module is an EC11 encoding module.

6. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The aircraft electronic component under test is an air traffic control / traffic alert and collision avoidance system (TAC / TACS).

7. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The STM32 main control module controls the output of AC interrupt control or DC interrupt control output control signals to perform interruption test and lightning test on the electronic components to be tested.

8. The aircraft electronic component power interruption test system according to claim 1, characterized in that: The system also includes a voltage and current protection circuit when applied to high AC voltage operation.

9. A method for testing power interruption of aircraft electronic components, characterized in that: The method comprises the following steps: S1: First, set the parameter requirements according to the interruption test requirements of the aircraft electronic components to be tested; S2: Select the peripherals and CPU required for the test, and construct the aircraft electronic component power interruption test system as described in any one of claims 1 to 8, so that the test system load test requirements and accuracy; S3: Write low-level interrupt test code; S4: Hardware circuit debugging and software code debugging; S5: Test run and debug the whole machine to achieve final stability.

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