Method for determining low-temperature working stress limit of aircraft anti-skid braking control box

A work stress, anti-skid braking technology, applied in measuring devices, instruments, measuring electricity and other directions, can solve problems such as unrealistic data

Inactive Publication Date: 2012-04-25
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

And at present, the low-temperature working stress limit test of other foreign electronic products is carried out under non-working conditions. The method of only applying environmental stress without applying

Method used

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  • Method for determining low-temperature working stress limit of aircraft anti-skid braking control box

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] This embodiment is a test for determining the low-temperature working stress limit of the first type of control box, and the test samples are 2 sets of control boxes. The design of the test sample has been improved for the low temperature problem in the development test.

[0028] The test of this embodiment uses a reliability enhancement test box model UHS1200, a digital multimeter, a signal source and an oscilloscope.

[0029] The concrete process of this embodiment is:

[0030] Step 1, determine the test parameters. The test parameters include test temperature starting point, cooling step size and cooling rate. The cooling step is not greater than 5°C, and the smaller the more accurate, the starting point of the test temperature in this embodiment is 20°C, the cooling step is 2°C, and the cooling rate is 25°C / min.

[0031] Step 2, heating the test sample. Install the 2 sets of test samples on the moving coil in the strengthening test box with fixtures. Heat the t...

Embodiment 2

[0036] This embodiment is a test for determining the low-temperature working stress limit of the second type of control box, and the test sample is a set of control boxes. The design of the test sample has been improved for the low temperature problem in the development test.

[0037] The test of this embodiment uses a reliability enhancement test box model UHS1200, a digital multimeter, a signal source and an oscilloscope.

[0038] The concrete process of this embodiment is:

[0039] Step 1, determine the test parameters. The test parameters include test temperature starting point, cooling step size and cooling rate. The cooling step is not greater than 5°C, and the smaller the more accurate, the starting point of the test temperature in this embodiment is 30°C, the cooling step is 5°C, and the cooling rate is 40°C / min.

[0040] Step 2, heating the test sample. One set of test samples is installed on the moving coil in the strengthening test box with the fixture. Heat th...

Embodiment 3

[0045] This embodiment is a test for determining the low-temperature working stress limit of the third type of control box, and the test sample is a set of control boxes. The design of the test sample has been improved for the low temperature problem in the development test.

[0046] The test of this embodiment uses a reliability enhancement test box model UHS1200, a digital multimeter, a signal source and an oscilloscope.

[0047] The concrete process of this embodiment is:

[0048] Step 1, determine the test parameters. The test parameters include test temperature starting point, cooling step size and cooling rate. The cooling step is not greater than 5°C, and the smaller the more accurate, the starting point of the test temperature in this embodiment is 25°C, the cooling step is 1°C, and the cooling rate is 60°C / min.

[0049] Step 2, heating the test sample. One set of test samples is installed on the moving coil in the strengthening test box with the fixture. Heat the...

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Abstract

The invention discloses a method for determining low-temperature working stress limit of an aircraft anti-skid braking control box. The low-temperature working stress limit of the control box is determined by applying low-temperature stress to the control box in a stepped mode with a low-temperature step environment stress test method. In the method, the test time for testing the low-temperature working stress limit of the control box is 6-8 hours; the temperature drop step length is 1-5 DEG C; the temperature drop rate is 25-60 DEG C/minute; the temperature is kept for 5 minutes each time after the temperature is dropped to a specified value; the time for temperature balance of the control box is reserved; then performance test is performed, and the test time is 5 minutes; and the sum oftemperature keeping time at each step is 10 minutes. The low-temperature working stress limit of a sample is obtained according to such stepped temperature drop test method. Since the failure of the control box occurs in a working process, application of working stress in the test process of dropping the temperature by using the stepped method more facilitates excitation and observation of the failure; and a test method capable of quickly determining the low-temperature failure hidden trouble of the control box and determining the low-temperature working stress limit of the control box is formed.

Description

technical field [0001] The invention relates to the field of electronic products of a landing gear control system of a transport aircraft. Specifically, it is an aircraft anti-skid brake control box, referred to as the control box. Background technique [0002] The control box is the control unit in the aircraft electric anti-skid braking system, which is designed with the functions of take-off line braking, anti-skid function during landing braking, grounding protection function during landing, inter-wheel protection of left and right landing gear wheels during landing, etc. A variety of functions, any one of which does not meet the design requirements is a failure. In the present invention, the working performance of the control box refers to the quantitative requirements of the above-mentioned various functions. [0003] In order to ensure the reliability and safety requirements of the control box, the high-accelerated life test technology is used internationally to sti...

Claims

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Application Information

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IPC IPC(8): G01R31/00
Inventor 乔建军田广来黄智商海东张谦刘忠平
Owner XIAN AVIATION BRAKE TECH
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