Simulation part load conversion method based on local actually measured strain at crack tip of actual structural part of airplane

A crack tip, measured strain technology, used in measuring devices, railway vehicle testing, instruments, etc., can solve problems such as tediousness and complex stress on actual structural parts, and achieve the effect of accurate computing resources

Active Publication Date: 2018-12-11
BEIJING UNIV OF TECH +1
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

This method is not only cumbersome, but also the force of the actual structural parts is relatively complicated, and it is difficult to use the finite element method to load it. Moreover, if the actual structural parts have cracks, the stress field near the crack tip will change, and the finite element method cannot be used anymore. Calculations

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  • Simulation part load conversion method based on local actually measured strain at crack tip of actual structural part of airplane
  • Simulation part load conversion method based on local actually measured strain at crack tip of actual structural part of airplane
  • Simulation part load conversion method based on local actually measured strain at crack tip of actual structural part of airplane

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Embodiment Construction

[0030] The specific embodiment of the present invention will be described with reference to the accompanying drawings.

[0031] The present invention further illustrates the present invention by measuring the strain of the actual structural part of the aircraft and transforming the load of the simulated part,

[0032] A load conversion method for simulated parts based on the local measured strain at the crack tip of an actual aircraft structural part. The specific calculation method is as follows:

[0033] Step 1): Measure the crack length a, attach No. 1 and No. 2 strain gauges to the tip of the crack, make the measured strain direction perpendicular to the crack, and ensure that the connection of the two strain gauges is on the extension line of the crack, record No. 1 and No. 2 The distance between No. 2 strain gauge and the crack tip is r 1 and r 2 , and let r 1 and r 2 greater than 0.1 times the crack length a;

[0034] Step 2): Record the strain values ​​measured by...

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Abstract

The invention discloses a simulation part load conversion method based on local actually measured strain at a crack tip of an actual structural part of an airplane and relates to the field of fatiguelife test. The method comprises the following steps: (1) measuring crack length and adhering a strain gauge; (2) converting the measured strain into local strain; (3) calculating a strain strength factor by employing the local strain; (4) calculating nominal strain through the strain strength factor and judging whether a calculating result is accurate or not; and (5) solving a load of the test simulation part by employing the calculated nominal strain. The conversion result shows that the method can convert the load of the actual structural part with the crack into the load of the test simulation part accurately and quickly.

Description

technical field [0001] The application field of the invention is the direction of fatigue life testing, in particular a method for transforming the load of a simulated part based on the locally measured strain at the tip of a crack in an actual structural part of an aircraft. Background technique [0002] Aircraft, high-speed rail and other machinery have high requirements on safety and life, and fatigue tests are required. However, due to the difficulty and high cost of fatigue tests on the whole machine, it is often necessary to simplify the real components to make corresponding test simulations for fatigue testing. Life test, but it is necessary to ensure that the key parts of the test simulation part and the real structural part have the same force effect. Therefore, it is of great practical significance to invent a load conversion method between the actual structural part and the test simulation part, which can ensure the rationality and reliability of the fatigue test ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/00G01N3/02
CPCG01M17/08G01N2203/0073
Inventor 尚德广惠杰陈群志蔡佳昆张强王智
Owner BEIJING UNIV OF TECH
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