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Damage-tolerance testing method for lower wall panel of airplane outboard wing

A damage tolerance and test method technology, which is applied in measuring devices, instruments, measuring electrical variables, etc., can solve the problems of unclear crack propagation characteristics and imperfect damage tolerance analysis methods, and achieve the effect of ensuring authenticity

Inactive Publication Date: 2009-10-21
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The crack propagation characteristics of this structural form are not yet clear, and the damage tolerance analysis method is not yet perfect. Boeing series aircraft wing wall panels and skins at the ribs all have bosses, but the related analysis manual Does not reflect the boss effect, so experimental research is needed

Method used

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  • Damage-tolerance testing method for lower wall panel of airplane outboard wing
  • Damage-tolerance testing method for lower wall panel of airplane outboard wing
  • Damage-tolerance testing method for lower wall panel of airplane outboard wing

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Embodiment

[0025] The specific design of the test piece is as follows: the test piece is composed of skin and five reinforced long stringers, the skin material is LY12CZ, its basic thickness is 1.5mm, and the skin thickness at the long stringer is 1.8mm, which needs to be processed by chemical milling process. processing. The reinforced long trusses are all 'Z' shaped profiles, and the grade is XC411-3. The reinforced long trusses need to be cut to transition to a flat state; Pad the leather with the bottom edge of the stringer, and then add a 1.5mm thick square backing plate and a 3mm rectangular backing plate on the finger backing plate; similarly, use a 1.5mm thick square backing plate and a 3mm rectangular backing plate to install Below the siding, the siding is bolted to these backing plates. Insert the splint in the middle, 8mm from the wall plate, also bolted. The cross-sectional schematic diagram of the test piece is shown in figure 1 , figure 2 and image 3 .

[0026] Ini...

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PUM

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Abstract

The invention pertains to airplane fatigue and damage-tolerance testing technologies, and relates to a damage-tolerance testing method for a lower wall panel of an airplane outboard wing. The method comprises the steps of: (I) fabricating a test part, (II) conducting a test and (III) calculating finite element. The method considers test room and technique conditions in the design of the test part and utilizes the test part with simple structure to reflect the complicated structure of the lower wall panel, thereby not only ensuring the realness of a load path and structural characteristics, but also being beneficial to the easy implementation of the test; when cracks are prefabricated, the damage of single part as well as the damage of a plurality of parts are considered, thereby being beneficial to the study of the lower wall panel with widely distributed damage; finite element software is used for conducting comparison analysis and calculating a variation curve with crack propagation of an overall correction factor; comparison analysis is conducted to a convex plate; the method is perfected by combining with testing results; and a correction factor of the finite element method is given, thus providing technical support for the damage tolerance analysis of the part.

Description

technical field [0001] The invention belongs to the aircraft fatigue damage tolerance test technology, and relates to a damage tolerance test method for the lower wall plate of the outer wing of the aircraft. Background technique [0002] In the late 1970s, aircraft design gradually changed from damage-safe design thinking to damage tolerance / durability design thinking. Damage tolerance technology is a complex system engineering. It is based on fracture mechanics, aims to ensure structural safety, and uses damage inspection as a means to ensure that the aircraft body structure will not suffer from fatigue, corrosion, accidents and damages during its service life. Damage such as a discrete source causes catastrophic damage to the aircraft. [0003] The skin of the lower panel of the outer wing of the aircraft has a variable thickness, gradually thickening from the front beam to the rear beam, and the thickness also changes along the wingspan, and bosses are arranged at the c...

Claims

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Application Information

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IPC IPC(8): G01R19/00
Inventor 秦剑波王新波王锋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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