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A test method for damage tolerance strength of aircraft full-scale composite spoiler

A composite material and strength test technology, which is applied in the direction of applying stable tension/pressure to test the strength of materials, analyzing materials, strength characteristics, etc., can solve the problems of not being able to fully assess the structure of the spoiler, so as to save development costs and shorten The effect of the test cycle

Active Publication Date: 2022-03-15
中航西飞民用飞机有限责任公司
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AI Technical Summary

Problems solved by technology

If the above factors are ignored, it will not be possible to fully assess the spoiler structure. Therefore, a method that can comprehensively consider manufacturing defects and impact damage, actuator levers, and wing deformation factors is needed to fully assess the spoiler structure. test method

Method used

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  • A test method for damage tolerance strength of aircraft full-scale composite spoiler
  • A test method for damage tolerance strength of aircraft full-scale composite spoiler
  • A test method for damage tolerance strength of aircraft full-scale composite spoiler

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Embodiment Construction

[0023] Referring to the accompanying drawings, the invention provides a method for testing the damage tolerance strength of an aircraft full-scale composite material spoiler.

[0024] The present invention will be described in further detail below through specific implementation examples and in conjunction with the accompanying drawings.

[0025] Step 1: According to the definition of various damages in the spoiler acceptance technical conditions, combined with the damage that may be caused during the manufacture and use of the spoiler, determine the manufacturing defects and impact damage sources of the spoiler test piece, and plan the spoiler The damage layout of the plate test piece shall be drawn, and the damage layout diagram shall be drawn. Among them, manufacturing defects are mainly delamination, and the impact damage sources include primary impact damage and secondary impact damage, primary impact damage is barely visible damage, and secondary impact damage is visuall...

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Abstract

This application provides a tolerance strength test method for full-scale composite material spoilers of aircraft that can meet the requirements of flight trials. The effects of manufacturing defects and impact damage, actuator arm, and wing deformation are comprehensively considered on one test piece. The development cost of the test piece is saved, the structure of the spoiler can be fully examined, and the test cycle can be shortened.

Description

technical field [0001] The invention belongs to the technical field of aircraft strength tests and relates to a method for testing the damage tolerance strength of aircraft full-scale composite spoiler spoilers. Background technique [0002] Damage tolerance refers to the ability of an airframe structure to perform its function in the presence of defects or other damage during a given period of use without repairs. The spoiler is a movable airfoil structure, and its design must meet the requirements of static strength and damage tolerance. At present, the strength test of the full-scale movable airfoil structure mainly considers the influence of wing box deformation, and the consideration of influencing factors is relatively simple. The deflection angle of the spoiler structure ranges from 0° to 60°, and the force arm of the actuator on the spoiler shaft is different under different opening angles. Especially when the spoiler structure is made of composite materials, in add...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N3/00G01N3/08G01N3/02G01N3/04
CPCG01N3/00G01N3/08G01N3/02G01N3/04G01N2203/0019G01N2203/0073G01N2203/0258G01N2203/04
Inventor 高洁文琦龙雷江龙
Owner 中航西飞民用飞机有限责任公司
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