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Method for eliminating residual stress of airplane skin panel

A residual stress and skin plate technology, applied in heat treatment equipment, furnaces, heat treatment furnaces, etc., to achieve the effect of improving surface quality, small deformation, and low material cost

Inactive Publication Date: 2014-02-05
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The advantages and beneficial effects of the present invention, the present invention adopts a simple and easy-to-operate new technology, that is, the pre-stretching method eliminates the residual stress of the thin plate, solves the deformation of the large-area skin plate after chemical milling and improves its surface quality, etc., so as to meet Design and process specification requirements

Method used

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  • Method for eliminating residual stress of airplane skin panel

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Embodiment Construction

[0008] The present invention will be described in further detail below in conjunction with the accompanying drawings. figure 1 It is a typical aircraft sheet metal chemical milling part structure. The central area of ​​this part is non-chemical milling area 3, and the upper and lower sides of the part need large area chemical milling areas 1 and 2, and the thickness requirements of different areas after chemical milling are different. Similarly, if the traditional skin plate (thin plate without stress relief) is used, there will be the following problems after chemical milling: first, the actual parts are deformed after chemical milling, and there are many agitation deformation areas; second, wrinkles, agitation, etc. Surface quality problems; adopt the manufacturing method proposed by the present invention to avoid the above problems.

[0009] Main steps of the present invention are as follows:

[0010] Ingot casting, melting casting (flat ingot)→rolling→edge trimming→etchin...

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Abstract

The invention belongs to the technical field of aircraft material production, and relates to a method for eliminating the residual stress of an airplane skin panel, which is capable of eliminating the stress of aircraft materials and controlling the surface quality and the like. The method comprises the following steps: carrying out solid solution heat treatment on the airplane skin panel, and carrying out prestretching permanent deformation in the length direction of the airplane skin panel, wherein the deformation is 0.8-1% of the length of the airplane skin panel; then carrying out artificial aging and ultrasonic flaw detection treatment. A novel simple easy-to-operate technology, namely a prestretching manner is used for eliminating the residual stress of the panel so as to solve the problems that after the large-area skin panel is chemically milled, the skin panel deforms, and the surface quality of the skin panel is improved, thus the design and process specification requirements are satisfied.

Description

technical field [0001] The invention belongs to the technical field of aviation material production, and relates to a method for eliminating residual stress of aircraft skin panels for stress elimination and surface quality control of aviation materials. Background technique [0002] In the process of aircraft development, due to the requirement of weight reduction, some skin panels and webs need to be milled in large areas. After the milling, there are large deformations to varying degrees. If the assembly is forced, there will be a lot of stress. Parts of the aircraft fuselage are generally made of 2A12-T4 large-scale thin plates, and the deformation after chemical milling is required to be small. In practice, this traditional thin plate material is used, and the deformation of the parts after chemical milling is much higher than the specified value, and there are many agitation deformation areas. , Poor surface quality and other serious problems. Therefore, in order to s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C21D8/00C21D1/78C21D9/00
CPCY02P10/20
Inventor 姬浩
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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