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Shape maintenance shot peening strengthening and calibration method for preventing in-plane bending of wall panel

A technology of shot peening and correction method, which is applied in the field of shape-preserving shot peening and correction to prevent in-plane bending of wall panels, and achieves the effects of reducing parts scrap rate, avoiding major economic losses, and good technical and economic benefits

Active Publication Date: 2012-10-31
BEIJING AERONAUTICAL MFG TECH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is mainly aimed at the problem of in-plane bending caused by shot peening of complex structure wall plate parts, and proposes a shape-preserving shot peening method and a correction method for preventing wall plate in-plane bending

Method used

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  • Shape maintenance shot peening strengthening and calibration method for preventing in-plane bending of wall panel
  • Shape maintenance shot peening strengthening and calibration method for preventing in-plane bending of wall panel
  • Shape maintenance shot peening strengthening and calibration method for preventing in-plane bending of wall panel

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Embodiment 1

[0052] For shot peening of aircraft wing panels, first follow image 3 Divide the area, and the thickness is Z1, Z2, Z3, Z4 from large to small. The given shot peening intensity range is 0.15~0.2mmA, then it is divided into five equal parts, and the shot peening intensity of each level is:

[0053] Q1=0.2mmA; Q2=0.1875mmA; Q3=0.175mmA; Q4=0.1625mmA; Q5=0.15mmA

[0054] , the shot peening strength of the inner and outer surfaces of the four areas of the panel is shown in the table below.

[0055] spray position

Z1

Z2

Z3

Z4

The outer surface

Q1

Q2

Q3

Q4

The inner surface

Q2

Q3

Q4

Q5

[0056] Detailed process parameters include:

[0057]

[0058] Shot peening was carried out on the MP15000 CNC shot peening machine of the French Wheelaborator company, and the wing panel after shot peening was deformed as follows: figure 2 , need to be corrected, according to Figure 4 T...

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Abstract

The invention belongs to the forming technique of aerospace wall panels, relating to a shape maintenance shot peening strengthening and calibration method for preventing the in-plane bending of a wall panel. The method comprises the following steps of: firstly carrying out regional division on the spare parts of the wall panel, then inputting data in a shot peening device, and finally carrying out shot peening strengthening in a double opposite spraying manner; when in-plane bending occurs for the shot peening, calibrating thin-gauge skins, firstly choosing a calibration region, and then inputting the data into the shot peening device; and carrying out double opposite spraying on the inner and the outer thin-gauge skins in the deformed region with in-plane bending. According to the invention, aiming at the complicated structural shape, shot peening strengthening is carried out on the wall panel under the condition of guaranteeing that the space shapes of the spare parts are not changed after deformation, and the calibration method for forming the in-plane bending after the shot peening strengthening reduces the rejection rate of the spare parts, avoids severe economic lost and has good technological and economic benefits.

Description

technical field [0001] The invention belongs to the aerospace wall plate forming technology, and relates to a shape-preserving shot peening strengthening and correction method for preventing the in-plane bending of the wall plate. Background technique [0002] Siding is one of the most important types of parts in aerospace vehicles. It is not only an important part of the aerodynamic shape, but also the main load-bearing component of aircraft wings and fuselage. The main forming method of wall plate parts is shot peening. In order to improve the fatigue strength and fatigue limit of the parts, it is generally necessary to carry out shot peening treatment on the entire surface of the parts after shot peening. Most of the original wall panel parts are of equal thickness design, and the structural features are less complex. There is little in-plane bending of the parts after shot peening. [0003] With the continuous improvement of aircraft performance, the requirements for a...

Claims

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Application Information

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IPC IPC(8): B24C1/10
Inventor 曾元松白雪飘张新华
Owner BEIJING AERONAUTICAL MFG TECH RES INST
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