Creep age forming technological method

A creep aging forming and process method technology, applied in the field of creep aging forming, can solve the problem of mold springback compensation algorithm not suitable for forming process, and achieve the effect of eliminating uneven distribution, increasing volume fraction and improving strength

Active Publication Date: 2015-04-29
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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Problems solved by technology

[0007] After the sheet metal is rolled, there is plastic strain in the material, which has a great influence on the subsequent creep aging forming. The existing finite element simulation technology and mold springback compen

Method used

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Embodiment Construction

[0041] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clear, the present invention will be further described in detail below in conjunction with the embodiments and the accompanying drawings. Here, the exemplary embodiments and descriptions of the present invention are used to explain the present invention, but not to limit the present invention.

[0042] Please refer to Figure 1 to Figure 2C As shown, the present invention provides a creep aging forming process, which specifically includes the following steps:

[0043] Step S101: Acquiring the profile feature data of the target part 4;

[0044] Step S102: Pre-bending the initial sheet material 1 according to the profile characteristic data to obtain a pre-bending test piece 2;

[0045] Step S103: after placing the profile of the pre-bending test piece 2 corresponding to the profile of the aging forming mold 3, package them together and perform vacuum treatm...

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Abstract

The invention provides a creep age forming technological method. The technological method comprises the following steps: obtaining molded surface characteristic data of a target part; prebending an initial sheet material according to the molded surface characteristic data, so as to obtain a prebent test piece; placing the prebent test piece to enable the molded surface of the prebent test piece to correspond to that of an age forming die, then jointly packaging the prebent test piece and the age forming die, and performing vacuum treatment on a gap between the prebent test piece and the age forming die; putting the prebent test piece and the age forming die into an autoclave, and changing environment parameters in the autoclave, so as to ensure that the prebent test piece is closely adhered to the molded surface of the age forming die; separating the prebent test piece from the age forming die; enabling the prebent test piece to rebound, so as to form the target part. Accordingly, parts with complex molded surfaces and good material comprehensive properties are formed, the application field of the creep age forming technology is broadened, the flexibility of the forming technology of wallboard components with complex molded surfaces is improved, and the part forming precision is improved.

Description

technical field [0001] The invention relates to creep aging forming technology, in particular to a creep aging forming process method. Background technique [0002] Creep aging forming (CAF) is based on the principle of stress relaxation. The formed component is subjected to aging heat treatment while creep forming with a special mold. The stress on the formed sample is usually in the elastic range. This forming process is suitable for forming Large complex double-curvature panels with low curvature and low plastic strain, such as aircraft wing panels. This method is based on the creep / stress relaxation characteristics of metal materials, artificial aging treatment is performed, and the shape and excellent comprehensive performance of the complex component of the workpiece are obtained at the same time. [0003] At present, CAF, as an important forming method of large integral panel components in the aerospace field, has been extensively studied and achieved remarkable resu...

Claims

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Application Information

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IPC IPC(8): C22F1/00C21D8/00
CPCC21D8/005C22F1/00
Inventor 吴为张荣霞
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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