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Combined manufacturing method for large-scale integrated metal structure part

A technology of integral structural parts and manufacturing methods, which is applied in the field of combined manufacturing of large metal integral structural parts, to achieve the effects of eliminating the need for molds, shortening the processing cycle, and improving material utilization

Inactive Publication Date: 2016-05-11
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
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Problems solved by technology

[0003] The purpose of the present invention is: the purpose of the present invention is to propose a kind of manufacturing method of large-scale metal structure, and it can overcome the drawback of traditional manufacturing technology, make up for the deficiency of large-scale material and large-tonnage equipment, to solve the problem of aircraft large-scale metal overall structure Manufacturing issues while meeting aircraft design requirements

Method used

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Embodiment Construction

[0013] The present invention will be described in further detail below. The embodiment selects a typical structure of an aircraft (large plate and frame parts with lug bosses). If the conventional free forging process is simply adopted, it is necessary to forge a solid part capable of containing the entire part. For such a free forging, there are the following problems: One is that the specifications of raw materials need to be increased; the other is that the tonnage of forging equipment needs to be increased, and the thickness of the forgings is large, the free forging deformation is not sufficient, and the performance of the forgings cannot be guaranteed; the third is that a large amount of material removal machining is required after the forging is completed. From the above, the use of conventional forging technology to manufacture entities not only has high requirements for raw materials and equipment, but also requires a lot of raw materials, forging and machining costs, ...

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Abstract

The invention aims to provide a manufacturing method for a large-scale metal structure part. By adopting the method, the defects of a traditional manufacturing technology are overcome and the shortage of large-size materials and large-tonnage equipment is covered so that the manufacturing problem of the large-scale integrated metal structure of a plane can be solved and meanwhile the design requirements of the plane can be met. According to the method, the step-by-step forging technology and the laser rapid prototyping technology are combined, the advantages of the two technologies can be brought into full play, and hence the manufacturing method of the large-scale metal structure part can be obtained. The method specifically comprises the steps that the integrated metal structure part is divided into two parts manufactured through the step-by-step forging technology and the laser rapid prototyping technology, step-by-step forging is adopted for the body part, the laser rapid prototyping technology is adopted for the other parts, and the integrated structure part meeting the design requirements can be obtained ultimately.

Description

technical field [0001] The invention belongs to the technical field of aircraft manufacturing and relates to a combined manufacturing method of a large metal integral structural part. Background technique [0002] With the development of the aviation industry and the advancement of technology, the use of metal overall structures has become a trend, especially for large aircraft, the overall structure has significant benefits in improving aircraft life and reducing structural weight. The overall structure of metal materials is mostly made of forgings. At present, it is very difficult to obtain a large-scale overall structure that meets the design requirements through conventional forging technology in China. The main reason is that higher requirements are placed on forging equipment, forging technology and raw materials, that is, the specifications of raw materials are required to be larger, and the forging equipment has sufficient forging capacity. More stringent control ov...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00B22F3/105
CPCY02P10/25
Inventor 李宁秦锋英李辉
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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