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Method for forming integral panel of main body

A technology of integral siding and forming method, applied in the field of forming integral siding of the fuselage, can solve the problems of parts and tools prone to resonance, parts failure, etc., and achieve the effect of reliable quality, low value, and improved product quality

Inactive Publication Date: 2011-06-29
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

After the part is flattened by external force, there is a large internal stress, and the part and the tool are prone to resonance during processing, resulting in part failure. Therefore, the correct process parameters must be designed for mechanical milling

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  • Method for forming integral panel of main body
  • Method for forming integral panel of main body

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Embodiment Construction

[0013] refer to figure 1 . The outer surface of the integral wall plate part on the right side of the fuselage is an aircraft single-curvature aerodynamic shape, and only the inner surface is processed. More than 400 coordination holes need to be drilled on the siding for positioning frames, stringers and other parts, and the cutouts around the siding and door frames and window frames are of precise shape. According to the present invention, the curvature of the integral wall panel of the fuselage is first formed by rolling forming equipment; before rolling, it is confirmed whether the raw material for manufacturing the integral wall panel is flat and whether the thickness dimension meets the requirements. If it does not meet the flatness and thickness requirements, then proceed Supplementary milling processing to pass and then rolling forming. If the raw material meets the requirements, roll bending is performed directly. The integral wall panel is processed in a flat unfo...

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Abstract

The invention provides a method for forming an integral panel of a main body. The method comprises the steps as follows: firstly, the radian measure of the integral panel of the main body is formed through a roll bending forming device; secondly, the radian measure is unbent by utilizing the elastic deformation property of material after the integral panel is processed through roll bending forming, and then multi-stage steps, cut cavities and outlines are formed on the integral panel through mechanical milling; and thirdly, the restored outline / radian measure conditions of the integral panel are checked when in roll bending forming, and part of the integral panel is processed through sizing. By adopting the invention, the method that single-curved parts are processed through three-dimensional milling (comprising chemical milling and mechanical three-dimensional milling) after being formed over the years can be replaced, the manufacturing accuracy and the fatigue strength of products can be improved, the pollution on environment caused by chemical-milling solution as well as the high pollution discharge treatment cost can be avoided, and dedicated three-dimensional milling clamps and equipment for mechanical three-dimensional milling can also be avoided.

Description

technical field [0001] The invention relates to a method for machining and forming the integral wall plate of an aircraft fuselage by utilizing elastic deformation of materials. Background technique [0002] The overall panel of the aircraft fuselage is a load-bearing structural member made of a single sheet. Due to the advantages of the integral wall plate of the fuselage, such as the equal-strength design of the parts, high structural efficiency, suitable for bearing concentrated loads, smooth and streamlined aerodynamic shape, and relatively simple assembly process and good coordination, it has been increasingly used in modern aircraft. Wide range of applications. For example, the aerodynamic shape of the mid-fuselage of the DASH8 (Dash 8) Q400 aircraft developed by Bombardier is composed of five integral wall panels with a length of 8.5 meters, a width of 2 meters, and a material thickness of 2 to 6.5 mm. With the development of shot-peening forming technology, for the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00
Inventor 伍惠蒋建军阮超周豫蓉
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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