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Installation tool for airplane thin-wall component, tool manufacturing method and application method

A production method and a technology for installing tooling, applied in the aviation field, can solve problems such as failure to assemble composite material components, extrusion deformation, and difficult parts to fit perfectly.

Active Publication Date: 2021-08-13
浙江万丰飞机制造有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the fact that some thin-walled metal or wooden installation tools are difficult to achieve a perfect fit with the parts, it is easy to be squeezed and deformed during the bonding process of the parts, resulting in the phenomenon that the composite material components cannot be assembled.

Method used

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  • Installation tool for airplane thin-wall component, tool manufacturing method and application method
  • Installation tool for airplane thin-wall component, tool manufacturing method and application method

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Embodiment Construction

[0024] The tip rib of the wing is made of two layers of 92125 fiber cloth, with an average thickness of about 0.6mm. It is difficult to form a perfect fit between ordinary wooden tooling and the root rib of the wing tip, and it is easy to be squeezed and deformed during the gluing process, which makes it difficult to assemble the wing tip and the wing.

[0025] The invention provides an installation tool for aircraft thin-walled parts, such as figure 1 , including a frock body 1 and a handle insert 2 connected with the frock body, the outer contour of the frock body is copied to the inner surface of the tip rib of the wing. The steps to use the installation tool are as follows:

[0026] Step 1: Glue the corresponding small parts of the wing tip to the lower shell of the wing tip;

[0027] Step 2: Clamp the upper and lower shells of the wing tip;

[0028] Step 3: The worker holds the handle insert 2, presses the tooling body 1 into the inside of the wing tip rib, squeezes ou...

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Abstract

The invention discloses an installation tool of an airplane thin-wall component, a tool manufacturing method and a using method. The installation tool comprises a tool body and a handle insert, and the outer contour of the tool body is profiled on the inner surface of the component. The manufacturing method of the installation tool for the airplane thin-wall component comprises the following steps: attaching a transparent adhesive tape to the surface of the component; coating the surface of the component with a release agent; paving multiple layers of fiber cloth on the surface of the component; carrying out pre-curing treatment; demolding; gluing a corresponding insert; and after proper trimming and polishing, curing, and forming the installation tool. The application method of the installation tool comprises the following steps that the aircraft thin-wall component is glued to the corresponding position; the tool is pressed into the part, redundant adhesive is extruded out, and the outer wall of the part is evenly attached to the periphery of the part; and the tool and the component are separated after being subjected to pre-curing treatment, and then the component is trimmed and polished. According to the invention, the actual problem of extrusion deformation of an adhesive on a part in the composite material bonding process is solved.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to the installation of general aircraft thin-walled parts. Background technique [0002] General-purpose aircraft has extremely high requirements on the performance and lightweight properties of materials, and composite materials have been widely used in general-purpose aircraft because of their excellent performance. In the manufacturing process of aircraft composite materials, it is necessary to strictly control each procedure and continuously optimize the production process in order to ensure the high performance and light weight of the product and improve the competitiveness of the product. [0003] In the manufacturing process of aircraft composite materials, there are two curing procedures: pre-curing and post-curing. The post-curing procedure is usually carried out after it is bound and molded with the fuselage or wing. Therefore, composite parts only undergo a pre-curing ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/10B64F5/00
CPCB64F5/10B64F5/00Y02T50/40
Inventor 喻世豪张良多陈滨吕元
Owner 浙江万丰飞机制造有限公司
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