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Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof

A technology for aircraft fuselage and enclosure, applied in the direction of fuselage, aircraft accessories, home appliances, etc., can solve the problems of time-consuming, unsatisfactory, and NFC solutions do not provide fibers, etc., to simplify the manufacturing method and ensure continuity. , the effect of avoiding weaknesses and other shortcomings

Active Publication Date: 2017-05-17
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] However, these currently known solutions for strengthening the fenestration are unsatisfactory
NFC solutions do not provide controlled fiber orientation while TFP solutions are expensive and time consuming

Method used

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  • Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof
  • Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof
  • Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof

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Experimental program
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Effect test

Embodiment Construction

[0042] image 3 A roll 2 of woven material is shown. According to the invention, the perimeter of the roll of woven material is equal to the perimeter of the perforated enclosure to be produced. Therefore, the framework will have no discontinuities that could affect its coherence.

[0043] Then, along the image 3The cutting lines shown cut across the roll 2 of braided material to obtain sheets 3 of braided material. Due to the tubular condition of the braided material 2, each piece of braided material 3 has an annular shape. As noted above, this annular shape provides continuity and uniformity to the potential aperture enclosure while enhancing its strength by avoiding weakening of the joint area.

[0044] Once the endless woven material sheet 3 is obtained, said material sheet 3 is laminated around the inner mold 4 . Figure 4 A sheet of braided material 3 , an inner mold 4 and the sheet of braided material 3 laminated around the inner mold 4 are shown.

[0045] The la...

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PUM

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Abstract

The present invention refers to a manufacturing process of an aperture surrounding frame for an aircraft fuselage, the method comprising the steps of providing a tubular braiding material (2) having a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) having a surface with a desired shape for the aperture surrounding frame, laying up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing said aperture surrounding frame pre-form. The invention also refers to an aperture surrounding frame (1) for an aircraft fuselage obtained as a continuous body by forming at least one annular-shaped braiding slice (3) having a perimeter equal to the perimeter of the desired aperture surrounding frame.

Description

technical field [0001] The invention relates to a method for manufacturing an aperture surrounding frame of an aircraft fuselage and an aperture surrounding frame of an aircraft fuselage. Perforated enclosures typically include window or door frames for aircraft. Furthermore, the invention relates to a forming and injection molding tool for the manufacture of opening surrounds for aircraft fuselages. Background technique [0002] Historically, the structural elements of large airliners have typically been made of metal. For such aircraft, the fuselage shell is usually made of high-strength aluminum alloy or similar metal. [0003] However, the materials used in aviation have evolved considerably over the years in order to be able to increase their resistance while reducing their weight. For this purpose, most aircraft manufacturers are turning to fiber-reinforced resin materials, ie composite materials with a relatively high strength-to-weight ratio. [0004] Therefore, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/48B29C70/54B29C45/14B29C45/26B29B11/14B64C1/14B29L31/30B29L12/00B29L31/00
CPCB29B11/14B29C45/1418B29C45/2616B29C70/345B29C70/48B29C70/543B64C1/1461B29C2791/006B29L2012/00B29L2031/005B29L2031/3082B64C1/061B29L2031/7096B29C70/446B29C70/462B29C70/222B64C1/1492B29C70/342Y02T50/40B29C70/544B29C49/071B29C2949/0715B29C33/42B29C45/26B29K2105/08B29K2307/04
Inventor 大卫·阿方索·塞雷佐 阿尔塞梅拉尼娅·桑切斯 佩雷斯阿尔瓦罗·卡莱罗 卡萨诺瓦
Owner AIRBUS OPERATIONS GMBH
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