Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft

一种航空器、壳体的技术，应用在制造用于形成航空器用部件的增强壳体以及用于航空器用部件的壳体领域，能够解决不能保证等问题

Inactive Publication Date: 2008-05-28
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] Disadvantages of this method include, inter alia, the greater number of necessary processing steps, as well as the necessary assembly precision of reinforcing elements, connecting corners and shell skins, which cannot usually be guaranteed in the case of larger-sized shells

Method used

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  • Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft
  • Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft

Examples

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Embodiment Construction

[0027] 1 to 3, the following is an explanation of the inventive method and the inventive housing.

[0028] Figure 1 shows a partial perspective view of a housing to which reinforcing elements have been attached, according to a first embodiment of the method of the invention.

[0029] The housing 1 comprises a housing skin 2 , a reinforcing element 3 , and connecting elements 4 and 5 . As shown in Table 1, the reinforcing element 3 has a substantially rectangular cross-section. However, the reinforcing element 3 can also have other cross-sectional shapes. The connection elements 4 and 5 are connection corner pieces with a substantially L-shaped cross-section. The shell skin 2, the reinforcing elements 3 and the connecting elements 4 and 5 are produced from a plurality of semi-finished parts in the form of curable prepregs. Prepregs are carbon fiber reinforced sheet-like components impregnated or impregnated with curable epoxy resin. In their uncured state, virtually arbitra...

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PUM

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Abstract

The invention concerns a method for manufacturing a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, that is reinforced with a plurality of stiffening elements, for forming component parts for aircraft with high dimensional stability, wherein the stiffening elements and a shell skin are made with epoxy resin from at least partially cured carbon fiber reinforced semi-finished parts, the method comprising the following steps: positioning the stiffening elements on the shell skin, abutting connecting elements against the shell skin and the stiffening elements, and curing the connecting elements to form the shell. The invention also concerns a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, manufactured in accordance with the inventive method.

Description

technical field [0001] The invention relates to a method of manufacturing a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, which shell is reinforced by a plurality of reinforcing elements, with For the formation of parts for aircraft with high dimensional stability, wherein the reinforcing elements and shell skins are made of epoxy resin from at least partly cured carbon fiber reinforced semi-finished parts (semi-finished part). Background technique [0002] Furthermore, the invention relates to a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, manufactured according to the method according to the invention, said shell comprising A plurality of reinforcing elements for forming aircraft components with high dimensional stability, wherein the reinforcing elements and shell skins are made of epoxy resin derived from at least partially cured car...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/84B64C1/06B29C70/54B64C3/18B29C70/44
CPCB29K2307/00B29C65/48B29L2031/3082Y02T50/43B64C1/068B29C66/43441B29C70/543B29C70/44B29C70/845B29L2031/3085B29C66/112B29C65/483B29C65/5042B29C35/0227Y02T50/433B29L2031/3076B29C66/114B29K2063/00B29C65/5071B64C2001/0072B29C66/721B64C3/24B29C66/71B29C66/7212Y02T50/40B29K2307/04
Inventor 贝恩德·雷克尔斯
Owner AIRBUS OPERATIONS GMBH
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