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1. 发明申请

WO2007003372A1 PROCESS FOR PRODUCING A SUBSTANTIALLY SHELL-SHAPED COMPONENT 审中-公开
标题翻译：用于生产大量壳形成分的方法
公开(公告)号：WO2007003372A1
公开(公告)日：2007-01-11
申请号：PCT/EP2006/006384
申请日：2006-06-30
申请人： AIRBUS DEUTSCHLAND GMBH , LAW, Barnaby , SCHUMACHER, Kai , KOMADINA, Jonathon , MUELLER, Jochen , HELTSCH, Norbert
发明人： LAW, Barnaby , SCHUMACHER, Kai , KOMADINA, Jonathon , MUELLER, Jochen , HELTSCH, Norbert
IPC分类号： B29C70/84 , B29C70/44 , B64C1/12 , B29D31/00
CPC分类号： B64C1/12 , B29C70/44 , B29C70/84 , B29L2031/3082 , B29L2031/3085 , Y02T50/43
摘要： The invention relates to a process for producing a substantially shell-shaped component, from substantially carbon-fiber-reinforced synthetic material having at least one local reinforcing zone 3 and at least one stiffening element, in particular a fuselage shell, a wing shell, a vertical stabilizer shell or horizontal stabilizer shell of an aircraft or the like. The process according to the invention comprises the following steps: arranging at least one doubler 1 which has already been cured, on an at most partially cured shell skin 2 to form the local reinforcing zone 3, applying at least one stiffening element which has already been cured, and placing at least one at most partially cured connecting angle bracket 6 against the at least one stiffening element at least in the region of the at least one doubler 1, and curing the shell skin 2 and the connecting angle bracket 6. The invention also includes a substantially shell-shaped component having at least one local reinforcing zone 3 and having at least one stiffening element produced by the process according to the invention.
摘要翻译：本发明涉及一种从基本上碳纤维增强的合成材料制造基本上壳形的部件的方法，所述合成材料具有至少一个局部增强区域3和至少一个加强元件，特别是机身壳体，翼壳，飞机的垂直稳定器壳体或水平稳定器壳体等。根据本发明的方法包括以下步骤：将已经固化的至少一个倍增器1布置在最多部分固化的壳层2上以形成局部增强区3，施加至少一个已经被加工的加强元件固化，并且至少在至少一个倍增器1的区域中至少部分地固化的连接角支架6抵靠至少一个加强元件，并且固化壳体皮肤2和连接角度支架6.本发明还包括具有至少一个局部增强区3并且具有通过根据本发明的方法制造的至少一个加强元件的基本上壳形的部件。

2. 发明申请

WO2008119701A1 METHOD FOR PRODUCING A STRUCTURAL COMPONENT 审中-公开
标题翻译：生产结构部件的方法
公开(公告)号：WO2008119701A1
公开(公告)日：2008-10-09
申请号：PCT/EP2008/053539
申请日：2008-03-26
申请人： AIRBUS DEUTSCHLAND GMBH , LAW, Barnaby , LENGSFELD, Hauke
发明人： LAW, Barnaby , LENGSFELD, Hauke
IPC分类号： B29C70/34 , B29C70/54
CPC分类号： B29C70/342 , B29C70/543 , B29K2063/00 , B29K2105/24 , B29K2105/243 , B29K2105/246 , B29K2707/04 , B29K2709/08 , Y02T50/43 , Y10T156/1002
摘要： This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric (6) is formed from a composite fibre material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric (6) is then connected to at least one hardening part (12, 13) of a composite fibre material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric (6) in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric (6) connected to the at least one holding part (12, 13) is hardened at the first hardening temperature to form the structural component. The idea on which this invention is based consists in replacing expensive tools of special steel previously used for holding dimensionally unstable prepreg fabrics with at least one holding part (12, 13) of composite fibre materials, wherein the at least one holding part (12, 13) has a lower hardening temperature than the prepreg fabric (6), and can therefore be produced with a lower cost tool.
摘要翻译：本发明提供了一种用于制造结构部件的方法，特别是在航天领域。未硬化的预浸渍织物（6）由可在第一硬化温度下固化的复合纤维材料形成为预定形状。然后将未硬化的预浸渍织物（6）连接到在第二硬化温度下部分硬化的复合纤维材料的至少一个硬化部分（12,13），用于将未硬化的预浸料坯料（6）保持在预定形状，其中第二硬化温度低于第一硬化温度。在另一方法步骤中，连接到所述至少一个保持部件（12,13）的未硬化预浸料织物（6）在第一硬化温度下硬化以形成结构部件。本发明所基于的想法在于：用至少一个复合纤维材料的保持部件（12,13）代替先前用于保持尺寸不稳定的预浸料织物的特殊钢的昂贵工具，其中至少一个保持部件 13）具有比预浸织物（6）更低的硬化温度，因此可以用较低成本的工具生产。

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