CN1956837A - 制造窗框的方法 - Google Patents
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- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
- Y10T428/24124—Fibers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
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Abstract
一种制造安装在飞机外壳上的窗框的方法,该窗框包括至少一个外凸缘、一个内凸缘和一个垂直设置在内外凸缘之间的垂直凸缘,首先制造包括多个单独子结构的半成品部件,然后将其插入到模具中,在压力和温度下注入树脂,并且以这种方式制成的部件在模具中硬化。该半成品部件具有层结构,该层结构包括网状材料、纤维束或者网状材料与纤维束的组合。
Description
相关申请的参考
本申请要求2004年8月9日提交的美国临时专利申请No.60/600,103和2004年5月24日提交的德国专利申请No.102004025381的优先权,在此引用其全部内容作为参考。
技术领域
本发明涉及一种制造安装在飞机外壳上的窗框的方法。
背景技术
在大多数现今所制造及运行的飞机中,使用的是铝制窗框,其包括通过锻造、整形和深拉所制成的部件。该窗框被安排成总共三个区域:外凸缘、内凸缘和垂直设置在上述两缘之间的垂直凸缘。窗框通常通过外凸缘用两行铆钉连接在飞机结构上或者飞机外壳上。窗元件搁置在内凸缘上,通常包括两片窗格玻璃和布置在玻璃之间的密封件,通过一连接窗框的保持件或限位件而保持在其位置上。
除了固定窗元件外,这种窗框也具有吸收加大应变的功能,应变发生于安装在载荷传递外壳上的窗户上相对较大切口的边缘处。从而一方面窗框的外凸缘用来加强该切口,而另一方面,通过外凸缘,窗框和外壳通过铆钉相互连接到一起。由于制造这种已知的铝窗框通常是通过锻造,因此无法得到有利于铆钉力分布的窗框轮廓截面分布,因为为了能进行简单的铆接,凸缘的倾斜度最大可能会达到约两度。
内凸缘用于容纳窗元件,由此这里简化了窗安装的倾斜度。同时,由存在于客舱内部的压力所产生的载荷通过该内凸缘传递到飞机外壳。
通常,垂直凸缘专门用作窗框上的加强肋,以在最小的可能重量下最小化外壳上的张力。在该垂直凸缘上,连接有有眼螺栓,窗元件的限位件或者保持件通过该螺栓固定在其位置上。同时,当安装窗元件时,垂直凸缘还构成引导件。
发明内容
本发明的一个目的是提供一种制造窗框的方法,其可以简单、灵活并且节约成本地制造这种窗框。
根据本发明的典型实施例,提供了一种制造安装在飞机外壳上的窗框的方法,这种窗框包括至少一个外凸缘、一个内凸缘和垂直设置在这两个凸缘之间的垂直凸缘,从而通过外凸缘与飞机结构相连,通过垂直凸缘来保持的窗元件连接在内凸缘上。
根据一方面内容,首先制造由多个单独的子结构组成的半成品部件,然后将其插入到模具中,在压力和温度下将树脂注入到模具中。接下来以这种方式制成的组件在模具中硬化。
本发明可以以节省成本的方式制造多种不同的纤维复合结构的窗框,通过这种窗框,与现今使用的铝窗框相比,可以减轻50%的重量。除了能大大减轻重量的效果之外,这种部件的成本与铝锻构件制成的窗框相比并未升高。
同时,可以使得根据本发明的纤维窗框的制造公差为平均每5mm壁厚大约为0.2mm,相当于约4%的制造公差。相反地,对于铝锻窗框,根据加工方法的不同,对于同样厚度会达到大约1.5mm的公差,相当于大约30%的制造公差。因此,通过本发明,不仅仅可以在各窗框之间减轻重量波动,而且同时可以简化窗框在飞机上的安装或者窗元件在窗框上的安装。最后,根据本发明,相信能够实现其它优点,包括增强了安全性以及大大改善了绝热性。
附图说明
下面,将参考附图所示的一个实施例来更详细地介绍本发明。图中:
图1示出了窗框的透视图;
图2示出了根据图1窗框的安装位置的详细剖面图;
图3示出了图1窗框结构的分解视图。
图4示出了图1窗框的详细剖面图;
图5示出了第一预制件结构的剖面图;
图6示出了第二预制件结构的剖面图;
图7示出了第三预制件结构的剖面图。
具体实施方式
图1所示窗框1由纤维结构制成,与现有的铝锻窗框类似,也具有外凸缘2、内凸缘3以及设置在两内外凸缘之间的垂直凸缘4。与传统的铝窗框相反,在这种情况下外凸缘2具有均匀一致的周缘。另外,与相应的铝锻造部件相反,外凸缘2在不同径向区域具有变化的厚度。这使得在铆接区域和外壳切口区域具有大大改善的材料利用效率。图2用剖面图进行了更清楚地表示,其中示出了该窗框1在飞机外壳5上的安装位置。在该图中还示出了窗框连接外壳5的铆钉位置6,以及两个窗玻璃7和8,其和密封件9一起构成了窗元件。
窗框1通过所谓的“树脂转移模塑法”或者RTM技术进行制造。在此方面,首先由纤维制造模塑部件10,即所谓的预制件。其接下来放置在一个由两部分构成的模具中,闭合该模具,在压力和温度下将树脂注入该模具中。然后成品部件1在模具中硬化。
该预制件通过被称为“子预制技术”制成,其中完整的成品窗框1由多个单独的子结构元件或者子预制件11至17组成,如图3的分解视图所示。图4示出了由各子结构11至17组成的完整纤维复合窗框1的结构剖面图。相对较多数量的不同子结构能够以一种简单的方式来适应于不同的规格水平,其放置在用这种方法制造出来的窗框1上。从而,例如,对于较低载荷,该子预制件或者子结构元件14可以省略,然而相反,对于较高规格,要连接一个或多个结构元件14或者甚至可能还有结构元件15。因此各单独子预制件的良好连接性补偿了所存在的不同厚度。对于不同壁厚,可以平行移动飞机外壳5来补偿子预制件5的整个区域;这也能获得良好的连接性。
预制件大体上可以通过三种方式制成:
-网状半成品部件,
-纤维束,
-网状半成品部件与纤维束的结合。
图5示出了包括网状半成品部件的窗框1的层结构剖面图。在该图中,附图标记20表示内凸缘的0°芯部,附图标记21表示所有外部区域的±60°层以及从外凸缘2延伸到内凸缘3的±60°层,附图标记22表示垂直凸缘4区域的0°和90°层。这些层方向是在外凸缘2、内凸缘3和垂直凸缘4的交界面上测量的。在该区域以外,提供下述因素用于弯曲放置的网状半成品:
垂直凸缘4:
-所有纤维保持测量方向;
内凸缘3和外凸缘2:
-0°纤维保持为测量方向;
-±45°纤维保持测量方向,但被弯曲;
-±60°纤维保持测量方向,但被弯曲;
图6示出了带有纤维束的承载层结构,再次示出了穿过纤维束层结构的剖面图。在该图中,附图标记20表示内凸缘的0°芯部,附图标记23表示在所有外部区域的带有±60°层的纤维束以及带有从外凸缘2延伸到内凸缘3的±60°层的纤维束,附图标记24表示在垂直凸缘4区域内的带有0°和90°层的纤维束,附图标记25表示在外凸缘2区域带有±45°层的纤维束。这些层方向是在外凸缘2、内凸缘3和垂直凸缘4的交界面上测量的。为了进行纤维处理,使纤维能沿载荷方向,要选择窗框1的结构,概述如下:
外凸缘2:
-铆接区域的准各向同性径向结构;
垂直凸缘4:
-0°芯用于承受主要载荷;
-±60°层位于外侧。
内凸缘3:
-0°方向为主;
-±60°层位于外侧;
-90°用于加强。
以这种方式,各定位纤维具有下述具体细节:
垂直凸缘4:
-所有纤维保持测量方向;
内凸缘3和外凸缘2:
-0°纤维保持为测量方向;
-±45°纤维的角度变为±60°;
-±60°纤维的角度变为±70°。
最后,图7示出了带有网状结构和纤维束的组合的层结构。这里,同样附图标记20表示内凸缘的0°芯部的网状层,附图标记27表示0°卷绕挤出件(coiled push),28表示±60°网状层,29表示0°/90°网状层。
用这种方式制造的窗框1与普通的铝窗框相比在相同的制造成本下大约能减轻%50的重量。其公差基本低于相应铝部件的公差。同时,该窗框与普通的铝窗框相比能提供更高的安全性和更好的绝热性。
需要注意的是措辞“包括”不排除其它部件或步骤,“一”不排除多个的情况。同样结合不同实施例所描述的元件可以组合使用。
同样还需指出权利要求中的附图标记不应理解成是对权利要求保护范围的限制。
Claims (6)
1.一种制造安装在带有飞机结构的飞机外壳上的窗框的方法,该窗框包括外凸缘、内凸缘和大致垂直设置在该外凸缘和该内凸缘之间的垂直凸缘,其中外凸缘适于与飞机结构相连以将窗框连接到飞机上,并且窗元件抵靠着内凸缘进行支撑,该方法包括以下步骤:
提供由多个单独的子结构(11-17)构成的半成品部件;
将半成品部件插入到模具中;
在模具中注入树脂,其中该注入是在压力和温度下完成的;
在注入到模具中之后硬化该半成品部件以形成窗框(1)。
2.如权利要求1所述的方法,还包括步骤:
将该多个单独的子结构组装,以形成该半成品部件;
其中所述多个单独的子结构在将半成品部件插入模具中之前组装。
3.如权利要求2所述的方法,还包括步骤:
进行热塑焊接,以连接所述多个单独的子结构。
4.如权利要求1至3任意一个所述的方法,还包括步骤:
提供具有由网状材料制成的层结构的半成品部件。
5.如权利要求1至3任意一个所述的方法,还包括步骤:
提供具有由纤维束制成的层结构的半成品部件。
6.如权利要求1至3任意一个所述的方法,还包括步骤:
提供具有层结构的半成品部件,该层结构包括网状材料与纤维束的组合。
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004025381.1A DE102004025381B4 (de) | 2004-05-24 | 2004-05-24 | Fensterrahmen für Flugzeuge |
DE102004025381.1 | 2004-05-24 | ||
US60010304P | 2004-08-09 | 2004-08-09 | |
US60/600,103 | 2004-08-09 | ||
PCT/EP2005/005606 WO2005115728A1 (en) | 2004-05-24 | 2005-05-24 | Method for making window frame |
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CN1956837A true CN1956837A (zh) | 2007-05-02 |
CN1956837B CN1956837B (zh) | 2011-04-27 |
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CN200580016811XA Active CN1956837B (zh) | 2004-05-24 | 2005-05-24 | 制造窗框的方法 |
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US (1) | US8096506B2 (zh) |
EP (1) | EP1748879A1 (zh) |
JP (1) | JP2008500233A (zh) |
CN (1) | CN1956837B (zh) |
BR (1) | BRPI0511162A (zh) |
CA (1) | CA2563574A1 (zh) |
DE (1) | DE102004025381B4 (zh) |
RU (1) | RU2006140137A (zh) |
WO (1) | WO2005115728A1 (zh) |
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CN102041954A (zh) * | 2010-11-15 | 2011-05-04 | 陕西飞机工业(集团)有限公司 | 一种飞机舱内观察窗装饰罩装饰层的粘贴方法 |
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US20100096063A1 (en) * | 2006-11-13 | 2010-04-22 | Friddell S Douglas | Inspectability of composite items |
US7871486B2 (en) * | 2006-11-21 | 2011-01-18 | General Electric Company | Methods for making structures having mounting flanges |
FR2911111B1 (fr) * | 2007-01-05 | 2009-02-13 | Airbus France Sas | Procede d'assemblage d'un hublot pour aeronef |
BRPI0806560A2 (pt) | 2007-01-12 | 2014-04-29 | Nordam Group Inc | Quadro de janela de aeronave composto. |
CN101743117B (zh) * | 2007-02-28 | 2015-02-18 | 空中客车西班牙运营有限责任公司 | 用复合材料制造飞机框架的模具和方法 |
FR2913910B1 (fr) | 2007-03-19 | 2009-05-29 | Skf Aerospace France Soc Par A | Ensemble fibreux pour piece composite,piece composite et procede de fabrication d'une telle piece composite |
US8449709B2 (en) | 2007-05-25 | 2013-05-28 | The Boeing Company | Method of fabricating fiber reinforced composite structure having stepped surface |
DE102007049347B8 (de) * | 2007-10-12 | 2011-02-03 | Eads Deutschland Gmbh | Verfahren zur Herstellung eines Vorformlings aus Halbzeug, zur Herstellung eines ringförmigen Rahmenprofils, Verwendung des Vefahrens, sowie Rahmenprofil |
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CA2775894C (en) | 2009-10-01 | 2017-07-25 | Albany Engineered Composites, Inc. | Woven preform, composite, and method of making thereof |
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US10239289B2 (en) * | 2013-04-12 | 2019-03-26 | Hexcel Corporation | Multi-component composite structures |
FR3040014B1 (fr) * | 2015-08-14 | 2017-09-08 | Conseil & Technique | Procede de fabrication d’un cadre de forme annulaire |
DE102016210891A1 (de) * | 2016-06-17 | 2017-12-21 | Zf Friedrichshafen Ag | Verfahren und Anlage zur Herstellung eines Faserkunststoffverbundbauteils unter Verwendung von Sub-Preforms |
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-
2004
- 2004-05-24 DE DE102004025381.1A patent/DE102004025381B4/de not_active Expired - Fee Related
-
2005
- 2005-05-24 BR BRPI0511162-5A patent/BRPI0511162A/pt not_active IP Right Cessation
- 2005-05-24 CN CN200580016811XA patent/CN1956837B/zh active Active
- 2005-05-24 US US11/597,351 patent/US8096506B2/en active Active
- 2005-05-24 WO PCT/EP2005/005606 patent/WO2005115728A1/en not_active Application Discontinuation
- 2005-05-24 CA CA002563574A patent/CA2563574A1/en not_active Abandoned
- 2005-05-24 JP JP2007517109A patent/JP2008500233A/ja active Pending
- 2005-05-24 RU RU2006140137/12A patent/RU2006140137A/ru not_active Application Discontinuation
- 2005-05-24 EP EP05742702A patent/EP1748879A1/en not_active Ceased
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102041954A (zh) * | 2010-11-15 | 2011-05-04 | 陕西飞机工业(集团)有限公司 | 一种飞机舱内观察窗装饰罩装饰层的粘贴方法 |
CN102041954B (zh) * | 2010-11-15 | 2012-06-20 | 陕西飞机工业(集团)有限公司 | 一种飞机舱内观察窗装饰罩装饰层的粘贴方法 |
Also Published As
Publication number | Publication date |
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BRPI0511162A (pt) | 2007-12-04 |
US20080197237A1 (en) | 2008-08-21 |
JP2008500233A (ja) | 2008-01-10 |
WO2005115728A1 (en) | 2005-12-08 |
EP1748879A1 (en) | 2007-02-07 |
DE102004025381A1 (de) | 2005-12-22 |
CN1956837B (zh) | 2011-04-27 |
CA2563574A1 (en) | 2005-12-08 |
US8096506B2 (en) | 2012-01-17 |
RU2006140137A (ru) | 2008-05-20 |
DE102004025381B4 (de) | 2014-01-23 |
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