CN100526057C - 带填料层的层板 - Google Patents
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- 239000004033 plastic Substances 0.000 claims abstract description 12
- 229920003023 plastic Polymers 0.000 claims abstract description 12
- 239000010410 layer Substances 0.000 claims description 37
- 238000012856 packing Methods 0.000 claims description 31
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- 230000014509 gene expression Effects 0.000 description 1
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- B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
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- B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
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- Chemical & Material Sciences (AREA)
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Abstract
一种由交替错置的金属层和至少一层塑料结合层构成的层板,每个金属层包括至少两个金属层部分,所述金属层部分具有彼此结合在一起的相互交叠的边缘。为使不同部分在厚度上均匀,设置了填料层,其具有一定厚度,该厚度使得,在填料层的位置处,层板的厚度等于交叠边缘位置处的厚度。
Description
技术领域
本发明涉及一种由交替错置的金属层和至少一层塑料结合层构成的层板,其中每个金属层分别包括两个金属层部分,所述部分具有彼此结合在一起的相互交叠的边缘。
背景技术
这样的层板是公知的。所述层板可以是金属层通过粘合层彼此结合的层板;或者是在金属层之间具有渗入了粘合剂的一个或多个纤维层的层板。作为金属层部分交叠的结果,所述层板具有不均匀性,以致可在一些情况下引起不利后果。如果这类层板固定到结构件,如构架上,一个金属层部分必须被拼接以保证两个金属层部分可与构架直接接触。在用于飞机外壳的情况下,这就意味着外壳的外部也有一个拼接部,这种拼接在空气动学上是不理想的。
发明内容
因此,本发明的目的是提供一种没有上述缺点的层板。该目的通过设置填料层而实现,填料层具有一定厚度,该厚度至少使得层板在填料层的位置处,具有与交叠边缘位置处相等的厚度。
在依据本发明的层板中,其任何一侧上都没有拼接部,以使得为了组装在例如构架上,层板背对构架的一侧可保持完全平坦。优选地,填料层直接沿着(紧靠着)两个相互交叠的边缘延伸,以使层板的两侧具有尽可能一致的形状。在这一点上,在两个相互交叠边缘的每侧可以设有填料层。
相互交叠的金属层部分之一的边缘可以被拼接,以使金属层的金属层部分基本上位于彼此的延长线上。在这种情况下,填料层也可以位于彼此的延长线上。
如已经提到的,这种层板可以有利地结合到构架上。这样,不用必须在整个层板中设置填料层。因此,层板可以包括其中有至少一个填料层的部分和没有填料层的部分。
所述填料层可以不同的方法实现。例如,填料层可包括至少一个塑料结合层。在此也可以考虑包括多个金属层和多个塑料结合层。填料层也可包括其厚度大于其它金属层厚度的金属层。但是,那样塑料结合层必须相应地减薄。塑料结合层可只包括一个粘合层,或者渗有粘合剂的纤维层。
附图说明
下面参照附图中示出的实施例对本发明进行详细地解释。
图1示出了依据本发明的层板的俯视图。
图2示出了依据图1中线II—II的剖视图。
具体实施方式
图1中示出的层板包括三个层板部分1、2和3,它们依靠结合体4、5彼此固定在一起。此外,在层板中可分出两个不同的区域,即在层板的各层之间设有由附图标记8整体表示的填料层(fill)的区域6,和不带填料层的区域,换言之标准层板7。在区域6的位置处,层板可利用条形构架9固定到另一层板上。
已知在结合体4、5的位置处,由于层板的边缘在此彼此交叠,所以标准层板的厚度稍微有些大。这就意味着层板的至少一侧不平坦而在一定程度上具有阶梯。在一些应用中,这样是不理想的。例如,在用于飞机外壳的情况下,最好层板的两侧完全平坦。构架9可连接到一侧即内侧上,而同时另一侧由于其完全平坦的形式,所以具有空气动力特性。由于其它原因,层板表面平坦也是理想的。作为附加的例子,还要提到基础结构元件例如加固件、用于舱口或罩盖的边缘加强件、门开口角部。
依据本发明,整体由附图标记8表示的填料层由此设置在用于结合到构架9上的位置处的区域6中。在所述区域6之外,也就是在区域7内,不需要填料层。层板的外部在该区域完全平坦,但即使层板的内部在该区域呈现阶梯也不会成为问题。毕竟,构架不用必须在该区域连接至层板。
如图2中所示,结合体4、5以已知的方式构成,以使金属层10、11、12和13的边缘交叠。这些金属层利用纤维加固结合层14、15、16和17彼此结合。但是金属层也可利用粘合剂彼此直接结合,而在它们中间没有纤维层。
在结合体4、5的位置处,每个金属层10—13形成两个金属层部分18、19,它们分别具有各自的交叠边缘20、21。这些交叠边缘利用粘合剂22彼此固定,以便通过剪切力在层板内传递应力。
依据本发明,采用金属层24、25和塑料结合层28、29相结合形式的填料层8设置在金属层10的交叠边缘20、21的每侧上。如图1所示,根据结合体4、5的数量,可以设置多个填料层。所述填料层的厚度等于金属层10—13的厚度加上塑料结合层14—17之一的厚度,以使在结合体4、5的每侧上,层板的厚度与结合体4、5位置处的层板的厚度相同。由此,层板两侧26、27完全平坦。
Claims (11)
1、一种由交替错置的金属层(10—13)和至少一层塑料结合层(14—17)构成的层板,每个所述金属层(10—13)分别包括两个金属层部分(18、19),所述金属层部分具有彼此结合在一起的相互交叠的边缘(20、21),其特征在于,层板设有填料层(8),所述填料层包括至少一个金属层(23、24、25)并且具有一定厚度,该厚度至少使得在填料层(8)的位置处,层板的厚度与其在交叠边缘(20、21)的位置处的厚度相等。
2、如权利要求1所述的层板,其特征在于,填料层(8)直接沿着两个相互交叠的边缘(20、21)延伸。
3、如权利要求1或2所述的层板,其特征在于,在两个相互交叠的边缘(20、21)的每侧设有填料层(8)。
4、如权利要求1或2所述的层板,其特征在于,相互交叠的金属层部分(18)之一的边缘(20)是连续的,以使金属层(10—13)的所述金属层部分(18、19)基本上位于彼此的延长线上。
5、如权利要求3所述的层板,其特征在于,所述填料层(8)彼此位于对方的延长线上。
6、如权利要求1或2所述的层板,其特征在于,层板包括带有至少一个填料层(8)的区域(6)和不带填料层(8)的区域(7)。
7、如权利要求1或2所述的层板,其特征在于,填料层(8)还包括至少一个塑料结合层(28、29)。
8、如权利要求1或2所述的层板,其特征在于,填料层(8)包括至少一个金属层,该金属层的厚度大于层板中交替错置的金属层(10—13)的厚度。
9、如权利要求1或2所述的层板,其特征在于,塑料结合层包括一层粘合剂。
10、如权利要求1或2所述的层板,其特征在于,塑料结合层包括渗有粘合剂的纤维层。
11、如权利要求1或2所述的层板,其特征在于,填料层(8)设于层间。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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NL1023854 | 2003-07-08 | ||
NL1023854A NL1023854C2 (nl) | 2003-07-08 | 2003-07-08 | Laminaat met vullaag. |
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CN1819913A CN1819913A (zh) | 2006-08-16 |
CN100526057C true CN100526057C (zh) | 2009-08-12 |
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CNB2004800193812A Expired - Lifetime CN100526057C (zh) | 2003-07-08 | 2004-07-07 | 带填料层的层板 |
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Country | Link |
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US (1) | US7700174B2 (zh) |
EP (1) | EP1641611B1 (zh) |
JP (1) | JP5037940B2 (zh) |
CN (1) | CN100526057C (zh) |
BR (1) | BRPI0412383B1 (zh) |
CA (1) | CA2531536C (zh) |
NL (1) | NL1023854C2 (zh) |
RU (1) | RU2353525C2 (zh) |
WO (1) | WO2005002834A2 (zh) |
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NL1024479C2 (nl) * | 2003-10-07 | 2005-04-08 | Stork Fokker Aesp Bv | Verbindingsconstructie in een laminaat met een plaatselijke versterking. |
GB2447964B (en) * | 2007-03-29 | 2012-07-18 | Gurit Uk Ltd | Moulding material |
DE102007019716A1 (de) * | 2007-04-26 | 2008-10-30 | Airbus Deutschland Gmbh | Faser-Metall-Laminat-Panel |
ES2384920B1 (es) * | 2009-03-31 | 2013-05-21 | Airbus Operations, S.L. | Pieza de material con una rampa entre dos zonas. |
DE102009024397B4 (de) * | 2009-06-09 | 2015-10-08 | Airbus Operations Gmbh | Thermisch und/oder mechanisch fügbares Schalenbauteil zur Bildung einer Rumpfzelle eines Flugzeugs |
ES2396838B1 (es) * | 2010-09-13 | 2014-02-06 | Airbus Operations S.L. | Disposición de unión de piezas de material compuesto reforzada direccionalmente. |
TWI551208B (zh) * | 2011-10-26 | 2016-09-21 | 仁寶電腦工業股份有限公司 | 機殼 |
NL2012458B1 (en) * | 2014-03-17 | 2016-01-08 | Gtm-Advanced Products B V | Laminate of mutually bonded adhesive layers and metal sheets, and method to obtain such laminate. |
RU2570469C1 (ru) * | 2014-09-10 | 2015-12-10 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Способ соединения слоистого алюмостеклопластика |
RU2618072C1 (ru) * | 2015-11-05 | 2017-05-02 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Способ получения слоистого металлостеклопластика |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5160771A (en) * | 1990-09-27 | 1992-11-03 | Structural Laminates Company | Joining metal-polymer-metal laminate sections |
US5866272A (en) * | 1996-01-11 | 1999-02-02 | The Boeing Company | Titanium-polymer hybrid laminates |
ES2186184T3 (es) * | 1997-05-28 | 2003-05-01 | Structural Laminates Co | Procedimiento para realizar un laminado y laminado obtenido mediante dicho procedimiento. |
NL1015141C2 (nl) * | 2000-05-09 | 2001-11-13 | Fokker Aerostructures Bv | Verbindingsconstructie in een laminaat uit metalen en kunststof lagen. |
NL1019957C2 (nl) * | 2002-02-13 | 2003-10-03 | Stork Fokker Aesp Bv | Gelamineerd paneel met discontinue inwendige laag. |
-
2003
- 2003-07-08 NL NL1023854A patent/NL1023854C2/nl not_active IP Right Cessation
-
2004
- 2004-07-07 CN CNB2004800193812A patent/CN100526057C/zh not_active Expired - Lifetime
- 2004-07-07 EP EP04748712.9A patent/EP1641611B1/en not_active Expired - Lifetime
- 2004-07-07 JP JP2006518562A patent/JP5037940B2/ja not_active Expired - Fee Related
- 2004-07-07 RU RU2006103629/02A patent/RU2353525C2/ru not_active IP Right Cessation
- 2004-07-07 WO PCT/NL2004/000486 patent/WO2005002834A2/en active Application Filing
- 2004-07-07 CA CA2531536A patent/CA2531536C/en not_active Expired - Fee Related
- 2004-07-07 BR BRPI0412383-2A patent/BRPI0412383B1/pt not_active IP Right Cessation
- 2004-07-07 US US10/563,553 patent/US7700174B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
WO2005002834A2 (en) | 2005-01-13 |
JP2007521164A (ja) | 2007-08-02 |
CN1819913A (zh) | 2006-08-16 |
NL1023854C2 (nl) | 2005-01-11 |
EP1641611A2 (en) | 2006-04-05 |
EP1641611B1 (en) | 2020-08-26 |
BRPI0412383A (pt) | 2006-09-19 |
CA2531536A1 (en) | 2005-01-13 |
WO2005002834A3 (en) | 2005-03-17 |
BRPI0412383B1 (pt) | 2014-09-16 |
JP5037940B2 (ja) | 2012-10-03 |
RU2353525C2 (ru) | 2009-04-27 |
CA2531536C (en) | 2011-11-29 |
RU2006103629A (ru) | 2006-08-10 |
US20060159886A1 (en) | 2006-07-20 |
US7700174B2 (en) | 2010-04-20 |
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