CN101437668A - 用于抑制分层的装置和方法 - Google Patents
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Abstract
一种用于对层叠元件(2)的弯曲区域进行压缩的压缩装置,该弯曲区域具有沿第一弯曲路径的第一表面区域以及与所述第一表面区域对向的沿第二弯曲路径的第二表面区域,其中抵靠所述第一表面区域放置第一压缩件(40),并将其推向抵靠所述第二表面区域放置的第二压缩件(50)。
Description
技术领域
本发明涉及一种用于对层叠元件或结构的弯曲区域进行压缩以防止所述元件或结构分层的装置和方法。
背景技术
与很多现有金属材料相比,纤维加强层叠件在硬度和耐用性方面提供了相当多的优点。因此它们在很多行业、特别是在结构重量至关重要的飞行器制造中有广泛的应用。然而,在设计纤维加强层叠件时也存在一些复杂的情况。主要设计考虑因素源自这样一个事实,在最终产品中,多数载荷承受性能得自结构中的纤维排列。通常,将结构设计成待由结构承受的主要载荷作用在纤维层的纵向方向上。
层叠结构通常通过在上述纤维层上构造一个纤维层来设置。在每一纤维层内,所有纤维沿同一方向延伸。也就是说,每层不是经纬纤维编织的状态,因为经纬纤维编织必然会在纤维中产生褶皱而减小其抵抗压缩载荷的能力。为了生产组件,交替层沿不同方向布置,一般相互成90°。然而,简单地看,如果考虑由这样的层叠材料层制成的平坦面板,可以看出该面板相对于作用在面板平面上的力来说可能制造得比较坚固,但是没有垂直于面板平面延伸的纤维。因此,该面板对于试图使面板层相互分离的张力来说会相对较弱。当考虑平面元件的构造时,这一局限性通常不显著,但是当层叠元件中形成有弯曲时就变得更显著了。
发明内容
根据本发明的第一方面,提供一种用于压缩层叠元件的弯曲区域的压缩装置,该弯曲区域具有沿第一弯曲路径的第一表面区域以及与所述第一表面区域对向的沿第二弯曲路径的第二表面区域,其中抵靠所述第一表面区域放置第一压缩件,并将其推向抵靠所述第二表面区域放置的第二压缩件。
因此,可将层叠元件的弯曲区域夹在第一压缩件和第二压缩件之间,所述第一压缩件和第二压缩件有效地用作夹具的钳子,从而确保层叠元件的弯曲部中的纤维对于小于预定最大载荷的载荷总是相对于相邻载荷层保持处于压缩状态。
通常,所述层叠元件的弯曲区域被定义为构成所述元件的壁与凸缘之间的界面,使得所述层叠元件可被固定至相邻元件。所述弯曲区域可形成可延伸相当大距离的部分柱面。有利的是,所述第一压缩件和所述第二压缩件是细长件,使得可抵靠第一表面区域和第二表面区域中的每一个放置一个或多个部件,以在所述层叠元件的弯曲区域的长度的相当大的部分上并且优选在全部长度上保护该弯曲区域。
有利的是,至少一个紧固件在拉伸状态下在所述第一压缩件和所述第二压缩件之间延伸,从而将它们朝彼此推动,从而夹紧二者之间的所述层叠元件的弯曲区域。
根据本发明的第二方面,提供一种组合件,该组合件为具有弯曲部的层叠元件与根据本发明第一方面的用于压缩层叠元件的弯曲部的压缩装置的组合。
所述组合件还可包括第二元件,该第二元件可通过例如螺钉、螺栓、铆钉或者粘合剂之类的紧固件连接至所述层叠元件。通常,所述层叠元件具有可连接至所述第二元件的凸缘。优选的是,该凸缘适于与所述第二元件的表面基本平行。
通常,所述弯曲部在所述层叠元件的第一侧具有凹面,在所述层叠元件的第二侧具有凸面,并且所述第二元件适于被连接至所述层叠元件的第二侧。
根据本发明的第三方面,提供了一种防止层叠元件的弯曲区域分层的方法,该方法包括抵靠所述弯曲区域的第一表面放置第一部件,并且抵靠所述弯曲区域的第二表面放置第二部件,所述第一表面和所述第二表面位于所述弯曲区域的相对两侧,并将所述第一部件和第二部件推向一起以便将它们之间的所述弯曲区域置于压缩状态。
附图说明
参考相应的附图仅以实施例方式对本发明进行进一步描述,其中:
图1示意性地表示作用在第一层叠元件的平面内的力如何在所述元件的弯曲区域引起分层力;
图2表示现有技术的方案;
图3是构成本发明实施方式的压缩装置的平面图;和
图4是表示使用图3的装置以便于将翼梁连接至翼表面的立体图。
具体实施方式
图1示意性示出了在总体标为2的第一层叠元件和第二元件4之间的界面。第二元件4可以是层叠的或者不层叠的。元件2和4通过多个紧固件连接在一起,为简单起见示出了其中一个紧固件6。该紧固件可以是任意合适的紧固件,其用于将元件2和4保持在一起,以抑制元件2和4之间响应于作用在它们之间的载荷而产生的相对运动。适合的紧固件可包括但不限于螺钉、螺栓、铆钉和粘合剂。元件2具有弯曲区域10,其包括在元件2的第一侧上的凹面、和在元件2的第二侧上的凸面。元件4被连接至元件2的第二侧(即与凸面位于同一侧)。为了方便讨论,假设紧固件6是螺栓,该螺栓可选的地具有沉头以使外表面光滑,并且期望载荷沿A或B的方向作用,以使载荷基本垂直于面板4且基本上作用在面板2的不弯曲区域8的平面内。然而,可以看出,在面板2的整体标为10的弯曲区域中,该面板内的力没有沿着面板内的局部纤维轴线。
虽然面板2是实心的,但是有益的是考虑仅作用在面板2的最内表面和最外表面上的载荷。面板的弯曲区域可被视为在第一虚线12和第二虚线14之间延伸。可以看出,面板的最内表面16上的在线12和14之间延伸的纤维长度LI,小于面板的最外表面18上的在同样的线12和14之间延伸的纤维长度LO。
可以直观地看出,如果一个力沿着方向C作用以试图使面板的弯曲区域10变直,那么随着弯曲部被从面板去除,也就是说弯曲部从其制造角张开,线12和14之间的沿着内表面和外表面的距离将趋于相等。然而,纤维抵抗拉伸或者压缩,这产生一个力,该力沿着箭头F的方向作用,促使复合材料的邻近层互相分离。该力被称为“全厚”拉伸载荷,其将层叠件的保持邻近层的树脂置于拉伸状态,如果所述力超过树脂的拉伸强度,则层叠产品就会分层。层叠件内的材料矩阵没有沿着与其表面正交的方向被加强,因此与层叠产品的局部平面内的强度相比,其抵抗这种分层力的能力不足。尽管不是很直观,但是事实上沿方向A或B作用的力也会产生与会使弯曲部从其制造形状张开或闭合的作用力相同的效果,并可引起同时发生在弯曲部的不同部位处的两种作用。读者通过在适当情况下沿着与图1中所示类似的弯曲路径折叠一沓纸然后沿着方向A或B施加力可观察到这一点。当施加力时(要记住面板2的平面部分8的位置通常被禁止横向移动),曲率半径会略微变化而致使部分弯曲部受到在内外表面之间作用的压缩力,弯曲部的其它部分受到在内外表面之间作用的拉伸力。
对在层叠结构的角部半径内产生的抵抗施加载荷的内部载荷进行控制的这一问题是公知的,且在现有技术中已提出了解决该问题的方案。这种解决方案之一是包含从紧固件延伸进角部半径的“喉部”28(如图2所示)的各个垫圈,这些垫圈试图将载荷传递到更加靠近接合部的平面(图2中所示的垂直部分)。因此,在该实施例中,垫圈30具有非圆形对称外形,且具有朝层叠元件2的弯曲表面34延伸的部分32。垫圈的外形制成为与所述弯曲表面34匹配,从而将载荷传递到层叠元件的垂直部分内。在图2中,该垫圈和元件2、4被示出为通过与螺母38配合的螺栓36接合在一起。可以看出这种方案只是部分成功的,且只能被应用于具有诸如螺栓或螺钉之类的贯通紧固件的接合部。其对粘合连接不起作用。
试图保护元件2的弯曲区域免于分层的其他现有技术是将“Z形销”插入穿过层叠材料。存在纤维的有效短部分,它们基本上垂直于层叠元件的局部表面的法线延伸,试图在垂直于该局部表面的方向上增大层叠元件的强度。然而,Z形销本身仅通过用于将结构粘合在一起的树脂固定至层叠结构,因此可被Z形销吸收的最大作用力因距层叠结构表面的距离而异。这是因为,对于任意一纤维加强材料而言,加强功效与纤维长度成比例。因此,在层叠件的薄部,Z形销不够长,从而不能完全吸收并抵抗倾向于使材料分层的载荷。另外,当Z形销被插入层叠件中时,这些Z形销使现有纤维产生变形,这可导致层叠件内的性能整体下降,且该下降也与层叠件的厚度成比例。
为了避免分层的危险,本发明人意识到层叠结构的弯曲部应该被预加载至压缩状态,使得层叠结构的邻近层被压向彼此。其结果是,结构内的趋向于推动邻近层分离的内部作用力此时不得不克服压缩预载,从而吸收所有(或者至少显著降低)由角部的任何“张开”产生的全厚载荷。
为了提供预载,在元件2的弯曲区域10的凸起侧设置第一压缩件40,在该弯曲区域的凹入侧设置第二压缩件50。第一压缩件具有大致柱形的凹面42,其适于密切匹配元件2的凸外表面18的相应曲率半径。有利的是,可设置任何制造公差,使得所述凹面的曲率半径或多或少地大于弯曲区域中的凸外表面18的曲率半径,以使它们之间的任何间隙可被填充件(例如,树脂和微粒混合物)填充,从而确保在第一压缩件40和层叠元件的最外表面18之间进行均匀的载荷传递。
第二压缩件50具有柱形的凸面52,其与元件2的内凹曲面54的曲率半径基本匹配。这里,凸面侧应具有任意制造公差,使得凸面的曲率半径略小于凹面54的曲率半径,以使它们之间的任何间隙被填充件填充。如图4中所示,第一和第二压缩件可以为细长的拉伸件。第一和第二压缩件被多个紧固件60推动成与层叠元件2的相应配合表面接合,这些紧固件在拉伸状态下穿过贯通第一压缩件40和第二压缩件50以及在二者之间延伸的层叠结构的弯曲部延伸的相应通道(例如,钻孔)延伸。
所述或者每个拉伸紧固件可例如是螺栓或螺钉。该螺栓可与外部设置的螺母接合,或者与其中一个压缩件的螺纹部分接合。如图3所示,在适当情况下,可在螺栓64的头部与压缩件40或50中的任一个(在本实施例中为第二压缩件50)之间设置垫圈62,从而使压缩力在压缩件40和50内更均匀地展开。图3中所示的第一压缩件40在其通道中设有内螺纹面,以便与螺栓上的螺纹接合。
压缩件40和50可由任何合适材料制成,因此例如可由挤压金属制成。铝是一种合适的备选材料。然而,所述压缩件可方便地由其中纤维的纵向平行于压缩件的纵向轴线(即,图4中所示的上下方向)的纤维加强层叠件制成。压缩件由纤维加强层叠件制成的优点在于,固定层叠元件2的任一侧的压缩件所用的金属固定件的电化腐蚀减小。
所述压缩件可被视为加强元件,并且可自身有助于与接合部本身的交接。因此,观察图4,压缩件40抵靠元件4,这样可有助于元件2和元件4之间的载荷传递。而且,如果在压缩件40与元件2、4之间使用粘合剂,则接合部的整体强度增加。
紧固件60的设置(数量、尺寸和中间紧固件距离)由局部载荷并因此由所需的预加载程度决定。因此,可在变化很大的载荷范围内使用相同尺寸的压缩件,只要针对期望载荷使用适当数量的紧固件即可。
压缩件在元件2成形之后,优选在树脂固化之后在元件2周围放置。因此,钻通孔的动作不会破坏层叠件内除孔自身的区域之外的纤维排列。由于层叠组件的整体完整性未受到太大的不利影响,从而组件2的组合性能及其压缩布置会明显优于单独的未经改变的等同组件2。
本发明特别适用于航空领域。元件2可例如是在飞行器机翼内在上下表面之间延伸的翼梁,在这种情况下元件4可以是机翼的最上表面或者最下表面(附图可适当地重新取向)。
Claims (23)
1、一种用于对层叠元件的弯曲区域进行压缩的压缩装置,该弯曲区域具有沿第一弯曲路径的第一表面区域以及与所述第一表面区域对向的沿第二弯曲路径的第二表面区域,其中抵靠所述第一表面区域放置第一压缩件,并将其推向抵靠所述第二表面区域放置的第二压缩件。
2、如权利要求1所述的装置,其中至少一个紧固件在所述第一压缩件和所述第二压缩件之间延伸。
3、如权利要求2所述的装置,其中所述至少一个紧固件穿过所述层叠元件中的通道延伸。
4如权利要求2所述的装置,其中所述紧固件或每个紧固件穿过所述层叠元件中的相应通道。
5、如权利要求2、3或4所述的装置,其中所述至少一个紧固件在使用中处于拉伸状态。
6、如前述权利要求中任一项所述的装置,其中所述第一压缩件具有适于与所述层叠元件的第一表面区域匹配的凹面。
7、如前述权利要求中任一项所述的装置,其中所述第二压缩件具有适于与所述层叠元件的第二表面区域匹配的凸面。
8、如前述权利要求中任一项所述的装置,其中所述压缩件之一内具有与带螺纹的紧固件接合的螺纹孔。
9、如前述权利要求中任一项所述的装置,其中所述层叠元件被固定至另一元件,且所述压缩件之一与该层叠元件及该另一元件均抵接。
10、一种组合件,该组合件为具有弯曲部的层叠元件与前述任一权利要求所述的用于压缩该层叠元件的弯曲部的压缩装置的组合。
11、如权利要求10所述的组合件,该组合件还包括可连接至所述层叠元件的第二元件。
12、如权利要求11所述的组合件,其中所述层叠元件具有可连接至所述第二元件的凸缘。
13、如权利要求12所述的组合件,其中所述凸缘适于与所述第二元件的表面基本平行。
14、如权利要求11至13中任一项所述的组合件,其中所述弯曲部在所述层叠元件的第一侧具有凹面,在所述层叠元件的第二侧具有凸面,并且其中所述第二元件适于被连接至所述层叠元件的第二侧。
15、如权利要求11至14中任一项所述的组合件,该组合件还包括一个或多个用于将所述层叠元件连接至所述第二元件的紧固件。
16、如权利要求10至15中任一项所述的组合件,其中在所述第一元件和第二元件之间延伸有一个或多个紧固件,且所述紧固件处于拉伸状态。
17、如权利要求16所述的组合件,其中至少一个紧固件穿过所述层叠元件的弯曲部。
18、一种包括如权利要求1至9中任一项所述的压缩装置的飞行器。
19、一种包括如权利要求10至17中任一项所述的元件组合件的飞行器。
20、一种防止层叠元件的弯曲区域分层的方法,该方法包括抵靠所述弯曲区域的第一表面放置第一部件,并且抵靠所述弯曲区域的第二表面放置第二部件,所述第一表面和所述第二表面位于所述弯曲区域的相对两侧,并将所述第一部件和第二部件推向一起以便将它们之间的所述弯曲区域置于压缩状态。
21、如权利要求20所述的方法,其中在所述第一部件和所述第二部件之间延伸有紧固件,并且所述紧固件在使用中处于拉伸状态。
22、如权利要求20或21所述的方法,其中所述第一部件和第二部件的外形设定成具有与所述层叠元件的弯曲区域的表面互补的表面。
23、如权利要求20至22中任一项所述的方法,该方法还包括将一第二元件连接至所述层叠元件。
24、如权利要求20至23中任一项所述的方法,其中所述弯曲区域在所述层叠元件的第一侧具有凹面,在所述层叠元件的第二侧具有凸面,并且其中所述第二元件被连接至所述层叠元件的第二侧。
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CN103261022B (zh) * | 2010-12-14 | 2016-09-28 | 波音公司 | 降低层压桁条组件的分层风险的倾斜角半径填料 |
CN103492158A (zh) * | 2011-04-26 | 2014-01-01 | 株式会社Ihi | 成形部件 |
CN103492158B (zh) * | 2011-04-26 | 2016-06-15 | 株式会社Ihi | 成形部件 |
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CN110552937A (zh) * | 2018-05-31 | 2019-12-10 | 斯凯孚航空法国公司 | 包括连接件和至少两个承载件的连接组件 |
CN110552937B (zh) * | 2018-05-31 | 2022-11-04 | 斯凯孚航空法国公司 | 包括连接件和至少两个承载件的连接组件 |
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GB0609166D0 (en) | 2006-06-21 |
CN101437668B (zh) | 2012-11-14 |
BRPI0709782A2 (pt) | 2011-07-26 |
WO2007128997A1 (en) | 2007-11-15 |
EP2021164B1 (en) | 2014-05-21 |
JP2009536114A (ja) | 2009-10-08 |
US9346223B2 (en) | 2016-05-24 |
CA2646552C (en) | 2015-02-17 |
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US20100224084A1 (en) | 2010-09-09 |
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