CN104470707A - 通过树脂传递模塑制造t形复合部件的方法 - Google Patents
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Abstract
本发明涉及一种通过树脂传递模塑制造T形复合部件的方法,包括下列步骤:构成具有基本上平面的层片叠层(A)和具有两个L形的层片叠层(B,C)的预成型体;放置所述预成型体使得所述L形叠层(B,C)满足在树脂传递模塑工具(M)的两个型芯(M1,M2)之间;通过所述平面叠层(A)在垂直或准垂直于该叠层(A)的方向上插入和移出纤维,使得在基本上垂直于所述平面叠层的所述L形叠层(B,C)的部分(81,82)内形成环圈(b);闭合模塑工具(M);将树脂注入到模塑工具(M)中,以及加热模塑工具(M),从而使树脂固化。
Description
技术领域
本专利申请涉及采用复合材料制造部件,特别是用于航空的部件的领域。
背景技术
如本身所已知的,采用复合材料的部件可由纤维,特别是碳或玻璃的纤维的组织(通常称作“层片”)制成,其中用树脂(例如聚酰亚胺)浸渍这些组织,然后通过升高高压釜中的温度使树脂聚合。
通过这种方式获得了实际上可以具有任何几何形状以及电阻/重量的优异组合的部件。
存在不同的树脂浸渍技术:可以使用预浸渍的树脂层片或树脂传递方法。
这类方法,通常用于制造航空用部件,一般被称为RTM(“树脂传递模塑”)。
这项技术包括将由层片集合体构成的预成型体放置在闭合模具中,树脂在压力下被注入该闭合模具中。由此,这种树脂行进通过层片,并且逐渐填充所有可能的间隙。一旦完成这一填充,模具的温度升高,从而使树脂固化。
这项技术特别地用于制造T形部件,也就是说,用于制造包括基本上相互垂直的两个部分1、2的部件,如说明书附图1和图2中所见。
这类部件可特别地用于制造梁。
更具体地,制造这样一种部件,使用三个层片叠层:一个基本上平面的叠层A,以及两个基本上L形的叠层B和C,后两者被连接从而限定T形部件的基部。
当用树脂浸渍由叠层A、B和C构成的预成型体时,通常在这三个叠层的接合区域中观察到树脂簇3的形成。
该树脂簇没有纤维是最后获得的部件的一个弱点:实际上,它可能是周围层片分层的原因,并且限制了对倾向于使叠层B和C与叠层A分离的拉伸力(在图1和图2上的箭头5)的抵抗性。
为了克服这些缺点,至今为止使用两种解决方案。
第一种解决方案包括预填充三个固定在一起的纤维集合体叠层的接合区域:关于所述接合区域的横截面的形状称为“钉头”的这种解决方案在工业过程中产生许多困难。例如,所添加的纤维可在树脂注入期间移动,并最终占据对于对外力的抵抗性不是最佳的位置。
第二种解决方案包括将叠层A、B、C一起缝合在它们的接合区域中,如图2中所见(缝线7)。这种解决方案的缺点是仅能够在将由叠层A、B、C构成的预成型体建立在RTM模具上之前实现,RTM模具尤其包括防止缝合针穿到适当的点的两个金属型芯。另外,这种缝合解决方案实际上仅使得对倾向于使叠层B和C与叠层A分离的拉伸力的抵抗性的增加相当低。
发明内容
因此,本发明的目的尤其在于提供一种通过树脂传递模塑制造T形复合部件的方法,该方法易于工业化并且具有对于倾向于将T形复合部件的两个部分彼此分离的力的改进的抵抗性。
本发明的这个目的用一种通过树脂传递模塑制造T形复合部件的方法来实现,该方法包括下列步骤:
构成具有基本上平面的层片叠层和具有两个L形的层片叠层的预成型体,
放置所述预成型体使得所述L形叠层满足在树脂传递模塑工具的两个型芯之间,
通过所述平面叠层在垂直或准垂直于该叠层的方向上插入和移出纤维,使得在基本上垂直于所述平面叠层的所述L形叠层的部分内形成环圈,
闭合模塑工具,
将树脂注入到模塑工具中,以及
加热模塑工具,从而使树脂固化。
由于在这种方法中,纤维在平面的层片叠层的相同面上进入和离开,因此,一旦预成型体的不同叠层被放置在模塑工具的型芯之间,可以执行预成型体的不同叠层的接合区域的固结,在工业过程中这更易于实现:完成纤维环圈的缝合机的移动实际上可以限于线性移动。
另外,形成环圈的纤维的取向垂直于平面层片叠层,以及在基本上垂直于平面层片叠层的L形层片叠层的部分中的这些纤维的通道,也就是说实际上在T形复合部件的基部,提供了对于倾向于从平面叠层拉出L形叠层的力的特别显著的抵抗性。
下面是根据本发明所述的方法的其他可选特征:
在将预成型体引入模塑工具的两个型芯之间之前,将所述平面叠层和所述L形叠层进行组装;
对所述L形叠层进行组装,将其引入模塑工具的两个型芯之间,并且用所述平面叠层覆盖;
将所述L形叠层和所述平面叠层中的每一个一个接一个地放置在模塑工具中;
形成不同长度的环圈;
形成相对于垂直于所述平面叠层的方向稍微倾斜的环圈;
形成第一组环圈和第二组环圈,所述第一组环圈相对于垂直于所述平面叠层的方向的长度和倾斜度大于所述第二组环圈相对于垂直于所述平面叠层的方向的长度和倾斜度。
本发明还涉及根据上述方法获得的复合部件。
附图说明
根据接下来的说明以及对附图的审查,本发明的其他特征和优点将变得显而易见,其中:
图1是现有技术的复合部件的横截面视图,如本说明书的前面部分中所述,
图2是该同一部件的透视图,
图3是在利用本发明所述的方法进行制造期间的复合部件的剖视图,
图4是一旦制造好的该部件的横截面视图,以及
图5是利用根据本发明所述的方法制造的另一个部件的横截面视图。
在所有这些图中,相同或相似的附图标记表示相同或相似的构件或构件组。
具体实施方式
现在参考图3,在其中可以看到由平面的层片叠层A和由两个L形的层片叠层B和C所限定的预成型体被放置在模塑工具M上。
更具体地,L形的层片叠层B和C的部分(这些部分基本上垂直于平面的层片叠层A)被放置在模塑装置M的两个金属型芯M1和M2之间。
注意到,可以在将如此形成的预成型体引入两个型芯M1和M2之间之前将平面的层片叠层A组装到两个L形的层片叠层B和C。
根据另一个可能性,可以通过组装两个L形的层片叠层B和C开始,然后将它们引入两个型芯M1和M2之间,并且最后用平面的层片叠层A将其覆盖。
仍然根据另一个可能性,可以将L形的层片叠层B和C以及平面的层片叠层A中的每一个一个接一个地放置在模塑工具M中。
无论所保持的组装顺序如何,由此实现图3中所示的结构,其中在基本上垂直于平面的层片叠层A的L形的层片叠层B和C的部分81和82内完成纤维环圈b。
更具体地,通过包括针9的自动缝合机,这些纤维被从其自由面11插入到平面层片叠层A内,纤维穿透到每个L形的层片叠层B和C的各部分81和82内,在该部分内完成环圈b,然后在该叠层的该纤维的入口点附近由平面层片叠层A的自由面11除去纤维。
环圈b外的纤维的总方向基本上垂直于平面叠层A,如图3中所见。
根据需要该操作被再现多次,以便获得限定形成在L形的叠层B和C的部分81和82内的环圈b1、b2、b3中的每一个的多个纤维,这些纤维的总方向基本上垂直于平面叠层A。
这种执行环圈的方法,允许机器在复合的层片预成型体的一个面上作业,通常被称为“簇绒法”。
一旦这些执行的环状纤维被建立,模塑工具M闭合,并且这些纤维在压力下被注入到聚合树脂内,然后将填充由层片叠层A、B、C所限定的预成型体中的所有间隙。
该树脂将特别地被放置在形成环圈b1、b2、b3的纤维周围。
一旦执行这种树脂引入,模塑工具M温度升高,允许该树脂的快速聚合。
形成环圈b1、b2、b3的纤维使得三个层片叠层A、B、C的接合区域具有很强的抵抗性增强。
特别地,这些纤维允许获得对L形的层片叠层B和C相对于层片叠层A拉出的优异的抵抗性。
还应该注意的是,相比于如图2所示的传统的缝合操作,一旦预成型体在模塑工具M上,进行簇绒的可能性从工业的角度上是很方便的,需要一个或多个缝合机在预成型体的几个面上移动。
当然,可以随意选择形成环圈b1、b2、b3的纤维的特征,以及这些环圈的形状和空间分布。
例如,这些环圈可由碳纱制成,并且相对于彼此以3mm的间距间隔开,穿透到L形的叠层B和C的部分81和82内五十毫米。
同样作为例子,形成叠层A、B和C的层片可由缎纹碳形成。
叠层A可以包含例如20个层片,并且叠层B和C各包含5个层片。
图5示出了其中层片叠层A、B、C之间的接合与图4的实施例相比进一步得到加强的一个实施例。
在该实施例中,实际提供了第一组环圈b1、b2、b3和第二组环圈b4、b5,第一组环圈b1、b2、b3相对于垂直于平面叠层A的方向P的长度l1和倾斜度α1大于第二组环圈b4、b5相对于垂直于平面叠层A的方向P的长度l2和倾斜度α2。
当然,本发明并不限于所描述和所示出的、作为简单的例子提供的实施例。
Claims (8)
1.一种通过树脂传递模塑制造T形复合部件的方法,包括下列步骤:
构成具有基本上平面的层片叠层(A)和具有两个L形的层片叠层(B,C)的预成型体,
放置所述预成型体使得所述L形叠层(B,C)在树脂传递模塑工具(M)的两个型芯(M1,M2)之间,
通过所述平面叠层(A)在垂直或准垂直于该叠层(A)的方向上插入和移出纤维,使得在基本上垂直于所述平面叠层的所述L形叠层(B,C)的部分(81,82)内形成环圈(b1,b2,b3),
闭合模塑工具(M),
树脂注入到模塑工具(M)中,以及
加热模塑工具(M),从而使树脂固化。
2.根据权利要求1所述的方法,其特征在于,在将预成型体引入模塑工具(M)的两个型芯(M1,M2)之间之前对所述平面叠层(A)和所述L形叠层(B,C)进行组装。
3.根据权利要求1所述的方法,其特征在于,对所述L形叠层(B,C)进行组装,将其引入到模塑工具(M)的两个型芯(M1,M2)之间,并且用所述平面叠层(A)覆盖。
4.根据权利要求1所述的方法,其特征在于,将所述L形叠层(B,C)和所述平面叠层(A)中的每一个一个接一个地放置在模塑工具(M)中。
5.根据前述权利要求中任一项所述的方法,其特征在于,形成不同长度(b1,b2,b3和b4,b5)的环圈。
6.根据前述权利要求中任一项所述的方法,其特征在于,所述环圈(b1,b3和b4,b5)形成为相对于垂直(P)于所述平面叠层(A)的方向稍微倾斜(α1和α2)。
7.根据前述权利要求中任一项所述的方法,其特征在于,形成第一组环圈(b1,b2,b3)和第二组环圈(b4,b5),所述第一组环圈(b1,b2,b3)相对于垂直(P)于所述平面叠层的方向(P)的长度和倾斜度大于所述第二组环圈(b4,b5)相对于垂直于所述平面叠层的方向(P)的长度和倾斜度。
8.一种通过与前述权利要求中任一项所述的方法获得的T形复合部件。
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FR1257069A FR2993492B1 (fr) | 2012-07-20 | 2012-07-20 | Procede de fabrication d'une piece composite en t par moulage par transfert de resine |
FR12/57069 | 2012-07-20 | ||
PCT/FR2013/051673 WO2014013167A1 (fr) | 2012-07-20 | 2013-07-12 | Procédé de fabrication d'une pièce composite en t par moulage par transfert de résine |
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US (1) | US20150125654A1 (zh) |
EP (1) | EP2874799A1 (zh) |
CN (1) | CN104470707A (zh) |
BR (1) | BR112015001202A2 (zh) |
CA (1) | CA2879135A1 (zh) |
FR (1) | FR2993492B1 (zh) |
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DE102015201348A1 (de) * | 2015-01-27 | 2016-07-28 | Bayerische Motoren Werke Aktiengesellschaft | Verfahren zum Ausbilden eines Funktionsabschnitts an einem Faserverbundbauteil |
FR3036060B1 (fr) | 2015-05-12 | 2017-04-28 | Aircelle Sa | Piece en materiau composite comportant un raidisseur en t et procede de fabrication d'une telle piece |
FR3043356B1 (fr) | 2015-11-09 | 2018-08-31 | Safran Nacelles | Piece en materiau composite comportant un renfort contre le delaminage et son procede de fabrication |
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EP0556088A1 (fr) * | 1992-02-11 | 1993-08-18 | AEROSPATIALE Société Nationale Industrielle | Procédé pour la réalisation d'une armature de fibres pour pièce de matière composite, et pièce composite comportant une telle armature |
US5789061A (en) * | 1996-02-13 | 1998-08-04 | Foster-Miller, Inc. | Stiffener reinforced assembly and method of manufacturing same |
CN101970214A (zh) * | 2008-03-27 | 2011-02-09 | 空中客车运作股份公司 | 用热塑性复合材料制造毛坯的方法及相关制造工具,以及该方法在生产飞行器结构零件上的应用 |
CN102449326A (zh) * | 2009-05-20 | 2012-05-09 | 梅西耶-布加蒂-道提公司 | 制造复合材料连杆的方法 |
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FR2687174B1 (fr) * | 1992-02-11 | 1995-09-22 | Aerospatiale | Procede pour la realisation d'une armature de fibres pour piece de matiere composite a parois non coplanaires, et piece composite comportant une telle armature. |
EP2384884A1 (en) * | 2010-05-07 | 2011-11-09 | Eurocopter Deutschland GmbH | A method of fabricating a reinforced composite part and a reinforced composite part obtained with said method |
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2012
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2013
- 2013-07-12 RU RU2015105002A patent/RU2015105002A/ru not_active Application Discontinuation
- 2013-07-12 WO PCT/FR2013/051673 patent/WO2014013167A1/fr active Application Filing
- 2013-07-12 CA CA2879135A patent/CA2879135A1/fr not_active Abandoned
- 2013-07-12 CN CN201380038575.6A patent/CN104470707A/zh active Pending
- 2013-07-12 EP EP13744738.9A patent/EP2874799A1/fr not_active Withdrawn
- 2013-07-12 BR BR112015001202A patent/BR112015001202A2/pt not_active IP Right Cessation
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Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0556088A1 (fr) * | 1992-02-11 | 1993-08-18 | AEROSPATIALE Société Nationale Industrielle | Procédé pour la réalisation d'une armature de fibres pour pièce de matière composite, et pièce composite comportant une telle armature |
US5789061A (en) * | 1996-02-13 | 1998-08-04 | Foster-Miller, Inc. | Stiffener reinforced assembly and method of manufacturing same |
CN101970214A (zh) * | 2008-03-27 | 2011-02-09 | 空中客车运作股份公司 | 用热塑性复合材料制造毛坯的方法及相关制造工具,以及该方法在生产飞行器结构零件上的应用 |
CN102449326A (zh) * | 2009-05-20 | 2012-05-09 | 梅西耶-布加蒂-道提公司 | 制造复合材料连杆的方法 |
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BR112015001202A2 (pt) | 2017-08-01 |
RU2015105002A (ru) | 2016-09-10 |
US20150125654A1 (en) | 2015-05-07 |
CA2879135A1 (fr) | 2014-01-23 |
FR2993492A1 (fr) | 2014-01-24 |
EP2874799A1 (fr) | 2015-05-27 |
WO2014013167A1 (fr) | 2014-01-23 |
FR2993492B1 (fr) | 2014-07-18 |
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