CN101171122A - 制造中空纤维增强结构件的方法 - Google Patents
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Abstract
本发明提供制造中空纤维增强结构件的方法，所述结构件尤其是用于航空运输工具，其包括下列步骤：提供一第一圆形编造层；将一扁平的加固体置靠在所述第一编造层的表面的一部分上，该加固体包括至少一个构造物层，所述构造物层具有多根经线纤维和一根纬线纤维；围绕所述第一编造层和所述加固体提供一第二编造层；将所述第一编造层、所述加固体和所述第二编造层的组合体放置在一模具内；用树脂浸渍所述组合体；将所述用树脂浸渍的组合体从所述模具内移出。
Description
技术领域
[01]本发明涉及中空纤维结构件，尤其是用于航空运输工具的结构件，如作为起落装置、螺旋桨叶片和直升机桨叶(的一部分)。航空运输工具用的结构件——如航行器起落装置用的支柱或拉杆——被用于传递大部分单向负载，所述结构件传统地由金属——如钢、铝或钛制成。使用纤维增强的塑料材料可以很大程度地减少重量。这种材料的一个例子是由碳纤维增强的环氧树脂基体。传统地，这种材料在宇宙航空中被用于薄壁的、纤细的结构体如机翼或尾翼中。
背景技术
[02]在起落装置中使用这些材料的一个问题是在起落装置上高度集中的负载，这需要相对于其宽度而言很大的壁厚。仅可通过将很大数目的相对薄的层彼此堆叠起来按层状组合体的方式制造这些大的壁厚，使得该过程耗费很大的人力，从而成本高。在过去，人们努力按传统的预浸料坯(prepreg)组合体的方式制造这种类型的组成件，但是，由于材料和劳动力费用高，这些努力从来没有成功过。
[03]减少费用的方法之一是使用流体模制技术，如RTM(树脂转移模制)。使用该方法，纤维增强件首先完全组装为一预成形件，随后，所述预成形件和液体树脂一起注入到阴模。尽管这相对于费用来说是一个进步，但在制造预成形件中所耗费的人力仍然很大。
[04]过去开发了多种机械化制造预成形件的方法，如2D和3D编造的(braiding)、3D织造的(weaving)、无绉纹的构造物(fabric)和缝编构造物。所有这些方法在它们能制造的几何结构和层叠(lay-up)上受到特定的限制。例如，编造仅可完成有限数目的纵长纤维，而织造仅可制造扁平或半扁平形状的构造物。所有这些方法有不适于典型用于航行器起落装置组成件的梁型组成件。
发明内容
[05]一个方面，本发明的目的在于减少制造中空纤维增强结构件的费用，且另一方面，其目的在于提高其质量。因此，依据本发明的方法包括下列步骤：
[06]-提供一第一圆形编造层，
[07]-将一扁平的加固体置靠在所述第一编造层的表面的一部分上，该加固体包括至少一个构造物层，所述构造物层具有多根经线纤维和一根纬线纤维，
[08]-围绕所述第一编造层和所述加固体提供一第二编造层，
[09]-将所述第一编造层、所述加固体和所述第二编造层的组合体放置在一模具内，
[10]-用树脂浸渍所述组合体，
[11]-将所述用树脂浸渍的组合体从所述模具内移出。
[12]依据本发明制造的结构件具有很重要的优点，由于经线纤维和纬线纤维对所考虑的结构件的强度和硬度作出贡献，故其可从多个方向承受负载，例如在使用中空结构件过程中，用于提供对侧向力和制动力的抵抗。在没有使用如本发明的加固体的情况下，相比较地，更多的编造层应被使用，从而导致壁厚增加。
[13]依据另一个优选实施例，当加固体包括一构造物层叠堆时，尤其会达到加固的好处。
[14]通过在所述模具内、在提高的压力和提高的温度下用一树脂优选为热固树脂注入所述扁平的加固体和所述至少一个编造层，可实现编造层和加固体之间的良好的连接。
[15]优选地，编造纤维、经线纤维和/或纬线纤维是玻璃纤维、碳纤维、芳族聚酰胺(凯夫拉尔)纤维或聚酰胺纤维，这些纤维对所考虑的结构件具有良好的加固性能。
[16]本发明最后还涉及依据本发明的前述方法制造的中空纤维增强结构件。
[17]大体上，本发明的目的是减少费用，同时与现有技术相比，改进组合拉杆的质量。这可按这样的方式实现：将一常规(手动)的但优化的方法——该方法将纤维增强件放置在预成形件内，与一全自动方法——该方法将交叉帘布层(cross ply layer)放置在预成形件内，进行组合。更具体地，可从预成形的构造物叠堆上机械切除主要数目的层，从而形成一净尺寸的层叠堆，所述层叠堆按正确取向，且具有预成形件的确切尺寸。这些叠堆按正确的位置和取向被放置在一心轴上。在放置预切割的叠堆之前和之后，将一层构造物编造在所述心轴组装件上。这可在所谓的过编造机(over braiding machine)上预成形，所述过编造机由这样的一种编造机构成，该编造机具有一机构，该机构沿所述机器的旋转中心线按纵向方向移动所述心轴和预成形件。通过在编造时移动所述心轴，在所述心轴上产生一织造层。在该层的顶部，在特定的位置上再次放置预切割叠堆，通过编造另一层重复所述处理方法。
[18]该过编造处理方法的变量之一是在织造线筒的旋转速度和心轴的纵向速度之间的关系，以及已存在层的心轴的周长，因为这两者都决定了每个剖面上纤维的角度和层的厚度。通过改变这些参数，可以改变层的厚度或编造纤维的角度。
附图说明
[19]接下来，将参照本发明的一个优选实施例及下列附图对本发明进行阐述，其中：
[20]图1给出在使用依据本发明的方法制造的过程中结构件的剖面；以及
[21]图2是在制造的早期阶段过程中该结构件的透视图。
具体实施方式
[22]图1给出一心轴1，其具有带圆角的矩形剖面。心轴1位于一中空纤维增强结构件的最终内部的位置，该结构件是依据本发明的第一个优选实施例的方法制造的。一周向的第一编造层2绕着心轴1编造。为了清晰起见，在图1中，在心轴1和第一编造层2之间表示有一间距，该间距实际上不存在。
[23]第一编造层(以及还要被讨论的第二编造层3和第三编造层4)的编造按这样的方式完成：在围绕中心线6按照箭头7同时旋转心轴1的过程中，从依据虚线8的进给点5向心轴1进给编造纤维。同时心轴1垂直于所述图画(drawing)的平面来回移动，从而使得纤维在侧视图中限定出一V形形状，该V形形状具有一顶角，该顶角例如为90°或120°，这一方面取决于心轴1的旋转速度，另一方面取决于心轴1垂直于所述图画的平面来回移动的速度。可选择地，还可能的是，进给点5按箭头9的方向绕心轴1(的中心线6)转动，和/或进给点5(代替心轴1和可能的话甚至和心轴1同时)垂直于所述图画的平面来回移动。在这点上，纤维8和心轴1之间的相对运动是相关的。如果希望的话，已经刚好缠绕的一部分纤维8在编造过程中能压靠着压紧辊。
[24]一旦第一编造层2达到希望的厚度，所述编造——或者换句话说所述进给点5和心轴1之间的相对运动以及所述纤维8通过进给点5的进给——被中断，随后，一扁平的加固体10按这样的方式被配设在所述第一编造层2的外侧在心轴1的短的相对位置上：按手动方式或机械地——例如借助一拾放机器人(pick and place robot)、抵靠着在所述第一编造层2的外侧上的所考虑的部位地定位这些加固体10，并且借助例如用捆绑辅助件、机械销或其它固定装置固定在该位置。
[25]每个加固体由多个构造物层构成，所述构造物层具有彼此叠置的经线纤维和纬线纤维。在较早的阶段，在提高的压力和提高的温度下使用例如热塑粘结剂将所述构造物层相互连接。
[26]接下来，继续所述编造过程，从而导致开始形成一第二编造层3，第二编造层3将加固体10压靠在第一编造层2上。图2涉及这种情况。接下来，可按类似的方式，也取决于所需的强度和刚性，制造与图1中的加固体11相似的其它加固体以及与图1中的第三编造层4相似的其它编造层。
[27]一旦提供所需要数量的编造层和加固体，在下一步中，包括心轴1的整体放置在一完全包围所述整体的硬模内，随后，在提高的温度和提高的压力下将树脂如类似环氧树脂的热硬化树脂注入所述编造层2，3，4和加固体10，11。树脂硬化后，打开外模，移出心轴1，从而形成一个中空纤维增强结构件，其可通过例如机加工、钻或切割的方式进行机械处理。这种产品可用于如起落装置、螺旋桨叶片和直升机桨叶的一部分。
[28]尽管上述优选实施例中的加固体10，11配置在扁平的侧面，在本发明的框架内，还可能的是，加固体10，11配设在倒圆的位置，如位于心轴1的圆角位置处。
Claims (5)
1.制造中空纤维增强结构件的方法，所述结构件尤其是用于航空运输工具，其包括下列步骤：
提供一第一圆形编造层，
将一扁平的加固体置靠在所述第一编造层的表面的一部分上，该加固体包括至少一个构造物层，所述构造物层具有多根经线纤维和一根纬线纤维，
围绕所述第一编造层和所述加固体提供一第二编造层，
将所述第一编造层、所述加固体和所述第二编造层的组合体放置在一模具内，
用树脂浸渍所述组合体，
将所述用树脂浸渍的组合体从所述模具内移出。
2.按照权利要求1所述的方法，其特征在于：所述加固体包括一构造物层叠堆。
3.按照权利要求1或2所述的方法，其特征在于：在所述模具内，在提高的压力和提高的温度下，用一树脂优选为热固树脂注入所述扁平的加固体和所述至少一个编造层。
4.按照权利要求1、2或3所述的方法，其特征在于：编造纤维、经线纤维和/或纬线纤维是玻璃纤维、碳纤维、芳族聚酰胺纤维或聚酰胺纤维。
5.中空纤维增强结构件，其是按照权利要求1至4中任一项所述的方法来制造的。
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| NL1028946 | 2005-05-03 | ||
| NL1028946 | 2005-05-03 | ||
| PCT/NL2006/000235 WO2006118448A1 (en) | 2005-05-03 | 2006-05-02 | Method for the manufacturing of a hollow fiber reinforced structural member |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101171122A true CN101171122A (zh) | 2008-04-30 |
| CN101171122B CN101171122B (zh) | 2012-05-23 |
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| CN2006800150820A Active CN101171122B (zh) | 2005-05-03 | 2006-05-02 | 制造中空纤维增强结构件的方法 |
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| Country | Link |
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| US (1) | US8940378B2 (zh) |
| EP (1) | EP1877240B1 (zh) |
| JP (2) | JP2008540166A (zh) |
| CN (1) | CN101171122B (zh) |
| BR (1) | BRPI0607568A2 (zh) |
| CA (1) | CA2606810C (zh) |
| WO (1) | WO2006118448A1 (zh) |
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| CN102741043A (zh) * | 2010-01-26 | 2012-10-17 | 斯奈克玛 | 用于制造具有内部通道的复合材料叶片的方法及复合材料涡轮发动机叶片 |
| CN102844171A (zh) * | 2010-03-26 | 2012-12-26 | 梅西耶-布加蒂-道提公司 | 由拉-压和弯曲下具有改进的机械性能的复合材料制成的机械构件的制造方法 |
| CN103079800A (zh) * | 2010-09-06 | 2013-05-01 | 梅西耶-布加蒂-道提公司 | 生产具有编织覆盖层、由复合材料制成的零件的方法 |
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- 2006-05-02 WO PCT/NL2006/000235 patent/WO2006118448A1/en active Application Filing
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| CN102741043A (zh) * | 2010-01-26 | 2012-10-17 | 斯奈克玛 | 用于制造具有内部通道的复合材料叶片的方法及复合材料涡轮发动机叶片 |
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| CN102844171A (zh) * | 2010-03-26 | 2012-12-26 | 梅西耶-布加蒂-道提公司 | 由拉-压和弯曲下具有改进的机械性能的复合材料制成的机械构件的制造方法 |
| CN103079800A (zh) * | 2010-09-06 | 2013-05-01 | 梅西耶-布加蒂-道提公司 | 生产具有编织覆盖层、由复合材料制成的零件的方法 |
| CN102529106A (zh) * | 2011-12-12 | 2012-07-04 | 中国科学院宁波材料技术与工程研究所 | 一种纤维复合材料制件的局部可变厚度加固补强方法 |
| CN102529106B (zh) * | 2011-12-12 | 2013-11-20 | 中国科学院宁波材料技术与工程研究所 | 一种纤维复合材料制件的局部可变厚度加固补强方法 |
Also Published As
| Publication number | Publication date |
|---|---|
| US20080187699A1 (en) | 2008-08-07 |
| JP5404869B2 (ja) | 2014-02-05 |
| CN101171122B (zh) | 2012-05-23 |
| EP1877240A1 (en) | 2008-01-16 |
| US8940378B2 (en) | 2015-01-27 |
| CA2606810A1 (en) | 2006-11-09 |
| EP1877240B1 (en) | 2017-12-13 |
| CA2606810C (en) | 2013-08-20 |
| WO2006118448A1 (en) | 2006-11-09 |
| JP2013014875A (ja) | 2013-01-24 |
| BRPI0607568A2 (pt) | 2010-04-06 |
| JP2008540166A (ja) | 2008-11-20 |
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