CN109987218A - 夹层构件及包括其的飞行器部件 - Google Patents

夹层构件及包括其的飞行器部件 Download PDF

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Publication number
CN109987218A
CN109987218A CN201811636049.0A CN201811636049A CN109987218A CN 109987218 A CN109987218 A CN 109987218A CN 201811636049 A CN201811636049 A CN 201811636049A CN 109987218 A CN109987218 A CN 109987218A
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CN
China
Prior art keywords
layer
sandwich
mould part
finished product
sandwich component
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201811636049.0A
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English (en)
Inventor
马克·费特
马丁·亨切尔
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Airbus Operations GmbH
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Airbus Operations GmbH
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Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of CN109987218A publication Critical patent/CN109987218A/zh
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    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
    • B29C43/18—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. compression moulding around inserts or for coating articles
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    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
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    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
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    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
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Abstract

本发明涉及一种夹层构件及包括其的飞行器的翼尖、副翼、升降舵或方向舵、空气通道、座椅、躺椅或床、机翼、空气阀瓣或通风喷嘴、升降舵组或方向舵组。该夹层构件包括至少两个覆盖层(3’，5’)以及一个芯层(7’)，所述芯层包含由形状记忆金属制成的线材(24)。该夹层构件提供了一种改进的可调整的面型的构件，该构件允许简单的控制。

Description

夹层构件及包括其的飞行器部件
技术领域
本发明涉及一种夹层构件及包括其的飞行器部件，该夹层构件包括至少两个覆盖层以及一个芯层，该芯层包含由形状记忆金属制成的线材。
背景技术
在制造纤维复合材料时，多个由纤维材料制成的层能够重叠地成层且紧接着硬化，也称为固化。通过基质材料使硬化成为可能。基质材料能够为反应性树脂(热固性)或应用非反应性可熔化的塑料(热塑性)。要么基质材料已经处于纤维(所谓的预浸料坯)上，要么基质材料喷射到纤维材料中。未硬化的或尚未完全硬化的材料称为半成品。
用于制造纤维复合材料的另一种方法是，在模具中在压力和温度下硬化作为模压物料的由基质材料和长纤维形成的混合物。这样的长纤维增强的带有热固性基质的模压物料具有带有介于10mm和79mm的范围中、优选介于25mm和50mm的范围中的平均纤维长度的长纤维。长纤维为碳或玻璃纤维，其作为无序纤维、也就是说准各向同性地嵌入到基质中，该基质基于热固性或者热硬化的反应性树脂、例如不饱和聚酯树脂、乙烯基酯树脂、环氧树脂或聚芳醚胺树脂中。它们称为片状模塑料(SMC)或块状模塑料(BMC)。BMC与SMC的区别在于，BMC还在厚度方向上具有显著的膨胀。
夹层构件理解为纤维复合构件，其多层构建且在覆盖层之间具有至少一个芯层。芯层能够为木材、泡沫、蜂巢式核心。由此可行的是，制造相对轻的构件，其机械特性不通过由实心的纤维复合材料制成的具有相同重量的构件实现。
形状记忆合金(简称FGL，英语shape memory alloy，简称SMA)是特殊的金属，其能够以两种不同的晶体结构存在。形状记忆合金通常还称为记忆金属。这源自如下现象：形状记忆合金尽管随后发生强烈的变形但是似乎能够“记忆”从前的造型。大多数金属总是具有相同的晶体结构直至其熔点，而形状记忆合金则取决于温度具有两种不同的结构或相。因此形状变化基于取决于温度的晶格转换成两个晶体结构之一。通常存在称为奥氏体的高温相和低温相(马氏体)。两者能够通过温度变化可逆地相互过渡，这称为双向效果。
结构转换能够通过温度变化引起。
在车辆和飞行器制造中，除了非常多的刚性的或硬的构件之外还使用实现针对性的形状改变的构件。对此的示例是座椅或躺椅面以及流体动力的控制元件如舵、帆或输送通道。大多数情况下，这种改变其形状的构件包括柔性元件(通过铰接连接多个部分面)或能够可逆地变形的面型元件，例如由织物或薄的板状的板材或片材以及调整器械形成，借助于其实现构件的形状改变。
因此以所有这些为出发点，本发明的目的是提供一种改进的可调整的面型的构件，该构件允许简单的控制。
发明内容
现在对于本领域技术人员来说已经证实为完全令人吃惊的是，一种夹层构件弥补了现有技术的缺点，所述夹层构件包括至少两个覆盖层以及一个芯层，该芯层包含由形状记忆金属制成的线材。
优选的是，夹层构件能够通过带有下列步骤的方法获得：
(a)提供带有第一模具部分和第二模具部分的模压装置，所述第一模具部分和所述第二模具部分能够在闭合位置与打开位置之间相对彼此运动，在所述闭合位置中所述第一模具部分和所述第二模具部分围成空腔，在所述打开位置中所述空腔朝向周围环境敞开，其中所述第一模具部分和/或所述第二模具部分是能够加热的，
(b)提供夹层半成品，所述夹层半成品带有：由带有热固性基质的长纤维增强的模压物料制成的第一覆盖层半成品层、由带有热固性基质的长纤维增强的模压物料制成的第二覆盖层半成品层、以及在所述第一覆盖层半成品层与所述第二覆盖层半成品层之间的芯层半成品层，
(c)在所述模压装置的所述打开位置中将所述夹层半成品插入到所述空腔中，
(d)使所述第一和第二模具部分相对彼此运动到所述闭合位置中，
(e)压缩所述第一和第二模具部分，从而使得所述夹层半成品经受一定的挤压力，并加热所述第一和/或第二模具部分，从而使得所述夹层半成品经受一定的加工温度，其特征在于，所述模压装置具有间隔保持部，所述间隔保持部在所述闭合位置中限定在所述第一和第二模具部分之间的最小间距并由此确定所述空腔的最小尺寸，并且所述间隔保持部如此设定，使得挤压力在所述闭合位置中处于所述第一和/或第二覆盖层半成品层的最小加工压力与对于所述芯层半成品层最大允许的极限压力之间。进一步优选的是，在所述芯层中由形状记忆金属制成的所述线材基本上彼此平行地安排。进一步优选的是，在所述芯层中由形状记忆金属制成的所述线材相互基本上以织物的形式安排。进一步优选的是，在所述芯层中由形状记忆金属制成的所述线材是能够加热的。进一步优选的是，所述覆盖层的基质由环氧树脂、乙烯基酯树脂、酚醛树脂或不饱和聚酯树脂制成。进一步优选的是，所述中间层由弹性体制成。进一步优选的是，所述中间层由EPDM、BR和/或EVA制成。进一步优选的是，所述中间层由EPDM、BR和EVA制成。进一步优选的是，所述中间层由呈经压延的箔片形式的弹性体制成。进一步优选的是，所述中间层由呈经压延的多个箔片形式的弹性体制成，由形状记忆金属制成的所述线材安排在这些箔片之间。进一步优选的是，由形状记忆金属制成的所述线材是能够电加热的。进一步优选的是，通过能够将电压施加至所述线材本身，由形状记忆金属制成的所述线材是能够电加热的。进一步优选的是，由形状记忆金属制成的所述线材是能够通过感应加热的。进一步优选的是，由形状记忆金属制成的所述线材能够借助于冷却装置调温。本发明还包括飞行器的翼尖，所述翼尖具有根据以上权利要求之一所述的夹层构件。本发明还包括副翼、升降舵或方向舵，其具有根据本发明的夹层构件。本发明还包括用于飞行器的空气通道，其具有根据本发明的夹层构件。本发明还包括用于飞行器的座椅、躺椅或床，其具有根据本发明的夹层构件。本发明还包括用于飞行器的机翼，其具有根据本发明的夹层构件。本发明还包括飞行器的空气阀瓣或通风喷嘴，其具有根据本发明的夹层构件。本发明还包括飞行器的升降舵组或方向舵组，其具有根据本发明的夹层构件。
上述的方面和本发明的其他方面、特征以及优点同样可以从实施方式的实例中得出，这些实例在下文中参照附图来说明。
附图说明
将参照附图进一步详细地描述本发明，在附图中：
图1a-图1e示出了用于制造根据本发明的夹层构件的方法；以及
图2示出了根据本发明的夹层材料。
具体实施方式
在图1中示出了用于制造根据本发明的夹层构件1’的方法。该方法是冲挤方法，该冲挤方法具有以下步骤。
如在图1a中示出的那样，首先提供夹层半成品1，该夹层半成品具有第一覆盖层半成品层3、第二覆盖层半成品层5和在第一和第二覆盖层半成品层3、5之间的芯层半成品层7。第一和第二覆盖层半成品层3、5形成为SMC半成品层且具有带有热固性基质的长纤维增强的模压物料，其中带有介于25mm和50mm之间的平均纤维长度的碳或玻璃纤维作为无序纤维嵌入在热固性反应性树脂中。芯层半成品层7由泡沫材料形成，由形状记忆合金制成的线材嵌入到该泡沫材料中。由形状记忆合金制成的线材能够基本上单向地取向，形成90°织物或纺织品。
紧接着，如在图1b中示出的那样，夹层半成品1为冲压过程做好准备，其中夹层半成品1预成型且裁切，以为了以该方式与模压装置11的空腔9的形状相匹配。在此，由泡沫制成的带有由形状记忆金属制成的线材的芯层半成品层7预加热，从而其体积在插入到空腔9中时占据完成制造的夹层构件1’的芯层7’的体积的约80％。紧接着，准备好的夹层半成品1置入到模压装置11的空腔9中，如在图1c中示出的那样。模压装置11具有第一模具部分13和第二模具部分15，该第一模具部分和该第二模具部分能够在闭合位置17(在该闭合位置中第一模具部分和第二模具部分围成空腔9)和打开位置19(在该打开位置中空腔9朝向周围环境敞开)之间相对彼此运动。模压装置11在当前实施例中构造为沉入式边缘模具，其中第一模具部分13形成为凹模且第二模具部分15形成为凸膜。第一模具部分13是不可动的且第二模具部分15从打开位置19在竖直方向上从上方朝向第一模具部分13运动到闭合位置17中。第一模具部分13和第二模具部分15能够受控地加热。空腔9的形状相应于待制造的夹层构件1’的形状。
如在图1d中示出的那样，第二模具部分15现在朝向第一模具部分13运动，从而模压装置11被带到闭合位置17中。在闭合位置17中第二模具部分15以这样的力挤压到第一模具部分13上，即使得在空腔9中存在的夹层半成品1经受一定的挤压力，该挤压力是必须的，以为了成型且硬化夹层半成品1。同时第一和第二模具部分13、15如此加热，即使得夹层半成品1经受一定的加工温度，在当前情况中介于140°和150℃之间。以该方式冲挤夹层半成品1，也就是说被带到预期的形状、即空腔9的形状中，其中覆盖层半成品层3、5的基质转为流动状态，且紧接着硬化。
为了不因挤压力破坏芯层半成品层7的泡沫，模压装置11具有间隔保持部21，该间隔保持部在闭合位置17中限定在第一和第二模具部分13、15之间的最小间距且因此规定空腔9的最小尺寸和由此最大挤压力。间隔保持部21取决于空腔9的几何结构和覆盖层半成品层3、5和芯层半成品层7的材料如此设定，即使得在闭合位置17中当间隔保持部21将在第一和第二模具部分13、15之间的间距限制到最小间距时，挤压力处于第一和第二覆盖层半成品层3、5的最小加工压力和对于芯层半成品层7最大允许的极限压力之间。间隔保持部21在当前实施方式中构造为止挡元件22，该止挡元件在空腔9侧边设置在第二模具部分15处且在运动到闭合位置17中时止挡在第一模具部分13处，以为了以该方式规定在第一和第二模具部分13、15之间的最小间距。此外设置有控制装置23，该控制装置如此控制第二模具部分15朝向第一模具部分13运动到闭合位置17中或第二模具部分15推压到第一模具部分13上的力，即使得第一和第二模具部分13、15作用到夹层半成品1上的压力在止挡元件22止挡且达到挤压力之后仅非常缓慢地增大。
如在图1e中示出的那样，在夹层构件1’完成硬化之后，第二模具部分15运动远离第一模具部分13且带到打开位置19中，此后将完成制造的夹层构件1’从模压装置11中取出。夹层构件1’具有由泡沫制成的带有由形状记忆金属制成的线材的芯层7’以及由纤维增强的塑料制成的第一和第二覆盖层3’、5’。
图2示出了根据本发明的材料，其具有由纤维增强的塑料制成的第一和第二覆盖层3’、5’以及由泡沫或弹性体以及嵌入在其中的由形状记忆金属制成的线材(24)形成的芯层7’。
虽然本发明在附图和上述说明中进行了详细的展示和说明，但旨在：此类展示和说明仅为展示性或示例性的、而非限制性的，从而本发明不受所公开的实施方式限制。在权利要求书中词语“具有”不排除其他要素，并且不定冠词“一个(ein)”不排除多个。
仅在不同的从属权利要求中提及特定的特征并不限制本发明的主体。也可以有利地使用这些特征的组合。权利要求中的附图标记不应限制权利要求的范围。

Claims (22)

1.一种夹层构件(1’)，其包括至少两个覆盖层(3’，5’)以及一个芯层(7’)，所述芯层包含由形状记忆金属制成的线材(24)。
2.一种夹层构件(1’)，其包括至少两个覆盖层(3’，5’)以及一个芯层(7’)，所述芯层包含由形状记忆金属制成的线材(24)，能够通过带有以下步骤的方法获得：
(a)提供带有第一模具部分(13)和第二模具部分(15)的模压装置(11)，所述第一模具部分和所述第二模具部分能够在闭合位置(17)与打开位置(19)之间相对彼此运动，在所述闭合位置中所述第一模具部分和所述第二模具部分围成空腔(9)，在所述打开位置中所述空腔(9)朝向周围环境敞开，其中所述第一模具部分(13)和/或所述第二模具部分(15)是能够加热的，
(b)提供夹层半成品(1)，所述夹层半成品带有：由带有热固性基质的长纤维增强的模压物料制成的第一覆盖层半成品层(3)、由带有热固性基质的长纤维增强的模压物料制成的第二覆盖层半成品层(5)、以及在所述第一覆盖层半成品层与所述第二覆盖层半成品层之间的芯层半成品层(7)，
(c)在所述模压装置(11)的所述打开位置(19)中将所述夹层半成品(1)插入到所述空腔(9)中，
(d)使所述第一模具部分(13)和第二模具部分(15)相对彼此运动到所述闭合位置(17)中，
(e)压缩所述第一模具部分(13)和第二模具部分(15)，从而使得所述夹层半成品(1)经受一定的挤压力，并加热所述第一模具部分(13)和/或第二模具部分(15)，从而使得所述夹层半成品(1)经受一定的加工温度，其特征在于，所述模压装置(11)具有间隔保持部(21)，所述间隔保持部在所述闭合位置(17)中限定在所述第一模具部分(13)和第二模具部分(15)之间的最小间距并由此确定所述空腔(9)的最小尺寸，并且所述间隔保持部(21)如此设定，使得挤压力在所述闭合位置(17)中处于所述第一覆盖层半成品层(3)和/或第二覆盖层半成品层(5)的最小加工压力与对于所述芯层半成品层(7)最大允许的极限压力之间。
3.根据权利要求1或2所述的夹层构件，其特征在于，在所述芯层(7’)中由形状记忆金属制成的所述线材(24)基本上彼此平行地安排。
4.根据权利要求1或2所述的夹层构件，其特征在于，在所述芯层(7’)中由形状记忆金属制成的所述线材(24)相互基本上以织物的形式安排。
5.根据以上权利要求之一所述的夹层构件，其特征在于，在所述芯层(7’)中由形状记忆金属制成的所述线材(24)是能够加热的。
6.根据以上权利要求之一所述的夹层构件，其特征在于，所述覆盖层的基质由环氧树脂、乙烯基酯树脂、酚醛树脂或不饱和聚酯树脂制成。
7.根据以上权利要求之一所述的夹层构件，其特征在于，所述中间层(7)由弹性体制成。
8.根据以上权利要求之一所述的夹层构件，其特征在于，所述中间层(7)由EPDM、BR和/或EVA制成。
9.根据以上权利要求之一所述的夹层构件，其特征在于，所述中间层(7)由EPDM、BR和EVA制成。
10.根据以上权利要求之一所述的夹层构件，其特征在于，所述中间层(7)由呈经压延的箔片形式的弹性体制成。
11.根据以上权利要求之一所述的夹层构件，其特征在于，所述中间层(7)由呈经压延的多个箔片形式的弹性体制成，由形状记忆金属制成的所述线材(24)安排在这些箔片之间。
12.根据以上权利要求之一所述的夹层构件，其特征在于，由形状记忆金属制成的所述线材(24)是能够电加热的。
13.根据以上权利要求之一所述的夹层构件，其特征在于，通过能够将电压施加至所述线材本身，由形状记忆金属制成的所述线材(24)是能够电加热的。
14.根据以上权利要求之一所述的夹层构件，其特征在于，由形状记忆金属制成的所述线材(24)是能够通过感应加热的。
15.根据以上权利要求之一所述的夹层构件，其特征在于，由形状记忆金属制成的所述线材(24)能够借助于冷却装置调温。
16.一种飞行器的翼尖，所述翼尖具有根据以上权利要求之一所述的夹层构件。
17.一种飞行器的副翼、升降舵或方向舵，所述副翼、升降舵或方向舵具有根据以上权利要求之一所述的夹层构件。
18.一种用于飞行器的空气通道，所述空气通道具有根据以上权利要求之一所述的夹层构件。
19.一种用于飞行器的座椅、躺椅或床，所述座椅、躺椅或床具有根据以上权利要求之一所述的夹层构件。
20.一种飞行器的机翼，所述机翼具有根据以上权利要求之一所述的夹层构件。
21.一种飞行器的空气阀瓣或通风喷嘴，所述空气阀瓣或通风喷嘴具有根据以上权利要求之一所述的夹层构件。
22.一种飞行器的升降舵组或方向舵组，所述升降舵组或方向舵组具有根据以上权利要求之一所述的夹层构件。
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