CN101500796B - 叠层结构和构造型结构以及制造用于航空航天的部件的方法 - Google Patents

叠层结构和构造型结构以及制造用于航空航天的部件的方法 Download PDF

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CN101500796B
CN101500796B CN200780026548.1A CN200780026548A CN101500796B CN 101500796 B CN101500796 B CN 101500796B CN 200780026548 A CN200780026548 A CN 200780026548A CN 101500796 B CN101500796 B CN 101500796B
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奥拉夫·洛克尔
曼纽尔·荣格
索斯腾·布莱克
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Abstract

本发明提供一种用于制造用于航空航天的部件的方法，具有以下的方法步骤：通过带材敷设机(25)，为将被敷设的叠层结构(1)供给用树脂基体预浸过的玻璃纤维叠层(8)，和/或通过带材敷设机，为将被敷设的构造型结构(12)供给用金属形成并用树脂预浸过的结构(16)，通过带材敷设机(25)将叠层和/或构造型结构(1；12)敷设在层压装置(23)上，和固化叠层和/或构造型结构(1；12)并因而形成部件(37)。

Description

叠层结构和构造型结构以及制造用于航空航天的部件的方法
技术领域
本发明总体涉及一种通过带材敷设机敷设的叠层结构，和通过带材敷设机敷设的构造型结构，以及制造用于航空航天的部件的方法。
虽然可以用于任何所需的航空航天领域，本发明和其基于的问题将参考飞行器的机翼外壳进行详细的说明。
背景技术
在民用航空中，为了减轻飞行器的重量，越来越多地用CFRP材料来制造整个机翼外壳。基于这个目的，在层压装置中通过带材敷设机以一层设置在另一层上的方式构建一层或多层CFRP预浸材料(可以理解为包括用树脂基体预浸过的碳纤维叠层)形成在另一层上。在层压装置中带材敷设机确保CFRP预浸材料的高精度定位。这种高精度的定位对于以后的性能至关重要，具体地对于将要制造的飞行器外壳的强度至关重要。
此外，绝缘材料的层和/或避雷装置材料不得不施加到所述至少一层CFRP预浸材料上或下面。
典型地，这种类型的绝缘材料可以设计成玻璃纤维织物的形式。它们防止由CFRP制成的机翼外壳和铝部件之间的直接接触，例如机翼的肋或框架。因而，玻璃纤维材料在由CFRP制成的机翼外壳和铝部件之间提供电绝缘，并且因此防止铝部件的腐蚀。
典型地，避雷装置材料具有青铜网状物，这可以理解成包括由细青铜线制成的机织织物。它们使得在闪电击打到机翼外壳时电荷可以从机翼外壳上导走。
为了制造机翼外壳，第一步，设置具有树脂基体的玻璃纤维机织织物和/或青铜网状材料，第二步，将它们按照层压装置中的位置精确地敷设。这种连接中的问题是，目前这些步骤是手工操作的。这非常花费时间并且需要高额的人工费用，这导致生产这种类型的机翼外壳要花费高的生产成本。在定位步骤中需要的高精度也仅用高难度的手工来实现，因而常常会带来定位误差。
因此，本发明的一个目的是，使得有可能更加成本有效性，具体的是，自动地用绝缘的和/或避雷装置材料制造用于航空航天的部件。
发明内容
根据本发明，上述目的通过具有专利权利要求1的特征的叠层结构来实现，通过具有专利权利要求6的特征的构造型结构来实现，和/或通过具有专利权利要求12的特征的方法来实现。
据此，提供一种要通过带材敷设机敷设的叠层结构，叠层结构具有用树脂基体预浸过的玻璃纤维叠层。
此外，提供一种通过带材敷设机敷设的构造型结构，构造型结构具有用金属制造的结构并用树脂基体预浸过。
此外，提供一种用于制造航天航空用的部件的方法，所述方法具有步骤：供给通过带材敷设机敷设的叠层结构，所述叠层结构具有用树脂基体预浸过的玻璃纤维叠层，和/或供给通过带材敷设机敷设的构造型结构，所述构造型结构由金属制成并且用树脂基体预浸过，通过带材敷设机在层压装置上敷设叠层和/或构造型结构，和/或固化叠层和/或构造型结构，以形成部件。
本发明的原理在于使自动地敷设叠层结构和/或构造型结构成为可能。基于这个目的，代替玻璃纤维机织织物，预浸过的玻璃纤维叠层被用作绝缘材料。设置有树脂基体的玻璃纤维叠层对于自动化生产比玻璃纤维机织织物具有更好的操纵性。同样，对于由金属制成并且用树脂基体预浸过的结构也适用。相对于手工处理，在自动处理过程中会存在高机械应力，尤其在进料和供给步骤中，例如通过心轴和导向辊的方式。青铜网状物材料，例如，对于机械载荷相对敏感并且因此在自动处理过程中可能会损坏。
根据本发明，在带材敷设机通常用来敷设CFRP预浸材料并因此没有新的需求来处理叠层结构和/或构造型结构的范围内，通过带材敷设机敷设叠层结构和/或构造型结构是有益的。因此，所需资源可来自已有的资源，这有利于节约成本。手工处理步骤被去除了，结果进一步提高成本优势。此外，所需的定位精度通过自动带材敷设机能够容易实现。
本发明的更多有益的设计和改进在从属权利要求中可以找到。
根据本发明的优选的发展，玻璃纤维叠层设计成单一方向的叠层。叠层(包括多个层的构造)因此有益地构造，所述叠层具有低的重量和在所需的方向上非常高的强度。
根据优选的示例性实施例，叠层结构设计成织物材料的形式。这种类型的织物材料能易于在自动步骤中处理并且易于适合构造片状叠层。
在本发明还一优选的发展中，在一侧，玻璃纤维叠层设置有背衬材料，具体地，背衬纸，具体地可从所述玻璃纤维叠层上分离的背衬纸，用于支撑玻璃纤维叠层。所述背衬纸有两个基本的功能：第一，在叠层结构的自动处理过程中供给和进料步骤过程中背衬纸支撑预浸过的玻璃纤维叠层。第二，背衬纸防止树脂黏附到供给或进料装置，例如心轴或导向辊。
根据本发明的优选的示例性实施例，在另一侧，具体地，在与所述第一侧相对的一侧，玻璃纤维叠层设置有保护膜，具体地，可从所述玻璃纤维叠层上分离的保护膜，用于保护玻璃纤维叠层。保护膜具有便于处理的目的，具体地防止玻璃纤维叠层黏附至进料装置。
根据本发明优选的发展，构造型结构的金属包括铜、青铜和/或铝。这些材料适于，具体的，在闪电击打时传导电流。
根据本发明还一优选的发展，构造型结构以片状的方式设计，具体地以织物材料的形式设计。这带来自动化工艺过程中构造型结构的简化的操纵性，并且带来大型叠层的简单、经济的生产，正如通常航空中所需要的。
根据本发明的还一优选的发展，所述结构以网的方式设计，具体地，具有菱形形状、矩形和/或蜂窝形状凹陷，具体地，沿着其厚度。在这种情形中，厚度指的是片状构造型结构，厚度是所述构造型结构的三个宽度方向中最短的。这种类型的结构非常轻并且因此减小了飞行器的重量。此外，因为它们是固定的、限定的结构，它们比(例如)青铜网状物材料更适于自动化处理。
根据本发明的优选的发展，在至少一侧上，所述结构设置有背衬材料，具体是背衬纸，具体地能从所述结构分离的背衬纸，用于支撑所述结构。背衬纸的功能这里对应于叠层结构的背衬纸。
根据本发明的还一优选的示例性实施例，在一侧处，具体地在相对的另一侧，所述结构设置有保护膜，具体地能从所述结构分离的保护膜，用于保护所述结构。保护膜具有与叠层结构的保护膜相同的功能。
在本发明的还一优选的发展中，带材敷设机沿多个轴线移动，具体地通过计算机数字控制。这允许形成复杂的叠层，利用它就可能使叠层结构和/或构造型结构的定位和取向可以简单地、快速地并且高精度地进行调整。
在本发明的还一优选的示例性实施例中，叠层和/或构造型结构沿相对于层压装置的不同方向敷设。叠层和最终的部件因而具有高柔韧性的符合所需要求的结构。例如，玻璃纤维可以以相对于铝部件的方式取向，在使用时玻璃纤维邻近铝部件，最小化了玻璃纤维的磨损。
在本发明的还一优选的示例性实施例中，多个叠层和/或构造型结构以一层在另一层上的方式敷设。结果，获得叠层制品，所述叠层制品能承担避雷装置功能并且也能毫无问题地与铝部件相互作用而不会腐蚀它们。
在本发明的还一优选的发展中，至少一层CFRP预浸材料被敷设在叠层和/或构造型结构上、之间和/或下面，具体地通过带材敷设机和/或另一带材敷设机。这形成了具有高强度的复合材料(通过使用CFRP材料)，并且具有避雷装置和/或防腐功能。如果敷设CFRP预浸材料，叠层结构和/或构造型结构可以通过相同的带材敷设机制备，提供额外的机器来敷设叠层结构和/或构造型结构是不必要的，并且使高成本有效的生产工艺成为可能。
根据本发明的还一优选的发展，叠层结构敷设在部件上，具体地，用铝制成的部件，通过带材敷设机敷设。部件以自动的方式安装在叠层制品中，并被保护确保不会腐蚀。因为这个目的，带材敷设机能自动地辨认部件的存在，具体地，用铝制成的部件，并且能够自动地从CFRP预浸材料转变成将叠层结构敷设在所述部件上。
根据本发明的还一优选的发展，将叠层和/或构造型结构和/或CFRP材料按照所需的功能通过进料装置供给到带材敷设机。这形成一种高度灵活的并且快速的用这种复合材料制造叠层制品和最终的部件的方法。
叠层和/或构造型结构优选地作为盘绕织物材料提供。这种类型的盘绕织物材料可以以节省空间的方式容纳并且易于供给，例如在自动化工艺中通过心轴的方式提供。
下面应用示例性实施例并参考附图详细地介绍本发明。
附图说明
在附图中：
图1示出了根据本发明第一示例性实施例的叠层结构的透视图；
图2示出了沿图1的截面线I-I的截面图；
图3示出了根据本发明第二示例性实施例的构造型结构的透视图；
图4示出了沿图3截面线II-II的截面图；
图5示出了根据本发明第三示例性实施例的制造用于航空航天的部件的过程中的所述方法的状态；
图6示出沿图5的截面线III-III的截面图。
在附图中，如果没有说明，相同的附图标记指示相同的或功能相同的部件。
具体实施方式
图1以透视图示出根据本发明的第一示例性实施例的叠层结构1。
叠层结构1设置成绕心轴2盘绕的捆3的形式。已经展开的织物状端部用附图标记4指出。虚线示意地示出叠层结构1内的玻璃纤维5的纤维方向。优选地，玻璃纤维5在展开方向上延伸，也就是沿织物状端部4。
图2显示沿图1中的截面线I-I的截面图。
优选地，叠层结构1包括背衬层6、玻璃纤维叠层8和保护膜9。优选地，背衬层6设计成纸层的形式。在背衬层的上面设置相对于截面平面垂直地延伸的玻璃纤维层5。位于玻璃纤维5之间的是树脂基体10。玻璃纤维叠层8用这种树脂基体10预浸过。也就是说，树脂基体是柔软的状态，给玻璃纤维叠层8提供充分的支撑，使得在叠层结构自动处理过程的供给步骤中叠层结构不会被损坏，例如破裂。保护膜9在玻璃纤维叠层8上延伸。
图3示出根据本发明的第二示例性实施例的构造型结构12。这里的构造型结构12设置成绕心轴13盘绕的捆14的形式。构造型结构12的展开的织物状端部用附图标记15指出。虚线示出金属网16。金属网16具有菱形凹陷17。这些菱形凹陷17减小构造型结构12的重量。
图4示出沿图3的截面线II-II的截面图。金属网16(例如用铜制造的)在背衬层20上以片状形式延伸，优选地，背衬层20用纸材料制成。金属网16用树脂基体预浸。也就是说，凹陷17用树脂基体18填充并且树脂基体18处于足够柔软状态，以便允许自动的处理。在树脂基体之上，保护膜21邻近金属网16.
图5示出根据本发明第三示例性实施例的制造用于航空航天的部件的过程中所述方法的状态。
层压装置23设置有轮廓形成件24，例如，预定要制造的机翼部分37的外部轮廓。具有沿X轴线26可移动的框架27的带材敷设机25具有敷设装置28。敷设装置28沿Y轴线29在框架27上是可移动的。敷设装置28的下端处的敷设辊31也是沿Z方向32可移动的并且设计成使得，优选地，在三个自由度上是可枢转的。优选地，敷设装置28具有保护机构的膨胀波纹管28a和用于激活敷设辊31的电子装置。带材敷设机25以及敷设辊31的定位通过计算机数字控制的方式控制。
敷设装置28供给材料进行敷设并且因此通过进料装置34在轮廓形成件24上构建薄片制品。作为图5中示出的所述结构的可选择方式，其中进料装置34设计成独立的装置，进料装置34本身可以设置在敷设装置28中或设计成敷设装置28的一部分。
在给出的情形中，根据本发明第一示例性实施例，进料装置34给敷设装置28供给叠层结构1，这种结构由织物35和捆3示出。此外，根据本发明的第二示例性实施例，进料装置34优选地具有构造型结构12的捆14。此外，进料装置具有捆36，用CFRP预浸的材料盘绕在捆36上。进料装置34设计成使得按需要从捆3、14或36供给材料到敷设装置28。然后，通过层压装置28引导这种材料，在任一中情况下背衬层6和20都被去除。在带材敷设机25中，这种叠层结构1和/或构造型结构12优选地在没有保护膜9、21的情况下使用。
构造型结构12和/或叠层结构1和/或用CFRP预浸的材料基本上通过敷设辊31施加到轮廓形成件24。在本示例性实施例中，通过敷设装置28形成的示例性机翼部分37已经设置在轮廓形成件24上。
图6示出沿图5中示例性机翼部分37截面线III-III的截面图。
第一层39，其具有预浸过的金属网，对应于第二示例性实施例，通过敷设装置28被施加到轮廓形成件24。然后，由单一方向的CFRP预浸材料制成的第二和第三层40、41被施加到第一层39。接下来的步骤中，包括预浸过的玻璃纤维叠层的第四层42，对应于第三示例性实施例，被施加到第三层41上。
还有一个可能的情况，就是随后将用铝制成的部件敷设到第四层42、在该铝部件上还构建另一层预浸玻璃纤维叠层以及用多个CFRP预浸材料层完成整个结构。这也可以用全自动的形式完成。
在机翼部分37制成后，例如在压热器内固化。
虽然本发明已经用优选的示例性实施例进行了描述，但是并不局限于这些，而是可以以不同的方式进行修改。
例如，根据第三示例性实施例的机翼部分的层可以以不同的方式形成。不同材料的次序，也就是金属网的预浸层、CFRP层和/或预浸过的玻璃纤维层可以变化和/或非常多样的方式供给。
对于本发明，可以使用已熟知的带材敷设机或经过变更的带材敷设机，例如具有用于切割金属网的特定的切割刀。
1叠层结构
2心轴
3捆
4展开端部
5纤维
6背衬层
8玻璃纤维叠层
9保护膜
10树脂基体
12构造型结构
13心轴
14捆
15展开端部
16金属网
17凹陷
18树脂基体
20背衬层
21保护膜
23层压装置
24轮廓形成件
25带材敷设机
26X轴线
27框架
28敷设装置
28a膨胀波纹管
29Y轴线
31敷设辊
32Z轴线
34进料装置
35织物
36CFRP预浸材料的捆
37机翼部分
39第一层
40第二层
41第三层
42第四层

Claims (12)

1.一种制造用于航空航天的部件(37)的方法，所述方法具有以下步骤：
供给构造型结构(12)，所述构造型结构(12)包括用金属制成并且用树脂基体预浸过的结构(16)，其中所述树脂基体处于柔软状态，所述结构(16)形成为金属网，所述金属网具有菱形形状、矩形和/或蜂窝形状的凹陷(17)，并且所述凹陷用树脂基体填充，所述凹陷(17)沿着所述结构(16)的厚度延伸，并且其中所述金属网包括固定的、限定的结构，金属网以片状形式延伸，
通过带材敷设机(25)在层压装置(23)上敷设所述构造型结构(1；12)，和
固化所述构造型结构(1；12)以形成所述部件(37)。
2.如权利要求1所述的方法，其特征在于：所述带材敷设机(28)沿多个轴线(26，29，32)移动。
3.如权利要求2所述的方法，其特征在于：所述带材敷设机(28)沿所述多个轴线(26，29，32)通过计算机数字控制的方式移动。
4.如权利要求1所述的方法，其特征在于：沿相对于所述层压装置(23)的不同的方向(26，29，32)敷设所述构造型结构(1；12)。
5.如权利要求1所述的方法，其特征在于：多个叠层和/或构造型结构(1；12)以一层在另一层上的方式敷设成多个层(39；42)。
6.如权利要求5所述的方法，其特征在于：CFRP预浸材料(36)的至少一层(40，41)被敷设在所述叠层和/或构造型结构(1；12)上、之间和/或下面。
7.如权利要求6所述的方法，其特征在于：CFRP预浸材料(36)的所述至少一层(40，41)通过所述带材敷设机(25)和/或另一台带材敷设机被敷设在所述叠层和/或构造型结构(1；12)上、之间和/或下面。
8.如权利要求5所述的方法，其特征在于：所述叠层结构(1)通过所述带材敷设机(25)被敷设在部件上。
9.如权利要求8所述的方法，其特征在于：所述部件用铝制成。
10.如权利要求5所述的方法，其特征在于：所述叠层和/或构造型结构(1；12)和/或CFRP预浸材料(36)按照所需通过进料装置(34)被供给到所述带材敷设机(25)。
11.如权利要求5所述的方法，其特征在于：所述叠层和/或构造型结构(1；12)作为盘绕的板条材料(3；14)供给。
12.如权利要求1所述的方法，其特征在于：所述构造型结构(12)在一侧设置有背衬材料(20)，并且在相对侧设置有保护膜(21)或背衬材料(20)，
其中通过带材敷设机(25)在层压装置(23)上敷设所述构造型结构(1；12)的步骤包括如下步骤：分别去除在所述一侧的背衬材料(20)以及在所述相对侧的保护膜(21)或背衬材料(20)。
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CA2654248A1 (en) 2008-02-07
WO2008015082A1 (en) 2008-02-07
EP2046570A1 (en) 2009-04-15
DE102006035847B4 (de) 2009-11-19
JP2009545468A (ja) 2009-12-24
EP2046570B1 (en) 2018-09-05
CN101500796A (zh) 2009-08-05
JP4940301B2 (ja) 2012-05-30
US8709188B2 (en) 2014-04-29
BRPI0715080A2 (pt) 2013-04-09
RU2438876C2 (ru) 2012-01-10
US20090269596A1 (en) 2009-10-29
DE102006035847A1 (de) 2008-02-14
RU2009102192A (ru) 2010-09-10

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