CN101945807A - 在形成横向接合部和横向接合部连接体的情况下连接两个机身部段的方法 - Google Patents

在形成横向接合部和横向接合部连接体的情况下连接两个机身部段的方法 Download PDF

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CN101945807A
CN101945807A CN2009801058153A CN200980105815A CN101945807A CN 101945807 A CN101945807 A CN 101945807A CN 2009801058153 A CN2009801058153 A CN 2009801058153A CN 200980105815 A CN200980105815 A CN 200980105815A CN 101945807 A CN101945807 A CN 101945807A
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main body
body section
section
longeron
end regions
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CN101945807B (zh
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阿克塞尔·绍尔曼
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Airbus Operations GmbH
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Airbus Operations GmbH
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    • B64C—AEROPLANES; HELICOPTERS
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    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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    • B64C1/069—Joining arrangements therefor
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    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
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Abstract

本发明涉及一种方法，用于连接两个利用纤维增强的塑料材料构成的机身部段(1，2，21，22)、特别是飞机机舱的被卷绕的机身部段(1，2，21，22)，机身部段在形成横向接合部(5，30)的情况下具有多个在内部彼此平行均匀间隔分布地布置在蒙皮(3，4，25，26)上的纵梁(10，11，35，36)。特别为了可以接合被卷绕的CFK机身部段，其中在连续的、工业的制造过程中能够实现简单的公差补偿，根据本发明的方法包括的步骤是：将第一和第二机身部段(1，2，21，22)彼此对齐；这样地加热和调整至少一个利用纤维增强的热塑性的塑料材料构成的横向连接板(9，23)，即可以在第一和第二机身部段(1，2，21，22)的有偏差的横截面几何结构之间实现公差补偿或者加热利用纤维增强的热塑性的塑料材料构成的第二机身部段(2，22)的至少一个端部区域(27)；和将两个机身部段(1，2，21，22)接合在一起。

Description

在形成横向接合部和横向接合部连接体的情况下连接两个机身部段的方法
技术领域
本发明涉及一种方法，用于连接两个利用纤维增强的塑料材料构成的机身部段、特别是飞机机舱的被卷绕的机身部段，机身部段在形成横向接合部的情况下具有多个在内部彼此平行均匀间隔分布地布置在蒙皮上的纵梁。
此外本发明涉及在两个机身部段之间的一个横向接合部连接体的两个设计方案。
背景技术
在现代的飞机制造中，碳纤维增强的连接部件(CFK-部件)越来越多地代替了传统的铝合金材料。因此例如机身部段、包括在内部布置的纵梁一体化地在CFK的卷绕工艺中进行制造。在此，适合的增强纤维结构优选地在主负荷方向上嵌入塑料矩阵中。例如可以利用热固塑性的塑料或可在机械上高负载的热塑性的塑料构成塑料矩阵。作为热固塑性的塑料优选地使用环氧树脂系统，而在热塑性的塑料的领域中例如使用聚醚醚酮(PEEK)。为了形成增强纤维结构通常使用碳纤维、玻璃纤维、芳族聚酰胺
Figure BPA00001206540000011
纤维、凯夫拉尔
Figure BPA00001206540000012
纤维、陶瓷纤维或天然纤维。
在此存在的较大的问题是将多个CFK-机身部段接合成一个机舱，这是因为在加固CFK-机身部段时由于其较高的固有刚度而不再可能进行公差补偿，并且此外特别是在横截面几何结构方面的公差在卷绕工艺中取决于原理总是比在传统的铝制造工艺的情况下显著地大大下降。在另一方面，来自于在压热器中进行硬化时的收缩过程、在拆卸或卷绕过程时不同的增强纤维密度、温度波动和压力波动、纤维半成品的质量不稳定性以及另外的干扰作用产生了这些不可避免的升高的制造公差。然而由静力的原因出发也绝不可能在机械应力下实现将机身部段接合在一起。
一种用于进行公差补偿的可能性在于外加物(所谓的“垫片”)，其以液态的、可硬化的形式和/或以固体的形式插入在机身部段之间的接缝缝隙中。然而该外加物对连接上的机身部段的机械负荷能力产生了不利的影响并且还明显地提高了装配投入，这是因为例如液态的、可硬化的“垫片”需要很长的硬化时间，在此期间接合的机身部段必须保持在位置中。此外由于安全原因而不允许在一些高负荷的连接部位中使用外加物。
发明内容
因此，本发明的目的在于，实现一种用于连接特别是被卷绕的CFK-机身部段的方法，该方法可以在连续的、工业的生产过程中实现简单的公差补偿。
该目的通过权利要求1所述的以下方法步骤来实现：
a)将第一和第二机身部段彼此对齐；
b)这样地加热或调整至少一个利用纤维增强的热塑性的塑料材料构成的横向连接板，即可以在第一和第二机身部段的有偏差的横截面几何结构之间实现公差补偿或者加热利用纤维增强的热塑性的塑料材料构成的第二机身部段的至少一个端部区域；和
c)将两个机身部段接合在一起。
根据第一个可替换方法提出，优选地利用热固塑性的CFK-材料构成两个需要接合的机身部段。进行接合时的公差补偿在此情况下通过加热来实现，并且通过在公差偏差的情况下进行的、为了最终建立连接所使用的横向连接板和/或纵梁连接部的调整或变形来实现，这些横向连接板和/或纵梁连接部为此目的而利用可在热影响下变形的纤维增强的、热塑性的塑料材料构成。这样地实现变形，即横向连接板以尽可能最大的表面区域接触机身部段的蒙皮的内侧面和纵梁连接部上的纵梁。横向连接板和/或纵梁连接部的变形通常通过至少两个直线形的(在端部方面)部段在相对方向上彼此平行推移而实现，其中位于每两个部段之间的同样直线形的中间部段出现轻微的倾斜。
在第二个可替换方法的情况下，两个需要连接的机身部段优选地至少在端部方面利用被卷绕的热塑性的CFK材料构成。为了实施该方法，需要接合的机身部段彼此对齐，其中通过加热需要附加的机身部段的端部部段实现公差补偿。在需要接合的机身部段的横截面几何结构之间的在一定条件下存在的偏差通过至少逐段地压紧和/或伸展需要附加的机身部段的加热的端部区域从而实现补偿，在此之后，以常规的方式在使用附加的连接组件的情况下实现两个机身部段的连接。
当环氧树脂系统用于构造在热固塑性的CFK部件情况下的树脂基体时，对于CFK部件、特别是机身部段、横向连接板和纵梁连接部而言，例如PEEK(聚醚醚酮(Polyetheretherketon))证明为是适合的热塑性的塑料材料。
根据第一个方法变体的有利的改进方案提出，这些机身部段借助于至少一个横向连接板进行连接。通过在内侧布置和固定在两个机身部段之间的横向接合部区域中的横向连接板，这能够实现保留迄今使用的常规的连接技术。首先对可能的公差偏差、特别是高度偏移，在需要接合的机身部段之间在横向接合部的区域中利用适合的测量系统进行检测，这例如可以利用计算机控制的激光测量系统来实现。随后利用纤维增强的热塑性的塑料材料构成的横向连接板可以在可电加热的模具中加热到这个程度，直至能够实现无问题的、无延误的塑化变形。根据需要借助于模具在由激光测量系统检测的公差偏差或横向接合部的实际的几何数据的基础上实现横向连接板的变形或调整，用于在机身部段之间补偿公差。在至少一个横向连接板的调整或变形实现之后，由模具中取出冷却的横向连接板，并且在内侧在两侧和机身部段的端部区域在建立横向接合部的情况下以常规的方式固定连接。如果需要使用多个横向连接板，则为了简化方法过程而将横向连接板直接依次地加热和变形或调整，并且随后装配用于连接机身部段。使用计算机控制的激光测量系统能够实现将本方法整合到全自动的生产线中。将至少一个横向连接板加热直到为了构成矩阵而使用的热塑性的塑料材料的软化温度，以用于实现调整或变形。在优选地使用热塑性的高效塑料材料时，聚醚醚酮(PEEK)处于330°℃的熔融温度中。
根据本方法的另一个设计方案，至少一个横向连接板和机身部段的各个端部区域通过铆合、以螺栓拧紧、粘合、焊接或其中任意的组合进行连接。
通过该设计方案可以无问题地将根据本发明的方法在保留已知的接合技术的情况下整合到现有的生产线中。
另一个有利的设计方案提出，加热和调整至少一个纵梁连接部以用于实现公差补偿。
为此目的首先检测在需要接合的机身部段中的各个相对的纵梁之间的已有的公差偏差，这例如又可以借助于无接触的激光测量系统实现。随后将至少一个纵梁连接部插入合适的、可电加热的模具中并加热。在模具中，然后对于这种情况，即确定公差偏差、特别是在需要连接的纵梁之间的高度偏移和/或侧面偏移，基于由测量系统测定的实际几何结构数据并参考预定的额定值实现用于在机身部段之间最佳的横向接合部的调整或变形，其中通常力求达到缝隙尺寸的周向方面的最小化和均匀化。在此所需要的是，将至少一个纵梁连接部至少加热到在单独情况下使用的热塑性的塑料材料的软化温度，对于塑料材料来说优选地是PEEK。
第二个方法变体的改进方案提出，至少一个横向连接板和第一机身部段的端部区域通过铆合、以螺栓拧紧、粘合、焊接或其中任意的组合进行连接，第二机身部段的端部区域利用特别是可电加热的、布置在端部区域中的加热件、特别是加热垫进行加热，并且将第二机身部段的被这样加热的端部区域推移到第一机身部段的端部区域上。
由于该操作方法而可以实现简单的公差补偿而不需要在横向接合部区域中的需要接合的机身部段之间的另外的中间步骤。加热垫在周向方向上完全包围需要附加的机身部段的端部区域，从而可以将需要附加的第二机身部段的全部端部区域同时加热。在此必须实现将端部区域加热到机身部段的为了构成矩阵而使用的热塑性的塑料材料的软化温度的范围中。如在第一个方法变体的情况下，复杂的测量系统对于在该方法变体中的公差补偿而言不是必须的。公差补偿以简单的方式和方法通过将需要附加的第二机身部段的被加热的并且进而可伸展变形的端部区域推移到第一机身部段的已固定在端部区域上的横向连接板上而实现。在此，需要附加的第二机身部段的端部区域同样逐段地被伸展和/或压紧。第二个方法变体优选地在建立仅在机械上负载较小的横向接合部时使用，从而通常没有需要连接的纵梁在横向接合部区域中的机身部段中延伸。此外借助于该方法变体产生的横向接合部的优点在于，即在横向接合部区域中的机身部段的蒙皮没有偏差、也就是说几乎齐平地彼此毗邻。
第二个方法变体的一个有利的改进方案提出，第二机身部段的端部区域在冷却时在至少一个横向连接板上在建立压力连接(Pressschluss)的情况下进行热压配合。
因此获得附加的第二机身部段的特别正好合适的并且同时固定的底座。
在另外的权利要求中说明了本方法和横向接合连接部的另外的有利的设计方案。
附图说明
图1在等轴视图中示出了在两个机身部段之间的、利用第一方法变体制造的横向接合部；
图2在侧视图中示出了根据图1的横向接合部；
图3在俯视图中示出了根据图1的横向接合部；
图4示出了根据第二方法变体的横向接合连接部的制造过程的视图；
图5在横截面图中示出了在两个机身部段之间的、利用第二方法变体形成的横向接合部。
在附图中，同样结构的元件分别具有相同的参考标号。
具体实施方式
图1示出了视图的透视的剖面，该视图描述了在两个基本上为桶形的机身部段之间的、根据第一方法变体制造的横向接合部。
在带有蒙皮3，4的两个机身部段1，2之间存在带有缝隙6的横向接合部5。机身部段1，2的两个端部7，8借助于横向连接板9相连接。在蒙皮3，4的未示出的内侧上相对地固定了具有T形的横截面几何结构的纵梁10，11。纵梁10，11分别在两侧和带有L形横截面几何结构的纵梁连接部12，13连接。横向连接板9和两个近似于对接延伸的蒙皮3，4的连接以及纵梁连接部12，13和纵梁10，11的连接通过铆合、以螺栓拧紧、夹紧、粘合、焊接或其中任意的组合得以实现。机身部段1，2可以在端部区域7，8中具有和理想的圆形几何结构有偏差的横截面几何结构，并且例如具有卵形的、椭圆形的横截面几何结构或几乎每个任意的、优选地连续弯曲的横截面几何结构。
为了实现在加热的状态中为了公差补偿的可变形性或可调整性，横向连接板9和纵梁连接部12，13利用纤维增强的热塑性的塑料材料构成，其中优选的是碳纤维增强的聚醚醚酮(PEEK)。可替换的是，可以使用其它的具有可比较的机械特性的热塑性的高效塑料。机身部段1，2的其余的组件、特别是蒙皮3，4以及纵梁10，11优选地利用纤维增强的热固塑性的塑料材料、例如利用碳纤维增强的环氧树脂系统构成。可替换的是，蒙皮3，4和/或纵梁10，11也可利用纤维增强的热塑性的材料、例如PEEK构成。
图2在侧视图中示出了在图1中的横向接合部5。
在蒙皮3，4和纵梁10，11之间的垂直的高度偏移14通过横向连接板9和两个纵梁连接部12，13在塑化状态中实现的变形得到补偿。所述部件的变形在机身部段的装配线附近的、未示出的模具中基于实际的几何结构数据实现，利用全自动的测量系统、特别是计算机控制的激光测量系统在横向接合部5的区域中测定该几何结构数据，并且将其和在机身部段1，2之间的横向接合部区域中的额定几何结构数据进行比较，以用于确定可能的公差偏差的位置和绝对值。
横向连接板9和纵梁连接部12，13的变形过程或调整过程应示范性地在前面的纵梁连接部13上加以说明。为了使前面的纵梁连接部13变形，例如将纵梁连接部轮廓13的直线形的部段15相对于纵梁连接部13的另一个直线形的部段16平行推移，其中形成了倾斜延伸的中间部段17。根据需要，相应地对纵梁连接部12和/或横向连接板9进行处理。在此，所述组件的变形基本上垂直于蒙皮3，4、即在示出的实施例中在箭头18的方向上实现。
图3示出了带有根据图1的横向连接板9的横向接合部5的俯视图。在纵梁10，11之间附加地存在有位于蒙皮3，4之间的横向偏移19，通过纵梁连接部12，13的变形或调整对其进行补偿。横向偏移19的补偿相应于在补偿高度偏移14(比较图2)时的做法，通过将两个纵梁连接部12，13横向于纵梁10，11的延伸方向(纵向方向)在箭头20的方向上进行变形来实现。
同时参考图1至图3用于说明根据本发明的、根据第一变体的方法。
首先将需要接合的机身部段1，2的端部区域7，8借助于测量系统、优选借助于全自动的计算机控制的激光测量系统进行测量，以用于测定在横向接合部5的区域中的机身部段1，2的实际几何结构。接着将两个机身部段1，2彼此对齐。可替换的是，可以基于已经测出的实际几何结构数据进行对齐。通过将两个机身部段1，2对齐实现的是，使公差偏差越过圆周尽可能均匀地分布并且同时最小化。这意味着，例如在机身部段2的端部区域7的(反向)面对设置的切点处尽可能地同样大地取消各个未示出的、到机身部段1的端部区域8的相一致的切点的距离，以便使得越过机身部段1，2的圆周对称地形成所需的公差补偿。
然后将至少一个横向连接板9加热并且借助于可电加热的模具这样地变形或调整，即可以将在两个机身部段1，2的端部区域7，8之间的可能的高度偏移14完全地补偿，以用于公差补偿。在此由于将测得的实际几何结构数据和机身部段1，2的给定结构的额定几何结构数据进行比较，实现了对模具的控制。随后这样变形的横向连接板9和机身部段1，2的两个端部区域7，8连接。横向连接板9和端部区域7，8的连接可以通过铆合、以螺栓拧紧、夹紧、粘合、焊接或其中任意的组合进行。通过使另外同样存在的横向连接板重复地变形或调整，可以完成横向接合部5以及进而完成两个机身部段1，2的接合。
在此之后使在内侧在机身部段1，2中均匀地在圆周上、彼此平行间隔布置的纵梁10，11分别优选地通过两个在两侧布置在纵梁10，11处的纵梁连接部12，13进行连接。纵梁10，11的调整通过加热和随后的变形或调整以如横向连接板9的调整同样的方式实现。纵梁10，11和纵梁连接部12，13的连接可以再次通过铆合、以螺栓拧紧、夹紧、粘合、焊接或其中任意的组合进行。
根据本发明的方法在第一实施方式变体中由此取决于，即横向连接板9和纵梁连接部12，13利用合适的、纤维增强的热塑性塑料材料构成。机身部段1，2的其余的组件、特别是蒙皮3，4以及固定在其中的纵梁10，11也可以利用纤维增强的热固塑性塑料、例如碳纤维增强的环氧树脂构成。根据本发明的方法能够通过建立在横向接合部区域中的机身部段1，2的、彼此偏差微小的横截面几何结构之间的补偿可能性，对大体积的机身部段1，2进行无压力地装配。
根据图4应说明了第二方法变体的过程。首先将第一和第二机身部段21，22彼此对齐，至少是需要附加在第一机身部段21处的第二机身部段22至少在端部区域中利用纤维增强的热塑性塑料材料构成。例如可以利用具有碳纤维钢筋(Kohlefaserarmierung)的聚醚醚酮(PEEK)构成机身部段22。
接着将至少一个横向连接板23在内侧在第一机身部段21的端部区域24中和蒙皮25固定地连接。
接着将蒙皮26在需要附加的第二机身部段22的端部区域27中加热并且因此可实现有效地可塑性变形，以便实现公差补偿。
通过将带有软化的端部区域27的第二机身部段22在箭头28的方向上推移到横向连接板23处，在同时进行的可能需要的公差补偿的情况下将两个机身部段21，22在另外的方法步骤中进行接合。
为了最终连接两个机身部段21，22，通常需要将横向连接板23额外地和附加的机身部段22的端部区域27通过铆合、以螺栓拧紧、粘合、焊接或其中任意的组合进行固定连接。
为了加热端部区域27，将优选的可电加热的、柔性的以及环形的加热垫29或密封圈布置在该端部区域上。加热垫29以优选的方式保留在端部区域27上，直到第二机身部段22被完全推移到第一机身部段21上为止。加热垫29在径向方向上能够实现微小的纵向补偿，以便避免产生压力并且简化加热垫29或加热密封圈的取下。
在将第二机身部段22推移到第一机身部段21上之后，移开加热垫29，并且还可以在冷却之前在一定条件下使这样构成的横向接合部的上侧面变得平滑。可选择的平滑例如可以利用板实现，使其几何结构与横向接合部区域的所希望的外部几何结构取得一致，并且利用在横向接合部区域中的高的压下力来压紧该几何结构。对于这种情况，即在移开加热垫29之后尽可能地冷却横向接合部的区域，则板优选地具有集成的电加热装置，以便使横向接合部的区域重新至少加热到所使用的热塑性的纤维增强的塑料材料的塑化温度的范围中并且使其平滑。
大量的、成本高的测量和需要接合的机身部段21，22的两个端部区域24，27的精密的预对齐与第一方法变体相比被省去。
对于这种情况，即需要附加的第二机身部段22的端部区域27和第一机身部段21相比具有稍微变小的横截面几何结构，则在端部区域27冷却之后并由于受冷却限定的收缩，在端部区域27和横向连接板23之间出现轻微的压力连接，由此确保了特别正好合适的并且同时固定的底座。
横向连接板23优选地利用纤维增强的热固塑性的材料、例如碳纤维增强的环氧树脂构成。该根据第二变体的方法没有设计用于生产在飞机机舱的机械高负载的区域中的横向接合部，从而在横向接合部的区域中通常不布置纵梁并且由此也不设置纵梁连接部。
图5示出了穿过根据图4的、根据本发明构成的横向接合部的横截面示意图。
两个蒙皮25，26在端部区域24，27中借助于横向连接板23在建立横向接合部30的情况下相连接。细长的缝隙31在两个蒙皮25，26之间延伸。通过四条点划线勾画出固定件，例如铆钉、螺栓或类似物。此外在端部区域27中固定了下方的环形框架轮廓32以及夹子33以用于将环形框架在侧面支撑在横向连接板23上。具有近似于L形横截面几何结构的下方的环形框架轮廓32和上方的、相反的L形环形框架轮廓34通过两个固定件、例如铆钉进行连接，以用于构成近似于S形的横截面几何结构。因为这两个方法变体首要地设计用于在飞机机舱的负载弱的区域中建立横向接合部，所以在横向接合部30的区域中两个纵梁35，36或纵梁连接部并不是强制性地存在的或必需的。
两个环形框架轮廓32，34以及夹子33和可任意选择布置的纵梁35，36可以利用任意的材料构成。
参考标号表
1     机身部段(第一)
2     机身部段(第二、需要附加的)
3     蒙皮
4     蒙皮
5     横向接合部
6     缝隙
7     端部区域(第一机身部段)
8     端部区域(第二机身部段)
9     横向连接板
10    纵梁
11    纵梁
12    纵梁连接部
13    纵梁连接部
14    高度偏移
15    部段(纵梁连接部)
16    部段(纵梁连接部)
17    中间部段(纵梁连接部)
18    箭头
19    横向偏移
20    箭头
21    机身部段(第一)
22    机身部段(第二，需要附加的)
23    横向连接板
24    端部区域(第一机身部段)
25    蒙皮
26    蒙皮
27    端部区域(第二机身部段)
28    箭头
29    加热垫
30    横向接合部
31    缝隙
32    下方的环形框架轮廓
33    夹子
34    上方的环形框架轮廓
35    纵梁
36    纵梁

Claims (13)

1.一种方法，用于连接两个利用纤维增强的塑料材料构成的机身部段(1，2，21，22)、特别是飞机机舱的被卷绕的所述机身部段(1，2，21，22)，所述机身部段在形成横向接合部(5，30)的情况下具有多个在内部彼此平行均匀间隔分布地布置在蒙皮(3，4，25，26)上的纵梁(10，11，35，36)，包括步骤：
a)将第一和第二机身部段(1，2，21，22)彼此对齐；
b)这样地加热和调整至少一个利用纤维增强的热塑性的塑料材料构成的横向连接板(9，23)，即可以在所述第一和第二机身部段(1，2，21，22)的有偏差的横截面几何形状之间实现公差补偿或者加热利用纤维增强的热塑性的塑料材料构成的第二机身部段(2，22)的至少一个端部区域(27)；和
c)将两个所述机身部段(1，2，21，22)接合在一起。
2.根据权利要求1所述的方法，其特征在于，两个所述机身部段(1，2)借助于至少一个所述横向连接板(9)进行连接。
3.根据权利要求1或2所述的方法，其特征在于，至少一个所述横向连接板(9)和所述机身部段(1，2)的各个端部区域(7，8)通过铆合、螺纹接合、粘合、焊接或其中任意的组合进行连接。
4.根据权利要求1至3所述的方法，其特征在于，加热和调整至少一个纵梁连接部(12，13)以用于实现公差补偿。
5.根据权利要求1至4中任一项所述的方法，其特征在于，所述机身部段(1，2)的各个相对的所述纵梁(10，11)分别和至少一个纵梁连接部(12，13)连接。
6.根据权利要求1至5中任一项所述的方法，其特征在于，所述纵梁连接部(12，13)和所述纵梁(10，11)通过铆合、螺纹接合、粘合、焊接或其中任意的组合进行连接。
7.根据权利要求1至6中任一项所述的方法，其特征在于，在加热至少一个所述横向连接板(9)和/或至少一个所述纵梁连接部(12，13)时达到一个温度，所述温度等于纤维增强的、特别是碳纤维增强的热塑性的所述塑料材料的至少一个软化温度。
8.根据权利要求1所述的方法，其特征在于，至少一个横向连接板(23)和所述第一机身部段(21)的端部区域(24)特别是通过铆合、以螺栓拧紧、粘合、焊接或其中任意的组合进行连接，所述第二机身部段(22)的所述端部区域(27)利用特别是可电加热的、特别是至少布置在所述端部区域(27)中的加热件、特别是加热垫(29)进行加热，并且将所述第二机身部段(22)的被这样加热的所述端部区域(27)推移到所述第一机身部段(21)的所述端部区域(24)上。
9.根据权利要求8所述的方法，其特征在于，所述第二机身部段(22)的所述端部区域(27)在冷却时在至少一个横向连接板(23)上在建立压力连接的情况下进行热压配合。
10.根据权利要求8或9所述的方法，其特征在于，所述机身部段(21，22)的两个所述端部区域(24，27)借助于至少一个所述横向连接板(23)，特别是通过铆合、螺纹接合、粘合、焊接或其中任意的组合进行连接。
11.根据权利要求8至10中任一项所述的方法，其特征在于，在加热所述机身部段(22)的至少一个所述端部区域(27)时达到一个温度，所述温度等于纤维增强的、特别是碳纤维增强的热塑性的所述塑料材料的至少一个软化温度。
12.一种横向接合部连接体(5)，位于两个利用纤维增强的塑料材料构成的机身部段(1，2)、特别是被卷绕的所述机身部段(1，2)之间，具有：多个在内部彼此平行均匀间隔分布地布置在蒙皮(3，4)上的、特别是根据权利要求1至7中任一项所述的方法制造的纵梁(10，11)；至少一个横向连接板(9)和多个纵梁连接部(12，13)，其特征在于，为了通过热变形和调整来实现公差补偿，至少一个横向连接板(9)和至少一个纵梁连接部(12，13)利用纤维增强的热塑性的塑料材料、特别是碳纤维增强的聚醚醚酮构成。
13.一种横向接合部连接体(30)，位于两个利用纤维增强的塑料材料构成的机身部段(21，22)、特别是被卷绕的所述机身部段(21，22)之间，具有：多个在内部彼此平行均匀间隔分布地布置在蒙皮(25，26)上的、特别是根据权利要求8至11中任一项所述的方法制造的纵梁(35，36)；至少一个横向连接板(23)，其特征在于，为了通过取决于加热的塑化来实现公差补偿，至少一个机身部段(21，22)利用纤维增强的热塑性的塑料材料、特别是碳纤维增强的聚醚醚酮构成。
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CN106891531A (zh) * 2015-12-21 2017-06-27 空中客车运作有限责任公司 一种焊接系统
CN106891531B (zh) * 2015-12-21 2019-03-08 空中客车运作有限责任公司 一种焊接系统
CN106697327A (zh) * 2016-12-19 2017-05-24 中航成飞民用飞机有限责任公司 飞机壁板对接结构
CN106697327B (zh) * 2016-12-19 2019-10-18 中航成飞民用飞机有限责任公司 飞机壁板对接结构

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BRPI0907830A2 (pt) 2018-10-23
WO2009103635A1 (de) 2009-08-27
US20100320321A1 (en) 2010-12-23
US9187167B2 (en) 2015-11-17
CN101945807B (zh) 2013-10-23
DE102008010197B4 (de) 2012-03-22
JP2011514278A (ja) 2011-05-06
DE102008010197A1 (de) 2009-09-10
RU2010138606A (ru) 2012-03-27
CA2713115A1 (en) 2009-08-27
EP2242682A1 (de) 2010-10-27

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