CN102481732B - 结构构件和用于结构构件的制造方法 - Google Patents

结构构件和用于结构构件的制造方法 Download PDF

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CN102481732B
CN102481732B CN201080022906.3A CN201080022906A CN102481732B CN 102481732 B CN102481732 B CN 102481732B CN 201080022906 A CN201080022906 A CN 201080022906A CN 102481732 B CN102481732 B CN 102481732B
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汉斯-约尔根·韦伯
格雷格尔·克里斯蒂安·安德勒斯
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Abstract

本发明涉及一种用于飞机或宇宙飞船的结构构件(102)，具有：在构件平面上伸展的构件芯体(408)；具有第一和第二盖层(401、402)，其在构件平面上延伸地设计在构件芯体(408)的两个相互对立的界面上；具有大量在构件平面上分布的撑条(403)，其将第一盖层和第二盖层通过构件芯体相互连接；以及具有加固带(106)，其沿基本上平行于构件平面延伸的加固路径在盖层之间延伸。

Description

结构构件和用于结构构件的制造方法
技术领域
本发明涉及一种用于飞机或宇宙飞船的结构构件以及一种用于此类结构构件的制造方法。此外，本发明还涉及一种具有此类结构构件的飞机或宇宙飞船。
背景技术
尽管可用于任意的结构构件，本发明以及其所解决的技术问题还是参照运输飞机的机身外皮来详细描述。
EP1134069公开了一种由芯体连接构件以双外皮的构造方式制成的用于飞机的结构构件，芯体连接构件具有发泡材料芯体。此类结构构件(特别是由纤维增强的塑料制成)提供了相对于由常见的材料比如铝制成的结构构件的较大的重量优势。不过以双外皮构造方式的此类结构构件的制造和操作在安装成更大的结构比如飞机或宇宙飞船时特别费时且昂贵。此外在安装时出现的损坏的修复也很耗费。
发明内容
因此本发明的目的在于，实现双外皮结构构件的可靠和成本低廉的应用。
根据本发明该目的通过具有权利要求1的特征的结构构件或通过具有权利要求13的特征的制造方法实现。
本发明的基本思路在于，以如下方式加固平面般地在构件平面上伸展的、具有两个通过在其间包入的芯体连接的盖层的结构构件，在盖层之间设置加固带，其沿基本上平行于构件平面延伸的加固路径在盖层之间延伸。由于加固带如芯体在盖层之间的内部延伸，其可以利用在芯体复合件的制造中采用的方法构建，这相对于利用常见的加固元件比如纵梁或舱壁的安装提供了较大的成本优势。此外由于加固带在盖层内部延伸，还在盖层之间保护其不受损。
根据一种优选的改进，构件芯体具有发泡材料。这实现了成本低廉地制造结构构件，其中，发泡材料中的撑条被设计成临时支撑的辅助材料并且与盖层连接，其中，发泡材料由于其重量轻可以节省成本地简单地保留在结构芯体中。可替换的是还可以除去发泡材料，用以实现更轻的重量。
根据一种优选的改进，撑条分别具有树脂灌入的纤维束。这实现了成本低廉地制造结构构件，其中撑条比如以简单的缝纫方法构建在发泡材料中并且以树脂灌入在此产生的穿通孔中。
根据一种优选的改进，加固带通过构件芯体中提高的撑条密度的区形成。这实现了极其小的制造成本，因为加固带可以利用为置入撑条总归要采用的方法和设备产生。此外撑条可以几乎在针对加固带的延伸的几何尺寸上不受限地置入。
根据一种可替换的优选的改进，加固带通过构件芯体中的在加固路径上延伸的衬垫(Einlage)形成。以这种方式可实现较高的稳固性；还实现了将沿与衬垫邻接的盖层稳固地相互连接起来。衬垫优选具有软管状的纤维网，其包围衬垫芯体，因为该结构在极小的自重的情况下特别稳固。
根据一种优选的改进，至少一个撑条不仅穿透结构芯体而且该穿透衬垫芯体。这样将衬垫特别牢固地捆扎(Einbinden)起来。优选撑条相对于构件表面对角地延伸，因为这样就可以简单地将其从外部置入。
根据一种优选的改进，构件平面具有在至少一个空间方向上的弯曲，其中，加固带螺旋状地相对于弯曲的方向成对角地延伸。由此可以有利地使构件克服沿弯曲轴线的扭转振动进行加固。
根据一种优选的改进，设置第一和第二加固带，它们相互以一个角度交叉地延伸。由此可以有利地使构件克服在不同方向中受载的情况下的变形进行加固。
根据一种优选的改进，加固带在第一和第三分段中基本上在一致的方向上延伸并且在第一和第三分段之间设置的分段中具有形成两个环形连接的分支的分裂处。以这种方式可以将加固件在没有实质上的稳固性丧失的情况下围绕结构构件中的平面的分段(比如窗口截面)引导。
附图说明
下面参照附图借助于实施例详细描述本发明。其中：
图1为根据一种实施方式的示例性结构构件的截面图；
图2为具有根据一种实施方式的结构构件的飞机的机身桶段的侧视图；
图3为根据一种实施方式的、具有衬垫的结构构件的示意性侧视图；
图4为根据一种实施方式的、用于图3的结构构件的制造方法的示图；
图5为根据另一种实施方式的、具有衬垫的结构构件的示意性截面图；
图6为根据一种实施方式的、具有窗口开孔的结构构件的示意性截面图；以及
图7为根据一种实施方式的、具有门开口的结构构件的示意性截面图。
只要没有给出相反的说明，附图中相同的附图标记表示相同的或功能相同的部件。
具体实施方式
图1示出了由发泡材料制成的具有平面般地在复合构件的构件平面上伸展的构件芯体408的结构构件102的截面视图，在其相对的、基本上平行延伸的面上构建由纤维材料制成的第一盖层401和第二盖层402。该构件平面平行于盖层401、402延伸且垂直于图1的绘图平面竖立。在第一盖层401和第二盖层402之间，由纤维束构成的撑条403穿过构件芯体408延伸，撑条403的端部406贴靠在盖层401、402上。盖层401、402和撑条403以共同的塑料基体填充。
撑条403以基本上恒定的最小表面密度分布在结构构件102的整个构件平面上。此外沿加固带106(该加固带沿基本上平行于构件平面延伸的加固路径104在盖层之间延伸)的伸长的区，撑条103的表面密度被提高到超过最小表面密度。由此该结构构件102在加固带106的区域中具有提高的刚性。
图2示出了飞机的机身桶段206的侧视图。该机身桶几何形状在纵向上被分开，其中，机身桶段上半部由具有如图1所示的双外皮构造的结构构件102形成。该结构构件102一体地制成，比如借助于具有内成形面的成形工具，用以确保外公差。机身桶段下半部202可以比如以类似的方式由金属或另一种材料制成。
在结构构件102中通过提高的撑条403的表面密度形成的加固带106、106′、106″、106″′不仅在飞机纵向203上延伸，而且在既相对于飞机纵向又相对于基本上圆筒状弯曲的结构构件102的弯曲方向204倾斜的方向上延伸，并且螺旋状成对角地围绕机身桶段206盘绕。此外成对角地延伸的加固带106、106′以大约90°的角度α相交。
在机身桶段206中设计一排窗口开孔208，它们由环形的加固部200包围。环形的加固部200被包含在加固带106、106′、106″、106″′的延伸中，其中，比如加固带106的第一分段211在对角的加固路径104的方向上延伸，直到其遇到围绕窗口开孔208的环形加固部200。在窗口开孔的区域中的第二分段212中环形加固段200接管加固带的功能，该加固带在此分裂成两个环形的相互关联的分支。在环形加固部200的相对立的一侧这些分支结合到一起，并且加固带的延伸在第三分带213中朝加固路径104的方向延续。
所示的加固模式纯粹是示例性的且可以完全与局部的受载(载荷导入、剪切)进行匹配。还可以在该加固模式中纳入发泡材料的几何尺寸的变型(厚度跃变、弯曲度、坡度)。
图3示出了另一种结构构件102的示意性截面图，其由具有发泡材料芯体408和盖层401、402的第一构件半部311以及具有发泡材料芯体408′和盖层401、402的第二构件半部312沿在图3中心垂直于绘图平面延伸的接合线接合到一起。沿接合线在盖层401、401′和402、402′之间置入具有由发泡材料制成的衬垫芯体302和由软管状纤维网制成的外罩300的衬垫(Einlage)302、300。外罩300比如与盖层401、401′、402、402′和撑条403一起以树脂灌入。衬垫通过外罩用作加固带106。
图4示出了用于图3的结构构件的一种可能的制造方法，其中，在两个构件半部311、312上除去各芯体408、408′的一部分并且代替该部分推入衬垫300、302。通过额外置入的撑条500、502(其不仅贯穿盖层401、401′、402、402′而且贯穿衬垫300、302的外罩300)可以进一步加固衬垫的捆扎。
图6示出了具有窗口600的开孔的结构构件102的示意性截面图，其中，由如图2描述的三个分段211、212、213构成的加固带越过窗口开孔延伸。环形的衬垫200比如如图3中的衬垫300、302那样构建。图7示出了具有门704的开孔的结构构件102的示意性截面图。作为额外的加固件将托架700和另一个盖层702安装在飞机机身的内侧面上。
尽管本发明在此借助于优选的实施例进行描述，但其不限于此，而是可以以各种各样的方式进行改变。
比如可以以所述的方式构建飞机的其它结构构件比如承载面或尾翼。
附图标记
102结构构件
104加固路径
106加固带
200环形结构
202下部外皮
203飞机纵向
204弯曲方向
206机身桶段
211-213带分段
300软管网
302衬垫芯体
311、312构件半部
401、402盖层
403撑条
406锚固件
408构件芯体
500、502额外的撑条
600窗口
500竖直的撑条
502对角的撑条
700托架
702其它的盖层
704门

Claims (14)

1.一种用于飞机或宇宙飞船的结构构件(102)，具有：
在构件平面上伸展的构件芯体(408)；
第一盖层(401)和第二盖层(402)，其在构件平面上延伸地设计在构件芯体(408)的两个相互对立的界面上；
加固带(106)，其通过沿基本上平行于构件平面延伸的加固路径(104)在盖层(401、402)之间延伸的、具有衬垫芯体(302)和包围衬垫芯体(302)的软管状的纤维网(300)的衬垫形成到构件芯体(408)中；以及
大量在构件平面上分布的撑条(403、500、502)，其将第一盖层(401)和第二盖层(402)通过构件芯体(408)相互连接，其中，至少一个撑条(500、502)不仅穿透至少一个盖层(401、402)而且穿透软管状的纤维网(300)。
2.根据权利要求1所述的结构构件(102)，其特征在于，所述构件芯体(408)和/或衬垫芯体(302)具有发泡材料。
3.根据权利要求1或2所述的结构构件(102)，其特征在于，所述撑条(403)分别具有一个树脂灌入的纤维束。
4.根据权利要求1或2所述的结构构件(102)，其特征在于，至少一个撑条(500、502)穿透衬垫。
5.根据权利要求4所述的结构构件(102)，其特征在于，至少一个撑条(500、502)相对于构件平面成对角地延伸。
6.根据权利要求1或2所述的结构构件(102)，其特征在于，盖层(401、402)、软管状的纤维网(300)和撑条(403、500、502)共同以树脂灌入。
7.根据权利要求1或2所述的结构构件(102)，其特征在于，所述构件平面具有在至少一个弯曲方向(204)上的弯曲部，其中，加固带(106)螺旋状地相对于弯曲方向(204)成对角地延伸。
8.根据权利要求1或2所述的结构构件(102)，其特征在于，第一加固带(106)和第二加固带(106′)相互以角度交叉地延伸。
9.根据权利要求1或2所述的结构构件(102)，其特征在于，所述加固带(106)在第一分段(211)和第三分段(213)中基本上在加固路径(104)的方向上延伸，并且在第一分段(211)和第三分段(213)之间设置的第二分段(212)中具有形成两个环形连接的分支的分裂处(200)。
10.一种用于飞机或宇宙飞船的机身外皮(206)，具有按照权利要求1至9中任一项所述的结构构件。
11.一种飞机或宇宙飞船，具有按照权利要求10所述的机身外皮(206)或按照权利要求1至9中任一项所述的结构构件(102)。
12.一种用于制造用于飞机或宇宙飞船的结构构件(102)的方法，具有下列步骤：
提供在构件平面上伸展的构件芯体(408)，其具有发泡材料；
在构件芯体(408)的两个相互对立的界面上设置第一盖层(401)和第二盖层(402)，其在构件平面上延伸；
置入加固带(106)，其通过沿基本上平行于构件平面延伸的加固路径(104)在盖层(401、402)之间延伸的、具有衬垫芯体(302)和包围衬垫芯体(302)的软管状的纤维网(300)的衬垫形成到构件芯体(408)中；以及
构建大量在构件平面上分布的撑条(403、500、502)，其将第一盖层(401)和第二盖层(402)通过构件芯体(408)相互连接，从而使至少一个撑条(500、502)不仅穿透至少一个盖层(401、402)而且穿透软管状的纤维网(300)。
13.根据权利要求12所述的方法，其特征在于，盖层(401、402)、软管状的纤维网(300)和撑条(403、500、502)共同以树脂灌入。
14.根据权利要求12或13所述的方法，其特征在于至少部分地除去发泡材料的步骤。
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