Skew-angle radius filler to reduce the risk of delamination of a laminated stringer assembly

A technology of inclination angle and radius, used in thin material processing, aircraft parts, chords/stringers, etc., can solve problems such as adding extra weight to aircraft, and achieve the effect of large operating load and enhanced joint ability.

Active Publication Date: 2013-08-21
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, adding extra weight to the aircraft is not desirable

Method used

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  • Skew-angle radius filler to reduce the risk of delamination of a laminated stringer assembly
  • Skew-angle radius filler to reduce the risk of delamination of a laminated stringer assembly
  • Skew-angle radius filler to reduce the risk of delamination of a laminated stringer assembly

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[0030] 本文描述了用于使用倾斜角半径填料增强接合能力和降低在桁条中分层的风险的技术。通过利用本文所呈现的技术和概念,与使用常规矩形半径填料的现有的桁条相比,所述桁条条形件可以通过使用倾斜角半径填料承受更大的平面外(引出)载荷,而不分层。

[0031] 在下面的具体实施方式中,参考构成特定实施例或示例的一部分并且以说明的方式示出的附图。现在参考附图,其中类似标记贯穿几个附图表示类似的元件,将描述用于使用根据各种实施例的倾斜角半径填料增强接合能力和降低蒙皮-桁条组件的分层风险的技术。

[0032] figure 2 示出了根据各种实施例的飞行器机翼的翼盒的透视图。翼盒200是飞行器机翼的结构核心,并提供了结构支撑以及对附连到机翼的各种飞行器部件的附连点。翼盒200可包括横跨翼盒200的跨度横向延伸的肋条区段210A、210B、210N。任何特定的肋条区段(如肋条区段210A)通常可在这里称为肋条区段210。肋条区段210可附连到沿翼盒200的跨度纵向延伸的多个桁条220A、220N。任何特定桁条(如桁条220A)通常可在这里称为桁条组件220。桁条组件220可用于向所述机翼的机翼蒙皮(figure 2 not shown) to provide additional stiffness. According to various embodiments, the wing skin may be attached to the stringer assembly forming a skin-stringer panel.

[0033] It should be understood that wing box 200 has been greatly simplified in the drawings for clarity. For example, the spars and all aircraft system components located in the wings are not shown. Furthermore, only a small number of representative rib segments 210 and stringer assemblies 220 are shown. ...

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Abstract

Technologies are described herein for enhancing joint capability and reducing the risk of delaminating a stringer using skew-angle radius fillers. A skew-angle radius filler (302A, 302B) for enhancing joint capability includes a top surface (303A, 303B) and a bottom surface (305A, 305B) separated by a thickness. The radius filler also includes a radius contact (304A, 304B) side that has an edge radius (307A, 307B) that is sized to match a radius of a web joint of a stringer. The radius filler also includes a pair of opposing non-parallel sides (306A, 308A, 306B, 308B) that extend from the radius contact side at an acute angle, and a rear side (310A, 310B) that is shorter than the radius contact side.

Description

technical field [0001] 本公开的领域一般涉及半径填料。特别地,本公开的领域涉及降低层压桁条组件的分层风险的倾斜角半径填料。 Background technique [0002] 飞行器翼盒为飞行器机翼提供了结构核心。所述翼盒包括一系列肋条区段,所述肋条区段沿纵向间隔开并连接到一个或更多个延伸翼盒长度的翼梁和桁条。所述桁条用于将所述机翼的机翼蒙皮或外层附连到所述翼盒的肋条区段。所述桁条可在结构上支持所述机翼蒙皮并且将蒙皮载荷传递到所述机翼的内部结构。在碳纤维增强的塑料(CFRP)桁条制造中,每个桁条可以由被固化和 / 或结合在一起以形成所述桁条的多个结构部件或构件制成。 [0003] 例如,如图1所示,CFRP I-桁条100通过以下方式形成,即通过固化两个预成型的C形装载构件(charge member)110、120到一起而形成腹板和部分所述桁条120的上凸缘112、122和下凸缘114、124。顶部构件130和底部构件140也固化到连接的C形装载构件110、112的上凸缘112、122和下凸缘114、124,从而分别建立顶盖和底盖。条状材料,例如所谓的条形件150用在所述顶部构件130和C形装载构件110、120之间,并且底部条形件160在所述底部构件140和C形装载构件110、120之间,以便填充可应用的空间。当所有部件被固化在一起时,所述CFRP I-桁条100被形成并准备投入使用。 [0004] CFRP桁条所遇到的一个问题是,如果过多的剪力和弯矩力被施加在所述桁条上,则所述CFRP桁条可能容易出现分层。增加的剪力和弯矩力在所述桁条上的常见位置包括肋条被栓接到桁条的位置。所述分层可能发生在所述I-桁条100的条形件150、160周围的区域。为了减少分层的可能性,半径填料用在肋条被栓接到桁条的位置。半径填料通常被配置为夹在肋条和桁条之间的矩形件材料。半径填料具有的边缘的形状被设计为邻接所述C形装载构件110的垂直构件116和下凸缘114的接缝,并且填充形成在所述C形装载构件110的垂直构件116和下凸缘114之间的半径118。这样做,半径填料对此接点提供了额外的结构增强件,并分配所述剪力和弯矩力,以便降低在所述I-桁条100的条形件区域处出现分层的风险。 [0005] CFRP桁条所遇到的一个问题是...

Claims

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Application Information

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IPC IPC(8): B64C3/18B64C3/26
CPCB64C3/182B64C3/187B64C3/26Y10T428/24174Y10T428/24479Y10T428/24488Y10T29/49826
Inventor H·权D·P·墨菲K·B·李
Owner THE BOEING CO
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