CN105539809A - 一种分段式蜂窝夹层结构 - Google Patents

一种分段式蜂窝夹层结构 Download PDF

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Publication number
CN105539809A
CN105539809A CN201410592470.1A CN201410592470A CN105539809A CN 105539809 A CN105539809 A CN 105539809A CN 201410592470 A CN201410592470 A CN 201410592470A CN 105539809 A CN105539809 A CN 105539809A
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CN
China
Prior art keywords
honeycomb
laying
oblique angle
technical
inclined corner
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Pending
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CN201410592470.1A
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English (en)
Inventor
李程文
牛英杰
王宝民
荆磊
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Harbin Aircraft Industry Group Co Ltd
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Harbin Aircraft Industry Group Co Ltd
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Application filed by Harbin Aircraft Industry Group Co Ltd filed Critical Harbin Aircraft Industry Group Co Ltd
Priority to CN201410592470.1A priority Critical patent/CN105539809A/zh
Publication of CN105539809A publication Critical patent/CN105539809A/zh
Pending legal-status Critical Current

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Abstract

本发明属于蜂窝夹层结构技术领域,涉及一种分段式蜂窝夹层架构。本技术方案的主要特点在于,在蜂窝(2)的斜角处端面上铺设的铺层(1)与斜角上铺设的铺层(1)为分段式,即端面上的铺层(1)只延伸到斜角的最下方,斜角上的铺层(1)从斜角的最上方开始铺设,二者在斜角处为搭接形式。这一技术方案解决了现有技术中,蜂窝在受压成型时易向四周滑移的技术问题。

Description

一种分段式蜂窝夹层结构
技术领域
本发明属于蜂窝夹层结构技术领域,涉及一种分段式蜂窝夹层架构。
背景技术
在现有飞行器的蒙皮及整流罩设计制造中,主要采用复合材料蜂窝夹层结构,如图1所示,在设计上蜂窝上表面与层压板区域一般采用同一铺层。但是,这一设计在加压固化的过程中容易导致蜂窝向四周滑移。
发明内容
本发明要解决的技术问题:
提供一种能够防止蜂窝在加压固话过程中发生滑移的夹层结构。
本发明的技术方案:所述的夹层结构包括铺层1和蜂窝2,蜂窝2在周边切有斜角,蜂窝2端面上铺设的铺层1与斜角上铺设的铺层1为分段式,蜂窝2端面上铺设的铺层1覆盖至斜角的最下端,并覆盖在斜角上铺设的铺层1上方。
本发明的有益效果:
现有技术中蜂窝上表面与层压板区域采用同一铺层,在加压固化的过程中导致蜂窝向四周滑移。本发明采用了蜂窝内侧铺层分段形式,蜂窝区域处铺置的纤维材料与夹层板处纤维材料不为一体,两者在蜂窝斜角处进行搭接,减少了从层压板传递到蜂窝区域的压力,从而减少蜂窝受压向四周延伸;并且在蜂窝切角处进行搭接,变相增加了此处的铺层,相对来说切角处纤维材料中更多的胶液浸入蜂窝切角,阻止了蜂窝的滑移。
附图说明
图1为连续式蜂窝夹层结构示意图;
图2为分段式蜂窝夹层结构示意图;
图中:1为铺层,2为蜂窝。
具体实施方式
下面结合附图对本发明做详细说明。
如图2所示,该技术方案主要包括铺层1和蜂窝2,蜂窝2在周边切有斜角,蜂窝2端面上铺设的铺层1与斜角上铺设的铺层1为分段式,蜂窝2端面上的铺层1覆盖在斜角上的铺层1上方,两者在分段处为搭接形式。斜角上的铺层1是从斜角的最上端开始铺设,直至延伸到层压板区域。而蜂窝2端面上的铺层1从端面上开始一直延伸到斜角的最下端。二者在斜角上为搭接方式,端面上的铺层覆盖在斜角的铺层上。

Claims (1)

1.一种分段式蜂窝夹层结构,其特征为:所述的夹层结构包括铺层(1)和蜂窝(2),蜂窝(2)在周边切有斜角,蜂窝(2)端面上铺设的铺层(1)与斜角上铺设的铺层(1)为分段式,蜂窝(2)端面上铺设的铺层(1)覆盖至斜角的最下端,并覆盖在斜角上铺设的铺层(1)上方。
CN201410592470.1A 2014-10-28 2014-10-28 一种分段式蜂窝夹层结构 Pending CN105539809A (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410592470.1A CN105539809A (zh) 2014-10-28 2014-10-28 一种分段式蜂窝夹层结构

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410592470.1A CN105539809A (zh) 2014-10-28 2014-10-28 一种分段式蜂窝夹层结构

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CN105539809A true CN105539809A (zh) 2016-05-04

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4622091A (en) * 1984-11-29 1986-11-11 The Boeing Company Resin film infusion process and apparatus
WO1997025198A1 (en) * 1996-01-11 1997-07-17 The Boeing Company Composite honeycomb sandwich structure
WO1999061233A2 (en) * 1998-05-22 1999-12-02 Cytec Technology Corp. Products and method of core crush prevention
WO2009083494A1 (fr) * 2007-12-21 2009-07-09 Sonaca S.A. Procede de fabrication d'un panneau comprenant au moins un corps en nid-d'abeilles et une premiere peau realisee en materiau composite
CN102686382A (zh) * 2009-12-15 2012-09-19 波音公司 复合层板稳定机构和方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4622091A (en) * 1984-11-29 1986-11-11 The Boeing Company Resin film infusion process and apparatus
WO1997025198A1 (en) * 1996-01-11 1997-07-17 The Boeing Company Composite honeycomb sandwich structure
WO1999061233A2 (en) * 1998-05-22 1999-12-02 Cytec Technology Corp. Products and method of core crush prevention
WO2009083494A1 (fr) * 2007-12-21 2009-07-09 Sonaca S.A. Procede de fabrication d'un panneau comprenant au moins un corps en nid-d'abeilles et une premiere peau realisee en materiau composite
CN102686382A (zh) * 2009-12-15 2012-09-19 波音公司 复合层板稳定机构和方法

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