Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load

LU Binghe

doi:10.16080/j.issn1671-833x.2017.14.106

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Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load

更新时间：2026-04-17

- Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load
- Aeronautical Manufacturing Technology Vol. 60, Issue 14, Pages: 106-108(2017)
- 作者机构：
  
  上海飞机设计研究院,上海,201210
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2017.14.106
  CLC：
- Published：2017
- 稿件说明：
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卢秉贺. Ω 型加筋壁板连接结构在拉伸载荷下的破坏研究[J]. 航空制造技术, 2017, 60(14): 106-108.

LU Binghe. Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load. Aeronautical Manufacturing Technology, 2017, 60(14): 106-108.
卢秉贺. Ω 型加筋壁板连接结构在拉伸载荷下的破坏研究[J]. 航空制造技术, 2017, 60(14): 106-108. DOI： 10.16080/j.issn1671-833x.2017.14.106.

LU Binghe. Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load. Aeronautical Manufacturing Technology, 2017, 60(14): 106-108. DOI： 10.16080/j.issn1671-833x.2017.14.106.

摘要

考察机身收缩段的复合材料Ω 型加筋壁板前段和后段连接结构在拉伸载荷下的承载能力，开展了拉伸破坏试验研究。试验件为壁板与框呈75° 夹角的倾斜结构，试验考核了加筋壁板、连接框、连接角盒和紧固件的应变水平、试验件的载荷- 位移曲线和破坏载荷。试验结果表明，Ω 型加筋壁板前后段连接结构在拉伸载荷下，角盒和框的连接处的紧固件以及框的转角处最先发生破坏。试验结果可作为飞行机身复合材料结构连接的设计和评定依据。

Abstract

In order to gain the load capability of connection structure of composite Ω type stiffened panels in after fuselage

failure experiments for connection structure of Ω stiffened panels subjected to tension load were conducted. The specimen was a sloping structure with the angle of 75° between stiffened panel and the frame. The experiment tested strain of stiffened panel

frame

fitting and fasteners and gained the load-displacement curve and cracking load. The experiment results show that the corner of the frame and the fasteners which connect the fittings and the frames are the prior damage points in tension load. The experiment result is meaningful to connection design for composites structure on fuselage.

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