Variable-stiffness composite panels: Defect tolerance under in-plane tensile loading

被引：43
作者：
Falco, O. [1 ]
Mayugo, J. A. [1 ]
Lopes, C. S. [2 ]
Gascons, N. [1 ]
Costa, J. [1 ]
机构：
[1] Univ Girona, Polytech Sch, AMADE, Girona 17071, Spain
[2] IMDEA Mat Madrid Inst Adv Studies Mat, Getafe 28906, Spain
来源：
COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING | 2014年 / 63卷
关键词：
Carbon fibers; Defects; Variable-Stiffness Panels; NOTCHED COMPOSITES; OPTIMIZATION; DESIGN;
D O I：
10.1016/j.compositesa.2014.03.022
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
Automated Fiber Placement is being extensively used in the production of major composite components for the aircraft industry. This technology enables the production of tow-steered panels, which have been proven to greatly improve the structural efficiency of composites by means of in-plane stiffness variation and load redistribution. However, traditional straight-fiber architectures are still preferred. One of the reasons behind this is related to the uncertainties, as a result of process-induced defects, in the mechanical performance of the laminates. This experimental work investigates the effect of the fiber angle discontinuities between different tow courses in a ply on the un-notched and open-hole tensile strength of the laminate. The influence of several manufacturing parameters are studied in detail. The results reveal that 'ply staggering' and '0% gap coverage' is an effective combination in reducing the influence of defects in these laminates. (C) 2014 Elsevier Ltd. All rights reserved.
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收藏
页码：21 / 31
页数：11
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