Low Velocity Impact Response of Composite Panels for Aeronautical Applications

被引:0
作者
Grasso, M. [1 ]
Penta, F. [1 ]
Pucillo, G. P. [1 ]
Ricci, F. [1 ]
Rosiello, V. [1 ]
机构
[1] Univ Naples Federico II, Dept Ind Engn, I-80125 Naples, Italy
来源
WORLD CONGRESS ON ENGINEERING, WCE 2015, VOL II | 2015年
关键词
hybrid composite; low-velocity impact; delamination; non-destructive testing; polymer-matrix composites; ENERGY; DAMAGE; THICKNESS; PENETRATION; PLATES;
D O I
暂无
中图分类号
TP39 [计算机的应用];
学科分类号
081203 ; 0835 ;
摘要
The present experimental work analyses the impact behaviour of thermosetting composite materials for aeronautic applications. The main goal of the experimental activity was to identify the energy level in correspondence of which penetration occurs. The initial values of the impact energy were estimated according to analytical correlations found in literature. Tests were performed on three types of composite panels: carbon fibre laminated panels, fibreglass laminated panels and hybrid panels. The technology of lamina is that of prepeg fabric with twill sequence and fibres weaving at 0 degrees-90 degrees and +/- 45 degrees. The fixture used for tests is a Charpy impact test machine, which was conveniently equipped to evaluate the angular variation and the acceleration of the impacting mass. Preliminarily, non-destructive ultrasonic controls were performed to check that the specimens were not damaged before impacts tests. The interesting results of the tests were identification of the energy absorbed and the impact force for each specimen. Moreover, for each energy and force level, it was possible to associate a different fracture state. Conivkrisos among the results obtained for specimens made up of just one type of reinforcement (glass or carbon) and the result obtained with hybrid specimens were performed.
引用
收藏
页码:1138 / 1143
页数:6
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