An empirical prediction formula for compressive strength of composite laminates after impact

被引：0
|
作者：
Huang X. [1 ]
Wang J. [2 ]
Han T. [2 ]
Guan Z. [1 ]
Li Z. [1 ]
Sun W. [1 ]
机构：
[1] School of Aeronautic Science and Engineering, Beihang University, Beijing
[2] Shenyang Aircraft Design and Research Institute, Shenyang
来源：
Guan, Zhidong (07343@buaa.edu.cn) | 2018年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 35期
关键词：
Composite laminates; Compressive strength; Empirical formulas; Experimental study; Low velocity impact;
D O I：
10.13801/j.cnki.fhclxb.20170713.001
中图分类号：
学科分类号：
摘要：
Composites are widely used in the aircraft structure and its damage tolerance property is an important index of aircraft design. An empirical prediction formula for compressive strength of composite laminate after impact based on energy was formulated. With experimental studies, influence factors for compressive strength were analyzed to determine the forms and parameters of the empirical formula, and the predicted results were compared with experimental data as well. The predicted results of the empirical method accord well with sufficient experimental data by general verification. The results indicate that it is a convenient and efficient engineering prediction method for compressive strength after impact. In addition, the experimental results indicate that the relationships between compressive strength and impact energy are suitable for piecewise power function fitting. Impact energy, thickness of laminate, ply proportion and material tenacity have obvious effect on compressive strength of composite laminate after impact, while the diameter of impactor has no significant effect. © 2018, Editorial Office of Acta Materiae Compositae Sinica. All right reserved.
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页码：1158 / 1165
页数：7
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