Evaluation of Notched Strength of Composite Laminates for Structural Design

被引：15

作者：

Shah, Pranav D. ^{[1
]}

Melo, Jose Daniel D. ^{[1
]}

Cimini, C. A., Jr. ^{[2
]}

Ridha, Muhammad ^{[3
]}

机构：

[1] Stanford Univ, Dept Aeronaut & Astronaut, Stanford, CA 94305 USA

[2] Univ Estadual Campinas, UNICAMP, Dept Mech Design, BR-13083970 Campinas, SP, Brazil

[3] Natl Univ Singapore, Dept Mech Engn, Singapore 117576, Singapore

来源：

JOURNAL OF COMPOSITE MATERIALS | 2010年 / 44卷 / 20期

关键词：

design allowable; failure criterion; failure envelope; open hole; PROGRESSIVE FAILURE ANALYSIS; HOLE TENSILE-STRENGTH; DAMAGE-MECHANICS;

D O I：

10.1177/0021998310372713

中图分类号：

TB33 [复合材料];

学科分类号：

摘要：

The use of notched specimens to generate design allowable is common practice among aircraft designers. This article assesses the limitations of open-hole tests and emphasizes the importance of numerical simulations to produce notched strength data for structural design allowable. Using numerical simulations, failure envelopes of open-hole specimens were obtained for two different quasi-isotropic carbon fiber-epoxy laminates, namely, [pi/4]: [45/90/-45/0](4s) and [pi/3]: [0/+/- 60](5s). It was demonstrated that open-hole tests produce data that is very limited to the specific loading conditions and, therefore, shall not be directly applied to structural design.

引用

页码：2381 / 2392

页数：12

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