Evaluation of Mode II Interlaminar Fracture Toughness of Composite Laminates under Impact Loading
Prochnost' i ustoichivost' elementov i soedinenii aviatsionnykh konstruktsii iz kompozitov The strength and stability of elements and compounds of aircraft structures made of composites , Moscow, Izdatel'stvo fiziko-matematicheskoi literatury, , p. Kurennov S.
Malysheva G. Popov B. Raschet mnogosloinykh konstruktsii variatsionno-matrichnymi metodami Calculation of multilayer structures variational-matrix methods: A manual for schools of mechanical engineering and instrument specialties , Moscow, Izd-vo MGTU im.
ISBN 10: 044487285x
Baumana, , p. Vasil'ev V. This book presents the topics of major importance toward understanding the most feared failure mode in composite laminates, namely delamination. There are few books at present that describe the phenomenon of composite laminate failure by delamination in such detail. Written by pioneers and principal researchers in various aspects of composite delamination, starting from basic principles to the most current research findings, the work provides a complete study of the theoretical and experimental aspects of composite delamination in one volume.
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For virtually all carbon fiber-reinforced polymer matrix composites, the compression strength is significantly lower than the tensile strength and, therefore, is the limiting design value. Interestingly, those who identify compression testing as most important sometimes will also identify the most important test environment in which to perform the test.
For polymer matrix composites, the most severe environmental condition is often the highest service temperature, coupled with a moisture saturation condition.
In my July column, I discussed the variety of test methods available for determining the compression strength of composites. The primary way in which they differ is the method of load introduction into the specimen. The three most commonly performed tests Fig.
The final category of test methods that have received a considerable number of most important votes are those used to develop structural design allowables.
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For this purpose, the open-hole compression test, ASTM D 6 , and the compression-after-impact test, ASTM D 7 , have been named most important, particularly for aerospace applications. The open-hole compression test Fig. To prevent buckling during compression loading, a support fixture is bolted to the mm-long specimen.
The ASTM D compression-after-impact test uses a mm-wide by mm-long specimen that is loaded in edgewise compression while it is supported to prevent out-of-plane bending along the vertical edges Fig.
Note that when structural design allowables are generated using either test method, the composite laminate used in the test specimen is representative of the laminate that will be used in the intended application. For compression-after-impact testing, the impactor shape and impact energy used to produce the damage are also selected to represent impact threats for the application of interest. In addition to producing critical structural design allowables for a variety of applications, these two test methods share other important features.
First, both are performed under compression loading because the resulting strengths typically are lower than those under tension loading.
Second, both tests produce design allowables that typically are more critical than those resulting from the strength-based material properties discussed in the previous category. As a result, both the open-hole-compression and compression-after-impact tests also are commonly used in the material selection process for an intended application.
Because a consistent laminate must be used when testing to compare candidate materials, the use of a quasi-isotropic laminate is suggested.
Related Interlaminar Response of Composite Materials
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