Graduate Thesis Or Dissertation
 

An experimental approach to analyze large notched composite panels loaded in out-of-plane shear

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  • Identifying material characteristics of composites is important in designing any structural system. The aerospace industry relies on these material properties not only to design a functional aircraft, but also a safe and reliable one. Since carbon fiber composites are relatively new materials, little is known about its characteristics under certain loading conditions. The majority of previous research has been dedicated to inplane tension, bending, and shear loading. However, little to no research has been devoted to out-of-plane shear loading (Mode III) of notched panels. This document presents a novel approach to test and analyze panels loaded in Mode III. Literature provided some excellent inspiration for designing a feasible testing method. The proposed method consists of a testing fixture, as well as a testing procedure. One component of the testing fixture includes a hinged grip mechanism to apply load to the panel. The grips are clamped on each side of the notch and then loaded in opposite directions. The hinge gives the system a rotational degree of freedom and helps eliminate any unwanted damage near the grips. This creates high stress concentrations at the notch tip. To validate this testing method, six different ply layups were analyzed. Each ply layup was tested using six repeated specimens to show consistency between similar panels. The optical method, digital image correlation (DIC), provided a full-field strain measurement of the region of interest every two seconds throughout the test. Specific strain concentrations, secondary strain buildup, and early fracture patterns were extracted from the digital image correlation results. Along with strain patterns, applied load and grip displacement was recorded using the Bluehill® software. Information about the stiffness of the panel, maximum applied load, and work to maximum load was correlated with the number of 0-degree plies of each panel.
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