On the feasibility of using thermal gradients for active control of interlaminar stresses in laminated composites |
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Authors: | T. Kim D. Steadman S. V. Hanagud Satya N. Atluri |
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Affiliation: | FAA Center of Excellence for Computational Modeling of Aircraft Structures, Georgia Institute of Technology, Atlanta, GA 30332-0356, USA |
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Abstract: | In this paper, a method is proposed to actively control interlaminar stresses near the free edges of laminated composites by though-thickness thermal gradients. Theoretical solutions are given for optimal steady-state through-thickness temperature distributions under uniaxial loading that are required to eliminate or reduce the interlaminar stresses below a prescribed level. The optimal solutions are obtained by minimizing appropriate performance indices that are functions of the far-field properties, with respect to the through-thickness temperature differences. In the second part, an experimental investigation is conducted on a glass/epoxy cross-ply laminate with embedded piezoelectric sensors and a thermal heater. Through the experiment, the feasibility of the thermal control of interlaminar stresses is demonstrated. |
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