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On the Feasibility of Using Thermal Gradients for Active Control of Interlaminar Stresses in Laminated Composites

Boeing Commercial Airplane Group, PO. Box 3707 MS 67-HM, Seattle, WA 98124-2207

D. Steadman

FAA Center of Excellence for Computational Modeling of Aircraft Structures, Georgia Institute of Technology, Atlanta, GA 30332-0356

S. V. Hanagud

FAA Center of Excellence for Computational Modeling of Aircraft Structures, Georgia Institute of Technology, Atlanta, GA 30332-0356

S. N. Atluri

FAA Center of Excellence for Computational Modeling of Aircraft Structures, Georgia Institute of Technology, Atlanta, GA 30332-0356

In this paper, a method is proposed to actively control interlaminar stresses near the free edges of laminated composites by through-thickness thermal gradients. Theoretical solutions are given for optimal steady-state through-thickness temperature distributions under uniaxial loading that are required to elmininate 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 feasiblity of the thermal control of interlaminar stresses is demonstrated.

Journal of Composite Materials, Vol. 31, No. 16, 1556-1573 (1997)
DOI: 10.1177/002199839703101601


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