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A simple and relatively inexpensive technique is presented for determining the inplane shear stress-strain response of unidirectional composites. The method utilizes the stress-strain results from an uniaxial test on a ±45-deg laminate which is symmetrically laminated about the midplane. Through the use of relations derived from laminated plate theory, expressions are presented which allow the inplane laminae shear stress-strain curve to be incrementally reproduced from the ±45-deg laminate stress-strain curve. The simple coupon and uniaxial sandwich beam specimens, which may be utilized to obtain the data, are described. Comparisons are presented between boron/epoxy and graphite/epoxy shear stress strain curves obtained by this technique and the curves from cross-sandwich beam tests.
composite materials, boron, fiber composites, graphite, mechanical properties, shear tests, shear strength, evaluation, tests
Petit, P. H.
Senior aircraft structures engineer, Lockheed-Georgia Co., Marietta, Ga.