SYMPOSIA PAPER Published: 01 January 1969
STP49808S

A Simplified Method of Determining the Inplane Shear Stress-Strain Response of Unidirectional Composites

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.

Author Information

Petit, P., H.
Lockheed-Georgia Co., Marietta, Ga.
Price: $25.00
Contact Sales
Related
Reprints and Permissions
Reprints and copyright permissions can be requested through the
Copyright Clearance Center
Details
Developed by Committee: D30
Pages: 83–93
DOI: 10.1520/STP49808S
ISBN-EB: 978-0-8031-8904-1
ISBN-13: 978-0-8031-0017-6