Accession Number : AD0779927

Title :   Ultimate Strength Analysis of Symmetric Laminates.

Descriptive Note : Technical rept.,

Corporate Author : AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Sandhu,R. S.

Report Date : FEB 1974

Pagination or Media Count : 87

Abstract : A technique is presented for predicting the response to failure of composite laminates. In this technique, cubic spline interpolation functions are used to represent basic stress-strain curves obtained from simple tests. This representation in conjunction with an incremental constitutive law is used to generate response of laminates subjected to incremental loads. The ultimate load- carrying capacity of the laminates is determined by the plywise application of a new failure criterion using strain energy under longitudinal, transverse, and shear loadings as independent parameters. Results obtained by this technique are compared with the available experimental data of boron- epoxy laminates as well as the responses generated by methods of Petit-Waddoups and Hahn. Analytical results determined by the present theory correlate with the experimental data better than those obtained by the other two techniques. (Author-PL)

Descriptors :   *Composite materials, *Laminates, Strength(Mechanics), Failure(Mechanics), Failure, Mathematical analysis, Epoxy compounds, Boron, Fiber reinforced composites

Subject Categories : Laminates and Composite Materials

Distribution Statement : APPROVED FOR PUBLIC RELEASE