TY - GEN
T1 - Modeling the Effective Elastic Behavior of a Transversely Cracked Laminated Composite
AU - Thomas, David J.
AU - Wetherhold, Robert C.
N1 - Publisher Copyright:
Copyrig © 1998 by ASME.
PY - 1996
Y1 - 1996
N2 - The solution for the stress state present in the vicinity of transverse matrix cracks within a composite laminate is typically obtained by assuming a regular crack spacing geometry for the problem and applying a shear-lag analysis. In order to explore the validity of this underlying assumption, the probability density function for the location of the next transverse matrix crack within a crack bounded region is examined. The regular crack spacing assumption is shown to be reasonable from an engineering point of view. Continuing with this assumption, a generalized shear-lag model for multi-layer, off-axis laminates subjected to full in-plane loads is developed. This model is used to quantitatively evaluate the effective elastic properties of the damaged material. The results are applicable to materials such as ceramic matrix or polymer matrix unidirectional fiber systems where damage in the form of transverse matrix cracks arises.
AB - The solution for the stress state present in the vicinity of transverse matrix cracks within a composite laminate is typically obtained by assuming a regular crack spacing geometry for the problem and applying a shear-lag analysis. In order to explore the validity of this underlying assumption, the probability density function for the location of the next transverse matrix crack within a crack bounded region is examined. The regular crack spacing assumption is shown to be reasonable from an engineering point of view. Continuing with this assumption, a generalized shear-lag model for multi-layer, off-axis laminates subjected to full in-plane loads is developed. This model is used to quantitatively evaluate the effective elastic properties of the damaged material. The results are applicable to materials such as ceramic matrix or polymer matrix unidirectional fiber systems where damage in the form of transverse matrix cracks arises.
UR - https://www.scopus.com/pages/publications/85150238013
U2 - 10.1115/96-GT-495
DO - 10.1115/96-GT-495
M3 - Conference contribution
AN - SCOPUS:85150238013
T3 - ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1996
BT - Aircraft Engine; Marine; Microturbines and Small Turbomachinery
PB - American Society of Mechanical Engineers
T2 - ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1996
Y2 - 10 June 1996 through 13 June 1996
ER -