Fatigue damage evolution in woven fabric composites Conference Paper

abstract

• Fatigue testing of 5-harness satin woven laminates indicates damage in the form of matrix cracking in transverse bundles and internal delamination at the tip of these cracks. These damage entities reduce the overall elastic properties of the laminate. The woven laminate is modeled by approximating it to an equivalent cross-ply laminate. The evolution of cracks during constant amplitude fatigue loading is explained by modeling both the cracks and internal delamination and assuming frictional stresses at the delaminated interface. 2000 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

name of conference

• 41st Structures, Structural Dynamics, and Materials Conference and Exhibit

authors

• Talreja, Ramesh

published proceedings

• COLLECTION OF THE 41ST AIAA/ASME/ASCE/AHS/ASC STRUCTURES, STRUCTURAL DYNAMICS, AND MATERIALS CONFERENCE AND EXHIBIT, VOL 1 PTS 1-3

author list (cited authors)

• Kumar, R., & Talreja, R.

citation count

• 21

complete list of authors

• Kumar, R||Talreja, R

publication date

• January 2000

publisher

• American Institute of Aeronautics and Astronautics (AIAA)  Publisher

Digital Object Identifier (DOI)

• 10.2514/6.2000-1685

International Standard Book Number (ISBN) 10

• 1-56347-449-2

start page

• 1841

end page

• 1849

URL

• http://dx.doi.org/10.2514/6.2000-1685