A Constitutive Model for Distributed Microcracking In Titanium Matrix Composite Laminae

[+] Author and Article Information
D. L. Ball

Lockheed Martin, Tactical Aircraft Systems, Fort Worth, TX 76112

W. S. Chan

Department of Mechanical and Aerospace Engineering, University of Texas at Arlington, Arlington, TX 76019-0023e-mail: chan@mae.uta.edu

J. Eng. Mater. Technol 122(4), 469-473 (May 12, 2000) (5 pages) doi:10.1115/1.1289286 History: Received December 09, 1999; Revised May 12, 2000
Copyright © 2000 by ASME
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Grahic Jump Location
Schematic of lamina microcracks
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Variation of lamina longitudinal modulus as a function of one-direction crack number density and size.
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Variation of lamina transverse modulus as a function of two-direction crack number density and size
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[0°]4 Laminate stress-strain response during R=0.1 Nx loading at 900°F
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Measured and predicted variation of [0°]4 laminate longitudinal modulus (secant), EL, during isothermal low cycle




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