Journal Published Online: 01 December 1993
Volume 15, Issue 4

Stress-Strain Analysis of a [0/90] Titanium Matrix Laminate Subjected to a Generic Hypersonic Flight Profile



Cross-ply laminate behavior of Ti-15V-3Cr-3Al-3Sn (Ti-15-3) matrix reinforced with continuous silicon-carbide fibers (SCS-6) subjected to a generic hypersonic flight profile was evaluated experimentally and analytically. Thermomechanical fatigue (TMF) test techniques were developed to conduct a simulation of a generic hypersonic flight profile. A micromechanical analysis was used. The analysis predicts the stress-strain response of the laminate and of the constituents in each ply during thermal and mechanical cycling by using only constituent properties as input. The fiber was modeled as elastic with transverse orthotropic and temperature-dependent properties. The matrix was modeled using a thermo-viscoplastic constitutive relation. The fiber transverse modulus was reduced in the analysis to simulate the fiber-matrix interface failure. Excellent correlation was found between measured and predicted laminate stress-strain response due to generic hypersonic flight profile when fiber debonding was modeled.

Author Information

Johnson, WS
NASA Langley Research Center, Hampton, VA
Mirdamadi, M
NASA Langley Research Center, Hampton, VA
Bahei-El-Din, YA
Cairo University, Gaiza, Egypt
Pages: 7
Price: $25.00
Reprints and Permissions
Reprints and copyright permissions can be requested through the
Copyright Clearance Center
Stock #: CTR10382J
ISSN: 0884-6804
DOI: 10.1520/CTR10382J