Volume 15, Issue 4 (December 1993)

    Stress-Strain Analysis of a [0/90]2s Titanium Matrix Laminate Subjected to a Generic Hypersonic Flight Profile

    CODEN: CTROAD

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    Abstract

    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:

    Mirdamadi, M
    Senior scientist and National Research Council Research Associate, NASA Langley Research Center, Hampton, VA

    Johnson, WS
    Senior scientist and National Research Council Research Associate, NASA Langley Research Center, Hampton, VA

    Bahei-El-Din, YA
    Associate professor, Cairo University, Gaiza,


    Stock #: CTR10382J

    ISSN: 0884-6804

    DOI: 10.1520/CTR10382J

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    Author
    Title Stress-Strain Analysis of a [0/90]2s Titanium Matrix Laminate Subjected to a Generic Hypersonic Flight Profile
    Symposium , 0000-00-00
    Committee D30