Composites made of Ti containing matrix reinforced with silicon carbid fibers are being considered as structural materials for elevated temperature applications in hyersonic vehicles. Thermomechanical response of a cross-ply SCS-6/Timetal-21S composite subjected to a generic hypersonic flight profile with the temperature ranging from -130 to 816 deg C was evaluated experimentally and analytically. A two-dimensional micromechanical analysis, Viscoply, was used to predict the stress-strain response of the laminate and of the constituents in each ply during thermomechanical loading conditions. In the analysis, the fiber was modeled as elastic with transverse orthotropic and temperature dependent properties and the matrix was modeled using a thermoviscoplastic constitutive relation. The fiber tansverse modulus was reduced in the analysis to simulate fiber-matrix interface failure. Good agreement was found between measured and predicted laminate stress-strain response when fiber-matrix debonding was modeled.
Prediction of stress-strain response of SCS-6/Timetal-21S subjected to a hypersonic flight profile
Voraussage des Spannungs-Dehnungs-Verhaltens von SCS-6/Timetal-21S unter Einfluß eines Überschall-Flugprofils
Composites, Part A: Applied Science and Manufacturing ; 27A , 11 ; 1033-1040
1996
8 Seiten, 15 Bilder, 2 Tabellen, 13 Quellen
Article (Journal)
English
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