NTRS - NASA Technical Reports Server

Back to Results
Prediction of thermal and mechanical stress-strain responses of TMC's subjected to complex TMF historiesThis paper presents an experimental and analytical evaluation of cross-plied laminates of Ti-15V-3Cr-3Al-3Sn (Ti-15-3) matrix reinforced with continuous silicon-carbide fibers (SCS-6) subjected to a complex TMF loading profile. Thermomechanical fatigue 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 thermoviscoplastic constitutive relation. The fiber transverse modulus was reduced in the analysis to simulate the fiber-matrix interface failures. Excellent correlation was found between measured and predicted laminate stress-strain response due to generic hypersonic flight profile when fiber debonding was modeled.
Document ID
Document Type
Conference Paper
Johnson, W. S. (NASA Langley Research Center Hampton, VA, United States)
Mirdamadi, M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1994
Publication Information
Publication: AGARD, Characterisation of Fibre Reinforced Titanium Matrix Composites
Subject Category
Distribution Limits
Document Inquiry