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Stress-strain analysis of a (0/90)sub 2 symmetric titanium matrix laminate subjected to a generic hypersonic flight profile

Technical Report ·
OSTI ID:7305926
;

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 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 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.

Research Organization:
National Aeronautics and Space Administration, Hampton, VA (United States). Langley Research Center
OSTI ID:
7305926
Report Number(s):
N-92-26128; NASA-TM--107584; NAS--1.15:107584; CNN: RTOP 763-23-41-85
Country of Publication:
United States
Language:
English

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Related Subjects

36 MATERIALS SCIENCE
360603* -- Materials-- Properties
ALLOYS
ALUMINIUM ALLOYS
CARBIDES
CARBON COMPOUNDS
CHROMIUM ALLOYS
COMPOSITE MATERIALS
DEFORMATION
FABRICATION
FAILURES
FATIGUE
FIBERS
FLUID FLOW
HEAT TREATMENTS
HYPERSONIC FLOW
INTERFACES
LAYERS
MATERIALS
MATERIALS WORKING
MATHEMATICAL MODELS
MATRIX MATERIALS
MECHANICAL PROPERTIES
PLASTICITY
REINFORCED MATERIALS
SILICON CARBIDES
SILICON COMPOUNDS
STRESS ANALYSIS
TEMPERATURE DEPENDENCE
THERMAL CYCLING
THERMODYNAMICS
THERMOMECHANICAL TREATMENTS
TIN ALLOYS
TITANIUM ALLOYS
TITANIUM BASE ALLOYS
VANADIUM ALLOYS
VISCOSITY