Direction-dependent mechanical properties of a triaxially braided quasi-isotropic carbon/epoxy composite

Keyphrases

• Aircraft Fuselage 50%
• Biaxial 50%
• Carbon-epoxy Composite 100%
• Carbon-epoxy Laminate 50%
• Classical Laminated Plate Theory 100%
• Composite Laminates 50%
• Directional Dependence 100%
• Discounting Models 50%
• Engine Applications 50%
• Epoxy Resin 50%
• Failure Strain 50%
• Fiber Architecture 100%
• Fiber Direction 50%
• Fiber Volume Fraction 50%
• Full-scale Test 50%
• Hand Lay-up 50%
• In-plane Orientation 50%
• Isotropic Pyrocarbon 100%
• Loading Direction 50%
• Manufacturing Process 50%
• Material System 50%
• Matrix Cracking 50%
• Mechanical Properties 100%
• Open Rotor 50%
• Poisson's Ratio 50%
• Predictive Models 50%
• Quasi-isotropic 100%
• Specimen Orientation 50%
• Tensile Modulus 50%
• Tensile Strength 50%
• Ultimate Strength 50%
• Undulation 50%
• Woven Fiber 50%

Engineering

• Carbon-Epoxy Laminate 50%
• Dependent Mechanical Property 100%
• Epoxy Composite 100%
• Failure Strain 50%
• Fiber Direction 50%
• Full-Scale Testing 50%
• Fuselage 50%
• Loading Direction 50%
• Manufacturing Process 50%
• Material System 50%
• Matrix Cracking 50%
• Plate Theory 100%
• Poisson Ratio 50%
• Rotors 50%
• Test Result 100%
• Ultimate Strength 50%
• Ultimate Tensile Strength 50%
• Young's Modulus 50%

Material Science

• Aircraft 50%
• Composite Laminate 50%
• Composite Material 100%
• Elastic Moduli 100%
• Epoxy 50%
• Laminated Plate 100%
• Matrix Cracking 50%
• Poisson Ratio 50%
• Ultimate Tensile Strength 50%
• Volume Fraction 50%