A temperature/strain-rate-dependent finite deformation constitutive and failure model for solid propellants

Engineering

• Constitutive Model 100%
• Strain Rate 100%
• Failure Model 100%
• Finite Deformation 100%
• Low-Temperature 50%
• Failure Strain 50%
• Stress-Strain Relations 33%
• Experimental Result 16%
• Rocket Engine 16%
• Model Prediction 16%
• Rate Dependence 16%
• Failure Envelope 16%
• Based Failure Criterion 16%
• Strain Energy Density 16%
• Induced Volume 16%

Material Science

• Strain Rate 100%
• Solid Propellant 100%
• Glass Transition Temperature 50%
• Stress-Strain Relations 33%
• Energy Density 16%