Experimental and numerical analysis of composite fuselage panel impacted by tire burst debris under airworthiness clause

Engineering

• Composite Material 100%
• Damage Mode 50%
• Debonding 50%
• Design Optimization 50%
• Dynamic Response 50%
• Failure Criterion 100%
• Failure Model 50%
• Fracture Surface 50%
• Impact Test 50%
• Matrix Damage 50%
• Progressive Failure 50%
• Rate Dependence 50%
• Rates of Strain 50%
• Reference Data 50%
• Strain Rate 50%
• Tensiles 50%