A quasi-isotropic fiber-reinforced composite combining high-modulus IM7 carbon fibers in the 0° load-bearing plies with Kevlar 49 aramid fibers in the ±45° shear plies, all bound in a toughened epoxy matrix and consolidated via autoclave prepreg processing. This hybrid architecture balances the stiffness and strength advantages of carbon fiber with the impact resistance and damage tolerance of Kevlar, while the toughened epoxy system resists matrix cracking under thermal and mechanical cycling. Widely used in aerospace primary structures (fuselage panels, wing skins), high-performance sporting equipment (bicycle frames, helmets), and defense applications where impact damage tolerance and environmental durability are as critical as structural efficiency; the hybrid approach is favored over carbon-only laminates when crash-resistance, vibration damping, or multi-impact scenarios are design drivers.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/45/-45/0]T
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Elongation at Break(εf) | 1.500 | - | — | ||
Ultimate Tensile Strength(σUTS) | 130.5 | ksi | — | ||
Young's Modulus(E) | 10,152.6 | ksi | — |
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Density(ρ) | 0.05238 | lb/in³ | — |