Abstract
Abstract Hybrid fiber composites are widely used to improve the anti-penetration performance. Carbon/Kevlar hybrid composites are used in aircrafts and safety devices, thanks to the strong toughness of Kevlar fibers and high strength of carbon fibers. In the present work, the contact force of hybrid composites under oblique impact is derived. The viscoelastic constitutive model of Kevlar layer is investigated and the dissipation energies of composites for different high velocity oblique impacts are simulated. The results show that hybrid composites have good bullet-proof performance, the contact forces are fluctuant in short time and the frictional dissipation energy allows us to prevent penetration.
Highlights
Composite materials are widely used in the aircraft structures, which should be of certain impedance capability for a variety of complex loads
Woo and Kim [10] showed that the high strain rate induced failure characteristics in a carbon/Kevlar hybrid composite subjected to high strain rate compressive loading using a novel SHPB-AE coupled test
Carbon/Kevlar hybrid composite is the optimal material with impact resistance potential, and the research on high velocity oblique impact over 200 m/s is scarce
Summary
Composite materials are widely used in the aircraft structures, which should be of certain impedance capability for a variety of complex loads. The analytical model has been worked to analyze the impact on hybrid composite material targets [12]. Carbon/Kevlar hybrid composite is the optimal material with impact resistance potential, and the research on high velocity oblique impact over 200 m/s is scarce. The contact force of hybrid composites under oblique impact is derived based on the cavity expansion theory, and the strain rate-dependent property of Kevlar, the stress distribution, damage dissipation, and frictional dissipation energies are simulated, in order to reveal the mechanism of oblique penetration and provide suggestions for the design of protective equipment. The radial stress on the surface of the projectile nose can be calculated with the velocity and angle as follows [17]:
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