Impact tests on fibrous composite sandwich structures
Marvin D. Rhodes, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Technology & Engineering - 40 pages
6 pages matching visible-damage threshold in this book
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1.5 Kinetic 181-style balanced 181-style graphite fabric 181-style Kevlar fabric 2.0 Kinetic energy Air Gun aluminum honeycomb core beams composite laminates Composite Sandwich Structures compression strength compression when impact compression-loaded laminates damage tolerance damaged by impact data indicate data shown delamination due to impact E. I. duPont effect of impact effect of low-velocity energy levels energy of projectile fabric and graphite fail catastrophically failure X Residual failure-threshold curves fiber Figure 11 graphite tape hybrid laminate hybrid of 181-style impact at energy impact damage impact failure threshold impact occurred impact projectile initiate catastrophic failures Kevlar and graphite Lamina orientation laminates on 48-kg/m Laminates The effect Langley Research Center loaded in compression loaded in tension low-velocity impact Nomex honeycomb core p/p ult Residual strength 2.5 runway debris encountered shown in figure Specific modulus Specific strength static load sustained local damage tensile strength tension or compression tension-loaded laminates test laminates visible damage visible-damage threshold