Abstract
Composites have gained wide use in structural applications; however, they are sensitive to impact damage. The use of hybrid composites is an effective way to overcome this deficiency. The effects of various hybrid structures of interlayer and intralayer warp-knitted fabrics with carbon and glass fibers on the low-velocity impact behavior of composite laminates were studied. Drop-weight impact tests were conducted on two types of interlayer, sandwich and intralayer hybrid composite laminates, which were compared with homogenous composite laminates. During low-velocity impact tests, the time histories of impact forces and absorbed energy by laminate were recorded. The failure modes were analyzed using the micro-CT (computed tomography) and C-scan techniques. The results revealed that the hybrid structure played an important role in peak force and the absorbed energy, and that the hybrid interface had an influence on damage modes, whereas the intralayer hybrid composite laminate damage was affected by the impact location. The intralayer hybrid laminate with C:G = 1:1 exhibited better impact resistance compared to the other hybrid structures.
Highlights
Composites are widely used in the fields of aviation and spaceflight because of their excellent specific strength and modulus. They are very sensitive to low-velocity impact damage, causing a potential threat as barely visible impact damage (BVID) [1,2,3], which is defined as impacts that show minimal surface damage but which can cause the internal structure to suffer a complex failure [4]
Various studies on the low-velocity impact behavior of hybrid composites have been conducted, concerning the sample size, material, and impactor type, most of which having focused on the effect of the stacking sequence [14], especially for the interlayer hybrid structure [15]
The results showed that the impact performance of the laminate with glass fiber in the outer layer was greatly affected by the layer angle, whereas the carbon fiber at the outer layer could decrease the deformation of the laminate by increasing the misalignment angle
Summary
Composites are widely used in the fields of aviation and spaceflight because of their excellent specific strength and modulus. Hybrids including carbon fibers are fabricated most frequently with glass fibers, which are typically reported to improve most mechanical properties [12,13]. This is especially true for the generation of commercial aircraft, wind-power blades, and some lightweight car parts. Various studies on the low-velocity impact behavior of hybrid composites have been conducted, concerning the sample size, material, and impactor type, most of which having focused on the effect of the stacking sequence [14], especially for the interlayer hybrid structure [15]. The low-velocity impact properties of carbon/glass fiber interlayer, sandwich and intralayer hybrid composite laminates were investigated. The impact damage mechanisms of different hybrid structures were revealed by visual inspection, C-scan, and micro-CT techniques
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