![]() ![]() The fabric preform of the 3D composite was a 3D orthogonal weave with approximately the same areal density as the 2D laminate. The fabric preform of the 2D composite was a 2D plain-woven laminate with four layers of S-2 Glass roving. reported the damage accumulation in two-dimensional (2D) and three-dimensional (3D) woven glass-fiber-reinforced composite panels under repeated transverse drop-weight impact loading conditions. Results indicated stitching considerably enhanced the damage resistance of the laminates by restricting the size of damage and improving ballistic limits. also reported the response of stitched S2-Glass/SC-15 Epoxy composites under low-velocity impact and ballistic impact loading. Unstitched satin and plain weave laminates exhibited higher peak stress and modulus than stitched satin and plain weave laminates for both in-plane loading directions. The peak stress and modulus increased with increasing strain-rate for both unstitched plain and satin weave samples. In both stitched and unstitched plain and satin weave samples, higher peak stress, higher modulus and low strain at peak stress were observed during dynamic loading when compared to static loading condition. A 3-cord Kevlar thread was used for stitching dry fabric preforms in a lockstitch pattern with a stitch pitch of 6 mm. reported the critical results on stitched and unstitched woven carbon/epoxy laminates subjected to high strain-rate compression loading in a modified Split Hopkinson pressure bar. However, 3D reinforced composite materials are specially designed for bearing high stress in the third direction, impact, crash, energy absorption and multiaxial fatigue to overcome the disadvantages of standard laminated composite materials. Also, the undulations or crimps in the yarns may reduce mechanical properties such as tension or compression strengths. To improve interlaminar properties of 2D laminates, 3-dimensional textile preforms are being developed by using different manufacturing techniques like weaving, knitting, braiding, and stitching. Absence of third direction reinforcement is attributed to the lower delamination resistance and out-of-plane properties. However, usage of 2D composite laminates in aircraft and automobile applications has limitation due to low impact damage resistance and low through thickness mechanical properties when compared to conventional materials like aluminum alloys and steel. Reduction in energy absorption for Supercomposite TM laminates with the replacement of 50% woven carbon fabric in control panel.Ĭomposite materials with unidirectional fibers or woven fabrics exhibit better in-plane strength and stiffness properties compared to those of metals and ceramics. Low-velocity punch-shear tests demonstrated In stiffness) and damping increased by about the same 25% - 30%. In Z direction dynamic flexural modulus reduced 25% - 30% (loss Replacement of woven carbon fabric in control panel with milled carbon fibers Impulse-frequency response vibration experiments show that with a 50% The Supercomposite TM laminate-both having same arealĭensity. With a dense interlaminar reinforcement of milled carbon fibers in Z- direction used in designing Control panels had all layers of 3K plain woven carbon/epoxy prepregs, Low-velocity punch-shear tests were performed on control and Supercomposite TM laminates according to ASTM D3763 Standard using a drop-weight impact test Loss factor (intrinsic damping) of woven carbon/epoxy control and Supercomposite TM laminates. Impulse-frequency response vibration technique is usedįor non-destructive evaluation of the dynamic flexural modulus (stiffness) and Reported here, the dynamic properties and low-velocity impact response of wovenĬarbon/epoxy laminates incorporating a novel 3D interlaminar reinforcementĬoncept with dense layers of Z-axis oriented milled carbon fiber Supercomposite TM prepregs, are presented. ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |