Abstract: A Finite Element (FE) based scheme is presented
for quantifying guided wave interaction with Localised Nonlinear
Structural Damage (LNSD) within structures of arbitrary layering
and geometric complexity. The through-thickness mode-shape of the
structure is obtained through a wave and finite element method. This
is applied in a time domain FE simulation in order to generate
time harmonic excitation for a specific wave mode. Interaction of
the wave with LNSD within the system is computed through an
element activation and deactivation iteration. The scheme is validated
against experimental measurements and a WFE-FE methodology for
calculating wave interaction with damage. Case studies for guided
wave interaction with crack and delamination are presented to verify
the robustness of the proposed method in classifying and identifying
damage.
Abstract: Delamination is one of the major failure modes in laminated composite structures. Delamination tips are mostly captured by spatial numerical models in order to predict crack growth. This paper presents some mechanical models of delaminated composite shells based on shallow shell theories. The mechanical fields are based on a third-order displacement field in terms of the through-thickness coordinate of the laminated shell. The undelaminated and delaminated parts are captured by separate models and the continuity and boundary conditions are also formulated in a general way providing a large size boundary value problem. The system of differential equations is solved by the state space method for an elliptic delaminated shell having simply supported edges. The comparison of the proposed and a numerical model indicates that the primary indicator of the model is the deflection, the secondary is the widthwise distribution of the energy release rate. The model is promising and suitable to determine accurately the J-integral distribution along the delamination front. Based on the proposed model it is also possible to develop finite elements which are able to replace the computationally expensive spatial models of delaminated structures.
Abstract: An automated fibre placement method has been
developed to build through-thickness reinforcement into carbon fibre
reinforced plastic laminates during their production, with the goal
of increasing delamination fracture toughness while circumventing
the additional costs and defects imposed by post-layup stitching
and z-pinning. Termed ‘inter-weaving’, the method uses custom
placement sequences of thermoset prepreg tows to distribute regular
fibre link regions in traditionally clean ply interfaces. Inter-weaving’s impact on mode I delamination fracture toughness
was evaluated experimentally through double cantilever beam tests
(ASTM standard D5528-13) on [±15°]9 laminates made from Park
Electrochemical Corp. E-752-LT 1/4” carbon fibre prepreg tape.
Unwoven and inter-woven automated fibre placement samples were
compared to those of traditional laminates produced from standard
uni-directional plies of the same material system. Unwoven automated fibre placement laminates were found to
suffer a mostly constant 3.5% decrease in mode I delamination
fracture toughness compared to flat uni-directional plies. Inter-weaving caused significant local fracture toughness increases
(up to 50%), though these were offset by a matching overall
reduction. These positive and negative behaviours of inter-woven
laminates were respectively found to be caused by fibre breakage
and matrix deformation at inter-weave sites, and the 3D layering
of inter-woven ply interfaces providing numerous paths of least
resistance for crack propagation.
Abstract: Composite materials are widely used in aviation industry due to their superior properties; however, they are susceptible to delamination. Through-thickness stitching is one of the techniques to alleviate delamination. Kevlar is one of the most common stitching materials; in contrast, it is expensive and presents stitching fabrication challenges. Therefore, this study compares the performance of Kevlar with an inexpensive and easy-to-use nylon fiber in stitching to alleviate delamination. Three laminates of unidirectional carbon fiber-epoxy composites were manufactured using vacuum assisted resin transfer molding process. One panel was stitched with Kevlar, one with nylon, and one unstitched. Mode I interlaminar fracture tests were carried out on specimens from the three composite laminates, and the results were compared. Fractographic analysis using optical and scanning electron microscope were conducted to reveal the differences between stitching with Kevlar and nylon on the internal microstructure of the composite with respect to the interlaminar fracture toughness values.
Abstract: Extensive experimental investigation on the effect of stitching pattern on tubular composite structures was conducted. The effect of stitching reinforcement through thickness on using glass flux yarn on energy absorption of fiber-reinforced polymer (FRP) was investigated under high speed loading conditions at axial loading. Keeping the mass of the structure at 125 grams and applying different pattern of stitching at various locations in theory enables better energy absorption, and also enables the control over the behaviour of force-crush distance curve. The study consists of simple non-stitch absorber comparison with single and multi-location stitching behaviour and its effect on energy absorption capabilities. The locations of reinforcements are 10 mm, 20 mm, 30 mm, 10-20 mm, 10-30 mm, 20-30 mm, 10-20-30 mm and 10-15-20-25-30-35 mm from the top of the specimen. The effect of through the thickness reinforcements has shown increase in energy absorption capabilities and crushing load. The significance of this is that as the stitching locations are closer, the crushing load increases and consequently energy absorption capabilities are also increased. The implementation of this idea would improve the mean force by applying stitching and controlling the behaviour of force-crush distance curve.
Abstract: In this paper, 3D image based composite unit cell is constructed from high resolution tomographic images. Through-thickness thermal diffusivity and in-plane Young’s modulus are predicted for the composite unit cell. The accuracy of the image based composite unit cell is tested by comparing its results with the experimental results obtained from laser flash and tensile test. The FE predictions are in close agreement with experimental results. Through-thickness thermal diffusivity and in-plane Young’s modulus of a virgin C/C composite are predicted by replacing the properties of air (porosity) with the properties of carbon matrix. The effect of porosity was found to be more profound on thermal diffusivity than young’s modulus.