In this work, the influence of composite laminates' orientation, on the peel and shear stresses in the adhesive layer of composite double lap joints subjected to in-plane impact loading, was investigated.
While past research has explored aspects of this problem separately – composite ply orientation, multiple load scenarios, and multiple performance objectives – there has been limited work addressing the interactions between these factors.
Numerical results for the amplitude-frequency response of generally orthotropic plates are presented for various high-modulus composite materials, orientation angles, aspect ratios, and boundary conditions.
As for these CNT/metal composites, the orientation of the CNTs, homogeneity of the composite, nanotube aspect ratio and the volume fraction of nanotubes are expected to have significant influences on the properties of the nanocomposite [14, 15].
A good agreement between the experimental values as obtained by neutron diffraction and the values predicted by the Eshelby model is obtained when the real composites microstructure (orientation and distribution of the reinforcement) is taken into consideration.
The maximal reduction of composite patch of orientation (1) is the order of 56% more important with regard to patch of orientation (2).
The effects of fiber orientation, composite laminate stacking sequence, overlap length, adhesive layer thickness, and adhesive stiffness on the shear and peel stress distribution are evaluated and presented.
Scanning electron microscope (SEM), X-ray diffraction (XRD) and micro-Raman measurements are carried out to characterize the change of phase composition, morphology and orientation of the composite films.
