In this study, a design procedure is proposed for a tapered FRP laminate with ply drop-offs to suppress the damage initiation. A stress index, based on the von Mises yield criteria, is defined and applied to the resin pockets formed adjacent to cut plies. First, finite element (FE) analysis of a three-ply tapered laminate consisting of a cover layer, a dropped layer, and a base layer is conducted to relate the fiber directions with the stresses caused by a ply drop-off. Using the stress values obtained from the FE analysis, a tapered quasi-isotropic laminate with a thickness decreasing from 16 to 8 layers is appropriately designed by minimizing the overall stress indexes in ply-dropped locations. The observation of the specimen manufactured...
Automated Fibre Placement (AFP) is a manufacturing technique to produce large, high quality composit...
The influence of ply-drop position in thickness direction under fatigue loading (R = -1) has been st...
In typical applications like in the top skin of the wing or in control surfaces of an airframe, lami...
Thickness tapered laminates obtained by terminating a certain number of plies contain resin-rich are...
The present investigation aims at developing a few guidelines for the design of tapered laminated co...
A global–local approach for the analysis of tapered laminated composites is presented. The method is...
Design and manufacture of a variable thickness composite laminate such as a helicopter yoke involves...
A novel ply drop-off element has been developed for the analysis of tapered laminated composites. Th...
Composite laminate thickness tapering is essential for weight efficient structures. This is achieved...
A tapered composite laminate subjected to tension load was analyzed using the finite-element method....
The aim of this study is to analyse the influence of ply drop-off regions and related parameters on ...
The thickness of a laminated composite structure can be varied by reducing the number of plies throu...
One major problem when using bonded fiber-reinforced plastic laminatesto strengthen and upgrade exis...
Any geometrical change and material transition renders a weak point accumulating stress concentratio...
Weight reduction in vehicles offers many advantages. Especially in aircraft, one of the advantages o...
Automated Fibre Placement (AFP) is a manufacturing technique to produce large, high quality composit...
The influence of ply-drop position in thickness direction under fatigue loading (R = -1) has been st...
In typical applications like in the top skin of the wing or in control surfaces of an airframe, lami...
Thickness tapered laminates obtained by terminating a certain number of plies contain resin-rich are...
The present investigation aims at developing a few guidelines for the design of tapered laminated co...
A global–local approach for the analysis of tapered laminated composites is presented. The method is...
Design and manufacture of a variable thickness composite laminate such as a helicopter yoke involves...
A novel ply drop-off element has been developed for the analysis of tapered laminated composites. Th...
Composite laminate thickness tapering is essential for weight efficient structures. This is achieved...
A tapered composite laminate subjected to tension load was analyzed using the finite-element method....
The aim of this study is to analyse the influence of ply drop-off regions and related parameters on ...
The thickness of a laminated composite structure can be varied by reducing the number of plies throu...
One major problem when using bonded fiber-reinforced plastic laminatesto strengthen and upgrade exis...
Any geometrical change and material transition renders a weak point accumulating stress concentratio...
Weight reduction in vehicles offers many advantages. Especially in aircraft, one of the advantages o...
Automated Fibre Placement (AFP) is a manufacturing technique to produce large, high quality composit...
The influence of ply-drop position in thickness direction under fatigue loading (R = -1) has been st...
In typical applications like in the top skin of the wing or in control surfaces of an airframe, lami...