2018
DOI: 10.1016/j.compstruct.2017.11.060
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Strength degradation and stress analysis of composite plates with circular, square and rectangular notches using digital image correlation

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Cited by 85 publications
(40 citation statements)
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“…8(a). In accordance with the established theory [45], 22 is maximum just ahead of the notch tip at  = 0º. The 22 remains highest at  = 0º for the case of two orthogonal fibre families with initial orientations of 0 º and 90 º (i.e.…”
Section: Effect Of Fiber Orientationsupporting
confidence: 86%
“…8(a). In accordance with the established theory [45], 22 is maximum just ahead of the notch tip at  = 0º. The 22 remains highest at  = 0º for the case of two orthogonal fibre families with initial orientations of 0 º and 90 º (i.e.…”
Section: Effect Of Fiber Orientationsupporting
confidence: 86%
“…At the first portion of the present work, a set of tensile experiments on laminates with different fiber direction angles and specimens with various notch diameter/width (D/W) ratios are made and tested to define the SCF and damage mechanisms for notched/ un notched samples. Moreover, failure patterns, strain distribution and fracture mechanisms of laminated specimens with rectangular and square holes with rounded corners have been researched [5]. The current research attempts to form composite plates using a blending of natural polymers and fibers to progress certain properties.…”
Section: Methodsmentioning
confidence: 99%
“…Stress distribution around slots can be assessed using computational methods, experimental and elasticity theory stress analysis. Considerable efforts have been formed in the development of precise analytical samples to define the distribution of stress in the segments of the compound [5].…”
Section: Figure1 Structures For Aircraftmentioning
confidence: 99%
“…1 и 2 видно, что максимальные значения поврежденности достигаются на контуре кругового выреза в случае всесторонне растягиваемой пластины и в точках кругового отверстия, лежащих на оси ординат. Поскольку распределения поврежденности, полученные в ходе конечно-элементного эксперимента, соответствуют известным экспериментальным результатам [48,49], рассматриваемая материальная модель была использована для решения более сложных задач, для анализа зон активного накопления повреждений у вершины трещины.…”
Section: распределение поврежденности в пластине с центральным круговunclassified