Ryoma Aoki 교수

Investigations were carried out on a horizontal tail assembly made of carbon fiber reinforced plastic for the Alpha Jet. The possibility of obtaining a leading edge nose design lighter but not more expensive than a metal version was studied. An important consideration was sufficient resistance of the leading edge against impact of stones and hailstones combined with high degree of stiffness. The improvement of energy reception characteristics of the materials through suitable laminate design was

The purpose of this study is to evaluate the effects of ply thickness on the progressive damage in thin-ply composite laminates experimentally and numerically. To investigate the influence of the ply thickness on the damage growth, loading and unloading tests were carried out on angle-ply and quasi-isotropic laminates with three different ply thicknesses. The damage evolution was evaluated quantitatively using continuum damage mechanics model. The evolution laws of damage in thin-ply composites

This study aims to conduct a fatigue simulation for predicting the stiffness degradation of thin-ply composite laminates with several ply thicknesses. For the simulation, a fatigue evolution model of intra-laminar damage in thin-ply composite laminates considering the effect of ply thickness was proposed. The intra-laminar damage evolution was modeled using the continuum damage mechanics model and the static and fatigue evolution law were formulated by relating the transverse crack density to th

Thin-ply composites, owing to their excellent damage resistance and mechanical strength, can significantly contribute to structural weight reduction. Additionally, they have the advantage of improving the design freedom in composite structures. In this study, the effects of the ply thickness and laminate layup on properties such as the damage resistance and mechanical strength in CFRP laminates with toughening interlayers were experimentally evaluated. Non-hole tensile (NHT), open-hole tensile (