• 대한기계학회논문집A
• /
• 제20권8호
• /
• pp.2491-2500
• /
• 1996

An experimental and analytical investigation is performed to study the buckling behavior of composite laminates with an embedded delamination. It is of particular interest to veryfy whether delamination growth cddurs with continuming deformation after buckling of composite laminates with an embedded delamination. Experiments are conducted for [0/sub 4///90/sub 8//0/sub 4/]/sub r/ laminates with delamination size in which local buckling mode governs buckling. Results show that delamination growth occurs in hgigher load after buckling and is accompanid by other damage mechanisms such as splitting. Also, it is found that transverse deformation before difurcation buckling is due to initial imperfection and structure such as plate with small bending stiffness is sensitive to that.

• 대한기계학회논문집
• /
• 제19권2호
• /
• pp.354-362
• /
• 1995

The finite element modeling is used to study the buckling and postbuckling behavior of composite laminates with an embedded delamination. Degenerated shell element and rigid beam element are utilized for the finite element modeling. In the nonlinear finite element formulation, the updated Lagrangian description method based on the second Piola-Kirchhoff stress tensor and the Green strain tensor is used. The buckling and postbuckling behavior of composite laminates with a delamination are investigated for various delamination sizes, stacking sequences, and boundary conditions. It is shown that the buckling load and postbuckling behavior of composite laminates depend on the buckling model which is determined by the delamination size, stacking sequence and boundary condition. Also, results show that introduction of couplings can reduce greatly the buckling load.

• 한국재료학회지
• /
• 제34권3호
• /
• pp.125-137
• /
• 2024

Composite laminates are used in a wide range of applications including defense, automotive, aviation and aerospace, marine, wind energy, and recreational sporting goods. These composite beams still exhibit problems such as buckling, local deformations, and interlaminar delamination. To overcome these drawbacks, a novel viscoelastic autoclave bonding with tapered epoxy reinforcement polyurethane films is proposed. In existing laminates, compression face wrinkling and interlaminar delamination is caused in the sandwich beam. The unique viscoelastic autoclave spunbond interlayer bonding is designed to prevent face wrinkling and absorb and distribute stresses induced by external loads, thereby eliminating interlaminar delamination in the sandwich beam. Also, the existing special reinforcement causes stress concentrations, and the core is not effectively connected, which directly affects the stiffness of the beam. To address this, a novel tapered epoxy polyurethane reinforcement adhesive film is proposed, whose reinforcement thickness gradually tapers as it enters the core material. This minimizes stress concentrations at the interface, preventing excessive adhesive squeeze-out during the bonding process, and improves the stiffness of the beam. Results indicate the proposed model avoids the formation of micro cracks, interlaminar delamination, buckling, and local deformations, and effectively improves the stiffness of the beam.

• Composites Research
• /
• 제18권1호
• /
• pp.30-37
• /
• 2005

본 연구에서는 3점 굽힘 실험과 코어의 실제 형상을 모델링한 유한요소 시뮬레이션을 병행하여 외피층의 항복, 층간분리 코어의 전단 및 국부적 좌굴과 같은 다양한 파손모드를 고려한 하니컴 샌드위치 복합재료의 강도 특성과 변형거동을 검토하였다. 외피층과 하니컴 코어층 사이를 완전 접착한 시험편과 부분 층간분리 시험편을 대상으로 하니컴 코어의 셀 크기와 외피층 두께를 변화시켜 시험편의 굽힘 강성, 굽힘 강도. 굽힘 응력, 변형 및 파손 거동을 해석하였다. 결론적으로 하니컴 코어의 셀 크기와 외피층의 두께가 하니컴 샌드위치 복합재료의 굽힘 강성과 강도, 변형/파괴 거동에 주된 영향을 미쳤으며 코어의 셀 크기가 크고 외피층의 두께가 얇은 경우 굽힘 강도는 $30\~68\%$ 정도까지 저하됨을 알 수 있었다.

• 한국자동차공학회논문집
• /
• 제2권6호
• /
• pp.66-75
• /
• 1994

In this paper, the effects of temperature change on the impact damages of CF/PEEK laminates are experimentally investigated. Composite laminates used in this experiment are CF/PEEK orthotropic laminated plates, which have two-interfaces$[0^{\circ}_4/90^{\circ}_4]_{9+} A steel ball launched by the air gun collides against CFRP laminates to generate impact damage. The delamination damages are oberved by a scanning acoustic microscope. And various relations are experimentally observed including the impact energy vs. delamination area, the specimen temperature vs. transverse crack, and the impact energy vs. residual bending strength of carbon fiber peek composite laminates subjected to FOD(Foreign Object Damage) under high temperatures.

• Structural Engineering and Mechanics
• /
• 제76권2호
• /
• pp.175-191
• /
• 2020

In this study, the effect of Nano silica (SiO2) on the buckling strength of the glass fiber reinforced laminates containing the machining process causes holes were investigated. The tests have been applied on two status milled and non-milled. To promote the mechanical behavior of the fiber-reinforced glass epoxy-based composites, Nano sio2 was added to the matrix to improve and gradation. Nano sio2 is chosen because of flexibility and high mechanical features; the effect of Nanoparticles on surface serenity has been studied. Thus the effect of Nanoparticles on crack growth and machining process and delamination caused by machining has been studied. We can also imply that many machining factors are essential: feed rate, thrust force, and spindle speed. Also, feed rate and spindle speed were studied in constant values, that the thrust forces were studied as the main factor caused residual stress. Moreover, entrance forces were measured by local calibrated load cells on machining devices. The results showed that the buckling load of milled laminates had been increased by about 50% with adding 2 wt% of silica in comparison with the neat damaged laminates while adding more contents caused adverse effects. Also, with a comparison of two milling tools, the cylindrical radius-end tool had less destructive effects on specimens.

• Composites Research
• /
• 제22권4호
• /
• pp.1-12
• /
• 2009

본 논문에서는 복합재 원형튜브의 에너지 흡수 특성을 평가하기 위해 준정적 압괴실험을 시행하였다. 사용된 시편은 필라멘트 와인딩 공법으로 제작된 GFRP(유리섬유/에폭시수지) 원형 튜브이다. 복합재 튜브의 에너지 흡수 특성 분석을 위한 파라미터로서 튜브의 트리거메커니즘, t/D, 섬유배향각 등을 고려하여 그 특성을 비교하였다. 튜브의 형상 측면에서 튜브 직경이 커짐에 따라 delamination에 의한 국부좌굴 발생빈도가 증가하게 되어 불안정한 압괴모드가 발생하는데 이러한 현상은 섬유 배향각을 조정하여 안정적인 압괴모드를 도출할 수 있었다.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2004년도 추계학술발표대회 논문집
• /
• pp.61-64
• /
• 2004

The strength characteristics as well as deformation behaviors of honeycomb sandwich composite (HSC) structures were investigated under bending in consideration of various failure modes such as skin layer yielding, interface-delamination, core shear deformation and local buckling. Deformation behaviors of honeycomb sandwich plates were observed with various types of aluminum honeycomb core and skin layer. Their finite-element analysis simulation with a real model of honeycomb core was performed to analyze stresses and deformation behaviors of honeycomb sandwich plates. Its results were very comparable to the experimental ones. Consequently, the increase in skin layer thickness and in cell size of honeycomb core had dominant effects on the strength and deformation behaviors of honeycomb sandwich composites.

• 한국해양공학회지
• /
• 제10권2호
• /
• pp.35-41
• /
• 1996

This paper is aimed to solve local buckling problem that can frequently occur when the high speed ship's hull of sandwich structural type is crushed by rarbour and cargo. Experiment is performed on 36 specimens cut of 4-plates that made of sandwich type(Kevlar-Epoxy, Klegecell foam) and 16-Edgewise compressive test specimen, 16-Flatwise test specimen were tested by A.S.T.M. test method. The result of this study is analyzed and compared in test method and test jig to perorm Edgewise compressive test and Flatwise test.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2002년도 추계학술발표대회 논문집
• /
• pp.88-91
• /
• 2002

The two dimensional size effect of specimen gauge section (length x width) was investigated on the compressive behavior of a T300/924 [45/-45/0/90]3s, carbon fiber-epoxy laminate. A modified ICSTM compression test fixture was used together with an anti-buckling device to test 3mm thick specimens with a 30$\times$30, 50$\times$50, 70$\times$70, and 90mm$\times$90mm gauge length by width section. In all cases failure was sudden and occurred mainly within the gauge length. Post failure examination suggests that $0^{\circ}$ fiber microbuckling is the critical damage mechanism that causes final failure. This is the matrix dominated failure mode and its triggering depends very much on initial fiber waviness. It is suggested that manufacturing process and quality may play a significant role in determining the compressive strength. When the anti-buckling device was used on specimens, it was showed that the compressive strength with the device was slightly greater than that without the device due to surface friction between the specimen and the device by pretoque in bolts of the device. In the analysis result on influence of the anti-buckling device using the finite element method, it was found that the compressive strength with the anti-buckling device by loaded bolts was about 7% higher than actual compressive strength. Additionally, compressive tests on specimen with an open hole were performed. The local stress concentration arising from the hole dominates the strength of the laminate rather than the stresses in the bulk of the material. It is observed that the remote failure stress decreases with increasing hole size and specimen width but is generally well above the value one might predict from the elastic stress concentration factor. This suggests that the material is not ideally brittle and some stress relief occurs around the hole. X-ray radiography reveals that damage in the form of fiber microbuckling and delamination initiates at the edge of the hole at approximately 80% of the failure load and extends stably under increasing load before becoming unstable at a critical length of 2-3mm (depends on specimen geometry). This damage growth and failure are analysed by a linear cohesive zone model. Using the independently measured laminate parameters of unnotched compressive strength and in-plane fracture toughness the model predicts successfully the notched strength as a function of hole size and width.