• Composites Research
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• 제33권5호
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• pp.288-295
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• 2020

섬유강화 복합재 적층판은 높은 비강성과 비강도를 가지고 있으며, 자동차 및 항공과 같은 무게에 민감한 산업에서 경량화에 유용할 것으로 기대되고 있다. 하지만 복합재 적층판의 설계는 적층 개수와 적층 순서를 모두 결정해야 하는 어려움으로 인해 설계자의 축적된 경험과 직관에 의존하는 경우가 많고, 이는 필요 이상으로 제품의 중량이 증가하는 과설계로 이어질 수 있다. 본 연구에서는 주어진 하중을 견디고 최소 무게를 갖는 복합재 적층판의 최적설계를 수행하였다. 나열법을 기반으로, 복합재 적층판의 설계 지침을 만족하는 모든 경우의 적층 조합을 고려하였다. 복합재 적층판을 여러 개의 패널로 나누고, 각 패널의 응력 분포와 인접한 패널 간 연결성을 고려하여 최적의 적층 수와 적층 순서를 결정하였다. 강도를 고려하기 위해 Tsai-Wu 파손 이론으로부터 파손 지수를 최적화하였고, 압축 하중에 대해서는 좌굴 해석을 수행하였다. 적층각은 일반적으로 사용하고 있는 0, ±45, 90°를 사용하였다.

• 한국생산제조학회지
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• 제6권4호
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• pp.96-100
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• 1997

Tensile properties of carbon fiber reinforce composite laminates with non-woven carbon mat are evaluated in this paper. Composite laminates are made by inserting non-wovon carbon mat between layers, The specimens were cut and polished according to ASTM standard . Longitudinal and Transverse Young's modulus are obtained by tensile test. Young's moduli without non-woven carbon mat are compared with those with non-woven carbon mat. Longitudinal and Transverse tensile strength are also investigated. Experimental results show that the transverse Young's modulus of composite materials with non-woven carbon mat is about 10% higher than that of composite materials without non-woven carbon mat. Longitudinal tensile strength of composite materials with non-woven carbon mat is about 24% higher than that of composite materials without non-woven carbon mat. Transverse tensile strength and torughness also increase by inserting non-woven carbon mat between layers.

• 한국안전학회지
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• 제13권4호
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• pp.41-48
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• 1998

In this paper, an investigation was performed on the dynamic interlaminar fracture toughness of CFRP(carbon fiber reinforcement plastics) composite laminates. Composite laminates used in this experimentation are CF/EPOXY and CF/PEEK laminated plates. In the experiments, Split Hopkinson's Bar(SHPE) test was applied to dynamic and notched flexure test. The mode Ⅱ fracture toughness of each unidirectional CFRP was estimated by the analyzed deflection of the specimen and J-integral with the measured impulsive load and reactions at the supported points. As an experimental result, the vibration amplitude of CF/PEEK laminates appear more than that of CF/EPOXY laminates for the J-integral and displacement velocity at a measuring point. Also, it is thought that the dynamic fracture toughness of two kind specimens(CFRP/EPOXY and CF/PEEK) with the in crease of displacement velocity becomes a little greater at a measuring point within the range of measurement.

• Composites Research
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• 제26권6호
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• pp.349-354
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• 2013

본 논문에서는 Carbon/Epoxy 복합재 적층판에 대하여 실사격 실험을 수행하였으며, 복합재 적층판의 흡수에너지를 예측하기 위한 개선된 방법을 제시하였다. 고속충격실험 과정에서 충격체의 질량손실을 고속카메라를 통하여 거시적으로 확인하였으며, 따라서 이를 고려하여 복합재 적층판의 흡수에너지를 계산하였다. 고속충격을 받는 복합재 적층판의 흡수에너지를 예측하기 위한 모델을 제시하였으며, 복합재 적층판의 흡수에너지는 크게 정적에너지와 동적에너지로 분류하였다. 정적에너지 계산은 섬유의 파손과 정적 탄성에너지와 관련 있는 준정적 관통실험식을 통해 구한 관통에너지를 사용하였다. 동적에너지는 변형되는 시편의 운동에너지와 손실된 파편 질량들의 운동에너지로 나뉠 수 있다. 최종적으로 충격체 질량손실을 고려하여 예측된 흡수에너지와 실험결과를 비교/분석하였다.

• Composites Research
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• 제12권4호
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• pp.8-16
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• 1999

본 연구는 인장하중의 방향변화에 따른 의사 등방성 복합재 적층판의 피로손상거동의 변화에 대하여 알아보았다. [0/-60/＋60]$_s$ 적층판과 [＋30/-30/90]$_s$ 적층판의 저 싸이클 피로시험을 행하였고, 재료계는 AS4/Epoxy와 AS4/PEEK를 사용하였다. [＋30/-30/90]$_s$ 적층판의 피로손상은 [0/-60/＋60]$_s$ 적층판에 비하여 아주 달랐다. AS4/Epoxy와 AS4/PEEK [＋30/-30/90]$_s$ 적층판에 발생한 층간분리의 위치가 모재의 종류에 따라 다르게 나타났다. 층간분리 진전시 측정된 변형률을 사용하여 임계 변형률 에너지 해방률을 계산하였다. 실험결과를 모드별 변형률 에너지 해방률의 제안된 계산법으로 얻어진 해석 결과와 비교한 결과, 잘 일치되었다.

• Journal of Mechanical Science and Technology
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• 제17권3호
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• pp.391-399
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• 2003

The thermo-acoustic emission (AE) technique has been applied for nondestructive characterization of composite laminates subjected to cryogenic cooling. Thermo-AE events during heating and cooling cycles showed a Kaiser effect. An analysis of the thermo-AE behavior obtained during the 1st heating period suggested a method for determining the stress-free temperature of the composite laminates. Three different thermo-AE types classified by a short-time Fourier transform of AE signals enabled to offer a nondestructive estimation of the cryogenic damages of the composites, in that the different thermo-AE types corresponded to secondary microfracturing in the matrix contacting between crack surfaces and some abrasive contact between broken fiber ends during thermal load cycles.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집A
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• pp.228-233
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• 2001

It is well known that composite laminates are easily damaged by low velocity impact. The damage of composite laminates subjected to impact loading are occurred matrix cracking, delamination, and fiber breakage. The damage of matrix cracking and delamination are reduced suddenly the compressive strength after impact. This study is to evaluate impact characteristics and the relationship between impact force and inside damage of composite laminates by low velocity impact loading. UT C-scan is used to determine impact damage areas by impact loading.

• 대한기계학회논문집
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• 제19권2호
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• pp.354-362
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• 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.

• 한국철도학회:학술대회논문집
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• 한국철도학회 2001년도 추계학술대회 논문집
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• pp.211-216
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• 2001

It is well known that composite laminates are easily damaged by low velocity impact. Low velocity impact damage characteristics and residual compressive strength of composite laminates used in light rail transit are investigated. The damage of composite laminates subjected to impact loading are occurred matrix cracking, delamination, and fiber breakage. The damage of matrix cracking and delamination are reduced suddenly the compressive strength after impact. The objectives of this study is to evaluate impact characteristics and the relationship between impact force and inside damage of composite laminates by low velocity impact loading. UT C-scan is used to determine impact damage areas by impact loading.

• 비파괴검사학회지
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• 제25권6호
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• pp.451-458
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• 2005

The effects of fiber orientation on acoustic emission(AE) characteristics have been studied for various composite laminates. Reflection and transmission optical microscopy were used to investigate the damage zone of specimens. AE signals were classified through short time Fourier transform(STFT) as different types: AE signals with a high intensity and high frequency band were due to fiber fracture, while weak AE signals with a low frequency band were due to matrix cracking and/or interfacial cracking. Characteristic feature in the rate of hit-events having high amplitudes showed a procedure of fiber breakages, which expressed the characteristic fracture processes of notched fiber-reinforced plastics with different fiber orientations. As a consequence, the behavior of fracture in the continuous composite laminates could be monitored through nondestructive evaluation(NDE) using the AE technique.