• Advanced Composite Materials
• /
• 제17권1호
• /
• pp.57-73
• /
• 2008

The present paper focuses on experimental verification of the ply-by-ply basis inelastic analysis of multidirectional laminates. First of all, rate dependence of the tensile behavior of balanced symmetric cross-ply T800H/epoxy laminates with a $[0/90]_{3S}$ lay-up under off-axis loading conditions at $100^{\circ}C$ is examined. Uniaxial tension tests are performed on plain coupon specimens with various fiber orientations $[{\theta}/(90-{\theta})]_{3S}$ ($\theta$ = 0, 5, 15, 45 and $90^{\circ}C$) at two different strain rates (1.0 and 0.01%/min). The off-axis stress.strain curves exhibit marked nonlinearity for all the off-axis fiber orientations except for the on-axis fiber orientations $\theta$ = 0 and $90^{\circ}$, regardless of the strain rates. Strain rate has significant influences not only on the off-axis flow stress in the regime of nonlinear response but also on the apparent off-axis elastic modulus in the regime of initial linear response. A macromechanical constitutive model based on a ply viscoplasticity model and the classical laminated plate theory is applied to predictions of the rate-dependent off-axis nonlinear behavior of the cross-ply CFRP laminate. The material constants involved by the ply viscoplasticity model are identified on the basis of the experimental results on the unidirectional laminate of the same carbon/epoxy system. It is demonstrated that good agreements between the predicted and observed results are obtained by taking account of the fiber rotation induced by deformation as well as the rate dependence of the initial Young's moduli.

• 한국자동차공학회논문집
• /
• 제4권4호
• /
• pp.147-155
• /
• 1996

The purpose of present paper is to estimate the static and fatigue bending strengths of CFRP(carbon fiber reinforced plastic) laminates having impact damage(FOD). The specimens which are formed with the different stacking composition, EPOXY and PEEK matirx and orthotropic and quasi-isotropic laminated plates, are prepared for this experiment. A steel ball is impacted on CFRP laminates, generating impact damages, and the three-point fatigue bending test is carried out by using the impacted laminates to investigate the influence of the stackin composition on the fatigue strength of CFRP laminates.

• Composites Research
• /
• 제12권1호
• /
• pp.28-36
• /
• 1999

본 연구에서는 얇은 탄소섬유/에폭시 복합적층판(두께 1mm)의 냉각열응력으로 인한 자유경계단 근처의 파손을 유한요소 수치해석과 초음파 C-scan, 광학 및 전자현미경 관찰을 통하여 검토하였다. 수치해석 결과, 복합적층판의 자유단 근처의 내부층에서 층냄 및 층간응력이 크게 나타났다. 액체질소에 의한 저온담금질 실험결과, 적층강도가 $[0_2/90_2]_s,\;[45_2/-45_0]_s,\;[0_2/60_2]_s$인 적층판의 층간근처의 내부층 쪽에서만 모재 및 계면부에서 진전하는 층내균열이 발생하였다. 이들 결과는 위의 수치해석 결과와 일치했다.

• 비파괴검사학회지
• /
• 제28권1호
• /
• pp.46-53
• /
• 2008

복합재료의 내부 결함 평가를 위해 일반적으로 적용되어온 초음파 C-스캔 기법은 섬유자동 배열을 통한 정밀 성형 공정에 적용하기에는 많은 어려움이 있다. 따라서 본 연구는 복합재료의 정밀 성형 공정 중에 발생되는 각종 내부 결함들을 비파괴적, 비접촉으로 평가하기 위한 새로운 하이브리드 초음파 평가 기법을 확립하는데 목적이 있다. 이를 위하여 본 연구에서는 초음파 산란 반사(scattering reflection) 방식을 토대로 한 새로운 이중 피치-캐치(dual pitch-catch) 기법을 확립하여 기존의 결함평가를 위해 시험편의 스캔에 소요되는 시간을 줄이면서 우수한 결함 영상을 얻을 수 있는 새로운 하이브리드 기법을 개발하였다. 즉 두 가지 종류의 열경화성 및 열가소성 복합재료(carbon/epoxy, carbon/PPS) 적층판의 내부 박리(delamination) 결함의 영상화를 위하여 레이저를 이용한 유도 초음파의 발생 및 이중 피치-캐치(pitch-catch)방식을 토대로 한 비접촉식 공기 정합 트랜스듀서(air-coupled transducer)를 이용하여 결함 영상을 얻기 위한 핵심 알고리즘을 확립하였다.

• Composites Research
• /
• 제23권5호
• /
• pp.15-21
• /
• 2010

본 연구에서는 손상된 복합재 구조의 유지 보수 방안에 대한 연구를 수행하였다. 복합재료 구조의 손상 수리 방안을 제시하고 수리 절차를 카본/에폭시 적층판 복합재 구조에 적용하여 시편 시험 및 수치 해석을 통해 분석하였다. 손상은 중량 낙하식 충격 시험기를 활용하여 복합재 구조 시편에 충격 손상으로 모사하였다. 손상된 복합재 적층판 구조는 충격 손상 부위 제거 후 외부 패치 수리 기법을 적용하여 수리하였다. 충격 손상 후 유지 보수된 시편과 손상이 없는 시편의 압축 강도를 실험적 및 해석적으로 비교 분석하였다. 이를 바탕으로 유지 보수된 시편의 강도 회복 능력을 고찰하였다.

• 한국정밀공학회지
• /
• 제27권2호
• /
• pp.102-108
• /
• 2010

Recently, carbon fiber reinforced plastic(CFRP) composite materials have been widely used in various fields of engineering because of its advanced properties. Also, CFRP composite materials offer new design flexibilities, corrosion and wear resistance, low thermal conductivity and increased fatigue life. However CFRP composite materials are susceptible to impact damage due to their lack of through-thickness reinforcement and it causes large drops in the load-carrying capacity of a structure. Therefore, the impact damage behavior and subsequently load-carrying capacity of impacted composite materials deserve careful investigation. In this study, the residual strength and impact characteristics of plain-woven CFRP composites with impact damage are investigated under axial tensile test. By using obtained residual strength and Tan-Cheng failure criterion, residual strength of CFRP laminate with arbitrary fiber angle were evaluated.

• 대한기계학회논문집A
• /
• 제24권8호
• /
• pp.2115-2122
• /
• 2000

The understanding of impact-induced delamination is important in safety and reliability of composite structure. In this study, a model for arrest toughness is proposed in consideration of fracture behavior of composite materials. Also, the probabilistic model is proposed to describe the variability of arrest toughness due to the nonhomogeneity of material. For these models, experiments were conducted on the Carbon/Epoxy composite plates with various thickness using the impact hammer. The elastic work factor used in J-Integral is applicable to the evaluation of energy release rate. The fracture behavior can be described by crack arrest concept and the arrest toughness is independent of the delamination size. Additionally, a probabilistic characteristics of arrest toughness is well described by the Weibull distribution function. A variation of arrest toughness increases with specimen thickness.

• 한국산학기술학회논문지
• /
• 제11권2호
• /
• pp.426-434
• /
• 2010

본 논문에서는 충격손상을 갖는 유리섬유강화 복합재료의 강도 저하 특성과 이의 통계적 특성을 실험적으로 평가하였다. 평직 복합재료의 주요 충격손상은 섬유파단과 모재균열로서 이는 층간분리가 주된 충격손상인 일방향 적층복합재료와는 상이한 양상이다. 일방향 적층복합재료에 대하여 제안된 기존의 잔류강도 예측모델을 이용하여 충격손상을 갖는 평직 glass/epoxy 복합재료의 잔류강도를 평가하였다. 그 결과 Avva 및 Caprino의 잔류강도 예측모델은 평직 복합재료의 잔류강도에 대해서도 잘 평가되었다. 또한 유리섬유강화 복합재료의 잔류강도에 대한 통계적 특성 평가를 위한 모델을 제안하였으며, 이를 통한 예측결과는 복합재료의 두께와 관계없이 실험결과를 잘 묘사하였다.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
• /
• pp.151-155
• /
• 2003

An apparatus was developed to repetitively apply a -196 $^{\circ}C$ thermal load to coupon-sized mechanical test specimens. Using this device, IM7/5250-4 (carbon / bismaleimide) cross-ply and quasi-isotropic laminates were submerged in liquid nitrogen (L$N_2$) 400 times. Ply-by-Ply micro-crack density, laminate modulus, and laminate strength were measured as a function of thermal cycles. Quasi-isotropic samples of IM7/977-3 (carbon / epoxy) composite were also manually cycled between liquid nitrogen and an oven set at 120 $^{\circ}C$ for 130 cycles to determine whether including elevated temperature in the thermal cycle significantly altered the degree or location of micro-cracking. In response to thermal cycling, both materials micro-cracked extensively in the surface plies followed by sparse cracking of the inner plies. The tensile modulus of the IM7/5250-4 specimens was unaffected by thermal cycling, but the tensile strength of two of the lay-ups decreased by as much as 8.5 %.

• Steel and Composite Structures
• /
• 제31권2호
• /
• pp.113-123
• /
• 2019

In this study, carbon fiber/epoxy (CF/EP) composites were interleaved with aramid nonwoven veils with an areal weight density of $8.5g/m^2$ to improve their Mode-I fracture toughness. The control and aramid interleaved CF/EP composite laminates were manufactured by VARTM in a [0]4 configuration. Tensile, three-point bending, compression, interlaminar shear, Charpy impact and Mode-I (DCB) fracture toughness values were determined to evaluate the effects of aramid nonwoven fabrics on the mechanical performance of the CF/EP composites. Thermomechanical behavior of the specimens was investigated by Dynamic Mechanical Analysis (DMA). The results showed that the propagation Mode-I fracture toughness values of CF/EP composites can be significantly improved (by about 72%) using aramid nonwoven fabrics. It was found that the main extrinsic toughening mechanism is aramid microfiber bridging acting behind the crack-tip. The incorporation of these nonwovens also increased interlaminar shear and Charpy impact strength by 10 and 16.5%, respectively. Moreover, it was revealed that the damping ability of the composites increased with the incorporation of aramid nonwoven fabrics in the interlaminar region of composites. On the other hand, they caused a reduction in in-plane mechanical properties due to the reduced carbon fiber volume fraction, increased thickness and void formation in the composites.