• 제목/요약/키워드: CFRP laminate

검색결과 133건 처리시간 0.022초

CFRP Prepreg 적층조건과 금형 마찰계수를 고려한 Double-dome 형상 성형해석 연구 (A study on the forming analysis of double-dome model considering CFRP prepreg laminate condition and coefficient of friction)

  • 김영주;이산호;김흥규
    • Design & Manufacturing
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    • 제10권2호
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    • pp.12-17
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    • 2016
  • Recently, lightweight material is attracting attention as a solution to the problem of fuel efficiency and increasing the need for development. CFRP has been attracting attention as lightweight materials for automobile because it has a high specific stiffness and specific strength compared to steel material. CFRP have a wide range of mechanical properties depending on the laminate condition. In this paper, study on the forming analysis of double-dome model was performed considering CFRP prepreg laminate condition and coefficient of friction. After forming analysis, the result has compared with wrinkling area and vertical strain of fiber to the laminated condition. And then compared with inflow of blank to the laminate condition. Through this paper, we propose the forming analysis methods of CFRP material.

섬유방향 변화에 따른 직물구조 CFRP 적층판의 균열진전 및 AE평가 (Crack Propagation and Acoustic Emission Evaluation of Plain Woven CFRP Laminate Composites for Fiber Orientation)

  • 윤유성;권오헌
    • 대한기계학회:학술대회논문집
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    • 대한기계학회 2003년도 춘계학술대회
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    • pp.364-369
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    • 2003
  • Crack propagation and AE characteristics of CFRP plain woven laminate composites are examined with acoustic sensor by AEDSP 32/16 board in PC system. AE signals are measured during the fracture behavior tests. The purpose of study is the estimation of the crack extension behavior effected between three kinds of fiber orientation for plain woven CFRP laminate composite and the relationship between AE characteristics and load-displacement curves and crack extension length.

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MMB시험에 의한 평직 CFRP/GFRP 적층판 혼합모드 층간분리의 실험적 평가 (The Experimental Evaluation of the Mixed Mode Delamination in Woven CFRP/GFRP Laminates under MMB Test)

  • 곽정훈;강지웅;권오헌
    • 한국안전학회지
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    • 제28권4호
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    • pp.14-18
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    • 2013
  • Blades of horizontal axis are nowadays made of composite materials. Generally, composite materials satisfy design provides lower weight and good stiffness, while laminate composites have often damages as like the delamination and cracks at the interface of laminates. The box spar and tail parts of a blade are composed of the CFRP/GFRP hybrid laminate composites. However, delamination and the interfacial crack often occur in the interface of CFRP/GFRP hybrid laminate composites under the mixed mode fracture condition, especially mode I and mode II. Therefore, there is a need for the evaluation of the mixed mode fracture behavior during the delamination of CFRP/GFRP hybrid laminates. This study shows the experimental results for the delamination fracture toughness in CFRP/GFRP hybrid laminate composites. Fracture toughness experiments and estimation are performed by using DMMB(Dissimilar mixed mode bending) specimen. The materials used in the test are a commercial woven type CFRP(Carbon fiber reinforced plastic) prepreg(CF3327) and UD type GFRP(Glass fiber reinforced plastic) prepreg(HD224A). A CFRP/GFRP hybrid laminate composite is composed by the 10 plies CFRP and GFRP prepreg for DMMB. A thickness of CFRP and GFRP layer is 2.5mm and 3.0mm, respectively. Also the fulcrum location which is a loading parameter is changed from 80 to 100mm on the specimen of length 120mm because it defines the ratio of mode I to mode II. In this study, the effects of the fulcrum location are evaluated in the viewpoint of energy release rate in mode I and mode II contribution. The results show that the delamination crack initiates at higher displacement and lower load according to the increase of the fulcrum location ratio. And the variation of the energy release rate for mode I and II contributions for the mode mixity are shown.

Al Shee/CFRP 다적층 하이브리드 복합재료의 굴곡강도에 미치는 카본섬유 체적률 및 배열방향 영향 (The Influence of Volume Fraction and Fiber Orientation of CERP Layer on Flexural properties of A17075/CFRP Multi-Layered Hybrid Laminate Material)

  • 유재환
    • 한국안전학회지
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    • 제19권4호
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    • pp.31-35
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    • 2004
  • The A17075/CFRP multi-layered hybrid laminate material consists of the alternating A17075-T6 sheets and carbon/epoxy prepregs of M40 fade. The influence of volume fraction and fiber orientation of A17075/CFRP layer on flexural properties of A17075/CFRP laminate alternating A17075-T6 and carbon/epoxy prepreg was investigated. The results obtained from the experimental analysis are as follows: 1. In the $0^{\circ}$ fiber orientation, the mont of increase of the flexural rigidity was $20.5\%$ at the $26.5\%$ volume fraction and $38.0\%\;at\;the\;35.7\%$ volume fraction compared with the flexural rigidity level(20.0GPa) of the $10\%$ volume fraction of CFRP. 2. In the $\pm45^{\circ}$ fiber orientation the amount of decrease of the flexural rigidity was $23.5\%\;at\;the\;20.0\%$ volume fraction and $31.5\%\;at\;the\;33.3\%$ volume fraction compared with the flexural rigidity level of the $10\%$ volume fraction of CFRP. 3. In the $0^{\circ}$ fiber orientation, the flexural strength was 481.5MPa at the $10\%$ volume fraction of CFRP and 583.8MPa at the $26.5\%$ volume fraction and 653.7MPa at the $35.7\%$ volume faction. 4. In the $\pm45^{\circ}$ fiber orientation, the flexural strength was 354.0MPa at the $20.0\%$ volume fraction of CFRP and 340.5MPa at the $33.3\%$ volume fraction.

원공노치를 가진 CFRP의 적층방향에 따른 기계적 특성 평가 (The Mechanical Properties Evaluation on Lay-up Orientation Effect of CFRP Laminate Composite with the Hole Notch)

  • 태영일;윤유성;권오헌
    • 한국안전학회지
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    • 제17권1호
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    • pp.25-32
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    • 2002
  • The tensile tests for [0/90]s, [90/0]s, and $[0/{\pm}45/90]s$ laminate composite were accomplished with acoustic sensor and failure processes were recorded by a video camera in real time. Also SEM examinations for fracture and side surface were carried out. The purpose of study is estimation of the failure mechanism and the mechanical properties effected by lay-up orientation for CFRP laminate composite with the hole notch. From the results, mechanical properties were obtained and they are similar between two kinds of cross-ply orientation in CFRP laminate composites, but not on $[0/{\pm}45/90]s$. And accordings to increasing the load, accumulate AE count was increased, regardless of lay-up orientation. Futhermore, failure mechanism was described by a video monitoring and SEM.

Evaluation of the Damage Mechanism in CFRP Composite Using Computer Vision

  • Kwon, Oh-Heon;Xu, Shaowen;Sutton, Michael
    • Journal of Advanced Marine Engineering and Technology
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    • 제34권5호
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    • pp.686-694
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    • 2010
  • Continuing progress in high technology has created numerous industrial applications for new advanced composite materials. Among these materials, carbon fiber-reinforced plastic (CFRP) laminate composite is typically used for low-weight carrying structures that require high specific strength. In this study, the damage mechanism of a compact tension (CT) specimen of woven CFRP laminates is described in terms of strain and displacement changes and crack growth behavior. The digital image correlation (DIC) method (which is employed here as a computer vision technique) is analyzed. Acoustic emission (AE) characteristics are also acquired during fracture tests. The results demonstrate the usefulness of these methods in evaluating the damage mechanism for woven CFRP laminate composites. From the results, we show these methods are so useful in order to evaluate the damage mechanism for woven CFRP laminate composites.

Mechanical Behaviors of CFRP Laminate Composites Reinforced with Aluminum Oxide Powder

  • Kwon, Oh-Heon;Yun, Yu-Seong;Ryu, Yeong-Rok
    • 동력기계공학회지
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    • 제18권6호
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    • pp.166-173
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    • 2014
  • In this study, a laminated composite material with dispersing aluminum oxide powder between the CFRP laminate plies, and also CFRP composites without aluminium oxide powder were fabricated for Mode I experiments using the DCB specimen and a tensile test. The behavior of the crack and the change of the interfacial fracture toughness were evaluated. Also in order to evaluate the damage mechanism for the crack extension, the AE sensor on the surface of the DCB test specimen was attached. AE amplitude was estimated for CFRP-alumina and CFRP composite. And the fracture toughness was evaluated by the stress intensity factor and energy release rate. The results showed that an unstable crack was propagated rapidly in CFRP composite specimen along with the interface, but crack propagation in CFRP-alumina specimen was relatively stable. From results, we show that aluminium oxide powder spreaded uniformly in the interface of the CFRP laminate carried out the role for preventing the sudden crack growth.

적층 각도를 가진 CFRP 접착 구조물의 파손 및 정적 파괴 특성에 관한 융합 연구 (Convergence Study on Damage and Static Fracture Characteristic of the Bonded CFRP structure with Laminate angle)

  • 이정호;김은도;조재웅
    • 한국융합학회논문지
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    • 제10권1호
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    • pp.155-161
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    • 2019
  • 복합소재는 기존의 일반적인 소재보다 내구성과 기계적 성질들이 뛰어난 경량 소재이다. 본 연구에서는 경량 복합소재에 주목하여, 접착제를 이용하여 접착한 CFRP 접착구조물의 정적 파괴 특성을 조사하고자 했고 적층 각도를 변수로 한 CFRP 이중외팔보 시험편을 설계하여 정적 파괴 해석을 수행하였다. 본 연구를 위하여 설계된 CFRP 이중외팔보 시험편들의 적층각도들은 각각 $30^{\circ}$$45^{\circ}$, $60^{\circ}$이며, 연구 결과로서는 적층 각도 $45^{\circ}$인 시험편이 가장 $30^{\circ}$, $60^{\circ}$의 적층 각도를 가진 시험편들보다 더 좋은 내구성을 보였으며, $30^{\circ}$의 적층 각도를 가진 시험편이 모든 시험편 중에서 내구성이 가장 취약한 것을 확인할 수 있었다. 이와 같은 본 연구 결과를 통하여 적층 각도 별 CFRP 접착구조물의 파손데이터를 확보할 수 있었으며, 본 연구결과를 토대로 얻은 접착 계면의 파손데이터를 활용함으로서 실생활에서의 기계나 구조물에 융합하여 그 미적 감각을 나타낼 수 있다.

Polybenzimidazole (PBI) Coated CFRP Composite as a Front Bumper Shield for Hypervelocity Impact Resistance in Low Earth Orbit (LEO) Environment

  • Kumar, Sarath Kumar Sathish;Ankem, Venkat Akhil;Kim, YunHo;Choi, Chunghyeon;Kim, Chun-Gon
    • Composites Research
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    • 제31권3호
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    • pp.83-87
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    • 2018
  • An object in the Low Earth Orbit (LEO) is affected by many environmental conditions unlike earth's surface such as, Atomic oxygen (AO), Ultraviolet Radiation (UV), thermal cycling, High Vacuum and Micrometeoroids and Orbital Debris (MMOD) impacts. The effect of all these parameters have to be carefully considered when designing a space structure, as it could be very critical for a space mission. Polybenzimidazole (PBI) is a high performance thermoplastic polymer that could be a suitable material for space missions because of its excellent resistance to these environmental factors. A thin coating of PBI polymer on the carbon epoxy composite laminate (referred as CFRP) was found to improve the energy absorption capability of the laminate in event of a hypervelocity impact. However, the overall efficiency of the shield also depends on other factors like placement and orientation of the laminates, standoff distances and the number of shielding layers. This paper studies the effectiveness of using a PBI coating on the front bumper in a multi-shock shield design for enhanced hypervelocity impact resistance. A thin PBI coating of 43 micron was observed to improve the shielding efficiency of the CFRP laminate by 22.06% when exposed to LEO environment conditions in a simulation chamber. To study the effectiveness of PBI coating in a hypervelocity impact situation, experiments were conducted on the CFRP and the PBI coated CFRP laminates with projectile velocities between 2.2 to 3.2 km/s. It was observed that the mass loss of the CFRP laminates decreased 7% when coated by a thin layer of PBI. However, the study of mass loss and damage area on a witness plate showed CFRP case to have better shielding efficiency than PBI coated CFRP laminate case. Therefore, it is recommended that PBI coating on the front bumper is not so effective in improving the overall hypervelocity impact resistance of the space structure.

외부긴장 보강을 위한 CFRP 판의 정착부 거동 실험 (Experimental Study on the Behaviore of Anchorage for Externally Prestressed CFRP Laminate)

  • 유영준;박종섭;박영환;정우태;강재윤
    • 한국콘크리트학회:학술대회논문집
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    • 한국콘크리트학회 2004년도 추계 학술발표회 제16권2호
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    • pp.17-20
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    • 2004
  • FRP strengthening system that bonds FRP sheet or laminate underneath structure has been used popularly thesedays. The failure of this bonding system occurs mainly at the interface of bonded surface abruptly. So it is difficult to expect the failure and FRP can't show its full material capacity that makes it uneconomically. By that reason, KICT proposed a system to install FRP aminate to structure for strengthening not by bondging but by unbonding. It is to install both ends of FRP laminate by anchoring underneath structure without bonding. Then, the failure is not an interfacial problem any more, it is governed by mechanical anchoring. This paper includes an experimental study about anchoring system for prestressing CFRP laminate.

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