In order to use PUR/CuO Composites as the sealing materials for ships equipment, this research has been performed. PUR/CuO composites are produced by using ultrasonic waves. The increase of CuO leads to increase in the tensile strength and shore hardness. The cumulative wear volume shows a tendency to increase in proportional to sliding distance. As the CuO particles of these composites indicated, the friction coefficient was slightly increased. The major failure mechanisms were lapping layers, deformation of matrix, plowing, debonding of particles and microcracking by scanning electric microscopy photograph of the wear tested surface.

In this study, the effect of temperature effect of the rubber matrix filled with nano sized silica particles composites with silica volume fraction of 19–25% was investigated by the Charpy impact test. The Charpy impact test was conducted in the temperature range from –40°C to 0°C. The critical energy release rate GIC of the rubber matrix composites filled with nano sized silica particles was considerably affected by temperature and it was shown that the maximum value was appeared at higher temperature between temperature tested and it was shown that the value of GIC increases as temperature tested increases. The major fracture mechanisms were matrix deformation, silica particle debonding and delamination, microcrack between particles and matrix, and/or pull out between particles and matrix which is ascertained by SEM photographs of Charpy impact surfaces fracture.

The present study is undertaken to evaluate the effect of volume fraction on the results of Charpy impact test for the rubber matrix filled with nano sized silica particles composites. The Charpy impact tests are conducted in the temperature range 0°C and –10°C. The range of volume fraction of silica particles tested are between 11% to 25%. The critical energy release rate GIC of the rubber matrix composites filled with nano sized silica particles is affected by silica volume fraction and it is shown that the value of GIC decreases as volume fraction increases. In regions close to the initial crack tip, fracture processes such as matrix deformation, silica particle debonding and delamination, and/or pull out between particles and matrix which is ascertained by SEM photographs of Charpy impact fracture surfaces.

The friction and wear characteristics of the rubber matrix composites filled with nano sized silica particles were investigated at ambient temperature by pin-on-disc friction test. The volume fraction of silica particles was 19%. The cumulative wear volume and wear rate of these materials on counterpart roughness were determined experimentally. The major failure mechanisms were lapping layers, deformation of matrix, ploughing, debonding of particles, fracture of particles and microcracking by scanning electric microscopy photograph of the tested surface. The cumulative wear volume showed a tendency to increase with increase of sliding distance. The wear rate of these composites tested indicated low value as increasing the sliding distance.

The characteristics of abrasive wear of the rubber matrix composites filled with nano sized silica particles were investigated at ambient temperature by pin-on-disc friction test. The range of volume fraction of silica particles tested are between 11% to 25%. The cumulative wear volume and friction coefficient of these materials on particle volume fraction were determined experimentally. The major failure mechanisms were lapping layers, deformation of matrix, ploughing, deboding of particles and microcracking by scanning electric microscopy photograph of the tested surface. The cumulative wear volume showed a tendency to increase nonlinear with increase of sliding distance. As increasing the silica particles of these composites indicated higher friction coefficient.

The characteristics of abrasive wear on sliding speed of glass fiber reinforcement (GF/PUR) composites were investigated at ambient temperature by pin-on-disc friction test. The cumulative wear volume, friction coefficient and surface roughness of these materials on sliding speed were determined experimentally. The major failure mechanisms were lapping layers, deformation of resin, ploughing, delamination, and cracking by scanning electric microscopy (SEM) photograph of the tested surface. As increasing the sliding speed the GF/PUR composites indicated higher friction coefficient. The surface roughness of the GF/PUR composites was increased as the sliding speed was higher in wear test.

The behavior of abrasive wear on counterpart roughness of glass fiber reinforcement polyurethane resin (GF/PUR) composites were investigated at ambient temperature by pin-on-disc friction test. The friction coefficient, cumulative wear volume and surface roughness of these materials against SiC abrasive paper were determined experimentally. The major failure mechanisms were lapping layers, ploughing, delamination, deformation of resin and cracking by scanning electric microscopy (SEM) photograph of the tested surface. As increasing the counterpart roughness the GF/PUR composites indicated higher friction coefficient. The surface roughness of the GF/PUR composites was increased as the sliding velocity was higher and the counterpart roughness was rougher in wear test.

The effect of load and sliding speed on abrasive wear characteristics of glass fiber/polyurethane (GF/PUR) composites were investigated at ambient temperature by pin-on-disc friction test. The friction coefficient, cumulative wear volume and surface roughness of these materials against SiC abrasive paper were determined experimentally. Experimental results showed that the surface roughness of the GF/PUR composites was increased as applied load was higher in wear test. The cumulative wear volume tended to increase nonlinearly with increase of sliding distance and depended on applied load and sliding speed for these composites. It could be verified by scanning electric microscopy (SEM) photograph of surface tested that major failure mechanisms were lapping layers, ploughing, delamination, deformation of resin and cracking.

The present study was undertaken to evaluate the effect of temperature on the results of Charpy impact test for glass fiber reinforced polyurethane(GF/PUR) composites. The Charpy impact test were conducted in the temperature range from -50˚ to 50˚. The impact fracture toughness of GF/PUR composites was considerably affected by temperature and it was shown that the maximum value was appeared at room temperature. It is believed that sensitivity of notch on impact fracture energy were increased with decrease in temperature of specimen. As the GF/PUR composites exposed in low temperature, impact fracture toughness of composites decreased gradually owing to the decrease of interface bonding strength caused by difference of thermal expansion coefficient between the glass fiber/polyurethane resin. And decrease of interface bonding strength of composites with decrease in specimen temperature was ascertained by SEM photographs of Charpy impact fracture surface.

Generally the side plate materials of FRP ship are composed of glass fiber and unsaturated polyester resin composites(GFRP composites). In this study, the effect of applied load and sliding speed on friction and wear characteristics of these materials were investigated at ambient temperature by pin-on-disc friction test. The cumulative wear volume, friction coefficient and wear rate of these materials for SiC abrasive paper were determined experimentally. The cumulative wear volume showed a tendency to increase nonlinearly with increase of sliding distance and was dependent on applied load and sliding speed for these composites. The friction coefficient of GFRP composites was increased as applied load increased at same sliding speed in wear test. It was verified by SEM photograph of worn surface that major failure mechanisms were microfracture, deformation of resin, cutting and cracking.

The main goal of this work is to study the effects of temperature and volume fraction of fiber on the Charpy impact test with GF/PP composites. The critical fracture energy and failure mechanisms of GF/PP composites are investigated in the temperature range of 60℃ to -50℃ by impact test. The critical fracture energy increased as the fiber volume fraction ratio increased. The critical fracture energy shows a maximum at ambient temperature and it tends to decreases as temperature goes up or goes down. Major failure mechanisms can be classified such as fiber matrix debonding, fiber pull-out and/or delamination and matrix deformation.

탄소 섬유강화 에폭시기지 복합재의 경면 가공한 스테인리스강 상대재와 마찰과 마모에 바탕을 둔 연구에서는 다음과 같은 결론을 얻었다. (1) 복합재의 비마모율은 하중이 증가하면 N방향와 P방향에서는 증가하는 경향을 보이며,AP방향에서는 감소한다. 이것은 마모 메카니즘의 영향으로 속도가 증가하면 마모 이착막의 생성이 빨라져 이착막 속의 탄소섬유가 윤활제의 역할을 하기 때문이다. (2) 복합재의 마찰계수는 하중이 증가하면 N방향과 AP방향에서는 하중 39.2N까지 증가하다가 그 이상의 하중에서는 감소되며 AP방향에서는 하중이 증가함에 따라 서서히 증가하며, 또한 그 값은 N방향에서 가장 크고, AP방향이 가장 적다. (3) 일방향 탄소섬유 강화 복합재의 마모 거동에 미치는 하중의 효과는 다르며 마찰초반에 발생한 섬유에 의한 쟁기질과 섬유 굽힘 및 미소크랙에 의한 섬유 균열과 파괴에 따른 마모 메카니즘의 형태에 의한 것이다.

탄소 섬유강화 에폭시기지 복합재의 경면 가공한 스테인레스 강 상대재와 마찰과 마모에 바탕을 둔 연구에서 다음과 같은 결론을 얻었다. (1) 일방향 탄소섬유 강화 복합재의 마모 거동에 미치는 미끄럼 방향의 효과는 다르며 작용하는 마모 메커니즘의 형태에 의존한다. (2) 상온에서 경면 가공한 스테인리스 스틸에 대하여 미끄럼이 일어나면 AP 방향에서 높은 마모 저항과 낮은 마찰계수가 관찰되었다. (3) 복합재의 비마모율은 미끄럼 속도가 증가하면 N방향과 P방향에서는 감소하는 경향을 보이며, AP 방향에서는 증가하다가 감소한다. 이것은 마모 메카니즘의 영향으로 속도가 증가하면 마모 이착막의 생성이 빨라져 이착막 속의 탄소섬유가 윤활제의 역할을 하기 때문이다. (4) 복합재의 마찰계수는 미끄럼 속도가 증가하면 3방향 모두 증가하다가 일정한 값에 수렴하면 N방향이 가장 크며, P방향과 AP방향 순이다. 이는 N방향에서 마찰초반에 발생한 섬유의 쟁기질에 의한 상대재 표면의 손상과 돌기변형에 따른 것이며, AP방향의 마찰계수가 가장 낮다.

하이브리드 복합재료(Hybrid composites) 의 층간 파괴 인성치에 영향을 주는 인자 중 적층순서, 하중점변위율, 초기크랙길이를 변화 시켰을 때의 실험 결과는 다음과 같다. (1) CF/CF, CF/GF. GF/GF로 적층하였을 경우 층간파괴인성치값은 서로 같은 계면을 성형한 것보다 서로 다른 계면을 적층한 CF/GF의 경우가 강도면에서 가장 높게 나타나는 것을 알 수 있었다. (2) 하중점변위율은 미세한 변동은 있었으나, 하중점변위율의 영향은 거의 받기 않는 것을 알 수 있었다. (3) 초기크랙을 변화시켰을 때, 초기크랙길이의 영향은 일정하지 않았다. CF/CF인 경우는 초기크랙이 짧은 경우, CF/GF. GF/GF인 경우는 초기크랙이 긴 경우에 높은 값을 나타났다. 이것은 GF 섬유가 직조형태의 프리프레그로 되어 있어 크랙의 진전에 따라 섬유부스러기 등의 생성에 따른 영향이라고 생각된다. (4) 적층순서에 따라 파면의 섬유 분포 형태가 달랐으며 CF/GF인 경우가 섬유의 파손형태가 가장 복잡하게 나타났으며, 이것이 높은 층간파괴인성치를 나타내는 원인이라고 판단된다.

The main goal of this work is to study the effect of glass fiber volume fraction on the result of tensile test with respect to glass fiber/polypropylene(GF/PP) composites. The tensile test and failure mechanisms of GF/PP composites were investigated in the fiber volume fraction range from 10% to 30%. The tensile strength and the fracture strength increased with the increasing of the fiber volume fraction in the tested range. Fiber pull-out and debonding of this composites increased with the fiber volume fraction in thc tested range. The major failure mechanisms were classified into the debonding, the fiber pull out, the delamination and the matrix deformation.

하이브리드 복합재료(Hybrid composite)의 모드 I 층간파괴인성치에 영영향 주는 인자 중 적층순서, 하중점변위율, 초기크랙길이를 변화 시켰을 때의 실험 결과는 다음과 같다. (1) CF/CF, CF/GF, GF/GF로 적층하였을 경우 층간파괴인성치값은 서로 같은 계면을 성형한 것보다 서로 다른 계면을 적층한 CF/GF 의 경우가 강도면에서 가장 높게 나타나는 것을 알 수 있다. (2) 하중점변위율을 0.2, 2, 20mm/min로 변화하였을 때, 미세한 변동은 있었으나, 허중점변위율의 영향은 거의 받지 않는 것을 알 수 있었다. (3) 초기크랙을 25, 30, 35, 40, 50mm로 변화시켰을 때 초기크랙길이의 영향은 일정하지 않았다. CF/CF인 경우는 초기크랙이 짧은 경우, CF/GF, GF/GF인 경우는 초기크랙이 긴 경우에 높은 값을 나타냈다. 이것은 GF 섬유가 직조형태의 프리프레그로 되어 있어 크랙의 진전에 따라 섬유부스러기 등의 생성에 따른 영향이라고 생각된다. (4) 적층순서에 따라 파면의 섬유 분포 형태가 달랐으며, CF/GF인 경우가 섬유의 파손형태가 가장 복잡하게 나타났으며, 이것이 높은 층간파괴인성치를 나타내는 원인이라고 판단된다.

Many of researches regarding mechanical properties of composite materials are associated with humid environment and temperature. Especially the temperature is a very important factor influencing the design of thermoplastic composites. However, the effect of temperature on impact behavior of reinforced composites have not yet been fully explored. An approach which predicts critical fracture toughness GIC was performed by the impact test in this work. The main goal of this work is to study the effect of temperature and span of specimen supports on the results of Charpy impact test for GF/PE composite. The critical fracture energy and failure mechanism of GF/PE composites were investigated in the temperature range of 60℃;to;-50℃ by the Charpy impact test. The critical fracture energy showed the maximum at the ambient temperature, and it tended to decrease as the temperature increased or decreased from the ambient temperature. The major failure mechanisms are the fiber matrix debonding, the fiber pull-out and/or delamination and the matrix deformation.n.

Thermosetting matrix composites have disadvantages in terms of moulding time, repairability and manufacturing cost. Thus the high-performance thermoplastic composites to eliminate such disadvantages have been developed so far. As a result of environmental and economical concerns, there is a growing interest in the use of thermoplastic composites. However, since their mechanical properties are very sensitive to the environment such as moisture, temperature etc., those behaviors need to be studied. Particularly the temperature is a very important factor influencing the mechanical behavior of thermoplastic composites. The effect of temperature have not yet been fully quantified. Since engineering applications of reinforced composites necessitate their fracture mechanic characterization, work is in progress to investigate the fracture and related failure behavior. An approach which predicts the tensile strength was perpormed in the tensile test. The main goal of this work is to study the effect of temperature on the result of tensile test with respect to GF/PE composite. The tensile strength and failure mechanisms of GF/PE composites were investigated in the temperature range 60℃ to -50℃. The tensile strength increased as the fiber volume fraction ratio increased. The tensile strength showed the maximum at -50℃, and it tended to decrease as the temperature increased from -50℃. The major failure mechanism was classified into the fiber matrix debonding, the fiber pull-out, the delamination and the matrix deformation.

장섬유 CF/에폭시 복합재료를 사용하여-50℃에서 60℃ 사이의 범위에서 스팬길이를 변화시켜 충격시험으로 얻어진 임계파괴에너지의 거동을 고찰한 결과는 다음과 같다. 1. CF/에폭시 복합재료의 온도 변화에 따른 임계파괴에너지 GIC는 동일한 스팬길에서는 실온의 경우가 가장 높고, 60℃, -15℃ 그리고 -50℃의 순으로 낮게 나타났다. 2. CF/에폭시 복합재료의 스팬길이의 변화에 대한 임계 파괴에너지 GIC는 동일한 온도조건하에서는 스팬길이가 20mm인 경우가 가장 높게 나타났으나 불안정하며, 스팬길이는 40mm인 경우 임계파괴에너지 GIC는 가장 낮게 나타났으나 실험치의 흩어짐을 고려할 때 40mm인 경우의 시험편이 더 적절한 조건이라 생각된다. 3. 본 실험에 사용한 재료의 파괴기구는 섬유의 풀아웃, 섬유와 매트릭스 사이의 디본딩 그리고 매트릭스의 변형을 관찰할 수 있었으며, 이와 같은 파괴기가구 종합적으로 상호작용한다고 생각된다.