• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 1999년도 추계학술발표대회 논문집
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• pp.88-94
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• 1999

Recently, PTFE-polyimide composites are being used self-lubricating parts for industrial field. Thus, this study is mainly concerned with friction and wear properties for the piston ring of non-lubricating air compressor which made of PTFE-polyimide composites. The friction and wear test was carried out for the different composition ratio under the atmosphere room temperature and constant load of 7.69N and their friction and wear properties were compared with each other at various sliding speed. Notable results are summarized as follows. PTFE 100% showed that friction coefficient was almost same values at 0.94 and 1.88m/s but the value was decreased at 2.83m/s because the friction temperature is higher than low speed. PTFE 80%-PI 20% showed the lowest mean friction coefficient at 2.83m/s. PTFE 20%-PI 80% showed the highest friction coefficient at 0.94m/s and the value was decreased at high speed but the value is higher than other materials except PTFE 100 %. PI 100% showed the highest friction coefficient at 0.94 and 1.88m/s because adhesive wear mainly occurred that speed. PTFE 100% showed highest specific wear rate on the whole. Specific wear rate of PTFE 80%-PI 20% was almost the same value with PTFE 20%-PI 80%. PI 100% showed the lowest value at high sliding speed because the friction surface was thicken and carbonated by high friction temperature.

• 대한기계학회논문집A
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• 제20권3호
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• pp.753-764
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• 1996

The metal matrix composites(MMC) are currently receiving a great deal of attention. These composites possess exellent mechanical and physical properties such as modulus, strength, wear resistance and thermal stability, which make them very attractive for use in automotive piston. In this study, $Al/{Al_2}{O_3}$(15%) composites are fabricated by the squeeze casting method. Mechanical properties such as tensile strength and ductility are performed at room and elevated temperature($250^{\circ}C$ and $350^{\circ}C$), respectively. Through thermomechanical analyser, thermal expansion coefficient of $Al/{Al_2}{O_3}$ composites are conducted for ranging from room temperature to ($400^{\circ}C$.And bending fatigue tests are also performed by the rotary bending machine at room temperature.The tensile strength and elastic modulus have been improved up to 38% and 35% by the addition of the reinforcements, respectively. Thermal expansion coefficients of MMCs which is located normal and parralel to the applied pressure are showed slightly different less than 10%. Fatigue strengh of the composite was improved by about 20% compared with that of unreinforced Al alloy. The results of this study will be used to understand the basic fracture behavior of MMCs and eventually to expand the applocation of MMCs as a machine parts undertaken various loadings.

• Structural Engineering and Mechanics
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• 제84권4호
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• pp.437-452
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• 2022

For the first time, the higher-order shear and normal deformable plate theory (HOSNDPT) is used for the vibration and flutter analyses of the multilayer functionally graded graphene platelets reinforced composite (FG-GPLRC) plates under supersonic airflow. For modeling the supersonic airflow, the linear piston theory is adopted. In HOSNDPT, Legendre polynomials are used to approximate the components of the displacement field in the thickness direction. So, all stress and strain components are encountered. Either uniform or three kinds of non-uniform distribution of graphene platelets (GPLs) into polymer matrix are considered. The Young modulus of the FG-GPLRC plate is estimated by the modified Halpin-Tsai model, while the Poisson ratio and mass density are determined by the rule of mixtures. The Hamilton's principle is used to obtain the governing equations of motion and the associated boundary conditions of the plate. For solving the plate's equations of motion, the Galerkin approach is applied. A comparison for the natural frequencies obtained based on the present investigation and those of three-dimensional elasticity theory shows a very good agreement. The flutter boundaries for FG-GPLRC plates based on HOSNDPT are described and the effects of GPL distribution patterns, the geometrical parameters and the weight fraction of GPLs on the flutter frequencies and flutter aerodynamic pressure of the plate are studied in detail. The obtained results show that by increasing 0.5% of GPLs into polymer matrix, the flutter aerodynamic pressure increases approximately 117%, 145%, 166% and 196% for FG-O, FG-A, UD and FG-X distribution patterns, respectively.

• Journal of Advanced Marine Engineering and Technology
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• 제24권1호
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• pp.67-74
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• 2000

Recently, PTFE-polymide composites are being used self-lubricating parts for industrial field. Thus, this study is mainly concerned with friction and wear properties for the piston ring of non-lubricating air compressor which made of PTFE-polymide composites. The friction and wear test was carried out for the different composition ratio under the atomsphere room temperature and constant load of 7.69N and their friction and wear properties were compared with each other at various sliding speed. notable results are summarized as follows. PTFE 100% showed that friction coefficient was almost same values at 0.94 and 1.88m/s but the value was decreased at 2.83m/s because the friction temperature is higher than low speed. PTFE 80%-PI 20% showed the lowest mean friction coefficient at 2.83m/s. PTFE 20-PI 80% showed the highest friction coefficient at 0.94m/s and the value was decreased at high speed but the value is higher than other materials except PTFE 100 %. PI 100% showed the highest friction coefficient at 0.94 and 1.88m/s becuase adhesive wear mainly occurred that speed. PTFE 100% showed highest specific wear rate on the whole. Specific wear rate of PTFE 80%-PI 20% was almost the same value with PTFE 20%-PI80%. PI 100%showed the lowest value at high sliding speed because the friction surface was thicken and carbonated by high friction temperature.

• Journal of Mechanical Science and Technology
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• 제16권1호
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• pp.1-12
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• 2002

In this study, a passive suppression scheme for nonlinear flutter problem of composite panel, which is believed to be more reliable than the active control methods in practical operations, is proposed. This scheme utilizes a piezoelectric inductor-resistor series shunt circuit. The finite element equations of motion for an electromechanically coupled system is derived by applying the Hamilton\\`s principle. The aerodynamic theory adopted for the present study is based on the quasi-steady piston theory, and von-barman nonlinear strain-displacement relation is also applied. The passive suppression results for nonlinear panel flutter are obtained in the time domain using the Newmark-$\beta$ method. To achieve the best damping effect, optimal shape and location of fille piezoceramic (PZT) patches are determined by using genetic algorithms. The effects of passive suppression are investigated by employing in turn one shunt circuit and two independent shunt circuits. Feasibility studies show that two independent inductor-resistor shunt circuits suppresses flutter more effectively than a single shunt circuit. The results clearly demonstrate that the passive damping scheme that uses piezoelectric shunt circuit can effectively attenuate the flutter.

• Restorative Dentistry and Endodontics
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• 제31권1호
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• pp.58-65
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• 2006

이번 실험의 목적은 이축 굴곡 강도 시험의 복합레진에서의 적용가능성을 위해 기존의 3점 굴곡 강도 시험과 이축 굴곡 강도 시험을 이용하여 치과용 광중합형 레진의 강도를 측정하고, 이를 Weibull modulus를 이용하여 상대적 신뢰도를 비교하는 것이다. 이번 실험에 사용된 재료는 $MICRONEW^{TM},\;RENEW^{(R)}$ (Bisco, Schaumburg, USA)의 두 가지 광중합형 수복 재료이다. 이축 굴곡 강도 측정에는 International Organization for Standardization (ISO) 6872 규정에 따라 piston-on-3-ball test를 사용하였으며 검사 시편은 직경이 각각 12 mm (지지원의 반지름 3.75 mm), 16 mm (지지원의 반지름 5 mm), 두께가 각각 0.5 mm, 1 mm, 2 mm인 여섯 개의 군으로 나누어 제작하였으며 각 군당 시편을 20개씩 제작하였다. $MICRONEW^{TM}$와 $RENEW^{(R)}$의 실험 결과, 이축 굴곡 강도가 3점 굴곡 강도보다 높은 평균값을 나타내었고 이축 굴곡 강도의 모든 군이 3점 굴곡 강도보다 높은 Weibull modulus 값을 보여, 이축 굴곡 강도 시험이 상대적으로 실험적 오차의 영향을 적게 받는 방법으로 신뢰 할 수 있었다. 또한 이축 굴곡 강도 시험에서 시편의 두께가 2 mm일 때 가장 높은 Weibull modulus를 나타내었으며 이축 굴곡 강도시험군 중, $MICRONEW^{TM}$의 두께 2 mm군에서는 지지원의 반지름에 따른 굴곡 강도의 통계학적 유의차이가 없었고 (p>0.05), 이를 제외한 모든 군에서 시편의 두께와 지지원의 반지름에 따른 굴곡 강도의 통계학적 유의차이가 있었다 (p<0.05). 위의 결과로 미루어 볼 때 두께 2 mm군에서 이축 굴곡 강도는 기존의 3점 굴곡 강도 시험보다 우수한 것으로 추천할 수 있는 방법이다.

• Composites Research
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• 제13권5호
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• pp.50-59
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• 2000

본 논문에서는 복합재료 패널 플러터를 억제할 수 있는 두 가지 방법에 대해서 연구하였다. 첫번째, 능동제어 방법에서는 선형 제어 이론을 바탕으로 제어기를 설계하였으며 제어입력이 작동기에 가해진다. 여기서 작동기로는 PZT를 사용하였다. 두 번째, 인덕터와 저항으로 구성되어진 션트회로를 사용하여 시스템의 감쇠를 증가시킴으로써 패널 플러터를 억제할 수 있는 새로운 방법인 수동감쇠기법에 대한 연구가 수행되었다. 이 수동감쇠기법은 능동적 제어보다 강건(robust)하며 커다란 전원 공급이 필요하지 않고 제어기나 감지 시스템과 같이 복잡한 주변 기기가 필요 없이도 실제 패널 플러터 억제에 쉽게 응용할 수 있는 장점을 가지고 있다. 최대의 작동력/감쇠 효과를 얻기 위해서 유전자 알고리듬을 사용하여 압전 세라믹의 형상과 위치를 결정하였다. 해밀턴 원리를 사용해서 지배 방정식을 유도하였으며, 기하학적 대변형을 고려하기 위해 von-Karman의 비선형 변형률-변위 관계식을 사용하였으며 공기력 이론으로는 준 정상 피스톤 1차 이론을 사용하였다. 4절점 4각형 평판 요소를 이용하여 이산화된 유한 요소 방정식을 유도하였다. 효율적인 플러터 억제를 위해 패널 플러터에 중요한 영향을 미치는 플러터 모드를 이용한 모드축약기법을 사용하였으며, 이를 통해 비선형 연계 모달 방정식이 얻어지게 된다. 능동적 제어 방법과 수동 감쇠 기법에 의해 수행되어진 플러터 억제 결과들을 Newmark 비선형 시분할 적분법을 통해 시간 영역에서 살펴 보았다.

• 한국주조공학회지
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• 제11권6호
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• pp.475-481
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• 1991

In this study the fabrication technology and mechanical properties of AC8A/$Al_2O_3$ Composites by squeeze casting process were investigated to develope for application as the piston materials that require good friction, wear resistance, and thermal stability. AC8A/$Al_2O_3$ composistes without a porosity and the break of preform were fabricated at the melt temperature of $740^{\circ}C$, the preform temperature of $500^{\circ}C$, and mold temperature of $400^{\circ}C$ under the applied pressure of $1200kg/cm^2$ as the results of the observation of microstructures. As the results of this study, the tensile strength of AC8A/$Al_2O_3$ composites was not increased linearly with $Al_2O_3$ volume fraction and so it seemed not to agree with the rule of mixture, which had been used often in metal matrix composite. Also the tensile strength after thermal fatigue test was little different from that before the test. Consequently it was thought that AC8A/$Al_2O_3$ composites fabricated under our experimental conditions had a good thermal stability and subsequently a good interface bonding. Wear rate(i.e., volume loss per unit sliding distance) of AC8A/$Al_2O_3$ composites was decreased with $Al_2O_3$ volume fraction and the sliding speed at both room temperature and $250^{\circ}C$ and so there was a good correlation between wear rate and hardness. Also the wear rate of AC/8A20% $Al_2O_3$ composities was obtained the value of $1.65cm^3/cm$ at sliding speed of 1.14m/sec as compared with about $3.0\;{\times}10^{-8}cm^3/cm$ hyereutectie Al-Si alloy(Al-16%Si-2%Cu-1%Fe-1%Ni), which applied presently for piston materials. The wear behavior of $Al_2O_3$ composites was observed to a type of abrasive wear by the SEM view of wear surface.

• 한국표면공학회지
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• 제31권1호
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• pp.12-23
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• 1998

The Thermal Barrier Coating(TBC) has been used to improve the heat barrier and tribological properties of the aircraft engine and the automobile engine in high temperature. Especially, the high temperature tribological propertied of the cylinder haed and the piston crown of diesel engine was emphasized. Therefore, the purpose of this work was to evaluate the microstructure, tribological propeer in high tempearmal shock resistance and bonding strength of five layer functionally gradient TBC for the applications. The five layerwere composed with 100% ceramic insulating later, 75(ceramic):25 (metal) layer, 50:50 layer, 25:75 layer and 100% metal bonding layer to redude the thermal stress. the YSL and MSL poweders were the insulation ceramics powers. The NiCrAly, Inconel625 and SUS powders were the bonding and mixingg powders for plasma spray process. According to the result of high temperature wear test, the wera resistance of YSZ/NiCrAlY siytem was most out standing at 600 and $800^{\circ}C$. At $400^{\circ}C$, the wear resistance of YSZ/Inconel system was better than others. Wear volume at other temperature because of the low temperature degration of zirconia. The thermal shock mechanism of 5 later is the vertical crack gegration in insulating layer. this means that the initial cracks were generated in the top layer, and then developed into the composite layers during thermal shock test. Finally, these cracks werereached to the interface of coating and substrate and also, these vertioal cracks join with the horizontal cracks of the each layers. The bonding strength of YSZ/NiCrAlY and YSZ/Inconel 5 layer system is better than other 5layer systems. The theramal shock resistance of thermal barrier coating s with 5 layer system is better than that of 3 layers and 2 layers.