• 한국정밀공학회지
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• 제28권2호
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• pp.185-192
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• 2011

This study deals with a basic proposal to prove the safety for the exhausted fittings of the hydrogen fuel cell vehicle. First, this study was approached to numerical analysis solving to close the exact boundary condition (Axial, Bending, Lateral) and the second, this study produced the Lateral movement equipment for the vibration. For the numerical analysis, This study was considered with the exact solution of Lateral movement and the resonance effect for durability sample according to fitting positions. The second, This study was made for special equipment for displacement/gas leak and the frequency because the domestic samples were comparing with foreign fitting and foreign fitting for the hydrogen fuel cell vehicle. The result of this study was satisfied with domestic fittings for the basic reference but it need more test because of other situation for hydrogen fuel cell vehicle.

• 한국음향학회지
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• 제39권6호
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• pp.568-575
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• 2020

초음파는 다양한 산업 분야에서 널리 사용이 되고 있다. 그 중에 도전적인 분야로 전자부품의 냉각이 있다. 초음파 냉각 기술은 작동 유체로, 기존의 지구온난화를 유발하는 프레온 가스 대신에 Ar(아르곤), N₂(질소) 등의 기체로 대체가 가능하다. 또한 움직이는 부품이 없어 높은 내구성을 가질 수 있다. 그러므로 이러한 환경 문제와 내구성 관점에서 초음파 냉각 장치의 개발이 필요하다. 본 논문에서는 설계와 제작 공정에 대하여 설명하고 있다. 이 시스템을 설계할 때, 냉각기 시제품을 이용하여 유효성 테스트를 수행하였다. 이 결과를 바탕으로, ANSYS 프로그램을 사용한 유한요소해석을 수행하였다. 반공진 주파수는 34.8 kHz로 예측이 되었으며, 이는 실험치인 34.6 kHz과 0.6 %의 오차로 잘 일치하였다. 또한 초음파 웨이브가이드의 반공진 주파수는 39.4 kHz로 예측이 되었고, 역시 실험치인 39.8 kHz과 1.0 %의 오차로 잘 일치함을 알 수 있었다. 이러한 결과를 바탕으로 볼 때, 개발된 초음파 웨이브가이드는 마이크로칩의 냉각에 활용 될 수 있을 것으로 보인다.

• 한국기계가공학회지
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• 제11권3호
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• pp.122-129
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• 2012

This study investigates structural and vibration analyses according to the thickness of bicycle frame tube. The model of bicycle frame has the dimension as length of 862mm, width of 100mm and hight of 402.5mm. There are 3 kinds of models with tubes of top, down and seat at bicycle frame as thicknesses of 10, 15 and 20mm. The maximum displacement and stress occur at the center part of seat stay and at the installation part of rear wheel respectively. Maximum displacements become 0.031936, 0.029159 and 0.027984mm in cases of thicknesses of 10, 15 and 20mm respectively. In case of thickness of 20mm among 3 cases, maximum displacement becomes lowest. But maximum stresses become 10.019, 8.5492 and 9.2511MPa in cases of thicknesses of 10, 15 and 20mm respectively. In case of thickness of 15mm among 3 cases, maximum stress becomes lowest. There is no resonance at practical driving conditions and natural frequency remains almost unchanged along the change of thickness. In case of the displacement due to vibration mode, the displacement difference at thickness between 15mm and 20mm becomes 1/2 times than that between 10mm and 15mm. Design at bicycle frame tube becomes most economical and durable effectively in case of thickness of 15mm among 3 cases.

• 한국소음진동공학회논문집
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• 제24권3호
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• pp.219-226
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• 2014

A bus duct system for wind tower is introduced. A marine cable has been widely used in wind tower or various offshore structures. However, as the electric load capacity is increases, large number of cable lines must be used to cover the huge amount of electric capacities. Therefore, the installation of the cable lines becomes very difficult due to the heavy weight and volume of the cables. On the other hand, by using a single bus duct system line, the power capacity amount of 16 cables can be delivered with significantly compacted form. However, unlike flexible cables, the bus duct is relatively stiff which could generate the resonance phenomenon in the operating condition of the wind tower. In this study, the vibration characteristics of the bus duct are investigated and its long-term reliability during the life time of the wind tower is verified.

• 한국기계가공학회지
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• 제10권6호
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• pp.63-69
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• 2011

This study analyzes stress, fatigue and vibration on main rotor and body of helicopter. The maximum stress is shown on adjoint part between body and main rotor at the lower position of main rotor. As the maximum displacement amplitude is happened at 4000Hz, there is no resonance and the state of helicopter becomes safe at hovering without the abnormal air current and the disabled rotor. Among the cases of nonuniform fatigue loads, 'SAE bracket history' with the severest change of load becomes most unstable but 'Sample history' becomes most stable. In case of 'Sample History' with the average stress of 0MPa to $-10^5MPa$ and the amplitude stress of 0MPa to $8.539{\times}10^5MPa$, the possibility of maximum damage becomes 3%. This stress state can be shown with 5 times more than the damage possibility of 'SAE bracket history' or 'SAE transmission'. The structural result of this study by using the analysis of vibration and fatigue can be effectively utilized for safe and durable design of helicopter.