• 대한전기학회:학술대회논문집
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• 대한전기학회 2002년도 하계학술대회 논문집 B
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• pp.729-731
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• 2002

This paper deals with 2D and 3D analyses by finite element method for the characteristics of reluctance type transverse flux linear motor. Although 3D analysis is essential because of the characteristics by flux direction. 2D analyses are also used by considering the effective axial length and using the equivalent reluctance 2D model. The thrust, the normal force and the coenergy of the machine are calculated and compared by the results of the three analysis methods.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.788-793
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• 2001

Test experience with a micro-turbine jet engine is introduced. The engine provides us with valuable opportunities to experience know-hows essential for engine development. It consists of a single radial compressor and a single stage turbine. Engine starting procedure has been established after many trials and errors. Static and dynamic engine performance tests were conducted. Static performance was found to be inferior to that advertised by the manufacturer. Further improvement is needed. Dynamic performance revealed that engine thrust overshoots unfavorably for the purpose of UAV control.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 춘계학술대회논문집
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• pp.876-880
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• 2000

Vibration problem of deckhouse structure in a container vessel was investigated through the analysis and measurement. The natural frequency of deckhouse structure was found to be resonant with main engine 4th order excitations in the operating range, major sources of which were main engine inertial moment and axial thrust of the propulsion shafting system. To investigate and solve the problem, exciter test was performed to identify the vibration chracteristics of the ship structure and mechanical balancer was installed to compensate the 4th order inertial moment. Measurement results under the conditions with and without balancer operating were compared and analyzed to confirm the balancer effect. Good coincidence was found between the measurement and analysis results, which made it possible to predict the vibration problem in the earlier design stage.

• 한국군사과학기술학회지
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• 제3권2호
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• pp.23-34
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• 2000

Three dimensional, compressible, mass weighted averaging of Favre, Navier-Stokes system with k-$\varepsilon$ turbulence, is numerically discretized to compute three dimensional multiple jet interaction flow fields for a hybrid projectile containing three rocket motors in the ogive section. Numerical flow field computations have been made for angled nose jets and rockets at supersonic speed using multiblock structured grid. The jet conditions include very high jet to free stream pressure ratio and high temperature. It is shown that the strength of nozzle stagnation pressure affects the flow field near the side nozzle and the high stagnation pressure increases total amount of drag by a few percent. However, minor drag loss due to the pressure drag might be fully overcomed by an additional axial thrust. The results of present study can be applied for the design of future hybrid projectile.

• 융복합기술연구소 논문집
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• 제7권2호
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• pp.1-5
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• 2017

The rotating electrodynamic wheel over a conductive plate produces thrust force as well as normal force. Specially, separating the conductive plate and spacing apart each part, the lateral stability of the rotating wheel is guaranteed due to the restoring force into neutral position. In this paper, the force characteristics of the electrodynamic wheel rotating over the conductive plate is analyzed using the finite element tool. First, the dominant parameters are identified considering the geometric configuration and the operating condition. And the sensitivity for the parameter deviation is quantified for the high force density. The above topology can be applied as an actuating principle for inter-city train as well as contact-free transfer device.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.644-648
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• 2004

In the present study were examined numerically and experimentally the off-design performance characteristics on an axisymmetric plug nozzle with variable throat area. In this nozzle concept, its throat area can be changed by translating the plug into the axial direction. First, a mixed-expansion plug nozzle, in which two expansion parts are arranged both inside and outside, was designed by means of the method of characteristics. Second, the CFD analysis was verified by the cold-flow wind tunnel test. Third, its performance characteristics were evaluated over a wide range of pressure ratio from half to double throat area through the design point, using the CFD code verified by the wind tunnel tests. It was made clear from the study that not so critical thrust efficiency losses were found and the maximum thrust efficiency loss was at most approximately 5 % under off-design conditions without external flow. This result shows that a plug nozzle can give the altitude compensation even under off-design geometry operations. However, shock waves were observed in the inner expansion part under the doubled throat area operation and thus some thermal problems may be caused on the plug surface. Furthermore, collapse of cell structure on the plug surface was observed with external flow (around Mach number 2.0) as it became lower pressure ratio below the design point and the fact may result in big efficiency loss regardless of geometrical configuration.

• 동력기계공학회지
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• 제6권1호
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• pp.20-26
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• 2002

The purpose of this study is preventing the stick, scuffing, scratch between piston and cylinder in advance, and obtaining data for duration test in actual engine operation. The temperature gradient in cylinder bore according to coolant temperature were measured using $1.5{\ell}$ class diesel engine. 20 thermocouples were installed 2mm deep inside from cylinder wall near top ring of piston in cylinder block, at which points major thermal loads exist. It is suggested as proper measurement points for engine design by industrial engineers. Under full load and $70^{\circ}$, $80^{\circ}C$ and $90^{\circ}C$ coolant temperature conditions, the temperature in cylinder block and engine oil increased gradually according to the increase of coolant temperature, the siamese side temperature of top dead center is $142^{\circ}C$ in peripheral distribution, that is about $20^{\circ}C$ higher than that at thrust, anti-thrust, and rear side temperature, respectively. The maximum pressure of combustion gas in $70^{\circ}C$ coolant temperature is about 2 bar lower than those of $80^{\circ}C$ and $90^{\circ}C$ coolant temperature. The engine torque in $80^{\circ}C$, $90^{\circ}C$ coolant temperature condition is about 4.9Nm higher than that of $70^{\circ}C$ coolant temperature.

• 한국항공우주학회지
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• 제50권1호
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• pp.1-12
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• 2022

소형무인기의 틸팅방식 추진장치로 소형덕티드팬을 적용하였을 때 나타나는 공력특성을 분석하기 위해 직경 104mm 전기추진 덕티드팬의 공력특성을 풍동시험을 통해 살펴보았다. 소형무인기 운영조건에서 나타나는 현상을 살펴보기 위해 OPPAV 축소시제기의 제자리비행, 전진비행 및 천이비행 조건을 시험조건으로 채택하였으며, 6분력 발란스를 사용하여 덕티드팬의 추력 및 측력, 토크를 측정하였다. 비행체 주날개 및 꼬리날개에 영향을 미칠 수 있는 팬 후류를 파악하기 위해 5공 프로브를 사용하여 덕트 후방 250mm 단면의 3차원 속도벡터를 측정하였다. 제자리비행 및 전진비행 조건에서 덕티드팬의 추력 및 토크 특성을 파악하였으며, OPPAV 축소시제기에 적용하기 위한 조건을 도출하였다. 천이비행 조건에서 틸트각 40° 이하에서는 각도가 변하여도 추력이 유지되는 특성을 보이고 있으며 그 이후 각에서는 점차 증가하는 경향이 나타났다. 측력은 틸트각 75°까지 지속적으로 증가하는 경향이 나타났다. 제자리비행 및 전진비행 조건에서 60m/s 수준의 축방향 속도성분과 12m/s 수준의 원주방향 속도성분이 측정되었다. 틸트각이 증가함에 따라 축방향 속도 최대값 위치가 회전중심선을 벗어나는 경향이 나타나고 있으며, 단면 와류 중심도 유사한 위치로 이동하는 경향이 나타나고 있다.

• Tribology and Lubricants
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• 제28권1호
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• pp.12-18
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• 2012

This application study of a swash-plate type axial piston pump was concerned about the lubrication characteristics between cylinder barrel and valve plate which are the main rotating body and its opposite sliding part respectively. A computer simulation was implemented to assess bearing and sealing functions of the fluid film between cylinder barrel and valve plate. A numerical algorithm was developed to facilitate simultaneous calculations of dynamic cylinder pressure, 3 degree-of-freedom barrel motions considering inertia effect, and fluid film pressure assuming full fluid film lubrication regime. Central clearance, tilt angle, and azimuth angle of the rotating body were calculated for each time step. Surface waviness was found to be an influential factor due to the small fluid film thickness which can appear in flat land bearings. Five surface lays which can form on the lubrication surface in accordance with machining process were defined and analyzed using the simulation tool. Oil leakage flow and frictional torque in the fluid film between cylinder barrel and valve plate were also calculated to discuss in the viewpoint of energy loss. The simulation results showed that in actual sliding conditions proper surface non-flatness can make a positive effect on the energy efficiency and reliability of the thrust bearing.

• 항공우주기술
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• 제6권2호
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• pp.205-210
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• 2007

75톤급 액체 로켓 엔진용 터보펌프의 산화제펌프에 대한 로터다이나믹 설계를 수행하였다. 인듀서와 임펠러 및 베어링의 축배치는 항우연에서 개발 중인 유사한 구조를 가지는 터보펌프를 근간으로 하였고, 75톤급 산화제펌프 수력 설계에 맞추어 인류서, 임펠러의 축길이가 반영되었다. 후방 베어링으로부터 임펠러까지의 거리를 베어링 하중 설계에 대한 설계 변수로 고려하였고, 전방 베어링과 후방 베어링의 강성을 변화시키면서 회전 속도에 따른 비동기 고유진동수 해석을 수행하여 산화제 펌프의 임계속도를 고찰하였다. 베어링에 적절한 하중이 부과된다면 산화제 펌프의 임계속도는 기준속도 11,000 rpm과 비교하여 충분히 높기에, sub-critical 로터로서 기준속도 이내에서 안정적인 터보펌프의 운용이 가능하리라 판단된다.