• Journal of Advanced Marine Engineering and Technology
• /
• 제25권4호
• /
• pp.797-808
• /
• 2001

Three-dimensional trajectory of fluid particle is simulated by a particle motion, which is able to examine the influences of changes in the several parameters. To calculate the trajectory of a particle, the Runge-Kutta method was utilized. The use of a projectile of particles for the trajectory of liquid jet has been shown to be useful to estimate the influence of different operating parameters such as best particle diameter, density of liquid body, initial take-off velocity, wind velocity, cross wind velocity, take-off angle, and base angle for a released flow from the nozzle. The results give the trajectories of various types of particle of body and at different elevations, base angles, wind velocities and densities of liquid body. The trajectories in a vacuum show that air resistances decreases both the distance and the maximum height of a projectile, and also explain that the termination time is also reduced in air. In addition, the maximum distance in the x direction was obtained with take-off angles from 30 degrees to 45 degrees in still air and the projectile of particles was highly effected by wind and cross wind. Clearly, a particle has to be so positioned as to take the optimum possible advantage of the wind if the maximum distances is requested. The wind astern increased the maximum distances of x direction compared with the wind ahead. Finally, it is possible to optimize the design of pump by using these results.

• 반도체디스플레이기술학회지
• /
• 제10권2호
• /
• pp.73-81
• /
• 2011

We manufactured the inkjet printing system for the application into the nano Ag finger line interconnection process in Si solar cells. The home-made inkjet printer consists of motion part for XY motion stage with optical table, head part, power and control part in the rack box with pump, and ink supply part for the connection of pump-tube-sub ink tanknozzle. The ink jet printing system has been used to conduct the interconnection process of finger lines on Si solar cell. The nano ink includes the 50 nm-diameter. Ag nano particles and the viscosity is 14.4 cP at $22^{\circ}C$. After processing of inkjet printing on the finger lines of Si solar cell, the nano particles were measured by scanning electron microscope. After the heat treatment at $850^{\circ}C$, the finger lines showed the smooth surface morphology without micropores.

• 대한기계학회논문집B
• /
• 제32권1호
• /
• pp.47-53
• /
• 2008

The effect of periodic blowing and suction of upstream flow on the separated shear flow behind the vertical fence was experimentally investigated. The fence was submerged in the turbulent shear flow and DPIV method was used to measure the instantaneous velocity fields around the fence. Periodic blowing and suction flow was precisely generated by the syringe pump. Spanwise nozzle made 2D planar periodic jet flow in front of the fence and the effect of frequency and maximum jet velocity was studied. From the results, the reattachment length can be reduced by 60% of uncontrolled fence case under the control.

• 항공우주시스템공학회지
• /
• 제4권1호
• /
• pp.10-14
• /
• 2010

The Fuel system of T-50 Advanced Trainer is equipped with two boost pump and fuel flow proportioner for feeding fuel to turbo jet engine. when an unexpected failure occurs, they can feed the fuel to turbo jet engine which fuel quantity required. fuel quantity control method is applied for minimizing the center of gravity change. and fuel quantity control method is controlled by FQMS(Fuel Quantity Measuring System) and FFP(Fuel Flow Proportioner). This paper presents life cycle extension plans of FFP hydraulic motor by design improvements of connecting and arrangement of pipe comparing with KF-16.

• 한국컴퓨터정보학회:학술대회논문집
• /
• 한국컴퓨터정보학회 2023년도 제68차 하계학술대회논문집 31권2호
• /
• pp.105-106
• /
• 2023

소형제트엔진은 주로 연구, 실험, 교육 등의 목적으로 사용되고 있다. 이러한 소형제트엔진은 고도가 높고 고속으로 비행하는 드론에 추력 발생 장치로서의 중요한 역할을 수행할 수 있다. 그러나 엔진의 실질적인 활용을 위해서는 기존의 유선으로 구성된 컨트롤러를 무선으로 제어할 수 있는 방식으로 재구성하는 것이 필요하다. 이 중에서도 연료펌프의 무선제어시스템이 우선적으로 개발되어야만 다른 부분에 대한 무선제어개발이 가능해질 것이다. 본 논문에서는 소형 제트 엔진의 연료 펌프를 무선으로 제어할 수 있는 방식을 적용한 임베디드 시스템의 구성과 방식에 대해 제안하고 있다.

• 한국기계가공학회지
• /
• 제12권6호
• /
• pp.152-158
• /
• 2013

The purpose of this study is to investigate cooling performance of high power LEDs from 100 to 200 W class by using a jet impingement cooling module. The numerical analysis of forced convection cooling inside cooling module is carried out using a multi-purpose CFD software, FLUENT 6.3. In the experiments, the LED cooling system consists of jet impingement module, heat exchanger, water reservoir, and pump. In the present study, the cooling performance of jet impingement cooling module is investigated to determine the effect of the heat sink types on the impinging surface, the space and length of fins. Numerical and experimental studies show the reasonable agreement of LED metal PCB temperature between those results and give the optimized design parameters such as the space of fin and the length of fin. Also, the pin fin type of heat sink is found to be more efficient than the plate type heat sink in jet impingement cooling.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2005년도 제24회 춘계학술대회논문집
• /
• pp.233-236
• /
• 2005

본 논문에서는 현재 개발 중인 스마트 무인기 연료 시스템의 기본설계 결과를 제시하고 이에 대한 신뢰도 분석을 수행하였다. 시스템 요구를 바탕으로 연료 시스템을 구성한 후, 이에 필요한 부스트 펌프, 제트펌프, 도관, 벤트 시스템 등 각 구성품에 대한 설계를 수행하였고 연료 시스템의 중량 예측을 수행하였다. 이를 바탕으로 연료 시스템의 신뢰도를 분석하였다.

• 한국마린엔지니어링학회:학술대회논문집
• /
• 한국마린엔지니어링학회 2011년도 후기공동학술대회 논문집
• /
• pp.61-61
• /
• 2011

Cavitation phenomena during the injection process of the conventional fuel injection pump for a medium-speed diesel engine can cause surface damage with material removal or round-off on the plunger and barrel port and may shorten their expected life time. An experiment of flow visualization was carried out to investigate the main cause of these cavitation damages and find the prevention method. Experimental results of flow visualization show that these damages are mainly affected by fountain-like cavitation and jet-type cavitation generated before and after the end of fuel delivery process and therefore the prevention method was designed to control these cavitation flows. From the visualization and endurance test, it was proved that this method can effectively prevent cavitation damages by controlling cavitation flows.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2004년도 제23회 추계학술대회 논문집
• /
• pp.5-8
• /
• 2004

본 논문에서는 현재 개발 중인 스마트 무인기 연료 시스템의 기본설계 결과를 제시하였다. 시스템 요구를 바탕으로 연료 시스템을 구성한 후, 이에 필요한 부스트 펌프, 제트펌프, 도관, 벤트 시스템등 각 구성품에 대한 설계를 수행하였고 연료 시스템의 중량예측을 수행하였다.

• 한국추진공학회지
• /
• 제9권2호
• /
• pp.54-61
• /
• 2005

본 논문에서는 현재 개발 중인 스마트 무인기 연료 시스템의 기본설계 결과를 제시하고 이에 대한 신뢰도 분석을 수행하였다. 시스템 요구를 바탕으로 연료 시스템을 구성한 후, 이에 필요한 부스트펌프, 제트펌프, 도관, 벤트 시스템 등 각 구성품에 대한 설계를 수행하였고 참고 중량 데이터를 이용하여 연료 시스템의 중량예측을 수행하였다. 이를 바탕으로 연료 시스템의 신뢰도를 분석하여 신뢰도 목표를 만족함을 확인하였다.