• 한국추진공학회지
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• 제14권3호
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• pp.9-15
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• 2010

과팽창 로켓노즐에서 발생하는 충격파 박리패턴의 천이 유동장을 예측하기 위해 축대칭 수치해석적연구를 수행하였다. 비정상, 압축성 N-S 방정식에 k-$\omega$ SST 난류모델을 적용하여, 유한 체적법으로 계산하였다. 종래의 실험적 연구 결과와 비교하였으며, 계산된 결과와 정성적으로 잘 일치하였다. 본 연구의 결과로부터 RSS에서 FSS로 천이할 때 가장 큰 횡력이 발생하며, 이는 비점성 제트 코어 영역에서 발생하는 Vortex ring의 발달로 기인됨을 예측하였다. 또한 엔진 시동과정과 정지과정에서 발생하는 히스테리시스 현상을 잘 모사하였다.

• Tribology and Lubricants
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• 제22권1호
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• pp.20-25
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• 2006

The stress behavior analysis of a-rings and packing for a LPG filling unit has been presented using a finite element analysis technique by non-linear MSC/MARC program. The sealing performance and endurance of a-rings and packing are affected by working conditions such as filling pressure, friction coefficient, compression ratio, and material properties. The elastomeric polymers of O-rings and packing are nitrile butadiene rubber (NBR) and polytetrafluoroethylene (PTFE), which are selected as proper materials of a-rings and packing based on the stress analysis results. The calculated FEM results showed that the proper material of O-ring is NBR as a secondary sealing component and the recommended material of packing is PTFE as a primary sealing unit during a LPG filling process.

• 한국전기전자재료학회논문지
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• 제20권10호
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• pp.869-872
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• 2007

In this study, in order to develop low temperature sintering ultrasonic nozzle, single-layer and multilayer ring-type piezoelectric actuators were manufactured using PMN-PNN-PZT ceramics, And then the electrical properties were investigated. A ring-type piezoelectric actuator was modeled by ATILA program using finite element method(FEM). The piezoelectric actuator dimension was $\Phi26.5$ (outer diameter), $\Phi12$ (inner diameter), 3.5 mm (thickness). By FEM analysis, resonant and anti-resonant frequencies were appeared as 56.7 kHz and 61.5 kHz. The displacement increased with the increases of the number of layer. Based on the result, ring-type multilayer piezoelectric actuators were manufactured at low co-firing temperature of $940^{\circ}C$. The resonant resistance decreased with the increases of the number of layer. And also, the capacitance increased with the increases of the number of layer. The mechanical quality factor (Qm) decreased with the increases of the number of layer.

• 대한기계학회논문집 C: 기술과 교육
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• 제1권2호
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• pp.187-192
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• 2013

노즐을 이용한 인쇄 기법은 주로 전자 소자의 봉지를 위한 접착제의 인쇄분야에 적용되어 왔다. 노즐 인쇄를 통한 기능성 물질의 필름 형성은 커다란 도전이 될 수 있다. 본 논문에서는 노즐을 이용한 유기 잉크의 인쇄 특성을 실험을 통하여 알아보았다. 본 연구의 노즐 인쇄 실험에서 패턴을 형성하기 위한 잉크는 유기 발광 물질인 TAPC를 사용하였다. 인쇄된 패턴 폭은 잉크 공급 유량의 증가와 기판의 온도의 상승에 따라 증가하였다. 또한 인쇄된 패턴은 건조 후 커피링 형상을 나타내었다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2014년도 제49회 KOSCO SYMPOSIUM 초록집
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• pp.339-342
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• 2014

Rotary kiln produces lime from limestone through thermal decomposition. Ring formation in kiln internal wall is known issue that decreases productivity. The cause of ring formation is temperature imbalance as flame leans toward upper wall. Therefore, burner nozzle geometry was changed to improve air-fuel mixing state which leads to prevention of ring formation. CFD simulation and experimental test were performed in this study to investigate the effect of air-fuel mixing on flame structure, temperature and $NO_X$ concentration. It is shown that combustion efficiency has been enhanced and $NO_X$ concentration has been decreased by using swirl flow for secondary combustion air. It's also shown that flame has been straightened by using straight flow for secondary combustion air.

• 한국유체기계학회 논문집
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• 제18권5호
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• pp.49-53
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• 2015

Thrust vector control is the method which generates the side force and roll moment by controlling exhausted gas directly in a rocket nozzle. TVC is classified by mechanical and fluid dynamic methods. Mechanical methods can change the flow direction by several objects installed in a rocket nozzle exhaust such as tapered ramp tabs and jet vane. Fluid dynamic methods control the flight direction with the injection of secondary gaseous flows into the rocket nozzle. The tapered ramp tabs of mechanical methods are used in this paper. They installed at the rear in the rocket nozzle could be freely moved along axial and radial direction on the mounting ring to provide the mass flow rate which is injected from the rocket nozzle. TVC of the tapered ramp tabs has the potential to produce both large axial thrust and high lateral force. We have conducted the experimental research and flow analysis of ramp tabs to show the performance and the structural integrity of the TVC. The experiments are carried out with the supersonic cold flow system and the schlieren graph. This paper provides to analyze the location of normal shock wave and distribution of surface pressure on the region enclosed by the tapered ramp tabs.

• 한국정보디스플레이학회:학술대회논문집
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• 한국정보디스플레이학회 2006년도 6th International Meeting on Information Display
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• pp.655-659
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• 2006

This paper presents a novel electrostatic drop-on-demand inkjet device featured by a MEMS fabricated pole-type and hole-type nozzle with tube shaped orifice and investigates the feasibility of applying the inkjet device to display fabrication process. The electric voltage signal applied to the ring shaped upper electrode plate, against the hole-shaped ground or pole-shaped ground, referred here pole-type and hole-type nozzle respectively, allows ejection of small droplet to take place: That is, a tiny droplet is taken away from the peak of the mountain shaped liquid meniscus formed at the nozzle orifice. It is verified experimentally that the use of the pole type nozzle allows a stable and sustainable micro-dripping mode of droplet ejection for a wider range of applied voltages and of liquid viscosities. This demonstrates a feasibility of electrostatic drop-on-demand inkjet device as a disruptive alternative to conventional print heads such as thermal bubble or piezoelectric inkjet heads.

• 한국자동차공학회논문집
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• 제14권1호
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• pp.138-143
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• 2006

Modification of injector, oil ring tension reduction and oil pump rotor re-matching with optimization of relevant engine control parameters could drive fuel consumption reduction of HSDI diesel engine. A 5 holes injector was replaced with a 6 holes with smaller nozzle hole diameter and 1.5 k factor, and evaluated in a view of fuel economy and emission trade-offs. With introducing smaller nozzle hole diameter injector, PM(Particulate Matter) was drastically decreased for low engine load and low engine rpm. Modification of oil pump and oil ring was to reduce mechanical friction and be proved to better fuel economy. Optimization of engine operating conditions was a great help for the low fuel consumption. Influence of the engine operating parameters· including pilot quantity, pilot interval, air mass and main injection timing on fuel economy, smoke and NOx has been evaluated with 14 points extracted from NEDC(New European Driving Cycle) cycle. The fuel consumption was proved to $7\%$ improvement on an engine bench and $3.7\%$ with a vehicle.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2007년도 하계학술대회 논문집 Vol.8
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• pp.254-256
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• 2007

In this study, in order to develop low temperature sintering ceramic ultrasonic nozzle, single-layer and multilayer ring-type piezoelectric vibrators were manufactured using PMN-PNN-PZT ceramics, And then the electrical properties were investigated. The piezoelectric vibrator were sintered at low temperature of $940^{\circ}C$. The resonant resistance decreased with the increases of the number of layer. And also, the capacitance increased with the increases of the number of layer. The mechanical quality factor (Qm) decreased with the increases of the number of layer.

• 한국유체기계학회 논문집
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• 제10권6호
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• pp.32-37
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• 2007

Aerodynamic forces and moments have been used to control rocket propelled vehicles. If control is required at very low speed, Those systems only provide a limited capability because aerodynamic control force is proportional to the air density and low dynamic pressure. But thrust vector control(TVC) can overcome the disadvantages. TVC is the method which generates the side force and roll moment by controlling exhausted gas directly in a rocket nozzle. TVC is classified by mechanical and fluid dynamic methods. Mechanical methods can change the flow direction by several objects installed in a rocket nozzle exhaust such as tapered ramp tabs and jet vane. Fluid dynamic methods control the flight direction with the injection of secondary gaseous flows into the rocket nozzle. The tapered ramp tabs of mechanical methods are used in this paper. They installed at the rear in the rocket nozzle could be freely moved along axial and radial direction on the mounting ring to provide the mass flow rate which is injected from the rocket nozzle. In this paper, the conceptual design and the study on the tapered ramp tabs of the thurst vector control has been carried out using the supersonic cold flow system and schlieren system. This paper provides the thrust spoilage, three directional forces and moments and distribution of surface pressure on the region enclosed by the tapered ramp tabs.