• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2002.04a
• /
• pp.57-58
• /
• 2002

램제트는 다른 여러 추진시스템에 비하여 획기적으로 증가된 사거리를 가지므로 가용범위의 확대는 물론, 목표물 타격 시 높은 명중률과 낮은 격추율을 가지는 효과적인 추진 시스템이다. 램제트 엔진을 장착한 미사일로는 프랑스의 Griffon, ASMP, 미국의 Bomarc, Talos, 영국의 Bloodhound, Sea dart, 소련의 SA4, SA6 등을 비롯하여 많은 종류가 개발되어 실전 배치되었다. 근래 들어 램제트는 군사전략과 전술적인 목적 이외에도 민간용으로도 그 실용성이 강조되고 있어 그 중요성은 날로 더할 것으로 예측된다. 램제트는 일반적인 공기흡입식 엔진과는 달리 엔진 내부에 기계적으로 구동되는 부분이 없이 충격파를 통과하면서 공기의 압력이 높아지는 현상인 램압축 현상을 이용하여 공기를 압축하게 되므로 엔진의 구조가 간단하고, 상대적으로 높은 비추력과 추력/중량비를 가진다. 램제트는 정지 상태에서는 작동되지 않으며 사용 가능한 최소의 압력비를 줄 수 있는 비행 마하수에 도달해야 램제트가 작동하게 된다. 따라서 이러한 비행속도를 줄 수 있는 별도의 추진장치가 필요하게 되는데 이와 같은 보조 추진장치로 부스터를 사용한다. 부스터가 엔진의 내부에 장착된 램제트를 일제형 램제트 (IRR: integral Rocket Ramjet)라 부르며, 현대의 전략미사일과 민간용 초음속 항공기의 엔진에 도입되어 활발한 연구가 진행 중이다. 램압력을 이용하여 압축하므로 램제트의 설계시 설계점 비행 속도에서 전압력 손실이 최소가 되도록 설계되어야 하며, 이를 실험이나 수치해석을 통해 확인하여야 한다.

• 방재와보험
• /
• s.107
• /
• pp.38-44
• /
• 2005

기존 화재감지 기술이 점차적으로 발전되어 가고 있지만, 이러한 기존 기술과 다른 자동식 연기감지 방식이 혁신적으로 변화하고 있다. 이런한 혁신기술로 인하여 성장기의 화재를 감지하고 감지기에서 데이터를 분석하고, 화재와 관련된 데이터를 소방관계자에게 전송하는 방법이 계속 변화하고 있다. 기존 화재감지 방식의 예는 여러 가지 감열소자(열감지기), 광전식, 이온화식, 공기흡입형(연기감지기), 자외선.적외선(불꽃감지기)감지 방식이다. 감지기에서 데이터 분석의 형태로 연기농도를 표시하는 방법 등이 있다. 화재조건을 전송하는 방법은 특정한 구성요소(발신기, 감지기 등)의 위치(어드레스), LCD, CRT 그래픽 표시장치에서 많은 발전이 있었다. 이러한 혁신 기술은 화재경보 설비 판매시장, 설치방법, 기술기준의 변화에 많은 영향을 미치고 있다. 최근 개발된 디지털 비디오 연기감지 방식은 자동화재 감지 방식에 있어서 새롭고 급진적인 변화를 요구하고 있다.

• Proceedings of the KIEE Conference
• /
• 2007.04c
• /
• pp.124-125
• /
• 2007

본 연구에서는 Free-piston 엔진용 원통형 선형 발전기의 전동기 운전을 이용한 기동에 관한 연구를 수행하였다. Free-piston 엔진의 피스톤이 흡기, 압축, 폭발, 배기 과정에 따라 정상 상태로 왕복운동을 하기 위해서는 기동 시 정지상태인 피스톤을 외부의 힘으로 움직여 연소실에 있던 공기를 밀어내고, 연료를 연소실안에 흡입한 뒤 다시 압축시켜 플러그를 통해 폭발시켜 주어야 한다. 이 과정에서 별도의 전동기를 사용하는 대신 Free-piston 엔진에서 사용하는 원통형 선형 발전기를 전동기로 사용하여 엔진의 기동을 위해 요구되는 속도와 토크를 만족시키는지 동특성 해석을 하였고, free-piston 엔진을 기동시키기에 충분한 속도와 토크를 낼 수 있다는 결론을 얻었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.988-991
• /
• 2011

This study aims to analyze the effects of design parameters of the slotted cooling liner for air-breathing propulsion system. The three kinds of design parameters of the slotted cooling liner were selected and were investigated effect on the cooling performance of the slotted cooling liner. In this paper calculation results for inner wall temperature of cooling liner from heat transfer calculations were presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.642-647
• /
• 2010

Film cooling is used to protect thermally the inner wall of combustion chamber exposed to hot gas in air-breathing propulsion system and specially film cooling using slotted cooling liner has been investigated to improve the cooling characteristics for a long time. In this paper results from gas dynamic and heat transfer calculations were presented in the combustion area and cooling area of multi-slotted cooling liner.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.05a
• /
• pp.87-90
• /
• 2003

It has been well known that the major feature of compressible flow fields might be different depending on their formation processes. The objectives of the present study is to investigates the effect of jet development on the time history of supersonic jet flow field, accompanying nonequilibrium condensation. Especially, the behaviors of Mach disk diameter and location in a supersonic moist air jet are presented in terms of nozzle pressure ratio and initial relative humidity. The relative humidity of moist air is controlled at the nozzle supply, and the nozzle pressure ratio is varied to obtain the moderately underexpanded flows at the exit of the nozzle, installed in an indraft wind tunnel. It is found that at the same pressure ratio the Mach disk diameter increases with the initial relative humidity, while moves further upstream. Furthermore, the values of Mach disk diameter and location for increasing pressure ratio show larger than those for increasing.

• Journal of Navigation and Port Research
• /
• v.31 no.10
• /
• pp.845-852
• /
• 2007

An OWC-type Wave Energy Conversion passes through 3 steps energy conversion process. This paper deal with the impulse turbine with staggered blade to improved performance by numerical analysis using commercial CFD code, FLUENT Maximum value of axial airflow velocity during exhalation is higher than that during inhalation This paper deal with special-type of Impulse Turbine so-called "Staggered Blade" for more efficiency to making air flow direct to on pressure side. Also, this paper has proposed special-type turbine with self-pitched blade more efficient.

• Journal of the Korean Society of Radiology
• /
• v.10 no.7
• /
• pp.489-494
• /
• 2016

Nuclear reaction which occurs in the cyclotron generate unnecessary neutrons. The results of this happening can radioactivate surrounding materials and radioactive materials cause radiation exposure. When people take radioactive air, it makes internal exposure. The purpose of this study was to analyze the radioactive air inside of the ultra-compact 16.5 MeV cyclotron in operation. As a result of study, the radio activation occurred by compact cyclotron generates a very low internal exposure to workers. Comparing the radioactivity from radioactive nuclide with legal standard, that was under reference value. However, it could be at risk for internal exposure in case of higher energy cyclotron. Therefore, legal standard is needed for ventilation equipment of radiation facilities.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.19 no.11
• /
• pp.529-535
• /
• 2018

The range extender vehicle runs on a mechanism that allows the small power generation engine to start in the most efficient specific operating range to charge the battery and extend the mileage. In this study, we developed a step motor type intake air supply system that replaces existing throttle body system to develop a simple low cost control logic system. The system was applied to the existing base engine, and in order to improve the performance by increasing the amount of intake air, the effect of changing the length of the intake and exhaust manifold was experimentally examined. As a result, the Type B intake air control actuator operated by one step motor showed higher performance than the Type A in all the operation region, but the performance was lower than that of the base engine due to the increase of flow resistance. To improve this, it was confirmed that the engine performance was improved at both speeds of 2200rpm and 4300rpm when the 140mm adapter was installed in the intake manifold and when the newly designed 70mm exhaust manifold was applied. Through this process, high - precision operation control was realized by connecting the generator load to the optimized engine for the range extender electric vehicle. Experimental results showed that the speed change rate was within ${\pm}2.5%$ at 2200rpm in 1st stage and 4300rpm in 2nd stage and the speed follow-up result of 610 rpm/s was obtained when the speed was increased from 2200rpm to 4300rpm.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.11 no.5
• /
• pp.846-855
• /
• 1987

The experimental study was carried out to investigate the performance characteristics of the aero-valved pulsating combustor designed to increase the practical applications of the system. The geometric effect on the stable condition and the dynamic behavior of the system is identified. The equivalence ratio, the inflammability limit, the operating frequency, and thrust were also measured when the system oscillated stably. It is found that while the operating condition is sensitive to the diameter of the inlet pipe and the length of the tailpipe, the maximum value of the turn down ratio was obtained up to 3.2. The measured air flow rate shows that the equivalence ratio increases monotonously with the increasing fuel flow rate and decreasing air inlet diameter and tailpipe length. The measured operating frequency can be approximated by the simple linear equation and the discrepancy is within five percent. The system produced the maximum total thrust of 14N and the minimum specific fuel consumption of 0.155 Nm$^{3}$/h.N when the total thrust was 13N.