• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.62-63
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• 2002

램젯 엔진을 장착한 미사일은 기존의 터보젯 이나 터보팬 엔진에 비해 압축기와 터빈과 같은 엔진 구성품이 없어 무게가 가볍고 초음속에서 저항도 적으며 고속의 비행영역에서 연료효율과 생존성능이 뛰어나기 때문에 차세대 미사일 추진 시스템으로서 세계 여러 국가에서 개발 및 운용이 이루어지고 있다. 하지만 램젯 엔진은 충분한 램 효과를 얻어야 초기 점화가 가능하기 때문에 현재 개발되고 있는 대부분의 시스템은 최초 발사시 로켓 부스터에 의해 가속하고 로켓연료를 모두 소모하고난 후에 흡입구가 개방되어 램젯 엔진이 점화하는 방식을 취하고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.588-593
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• 2011

In this study, the performance analysis method for ramjet engine system with atmospheric air disturbance was proposed. Flight path was determined to satisfy dynamic pressure constant at each flight altitude. The atmospheric air disturbance incoming into a engine intake was simulated by the model Tank proposed. The performance parameters was investigated at each flight condition with air disturbance. Engine operation stability was evaluated as analysis of the normal shock position.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.94-97
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• 2003

The effect of pressure perturbation in the ramjet engine on the characteristics of the inlet is studied via numerical simulation. The frequency and amplitude of the pressure perturbation are assumed to be 500Hz and 20% of the exit back pressure, respectively. The simulation shows the characteristics of the normal shock in the inlet according to the pressure perturbations. The relation between the captured mass flow rate and downstream pressure perturbation is studied. The mass flow rate decreases when the downstream pressure perturbation starts.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.419-422
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• 2010

An unsteady numerical combustion analysis was performed to investigate the combustion characteristics of A Dual Combustion Ramjet(DCR) engine using a gas generator. According to a variance of the equivalence ratio of the gas generator, the flow pattern in the combustor was analyzed. A typical acoustic frequency in the combustor was observed by detail analysis of pressure fluctuation at each location of the combustor.

• Journal of the Korea Institute of Military Science and Technology
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• v.5 no.1
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• pp.107-115
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• 2002

In this paper, spray and combustion characteristics of a liquid-fueled ramjet engine were experimentally investigated. The spray penetrations were measured to clarify the spray characteristics of a liquid jet injected transversely into the subsonic vitiated airstream, which Is maintained a high velocity and temperature. The spray penetrations are increased with decreasing airstream velocity, increasing airstream temperature, and increasing air-fuel momentum ratio. To compensate our results of penetrations, the new experimental equation were modified from Inamura's equation. In the case of insufficient penetration, the combustion phenomenon in ram-combustor were unstable. Therefore, the sufficient penetration must be considered to make a stable flame.

• 한국가시화정보학회:학술대회논문집
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• 2001.12a
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• pp.151-163
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• 2001

A two color PIV technique has been developed for visualization of complex and high speed flow in a ramjet combustor. Two color PIV has the advantages that velocity distributions in high speed flowfields can be measured simply by varying the time interval between two different laser beams and a directional ambiguity problem can be solved by color separation, and then a signal-to-noise ratio can be increased through nearly perfect cross-correlation. As a basic research of the ramjet engine, a 2-D shaped combustor with two symmetric air intakes has been manufactured and an experimental study has been conducted using a two color PIV technique. The flow characteristics such as recirculation zones, intake air mixing and turbulent kinetic energy have been investigated varying inlet angles and dome heights. It was found that the primary recirculation zone is affected mainly by the dome height, whereas the secondary recirculation zone is influenced by the air inlet angle.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.4
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• pp.50-60
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• 2014

Many countries are paying efforts to the research and development of water-breathing ramjet propulsion for submersible vehicle with the super-cavitation which makes traveling at high speed in underwater possible. In this study, a conceptual design of an underwater vehicle with water-breathing ramjet was carried out. Mission profiles and operating conditions are determined by examining the operation environment. Drag is estimated based on the theories of super-cavitation and fluid mechanics. The sizing and performance analysis of the components were performed using thrust required, thrust and specific impulse of designed engine were verified.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.5
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• pp.27-35
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• 2021

A technical review of Soviet/Russian supersonic anti-ship cruise missiles is presented. The supersonic anti-ship cruise missiles is one of the weapons for asymmetric power. The supersonic speed of the missiles is very useful both for attacking a time critical target and for improving target-penetration characteristics of the missile. The survivability of the missiles has also been increased by the improved concept of operation. Supersonic cruise missiles is greatly affected by the evolution of propulsion technology. Early supersonic cruise missiles adopt turbojet engines and rocket motors. The use of the integrated rocket-ramjet engine reduced the size of the supersonic missile, so today's supersonic cruise missiles are suitable to be deployed in various platforms. Nowadays, export versions of the missiles are actively being developed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.295-298
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• 2008

In this paper, prototype dynamic modeling scheme to control ramjet propulsion systems were proposed. From the physical understandings of engine system, a typical 2nd-order system model was applied to simulate the dynamic characteristics of fuel supply system. The shock location varience in diffuser to chamber pressure fluctuation is calculated so that the out of phase between two signals was observed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.331-334
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• 2011

The performance of ramjet engine is closely associated with a supersonic intake. In this study, experiments and computational simulations were conducted to observe the internal flow characteristics of the supersonic intake. The supersonic intake which have self-starting characteristics was designed and manufactured. The flow characteristics was analyzed from the experimental results using the supersonic wind tunnel testing and computational results using RANS equation and Menter's SST turbulence model. The detailed visualization results were suggested for the pseudo-shock wave of stable operations and for the inlet buzz phenomenon of unstable operations.