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

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.393-396
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• 2006

This paper presents the characteristics of the performance parameters of dual mode(ramjet-scramjet combined) engine, inlet and combustor for wide range of flight Mach number, resulted from the analysis of its operating limitations. The transitional-critical flight Mach number from ramjet to scramjet and the performance of two types of combustors, such as constant pressure- and constant area- combustor, are conceptually evaluated.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.115-128
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• 2006

A technical analysis of current scramjet and combined-cycle engine is presented. Substantial research has been pursued to characterize the operation mechanism of scramjet propulsion, especially in the areas of flame stabilization and system integration, dramatically over the years in support of both military and space access application. Major technology that had significant impact on the maturation of scramjet propulsion technology are dual combustion ramjet, dual mode ramjet, and combined cycle engine to cover a typical wide rage of flight, up to flight Mach number 10. Notable are the fundamental and practical techniques, for instance, scram propulsion itself, thermal relaxation and protection using endothermic fuel and/or CSiC composit materials, and design/manufacture of movable intake and nozzle, to realize high speed propulsion system in near future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.167-170
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• 2008

A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.14-20
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• 2007

In this study, characteristics of jet type flame holder for ramjet engine combustors are investigated Jet flame holder can be easily controlled by the injection angle change and jet momentum variation without any thermal protection devices. Due to the intensive turbulent mixing effect, jet flame holder shows better flame holding performance than mechanical flame holders such as cavity, step and v-shape flame holder.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.116-122
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• 2016

The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.5
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• pp.72-81
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• 2011

In order to understand the operation characteristics and major design parameters of a dual combustion ramjet engine, a fundamental analysis model based on gasdynamics and thermodynamic theories was established. The preliminary performance analysis was accomplished and the results clearly describe the intimate relationship between air inlets, gas generator, and supersonic combustor. The methodology presented provides a means for quantitatively determining the geometries of the gas generator and supersonic combustor and assessing the effects on performance of each of the engine components. Also the design results for a basic configuration were provided.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.318-325
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• 2011

In order to understand the operation characteristics and major design parameters of a dual combustion ramjet engine, a fundamental analysis model based on gasdynamics and thermodynamic theories was established. The preliminary performance analysis was accomplished and the results clearly describe the intimate relationship between air inlets, gas generator, and supersonic combustor. The methodology presented provides a means for quantitatively determining the geometries of the gas generator and supersonic combustor and assessing the effects on performance of each of the engine components. Also the design results for a basic configuration were provided.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.65-78
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• 2004

This research was conducted for an acquisition of the ramjet engine test facility design technique which are concerned about freejet type test facility. In this research, we concentrated on the design technique and the construction technique of the vitiation air heater(VAH), test section, diffuser and ejector. Based on the operating modes of the basic test facility, ten operating modes in coordinates "Altitude-Mach number" was regenerated from Mach 2, Altitude 0km to Mach 5, Altitude 15km. In this operating modes, we calculated a design parameter of the supersonic nozzle, VAH, diffuser and ejector and acquired a technique for the ramjet test facility operating and repairing.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.17-17
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• 1999

액체램제트 추진기관은 고체로케트 추진기관에 비해 복잡한 구조와 작동원리를 가지고 있지만 산화제인 공기를 대기로부터 직접 흡입하므로 비행체의 크기와 중량을 줄이고 순항거리를 최대한 증대시킬 수 있는 장점을 가지고 있다. 이러한 램제트 추진기관의 개발 및 실용화를 위해서는 램제트 추진기관의 유동 및 연소지상시험 설비의 구축이 필수적이다. 본 연구에서는 그 기초연구로서 연소기 입구의 속도, 온도와 같은 실제 액체램제트 추진기관의 비행조건을 완벽하게 모사할 수 있는 Vitiated Air Heater의 설계기술 확보에 연구목적을 두었다.