• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.371-374
• /
• 2011

High-resolution numerical study is carried out to investigate the flame stability of the turbulent supersonic combustion in a Dual-Combustion Ramjet (DCR). The auto-ignition in a shear layer between hydrogen/carbon-monoxide syngas and air was studied at elevated enthalpy condition. Comparison of a constant area combustor and a combustor with a small divergence angle shows that the supersonic combustion has a characteristics of the lifted flame and its stability is influenced significantly by the compressibility.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.386-387
• /
• 2012

This experimental study is the supersonic combustion of dual combustors in dual combustion ramjet engine. Through the preliminary performance analysis of DCR, the configuration of dual combustors was determined and constructed, supersonic experiments were accomplished.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1999.10a
• /
• pp.16-16
• /
• 1999

최근 세계적인 관심을 끌고있는 레이저 광원에 의한 공기흡입추진기술의 연구 동향을 소개하고 레이저 추진 램가속기의 응용 방법, 제안된 램가속기 탄체 형상, 작동원리, 사용 레이저 특성을 제시하고, 레이저 추진 기술의 주요기술인 레이저 유도 플라즈마 유동의 해석을 위한 매우 간단한 추력면 형상에 대한 수치계산 결과와 현상의 설명을 제시한다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.5
• /
• pp.49-58
• /
• 2018

This paper introduces a research on the control method design for the subsonic intake flow of a dual-combustion ramjet engine. To design the control method, the intake flow dynamic response characteristics, based on a designated flow condition and intake geometry, are investigated, and a control method concept considering the intake flow characteristics is established. Using a dynamic simulation model of a dual-combustion ramjet, control input/output linearized models are obtained such that a control loop design based on linearized models can be accomplished. Finally, from various control loop simulations, the performance of the control method, including its control loop stability, is evaluated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• v.y2005m4
• /
• pp.394-398
• /
• 2005

Ramjet engine have been usually operated on Mach $1.5\sim3$ as the vehicle of supersonic cruising engine and studied about the higher performance above Mach 4. The research of Duel mode Scramjet engine which have duel operating mode of ramjet/Scramjet are in progress actively nowadays. This paper suggests the effect the flow characteristics and the effects of back pressure, angle of attack, angle of yow on the supersonic air intake on mach 4 through the Schlieren/Oil flow visualization, and pressure measurement on experimental model.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.10
• /
• pp.68-74
• /
• 2005

Optimal shape of a typical ramjet intake is examined numerically to maximize the total pressure recovery. A response surface method is introduced to approximately predict its performance with respect to the design parameters over the each design domain. The first deflection angle of ramp, the area of inlet throat, and the diffuser angle are chosen as a design parameter. ANOVA is used to verify the trustability of the achieved response surface. The total pressure recovery of the optimum model, compared to that of the base model, is increased by 36%. The loss of viscosity through the diffuser is estimated less than 5%.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.10 no.2
• /
• pp.115-128
• /
• 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
• /
• 2011.11a
• /
• pp.595-598
• /
• 2011

Supersonic combustion phenomena in the main combustor of a dual combustion ramjet (DCR) engine are studied numerically. Since the supersonic combustion is affected significantly by the compressibility effects parametric studies have been carried out for the constant are length and the divergence angle. Numerical studies with fixed inflow condition for different geometric configurations reveals that the supersonic combustion in DCR combustor has the characteristics of lifting flame, where the lifting flame is maintained near the injector tip for the case of long combustor length with small divergence angle, but the lifting height is significantly increase for large divergence angle resulting flame blow-out of the combustor. Therefore, it is concluded that flame stability should be considered sufficiently in the design o DCR combustor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.05a
• /
• pp.93-95
• /
• 2009

This is a reviewing paper on the ramjet development programs of the U.S.A. and European countries through the presented papers at the ISABE 2005 and Joint Propulsion Conference 2008. Interestingly, the programs which are developing now are only limited on the ducted rocket, neither liquid nor pure solid fuel ramjet.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2001.04a
• /
• pp.42-42
• /
• 2001