• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.16-16
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• 1999

램 가속기 탄체 형상에 따른 가속 특성에 대한 연구는 열적 질식 모드에 대하여 Washington 대학, ISL 연구소 등에서 실험적으로 수행되어 졌으나 초폭굉 연소 모드에 대해서는 아직 미비한 실정이다. 초폭굉 연소 모드 램 가속기의 기본적인 탄체 형상은 원추-원통-원추로 이루어진 형상으로 탄체 전면에 형성된 경사 충격파가 탄체와 가속기 사이에서 반사되며 데토네이션파를 발생시켜 가속하게 된다. 탄체의 형상에 따라서 탄체 주위에 형성되는 충격파 구조는 차이를 나타내게 되고 발생되는 데토네이션파의 위치와 강도를 따라서 탄체의 가속특성은 상당한 차이를 나타낸다. 기본적으로 탄 체의 전면 형상은 경사 충격파의 강도와 단체 주위의 유동장의 특성을 결정하는 주요 요인이고 이에 따라 데토네이션파의 형성과 안정화 역시 결정되어 탄체의 가속 특성을 결정짓는다. 또한 데토네이션파를 임의의 위치에 형성하기 위해 이중 원추형상의 충격파-충격파 상호작용을 이용하여 데토네이션파를 발생시켜 탄체를 가속시킨다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.57-64
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• 2011

It has been suggested that turbulent effect should be considered for the study of highly unstable detonation of hydrocarbon fuels, as in the case of pulse detonation engine (PDE). A series of numerical study are carried out to understand the characteristics of the highly unstable detonation by considering viscosity, turbulence model and turbulence-combustion interaction model. Through studies of the different levels of modeling, it is understood that the viscosity and turbulence have negligible effects on low frequency characteristics, but tend to enhance the high frequency characteristics. It is also considered that the turbulence-chemistry interaction model should be taken the influence of the activation energy into account for detonation studies.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.221-224
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• 2003

A numerical study is carried out for the detonation wave propagation through a T-branch. The T-branch is a crucial part of the combustion wave igniter, a novel concept of rocket ignition system aimed for the simultaneous ignition of multiple combustion chambers by delivering detonation waves. Euler equation and induction parameter equation are used as governing equations with a reaction term modeled from the chemical kinetics database obtained from a detailed chemistry mechanism. Second-order accurate implicit time integration and third-order space accurate TVD algorithm were used for solution of the coupled equations. Over two-million grid points enabled the capture of the dynamics of the detonation wave propagation including the degeneration and re-initiation phenomena, and some of the design factors were be obtained for the CWI flame tubes.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.136-140
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• 2005

By extending one-dimensional ZND detonation structure analysis model, a simple model for two-dimensional oblique detonation wave structure analysis is presented by coupling Rankine-Hugoniot relation and chemical kinetics for oblique shock wave and oblique detonation wave. Base on this study, two-dimensional fluid dynamics analysis is carried out to investigate the detailed unsteady structure of oblique detonation waves involving triple point, transverse waves and cellular structures. CFD results provide a deeper insight into the detailed structure of oblique detonation waves, and the simple model could be used as a unified design tool for hypersonic propulsion systems employing oblique detonation wave as combustion mechanism.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.314-318
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• 2006

The interest on the detonation in small tubes, which can be applied to the ignition devices of propulsion system, is increasing. However, the propagation dynamics of detonation waves in small tubes has not been investigated clearly yet. In the present experiments, propagations of detonation waves in stoichiometric propane-oxygen mixture through transparent tubes were recorded using a high speed camera and average velocities were measured as well. In terms of average velocity, there exists a transition regime where the waves show smooth transition from the normal Chapman-Jouguet(CJ) detonation to the low velocity detonation$(\sim0.5V_{CJ})$ along the decreasing initial pressure. In this transition regime, the detonation waves are highly unstable and show cyclic or intermittent longitudinal velocity fluctuation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.858-869
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• 2014

Most of the aerospace propulsion is based on the Brayton cycle, in which the combustion is held through the constant pressure process, but further improvement of performance by increasing compression ratio is challenged by mechanical limits. Detonation propulsions, regarded promising for high-speed propulsion for a lase decade, is more rigorously studied in these days as a game-changer for the improvement of thermodynamic efficiency of propulsion and power generation systems. Since, the additional compression by the strong shock of the detonation wave is considered increasing thermodynamics efficiency that is hardly achievable by the conventional compression systems. Present paper will give an introduction the latest technical trends on the Pulse Detonation Engines(PDEs) and the activities on the Pressure Gain Combustion (PGC) based on Constant Volume Combustion (CVC).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1094-1103
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• 2008

A fuel specific detonation wave in a pipe propagates with a predictable wave velocity. This internal detonation wave speed determines the level of flexural wave excitation of pipes and the possibility of resonant response leading to a large displacement. In this paper, we present particular solutions of displacements and the resonance conditions for internally loaded pipe structures. These analytical results are compared to numerical simulations obtained using a hydrocode(multi-material blast wave analysis tool). We expect to identify potential explosion hazards in the general power industries.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.19-28
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• 2021

In rotating detonation engine(RDE), only the detonation wave is moving around the outer wall of the combustor. Neither a mechanical part nor flow is rotating in RDE. Thus, the RDE cross section is not necessary to be circular, but arbitrary closed section is possible. A RDE of tri-arc cross section is designed and As an example of an arbitrary cross sectioned RDE, a RDE of tri-arc cross section is designed in this study, and operational and performance characteristics were examined experimentally. The rotation of the detonation wave is confirmed by dynamic pressure sensor and high-speed camera, while the characteristics of the detonation wave were investigated at the concave and convex surfaces. In the present study, the thrust level of 17.0 N to 96.0 N was obtained depending on the mass flow rate.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.383-391
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• 2009

The detonation wave characteristics of JP-7 and oxygen mixture is investigated by one-step induction parameter model (IPM) obtained from a detailed chemistry mechanism. A general procedure of obtaining reliable one-step kinetics IPM for hydrocarbon mixture from the fully detailed chemistry is described in this study. The IPM is obtained by the reconstruction of the induction time database obtained from a detailed kinetics library. The IPM was confirmed by the comparison of the induction time calculations with that from detailed kinetics. The IPM is later implemented to a fluid dynamics code and applied for the numerical simulation of detonation wave propagation. The numerical results show the detailed characteristics of the detonation wave propagation in JP-7 and oxygen mixture at affordable computing time, which is not be possible by the direct application of the detailed chemical kinetics mechanism of hydrocarbon fuel combustion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.425-429
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• 2011

The development of metal plasma generated by high laser irradiance and its effect on the surrounding air using shadowgraph images after laser pulse termination are studied; hence the formation of laser supported detonation and combustion processes has been investigated. The core of the paper is in detecting chemical reaction using X-Ray Diffraction (XRD) between ablated aluminum plasma and oxygen from air by inducing high power laser pulse (>1000 mJ/pulse) and conduct a quantitative comparison of chemically reactive laser initiated waves with the classical detonation of exploding aluminum (dust) cloud in air. This study may suggest a new approach of initiating detonation from metal sample in its bulk form without the need of mixing nano-particles with oxygen for initiation.