• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.18-25
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• 2017

The study for the combustion characteristics of propellants for nozzleless boosters was carried out. The metal fuels of Al and Zr were introduced into solid propellant formulations in order to enhance the density-specific impulse and the high burning rate with low pressure exponent was investigated as the major combustion characteristic of propellant to design nozzleless boosters. The burning rate of Zr-containing propellant was higher than Al-containing propellant and, $13{\mu}m$ Zr-containing propellant exhibited the burning rate of 35 mm/s (at 1000 psi)and pressure exponent of 0.3282. The benefit of using Al and Zr-containing propellant into nozzleless boosters was demonstrated in these results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.66-71
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• 2005

In this study the regression rate of hybrid rocket fuel has been investigated by two methods. First method is to use swirl injectors for enhancement of regression rate. And second method is the modification of the helical grain deriving improvement of combustion area and generating swirl flow. Tests have been done with PMMA and gaseous oxygen. In this paper the incline angle of the helical grain was varied to find the optimal condition to obtain the max regression rate for a given operational condition.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.3
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• pp.25-30
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• 1999

An experimental investigation was conducted to explore the effects of air mass flux on the combustion efficiency and particle size distributions in a solid fuel ramjet using a fuel grain highly loaded with boron carbide. Particle distributions were measured at the grain exit and at the nozz1e entrance using a Malvern 2600 HSD. Combustion efficiency increased with decreasing air mass flux. In general, the particle distribution was trimodal or quadrimodal with node peaks at approximately 4, 15, and 25$\mu\textrm{m}$ and possibly one at less than 2$\mu\textrm{m}$. The larger particles were the result of surface agglomeration, primarily within the recirculation region. Higher inlet air temperature produced higher combustion efficiencies, apparently the result of enhanced combustion of the larger boron carbide particles that burn in a diffusion controlled regime.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.353-357
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• 2017

The research trends and major technologies of the divert attitude control system(DACS), which is the core of the anti-missile system, are described. The operating concept and characteristics according to the fuel used are summarized. The characteristics of typical weapon system applying solid(SM3 Block IB/IIA) and liquid(THAAD) fuels were discussed. In the future, it will be necessary to study various types of DACS in the strategic concept of the defense weapon system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.511-514
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• 2009

In this study, the combustion characteristics of hybrid rocket fuel with tapered grain port were studied. The regression rate was increased about 17.5% by using the convergence port shape fuel. On the other hand, in case of divergence port shape fuel, any notable difference of regression rate was not observed when compared with regression rate of the cylindrical port shape fuel. Also, in case of convergence port shape fuel, characteristic velocity efficiency was increased. From these results, one can notice that convergence port shape of hybrid rocket fuel can be effective configuration in terms of improvement of combustion efficiency and performance.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.121-131
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• 2005

For thrust motion of high speed underwater torpedo the special hydro reactive fuels that burns in vapor water and water supply from aboard is used. The main component of this hydro reactive fuel is the powder of active metal (Mg, Al) that can burn in water vapor with large heat generation in the rocket combustion chamber. The thermodynamic analysis of combustion properties of the burning of the particles of these active metal in the vapor water have been carried out. The conception for the possible content variants of the hydro reactive fuels have been discussed using the geometrical and thermodynamic combustion conditions with the basic recommendation for contents of designed hydro reactive fuels in future.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.4
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• pp.18-25
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• 2014

In this paper, the mechanism of the combustion instability which may occur in a hybrid rocket motor with a diaphragm was studied. And the new design for a hybrid motor grain was suggested. It could increase a regression rate of solid fuel, and reduce a large pressure oscillation in a hybrid rocket motor with a diaphragm. It was confirmed that the main mechanism of a large pressure oscillation was hole-tone, and it was caused by a collision between a diaphragm and a vortex which was generated in a pre-chamber. And 'Stepped Grain' design which had the mechanism for high regression rate in a motor with a diaphragm and could reduce a combustion instability was suggested.

• 한국신재생에너지학회:학술대회논문집
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• 2009.06a
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• pp.856-856
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• 2009

석유 및 천연가스를 대체하는 자원으로 석탄이 유망하다고 전망하고 있다. 미국에서는 6대 파괴력이 있는 기술로 청정석탄기술이 선정되었고, 한국에서도 15대 그린에너지 중 하나인 청정연료에 석탄전환기술이 포함되어 전략로드맵이 작성되고 있다. 국내에서 추진되고 있는 석탄기술은 석탄가스화를 기반으로 하고 있다. 석탄가스화는 고체연료인 석탄을 $1000^{\circ}C$ 이상의 고온에서 산소와 반응시켜 일산화탄소와 수소가 주성분인 합성가스로 전환하는 기술이다. 석탄을 가스화하면 석탄에 포함된 불순물을 쉽고 완벽하게 제거할 수 있으며 특히 CO2 제거를 값싸게 할 수 있어 청정화가 가능하다. 최근 고유가를 겪으면서 열량이 높은 고급탄의 확보가 어려워지면서 가격이 낮고 수급이 용이한 저급탄을 활용하는 기술의 수요가 발생되어 국내에서 기업을 중심으로 저급탄을 고효율로 가스화하는 기술 개발이 시도되고 있다. 정제된 석탄가스는 성분을 조절하여 촉매에 의해 메탄으로 전환시킬 수 있고, 이렇게 제조된 가스를 합성천연가스(SNG)라 한다. 값싼 저급탄을 사용하면 SNG를 천연가스보다 저렴하게 생산할 수 있다. 국내 기업이 SNG 제조 실증시설을 도입하고, 동시에 핵심기술인 SNG 합성반응공정을 개발하는 사업을 추진하고 있다. 석탄가스를 촉매반응에 의해 디젤 및 �F싸로 전환하는 석탄간접액화기술은 현재 남아공 Sasol사에서 상업적으로 운전되고 있는 기술이나 국내로의 기술이전이 거의 불가능하다. 철을 기반으로 하는 고유 촉매와 scale-up이 가능한 반응기가 핵심인 기술로 국내에서 세미-파일럿급 액화공정 기술개발이 진행중이다. 전세계적으로 석탄액화공장의 수요가 현재의 15만배럴/일에서 2030년 240만배럴/일로 증가한다고 예측된다. 따라서 200조원 이상의 플랜트 시장이 기대되며 국산 가스화, SNG 및 액화기술로 상당부분의 시장을 장악하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.1
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• pp.21-29
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• 2002

Hybrid propulsion systems provide many advantages in terms of stable operation and safety. However, classical hybrid rocket motors have lower fuel regression rate and combustion efficiency compared to solid propellant rocket motor. The recent research efforts are focused on the improvement of volume limitation and regression rate in the hybrid rocket engine. The present study has numerically investigated the combustion processes in the hybrid rocket engine. The turbulent combustion is represented by the eddy breakup model and Hiroyasu and Nagle and Strickland-Constable model are used for soot formation and soot oxidation. Radiative heat transfer is modeled by finite volume method. To reduce the uncertainties for convective heat transfer near solid fuel surface having strong blowing effect, the Low Reynolds number $\kappa-\varepsilon$ turbulent model is employed. Based on numerical results, the detailed discussion has been made for the turbulent combustion processes in the vortex hybrid rocket engine.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.136-141
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• 2008

Cylindrical supersonic exhaust diffuser, which utilizes the momentum of high temperature gas exhausted from nozzle, provides simple methods for obtaining stable and low pressure around the propulsion system. Hot zone on which exhausted gas from nozzle exit impinges directly should be cooled to avoid melting of diffuser. This paper describes method and result of subscale high altitude simulation test with water cooling. Subscale gas generator with solid propellant was used for hot gas source and tap water for coolant.