• Journal of the Korean Institute of Electrical and Electronic Material Engineers
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• v.20 no.6
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• pp.536-540
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• 2007

The Ce-doped YAG(Yttrium Aluminum Garnet, $Y_3Al_5O_{12}$) phosphor powders were synthesized by combustion method. The luminescence, formation process and structure of phosphor powders were investigated by means of XRD, SEM and PL. The XRD patterns show that YAG Phase can form through sintering at $1000^{\circ}C$ for 2 h. This temperature is much lower than that required to synthesize YAG phase via the conventional solid state reaction method. There were no intermediate Phases such as YAP(Yttrium Aluminum Perovskite, $YAlO_3$) and YAM(Yttrium Aluminum Monoclinic, $Y_4Al_2sO_9$) observed in the sintering process. The powders absorbed excitation energy in the range $410{\sim}510\;nm$. Also, the crystalline YAG:Ce showed broad emission peaks in the range $480{\sim}600\;nm$ and had maximum intensity at 528 nm.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.460-466
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• 2010

단일 알루미늄의 연소 모델을 사용하여 알루미늄 분말의 점화 과정에 대한 전산유체 해석 기법을 개발하였다. 유동의 계산은 Reynolds averaged Navier-Stokes식을 사용하였으며, $k-{\epsilon}$ 난류모델을 적용하였다. 입자는 Eulerian-Lagrangian 방법을 사용하여 유동과 독립적으로 계산을 수행하였으며 상용 전산유체해석 프로그램인 Fluent 6.3을 사용하여 해석을 수행하였다. 단일 모델에서 사용한 대류 및 복사 열전달, 표면이상반응, 알루미늄의 용융열을 입자 가열원으로 고려하였다. 같은 조건을 사용하여 단일 입자 모델 계산과 전산유체해석을 수행하였으며, 두 결과는 5% 이내로 잘 일치 하였다. 이를 통해 전산유체해석에서 알루미늄의 점화를 모사할 수 있음을 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.791-796
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• 2017

In this study, the combustion characteristics of paraffin blended fuel on aluminum particle size were investigated. The combustion experiments were carried out using aluminum particles with an average particle size of 100 nm and $8{\mu}m$ and microcrystalline paraffin wax (Sasol 0907). A series of comparison was conducted on the regression rate, the pressure curve and the characteristic velocity of pure paraffin and paraffin blended fuels with aluminum particles. It was found that the micro-sized particles enhance the regression rate as the oxidizer mass flux increased. However, the nano-sized particles decrease the regression rate as the oxidizer mass flux is increased.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.737-744
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• 2011

The success of continuous aluminum powder combustion with steam plasma is different from hydrocarbon ignition source. Ignition characteristics of aluminum powder with high temperature thermal plasma is studied with oxidizer-free environment. Experiment with argon plasma has same temperature conditions at 4500 K and particle feeding condition for previous combustion test with steam plasma and swirl combustor. The temperature of the plasma was measured using Optical Emission Spectroscopy method. Ignition characteristics were analyzed by SEM image and EDS. Aluminum powder with plasma has rapid evaporation mechanism contrast to hydrocarbon ignition source. It enhances to aluminum powder effective ignition characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.489-494
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• 2017

This paper describes the combustion characteristics of aluminized paraffin fuel on the contents of micron-sized aluminum particles with nominal diameters of $8{\mu}m$. Aluminized paraffin fuels with mixture ratio of aluminum 0 wt%, 5 wt% and 10 wt% as fuel and GOx(Gaseous Oxygen) as oxidizer were used to perform the experiments. The experimental investigations were performed on the regression rate, the chamber pressure and the combustion efficiency. Increasing a content of micron-sized aluminum particles, the results of regression rate, chamber pressure and combustion efficiency show minor increase compared to those without particles.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.2
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• pp.16-26
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• 2014

T-Burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.

• Proceedings of the Korean Powder Metallurgy Institute Conference
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• 2006.09b
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• pp.1071-1074
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• 2006

Fabrication and investigation of composite made of graphite, SiC, mullite and aluminum as the additive are the aim of this project. Aluminum acts as an anti-oxidant. SiC is a non-metallic anti-oxidant that increases composite strength. Different compositions with influent percents of aluminum have been selected to determine product specifications by XRD, SEM and STA methods. Results show that the composition of 40wt% graphite-20% SiC- 20% mullite-20% aluminum is a more robust and occurs at elevated temperatures than other graphite combustion composites.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.431-436
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• 2008

T-burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.

• Journal of the Korean Society of Combustion
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• v.19 no.2
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• pp.1-7
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• 2014

In this study, the variation of the flow field in Hydro-reactive engine combustor was numerically studied through 2-dimensional axisymmetric model with aluminum and heated water vapor. For calculating all velocity fields, compressible Navier-Stokes equation was used with Pre-conditioning. AUSM+up(p) method was used to exactly calculate mass flow in the control volume. As using SST model that is a turbulent model, the result had high accuracy for free stream and the flow near the wall. The effects of the temperature, variation of the flow field and distribution of chemical products on inject angle of heated water vapor were studied.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.5
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• pp.60-66
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• 2019

In this report, the process characteristic(viscosity), mechanical properties, combustion characteristics, ground and flight test results of propellants used for a rocket-assisted projectile are described according to several aluminum contents. As the aluminum content increased, initial viscosity decreased, viscosity build-up accelerated, and combustion rate and pressure exponent decreased. In the ground fire test, the total impulse of the rocket-assisted projectiles containing 10 wt% of aluminum were 5% higher than that of the rocket-assisted projectiles containing 2 wt% and 18 wt% of aluminum. The motor efficiency compared to the theoretical performance was 85.6% with 18 wt% of aluminum, the lowest value among the propellant compositions.