• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.125-128
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• 2008

Atomization characteristics of small LRE-injector spray are investigated by using dual-mode phase Doppler anemometry (DPDA). Velocity, size, number density, and volume flux were measured at various injection pressures along the radial distance to make a close inquiry into spatial distribution characteristic of spray droplets. As the injection pressure increases, the velocity, turbulence intensity, number density, and volume flux of spray droplets become higher, whereas the droplet size ($D_{10}$ or $D_{32}$) gets smaller. Also, velocity and volume flux are proportional to Sauter mean diameter (SMD, $D_{32}$).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.7-10
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• 2009

The development and evaluation of solid propellant were performed for the turbopump pyro starter, which start up the liquid propellant rocket engine for the Space Launch Vehicle (SLV). Requirements for the turbopump pyro starter propellant include the production of low flame temperature, low burning rate and nontoxic gas to protect the mechanical corrosion or air pollution. This study describes the development of the solid propellant composition which is based on PCP binder. DHG (Dihydroxy glyoxime), which has advantages of oxygen balance and ignition, was used as coolant. The mechanical properties and burning rate of the propellants were measured. Finally, static fired test was performed to prove the possibility of development.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.281-284
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• 2009

Acoustic tuning frequency of quarter-wave resonators is investigated numerically to suppress combustion instability in a liquid rocket engine. A quarter-wave resonator is adopted, which was designed from the cold acoustic test for optimal damping condition. First, in a model combustion chamber scaled down from a full-scale chamber, reactive flow filed is analyzed numerically and acoustic-pressure responses are examined. Next, thermodynamic properties in the resonators are predicted. Based on the data, frequency tuning method is studied. The optimum tuning length of each resonator is proposed and thereby, sufficient damping is produced.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.619-622
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• 2009

INCONEL 718합금은 상온, 고온 및 저온환경에서 기계적 특성이 아주 우수하다. 상온에서의 모재 강도는 약 900MPa이며, 열처리 후 시효경화처리에 의해 강도가 약 1300MPa까지 증가한다. 이러한 INCONEL 718합금의 기계적 특성은 시험결과에서도 유사한 값을 나타내었고, GTAW 용접부의 상온 기계적 특성도 모재보다 우수한 강도를 나타내었다. 또한 저온에서의 기계적 특성은 모든 시험조건에서 상온보다 높은 강도를 나타내었으며, 열처리 모재시편과 용접시편은 1400MPa에 달하는 고강도를 나타내었다. 이러한 결과를 바탕으로 INCONEL 718합금의 저온 기계적 특성이 우수한 것을 증명하였고, 용접성 또한 모재의 특성과 같이 상온 및 저온 특성이 우수한 것을 알 수 있었다. INCONEL 718 합금과 STS 316L의 이종접합의 경우에도 $-100^{\circ}C$환경의 인장강도가 상온보다 300MPa 이상 증가하는 것을 알 수 있었다. 따라서, INCONEL 718합금은 $100^{\circ}C$이하부터 일정온도까지는 기계적 특성이 계속 증가 할 것으로 사료되며, 극저온 고압 상태로 공급되는 산화제 배관 제작에 적합한 소재로 판단된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.145-148
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• 2009

Combustion tests of a fuel-rich gas generator had been conducted using the assembly of a powerpack. A gas generator is prone to longitudinal modes of combustion instabilities in a powerpack due to the increase of a characteristic length. It has been observed that the orifice inserted at the exit of the gas generator suppresses a longitudinal combustion instability. The intensities of pressure fluctuations in the manifolds and the chamber increase quadratically with a chamber pressure. Pressure fluctuations in the fuel manifold reveal two-fold strength greater than those in the oxygen manifold and the chamber. Frequency analysis indicates nonlinear characteristics inherent in the pressure fluctuations in the fuel manifold.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.603-607
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• 2009

A Ni/Cr plating process has been developed for applying to inner wall of liquid rocket engine(LRE) thrust chamber. Ni plating conditions were selected through thermal shock test and endurance verification of the plating layers was performed through hot firing test of a subscale thrust chamber with Ni/Cr plating. Test results showed that a crack or separation of the plating layers was not found. Judging from the results, Ni/Cr plating could be applied to LRE thrust chamber as a substitute of air plasma sprayed ceramic coating which is presently being used.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.97-100
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• 2009

Cold flow and ignition tests were performed for a technology demonstration model of a 75-tonf thrust chamber which is a candidate liquid rocket engine for a next Korea Space Launch Vehicle. The test facility was modified to support the new concepts of the thrust chamber such as ignition system, film cooling and LOx leading supply. The hydrodynamic characteristics of the supply pipelines, thrust chamber and igniter as well as the filling time of the propellants were obtained through the cold flow tests on the LOx and kerosene and the ignition cyclogram was determined using the results. The ignition test was successfully accomplished according to the cyclogram and therefore, a basic information was obtained for further hot firing tests.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.208-215
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• 2012

The acoustic noise around a launch pad by launches of space launch vehicles was analyzed. The magnitudes of sound noise at some points near launch pad were predicted by locating the sound source at the exhaust jet plume of the rocket engine and considering several factors such as the directivity of the sound propagation and atmospheric attenuation. Specifically, the launch noise of Korea Space Launch Vehicle-I (KSLV-I) was estimated, and was compared to the actual measurement results. The analysis results proved to be heavily affected by the characteristics of directivity of sound propagation and the analysis showed good agreements with the measurements when the directivity of the sound was appropriately adjusted.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.183-190
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• 2004

The performance analysis of a fuel pump for a liquid rocket engine has been performed numerically on its design condition. A commercial three-dimensional Navier-Stokes flow solver has been used for the computation. All of the fuel pump components - inducer, impeller, volute and secondary flow passages - are included in computation for the accurate estimation of the leakage flow rate which affects the performance and axial thrust. A pitchwise-averaged mixing plane method was used on the boundaries among the fuel pump components to save computational time. The predicted overall performance satisfied the design requirement. However, the axial thrust exceeded a permissible limit. In order to reduce the axial thrust, the secondary flow passage design has been changed. With this change, the axial thrust level has been reduced to 30% as compared with the original value.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.6 no.3
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• pp.98-104
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• 2007

The carbon fiber reinforced carbon composite (CFRC) materials are necessary for the advanced industries that require the thermal resistance. And the development and research for CFRC has been in progress in the field of aerospace and defense industry. CFRC have several advantages and special properties such as excellent anti ablation, outstanding strength retention at very high temperature, high heat capacity and thermal transport, high specific stiffness and strength, and high thermal shock resistance. They have been used as aircraft brake, rocket nozzle, nose cones, jet engine turbine wheels, and high speed craft. Since the technology related to CFRC was prohibited from importing and exporting, we developed our own technology to produce F-16 B32 brake disk made out of CFRC, and then we performed various tests to observe the characteristics of CFRC-based brake disk developed in this study in view of density, strength, friction, specific heat, and heat conductivity.