• 한국연소학회:학술대회논문집
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• 2002.11a
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• pp.237-240
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• 2002

Micro catalytic reactors are alternative propulsion device that can be used on a nano satellite. When used with a monopropellant, $H_2O_2$, a micro catalytic reactor needs only one supply system as the monopropellant reacts spontaneously on contact with catalyst and releases heat without external ignition, while separate supply lines for fuel and oxidizer are needed for a bipropellant rocket engine. Additionally, $H_2O_2$ is in liquid phase at room temperature, eliminating the burden of storage for gaseous fuel and carburetion of liquid fuel. In order to design a micro catalytic reactor, an appropriate catalyst material must be selected. Considering the safety concern in handling the monopropellants and reaction performance of catalyst, we selected hydrogen peroxide at volume concentration of 70% and perovskite redox catalyst of lantanium cobaltate doped with strondium. Perovskite catalysts are known to have superior reactivity in reduction-oxidation chemical processes. In particular, lantanium cobaltate has better performance in chemical reactions involving oxygen atom exchange than other perovskite materials. In the present study, a process to prepare perovskite type catalyst, $La_{0.8}Sr_{0.2}CoO_3$, and measurement of its propellant decomposition performance in a test reactor are described.

• 한국연소학회:학술대회논문집
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• 2005.10a
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• pp.269-272
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• 2005

Due to the high density and heating value, liquid fuel is attractive for ramjet propulsion system. Liquid fuel requires time to evaporation and mix with incoming air before ignition; insufficient evaporation and mixing result in low combustion efficiency and instability. So the numerical studies are conducted to investigate the spray and combustion characteristics of a liquid-fueled dump type Integrated Rocket Ramjet combustor. The governing equations are solved by means of a finite-volume using time derivative preconditioning method for chemical reacting flow. The liquid phase is treated by solving Lagrangian equations of motion and transport for the life histories of a statistically significant sample of individual droplets.

• Journal of Advanced Marine Engineering and Technology
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• v.30 no.7
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• pp.800-807
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• 2006

This paper introduces the hull deflection analysis method by using the direct measurements. Accordingly, this paper demonstrates how the hull deflection data is obtained by the reverse calculations using the bending moments from the stain gauge and bearing reactions from jack-up method. Where the hull deflection data provided by this research is used for the shafting alignment calculations for identical or similar vessels, shafting failures due to hull deflections can be minimized. It will also save time and expenses associated finite element method to predict hull deflections.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.1-2
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• 2006

선체 변형에 의해 발생할 수 있는 베어링 손상을 최소화하기 위해서는 설계 단계에서 선체 변형을 고려한 축계 배치 해석이 이루어져야 한다. 선체 변형은 유한 요소법을 이용한 구조해석에 의한 방법과 측정 데이터를 이용한 역분석 방법으로 구할 수 있다. 이 연구에서는 측정에 의해 얻어진 베어링 반력과 축의 굽힘 모멘트를 이용하여 선체 변형을 구하는 방법에 대해 설명하고, 이를 4만6천톤급 석유/화학운반선에 적용하여 다른 운전 조건에 대한 베어링 옵셋 변화와 선체 변형량을 검토한다.

• 한국연소학회:학술대회논문집
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• 2006.04a
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• pp.218-222
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• 2006

Due to the high density and heating value, liquid fuel is attractive for ramjet propulsion system. Liquid fuel requires time to evaporation and mix with incoming air before ignition; insufficient evaporation and mixing result in low combustion efficiency and instability. So the numerical studies are conducted to investigate the spray and combustion characteristics of a liquid-fueled dump type Ramjet combustor. The governing equations are solved by means of a finite-volume using time derivative preconditioning method for chemical reacting flow. The liquid phase is treated by solving Lagrangian equations of motion and transport for the life histories of a statistically significant sample of individual droplets.

• Proceedings of the KIEE Conference
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• 2000.07c
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• pp.2086-2088
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• 2000

Key elements of in the development Electro-Thermal-Chemical propulsion (ETC) are high current pulse shaping, switching and storage bank device with high energy density 300kJ pulse power capacitor bank module for ETC application is designed and fabricated. The tested result are described.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.14-21
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• 2010

Ion thruster is a kind of electrostatic thruster that use electrostatic field in order to accelerate ionized propellant. Ion thruster have characteristics of small thrust but very high specific impulse among the electric thrusters. High specific impulse can reduce propellant consumption significantly. So, ion thruster have advantage for long time and long distance mission. Recently, plans for space exploration is increasing gradually not only at traditional forward countries for space like USA, Russia and Europe, but also other countries like Japan, China and India. Exploration for superior planets and asteroids the propellant ratio can go up to about 99% when chemical propulsion is used as a cruising thruster. Therefore, latest space exploration vehicles use the ion thruster as main thruster for del-V burn and use monopropellant thrusters for attitude control. In this paper, the development process of preliminary ECR ion thruster and the ECR discharge test results will be presented.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.4
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• pp.37-44
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• 2015

An experimental study was performed for the analysis of frequency-equivalence ratio correlation in the methane-air premixed flame influenced by ultrasonic standing wave. Evolutionary features of the propagating flame were caught by high-speed camera, and the variation of flame-behavior including local velocities was investigated in detail using a post-processing analysis of the high-speed images. It was found that propagation-velocity augmentation of the methane-air premixed flame by the intervention of ultrasonic standing wave was made in leaner mixture, but the velocity diminished when the strength of chemical reaction was saturated around the slightly fuel-rich side of stoichiometry.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.608-611
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• 2011

Laser-induced combustions and explosions generated by high laser irradiances were explored by Laser-Induced Breakdown Spectroscopy (LIBS) in rich, and stoichiometric conditions. The laser used for target ablation is a Q-switched Nd:YAG laser with 7 ns pulse duration at wavelength of 1064 nm laser energies from 40 mJ to 2500 mJ ($6.88{\times}10^{10}-6.53{\times}10^{11}\;W/cm^2$). The plasma light source from aluminum detected by the echelle grating spectrometer and coupled to the gated ICCD(a resolution (${\lambda}/{\Delta}{\lambda}$) of 5000). This spectroscopic study has been investigated for obtaining both the atomic signals of aluminum (fuel) - oxygen (oxidizer) and the calculated ambient condition (plasma temperature and electron density). The essence of the paper is observing specific electron density ratio which can support the processes of combustion and explosion between ablated aluminum plume and oxygen from air by inducing high power laser.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.441-444
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• 2011

Type A and Type B and are commercial HTPB models, which are very popular prepolymer for polyurethane binder family. So the study has been performed on the physical, chemical characteristic of HTPB and viscosity, mechanical property of PBX-A applying to HTPB. But We excluded the Type A from Appication test, because of law Hydroxyl value. And in the case of Type B, Type B-1, 2 has mechanical disadvatage to apply to HTPB in the process comparing with B-3. It seems to make no problem if we change equivalence ratio or curing condition within standards. But if we are to apply process condition like R-45HT(US-sample), it would be essential to apply HTPB with higher Hydroxyl Value and hydroxyl Functionality.