• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.341-343
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• 2004

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2001.05a
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• pp.46-51
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• 2001

A mechanism of hovering flight of small insects which is called the Weis-Fogh mechanism is applied to ship propulsion. A model of the propulsion mechanism is based on a two-dimensional model of the Weis-Fogh mechanism and consists of one or two wings in a square channel. A model ship equipped with this propulsion mechanism was made, and working tests were performed in a sea. The model ship sailed very smoothly and the moving speed of the wing was small compared with the advancing speed of the ship.

• Proceedings of the KSR Conference
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• 2005.11a
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• pp.665-670
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• 2005

This paper introduces the propulsion system(Motor Block) stabilization test result for Korean High Speed Railway(HSR). The developed propulsion system using high power semiconductor, IGCT(Integrated Gate Commutated Thyristor) consists of two PWM converter and VVVF inverter. In this paper, overall configuration of propulsion system is briefly described and stabilization tests are made to verify the developed propulsion system. The presented test results shows beatless control method of inverter output current at the 200km/h and performance test of BCH.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.300-305
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• 2004

A preliminary study on. field emitter array cathodes was conducted aiming at applying for electrodymanic tether (EDT) propulsion systems. The EDT propulsion systems are assumed to use for active removal systems of post-mission spacecraft, which would otherwise become space debris. A survey on field emit-ter array cathode technology was conducted, and it showed that carbon nanotube (CNT) emitters are suit-able to EDT application. Trial fabrications and evaluation tests of CNT emitters were conducted, which demonstrated a target emission current density of 10 ㎃/$\textrm{cm}^2$. It was found out that the most important technical issue for developing CNT emitters is to improve the performance against voltage breakdown between the emitter and the opposite electrode.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1184-1187
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• 2017

The space launch vehicle needs the verification of each stage's propulsion system. The Propulsion System Test Complex(PSTC) is constructed for developing KSLV-II in the Naro space center. Hydraulic and pneumatic system of PSTC should supply propellants and various gases to propulsion system module according to required condition. This paper introduces liquid oxygen filling system of PSTC.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1142-1143
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• 2017

In this paper, Underwater propulsion test of SWASH(Small Waterplane Area Single Hull) type underwater vehicle with hybrid rocket system is performed. Watertight structure is applied to prevent a combustion chamber from water, and the control logic is constructed by setting the watertight ignition sequence. As a results, It is confirmed that the ignition is stable in water, and the propulsion system works well along the configured control sequence.

• Journal of Advanced Marine Engineering and Technology
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• v.29 no.4
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• pp.363-368
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• 2005

A mechanism of hovering flight of small insects which is called the Weis-Fogh mechanism is applied to ship propulsion. A model of the propulsion mechanism is based on a two-dimensional model of the Weis-Fogh mechanism and consists of one or two wings in a square channel. A model ship equipped with this propulsion mechanism was made. and working tests were performed in a sea. The model ship sailed very smoothly and the moving speed of the wing was small compared with the advancing speed of the ship.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.480-485
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• 2008

In this study, two types of ramjet intake were designed for the flight condition of Mach number 2 and 5 and numerical analysis was performed. In order to widen the flight envelope range(Mach number $2{\sim}6$), movable intake concept was applied. The central body was designed so that the capture area ratio which is one of most important factors of ramjet intake design could be adjusted. And various types of cowl and movable insert part of shell were designed in order to control throat area which could increase total pressure recovery. The numerical results showed that the designed ramjet intake could be applied in various flights Mach number.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.27-30
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• 2011

For the successful development of korean lunar lander, the ground test is required in order to verify performance of propulsion system, attitude control system, performance of landing device and etc. In order to develop the lunar lander ground test model, development of large size thruster and pressure regulated propulsion system is now in progress. In this paper, the results of 200N class monopropellant thruster development and propulsion system design will be presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.183-186
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• 2011

In this paper, we present some results of power analyses, and weight estimation on electric propulsion systems for Personal Air Vehicles(PAV) applications. When hybrid electric propulsion is adopted, its power performance using fuel cells and batteries is inferior to that of internal combustion engines for 1,000 kg PAV. However, hybrid electric propulsion systems may replace IC engines when energy density and power density is over $0.75kW{\cdot}hr/kg$and 2.5 kW/kg, respectively.