• Journal of the Korean Society of Marine Environment & Safety
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• v.18 no.4
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• pp.360-364
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• 2012

AC to DC converter that consists of relatively simple diode rectifier devices has been widely used in the field of the electric propulsion system. Also, since this rectifier includes large harmonics in the input current, a variety of researches have been developed to reduce the harmonics. The proposed method of this paper is to reduce the harmonics included in the input current of rectifiers and propulsion motor by injecting the output current of diode rectifier into the input of them. In addition, the proposed method ensures electrical safety through the respective isolation of the injection current, the source, and the loads using the Wye-Delta insulating transformer applied in current injection device that is installed in the input circuit of rectifiers and propulsion motor. The proposed method is simulated by applying to the electric propulsion ship that is currently operating. We confirm the validity of the proposed method compared with conventional power conversion system.

• Journal of the Society of Naval Architects of Korea
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• v.41 no.3
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• pp.13-21
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• 2004

This paper deals with a theoretical and experimental method for the design of a biased asymmetric pre-swirl stator propulsion system which is an energy saving device by recovering a propeller rotational energy. In the case of slow-speed ships, the upward flow is generated along the afterbody hull form at the propeller plane. The generated upward flow cancels the rotating flow of the propeller at the starboard part while it increases at port part. The present biased asymmetric pre-swirl stator propulsion system consists of three blades at the port and one blade at the starboard which can recover the biased rotating flow effectively. This paper provides the design concept which gives more simple and a high degree of efficiency and the experimental results for the compound propulsion system.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.1
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• pp.91-96
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• 2014

KSLV-I (Korea Space Launch Vehicle-I) upper stage KM (Kick Motor) is a solid propulsion system which consists of igniter, SAD (Safety Arming Device), composite case, and submerged nozzle capable of TVC (Thrust Vector Control) actuation. Each subsystem of KM fulfilled development requirements for achieving a flight mission successfully. We confirmed the successful development of KM from the $3^{rd}$ flight test results of NARO on January 30, 2013. This article deals with the requirements of KM and the results on configuration management, mass variation, thrust axis alignment, and major test results and so on.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.25-29
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• 2007

Minimization of conventional propulsion device has been studied for altitude control of micro satellite. We studied micro nozzle performance and found higher significant loss for a micro nozzle with smaller nozzle throat diameter. To overcome this loss, we proposed thermal transpiration based micro propulsion system. This new system has no moving parts and can control flow by temperature gradient, and this can be an option for potential new micro propulsion system.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.3
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• pp.80-89
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• 1998

Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.36-40
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• 2008

Minimization of nozzle induces many flow losses in micro-propulsion system. In this study, we studied about thermal transpiration based new conceptual micro propulsion system to overcome these losses. Thermal transpiration device(Knudsen pump) having no moving parts can self-pump the gaseous propellant by temperature gradient only (cold to hot). We designed, fabricated the knudsen pump and analyzed pressure gradient efficiency of membrane according to Knudsen number under vacuum condition. In this paper, we compared mass flow rate of Knudsen pump by using different membrane type ; Polyimide and Hangi, Korean traditional paper.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.8-13
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• 2018

Zirconium potassium perchlorate(ZPP) is an igniter composed of potassium perchlorate as an oxidizing agent and zirconium as a fuel with a Viton binder. ZPP has been used to provide an ignition source in the aerospace, propulsion, and automotive industries. This study investigates the manufacturing process and characteristics of ZPP, such performance and shape/calorimetry/pressure characteristics with respect to pyrotechnic mechanical device(PMD). During the production of ZPP, the mixing process was designed to produce uniform particle size and shape by mixing the raw materials at high speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.326-330
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• 2010

A laser based needle-free liquid drug injection device has been developed. A laser beam is focused inside the liquid contained in the rubber chamber of micro scale. The focused laser beam causes explosive bubble growth, and the sudden volume increase in a sealed chamber drives a microjet of liquid drug through the micronozzle. The exit diameter of a nozzle is 125 ${\mu}m$ and the injected microjet reaches an average velocity of 264 m/s. This device adds the time-varying feature of microjet to the current state of liquid injection for drug delivery.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.445-450
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• 2017

ZPP(Zirconium Potassium Perchlorate) is an igniter composed of potassium perchlorate as oxidizing agent and zirconium as fuel with a Viton binder. ZPP is used to provide ignition in the aerospace, propulsion, automotive industries. This research is investigated for the manufacturing process and characteristics analysis of the ZPP such as the performance and shape/calorimetry/pressure characteristics of the ZPP on PMD(Pyrotechnic Mechanical Device). During the production of ZPP, the mixing process was designed so that the ZPP could be produced in uniform particle size and shape by mixing the raw materials at high speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1144-1147
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• 2017

It was reviewed about the pressure oscillation on the inlet of turbo-pump at the moment of engine startup and shutdown. Specially, This research was performed how much is the effect of PSD(Pogo Suppression Device) about the pressure oscillation on the inlet of turbo-pump at the moment of engine startup and shutdown. For analysis, propellant tank PSD and Engine are modelled with Flowmaster which is the commercial 1D program. As the analysis results, even though the PSD is installed in the pipeline, the pressure drop or rising at the moment of engine startup and shutdown is same compared to the case without PSD. However, it was confirmed that PSD reduces the pressure oscillation of the high frequency band as the original purpose of PSD.