• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.76-86
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• 2008

The EP(electric propulsion) is unique in that several energy sources can be utilized to produce the electric energy and that high exhaust velocity can be achieved compared to the conventional chemical propulsion. Though a lot of variety of non chemical propulsion are under study, the fact that the EP's specific impulse ranges widely from 200s to 5000s led most research to concentrate on the electric propulsion research. This paper, therefore, is aimed to introduce the up-todate existing EP family such as electrothermal, electrostatic and electromagnetic thrusters where its operating concepts, characteristics and possible variants are presented for future applications.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.550-552
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• 2008

A small hall thruster with a thrust of about 10 mN and a specific impulse of about 1500 s is being developed with an intent to control or maintain the orbits of small satellites. The total mass, consumed electric power and efficiency of the thruster are approximately 10 kg, 300W and 30%, respectively. The thruster system consists of a hall thruster with a cylindrical cross section, a power processing unit and a Xenon(Xe) gas feed system. Laboratory examination of the thruster performance finds that the thruster meets the design specification.

• Journal of Navigation and Port Research
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• v.29 no.4
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• pp.335-339
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• 2005

The superconducting electromagnetic propulsion system has been proposed as one of new alternative propulsion systems. Especially, the helical-type propulsion system has the greatest merit that is able to use the solenoid-type superconducting magnets with high magnetic fields. In this study, calculations of characteristics of the large scale helical-type thruster are carried out on the basis of our experimental results. As a couple of results of calculations, it is found that the thruster efficiency quickly increases with the length of electrode up to about 5 m and then goes up to about 0.9. The thruster efficiency peaks at a certain point ($^{\sim}0.6\;m$) and then falls as length of pitch increases.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.254-257
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• 2011

Two types of thrusters(Descent Control Thruster (DCT) for reducing landing speed and Attitude Control Thruster (ACT) for attitude control) are mounted on the propulsion system of Ground test model lunar lander. In this paper, plume impingement effect and ground effect between DCT Modules are analyzed using numerical method when the impact occurred close to the ground.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.14 no.9
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• pp.1965-1971
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• 2010

A ship propulsion thruster platform which is used by safety sailing takes charge of remote control of a main engine in ship. This system not only guarantees safety and reliable flight sailing but also require remote control technology of a ship. Accordingly, in this paper it deals with a telegraph lever control unit system which is a part of propulsion thruster system as localization technology. Also it makes sure of knowledge and core technology through analysis and designing and developing a telegraph lever control unit system. Moreover, it is sure of acquisition of base technology for integration of a ship propulsion thruster platform.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.137-141
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• 2004

Many monopropellant thrusters use a catalyst for decompose the propellant, hydrazine. The catalyst directly affects the thruster performances and lifetime. Therefore, it is important to confirm that the catalyst is suitable for our thrusters. Until 2002, we used She1l405 catalyst, for satellite RCS thrusters, and H-IIA and M-V launch vehicle upper-stage RCS thrusters. In 2002, however, Shell Chemical Inc. ceased manufacturing She1l405 catalyst and transferred the product to AEROJET, where it was renamed S405. We subsequently investigated the characteristics of AEROJET's S405 catalyst and SOLVAY's KC12GA catalyst, (SOLVAY is a Belgian chemical company, and KC12GA is used for ASTRIUM's thruster) and conducted thruster firing tests using the new catalysts. After conducting, we confirm that the KC12GA catalyst was suitable for our thrusters, and decided to use KC12GA for two satellite programs.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.278-281
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• 2005

This paper present a study of size effect on electrostatic colloid micro thruster. According to results about size effect experiments indicates that the proposed mechanism allows at less than 500 volt of operating voltage for the micro thruster.

• 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.

• Journal of the Society of Naval Architects of Korea
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• v.59 no.1
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• pp.46-54
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• 2022

A magnetohydrodynamic (MHD) seawater propulsion thruster has been proposed to reduce propeller noise, propeller pitting, and vessel vibration originated from the propeller cavitation. The MHD thruster was also focused to overcome the limitation of propulsion velocity for the special purpose of marine ships. The research trends and key technologies in the worldwide leading countries are reviewed for the development of MHD propulsion thrusters in Korea. A small performance test device was developed firstly with a conventional solenoid magnet of ≤0.6 Tesla and a helical-type cylindrical duct(inner diameter of 5 cm) of thruster. The artificial seawater was fabricated by a salt solution including a conductivity of 5~6 S/m. The measured flow velocity of artificial seawater in the test device was 0.03~0.42 m/s (0.06~0.84 Knot) with a magnetic field strength of 0.6 Tesla and the applied currents of 10~80 A including the change of anode materials. It was found that the flow direction of seawater was reversed by the directional change of applied current in the solenoid magnet.

• Journal of computational fluids engineering
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• v.21 no.1
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• pp.72-77
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• 2016

In this study, effects of thurster axis tilting angle on the thruster-hull interaction and propulsion performance in a dynamic positioning system of offshore plant are numerically investigated. Straight and 7-degree tilted downward thruster models as a form of ducted propeller are considered. For numerical simulations, Reynolds averaged Navier-Stokes equations with SST turbulence model are solved by using STAR-CCM+. Results show that thruster-hull interaction is reduced in 7-degree tilted thruster model with lower vortex strength between thruster and hull bottom, although the propulsion performance does not have noticeable difference in a bollard condition.