• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제45회 KOSCO SYMPOSIUM 초록집
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• pp.295-296
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• 2012

In Korea, study of monopropellant thruster have been started from 1990s by KARI (Korea Aerospace Research Institute). 5N hydrazine thruster that is a first Koreanized hydrazine thruster, have been used as flight model for several satellite. In parallel, in order to retain core technology for monopropellant thruster, catalyst and test facility development have been carried out and successfully completed. On the basis of these technology, KARI is performing development of 1N/200N hydrazine thruster and basic research of green propellant thruster.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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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.

• 수산해양기술연구
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• 제42권2호
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• pp.111-118
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• 2006

It is indispensable to grasp the turning ability of a ship to operate her effectively. For this purpose, the author measured the turning ability of training ship, A-RA by use of bow thruster and stem rudder. The turning ability of this ship, in case of using both of stem rudder and bow thruster at the same time, caused by increase of steering angle provides more influence to the size of tactical diameter than it caused by the power of bow thruster. But the influence of bow thruster on the turning ability is available only within rudder angle $5^{\circ}\;-\;10^{\circ}$, so it is possible to grasp that the effect of bow truster is reduced as rudder angle become bigger. In case of the influence of bow thruster by her speed, the ability of bow thruster is very effective at low speed, but it is almost not available in normal turning speed. Therefore, the using both of stem rudder and bow thruster can be useful in case of low speed proceeding at entrance or departure of the narrow waterway or inside port which sea traffic is congest for collision avoidance.

• 대한조선학회논문집
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• 제57권1호
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• pp.52-59
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• 2020

This study aims to investigate the bow thruster performance of the research vessel "NARA" by full-scale maneuvering trials. The thruster test method refers to ITTC's recommended procedures and guidelines. Turning tests with the bow thruster are performed at speed conditions of 0, 2, and 4 knots. The test results indicate that the Rate of Turn (ROT) increased when the ship is in a higher speed condition. Due to the position of the propeller and the housing of the bow thruster, there is difference in the efficiency of the bow thruster according to the turning direction. Zigzag tests with the bow thruster were conducted at speed conditions of 2 and 4 knots. At speeds above 4 knots, it seems difficult to change the course only with the bow thruster.

• 한국전산유체공학회지
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• 제21권1호
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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.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2006년도 추계 학술대회논문집
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• pp.101-105
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• 2006

The computational fluid dynamic analysis has been conducted for the thermo-chemical flow field in an arcjet thruster with mono-propellant Hydrazine (N2H4) as a working fluid. The Reynolds Averaged Navier-Stokes (RANS) equations are modified to analyze compressible flows with the thermal radiation and electric field. The Maxwell equation, which is loosely coupled with the fluid dynamic equations through the Ohm heating and Lorentz forces, is adopted to analyze the electric field induced by the electric arc. The chemical reactions of Hydrazine were assumed to be infinitely fast due to the high temperature field inside the arcjet thruster. The chemical and the thermal radiation models for the nitrogen-hydrogen mixture and optically thick media respectively, were incorporated with the fluid dynamic equations. The results show that performance indices of the arcjet thruster with 1kW arc heating are improved by amount of 180% in thrust and 200% in specific impulse more than frozen flow. In addition to thermo-physical process inside the arcjet thruster is understood from the flow field results.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.753-756
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• 2017

기술의 발전에 따라 소형화, 집적화, 그리고 경량화가 가능해지면서, 기존의 중대형 인공위성이 소형 인공위성으로 대체됨으로써 미소 추력기에 대한 필요성이 대두되었다. 레이저 삭마 미소 추력기는 넓은 추력 운용범위와 낮은 단일 임펄스 추력, 그리고 높은 레이저 출력 대비 에너지 비를 가지고 있어 미소 추력기를 대체할 수 있는 세밀한 추력 제어기로서 떠오르고 있다. 본 논문은 레이저 삭마 미소추력기의 구조, 추진제, 그리고 연구 동향을 소개하고자 한다.

• Transactions on Control, Automation and Systems Engineering
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• 제3권4호
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• pp.257-261
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• 2001

Nonlinear pulse width modulation (PWM) controlled system is considered to achieve control performance of thruster controlled spacecraft. The actual PWM controlled motions occur, very closely, around the average model trajectory. Furthermore nonlinear PWM controller design can be directly applied to thruster controlled spacecraft to determine thruster on-time. Sliding mode control for attitude tracking of three-axis thruster-controlled spacecraft is presented. Simulation results are shown which use modified Rodrigues parameters and sliding mode control law to achieve attitude tracking of a three-axis spacecraft with thrusters.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.461-461
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• 2000

Nonlinear pulse width modulation(PWM) controlled system is considered to achieve control performance of thruster-controlled spacecraft. The actual PWM controlled motions occurs, very closely, around the average model rajectory. Furthermore nonlinear PWM controller design can be directly applied to thruster controlled spacecraft to determine thruster on-time. Sliding mode control for attitude tracking of three-axis thruster-controlled spacecraft is presented. Simulation results are shown which use modified Rodrigues parameters and sliding mode control law to achieve attitude tracking of a three-axis spacecraft with thrusters.

• 한국항공우주학회지
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• 제37권5호
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• pp.490-495
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• 2009

소형 인공위성의 궤도천이 및 보정을 위하여 추력이 약 10 mN이고 비추력이 1500 s인 홀 방식 전기추력기를 설계하였다. 개발된 추력기는 홀 방식의 추력부, 전력공급부 및 연료 공급부로 구성되어 있고, 무게, 소모전력 및 효율은 각각 10 kg, 300 W 및 30%정도이다. 개발된 추력기 시스템에 대한 간략한 소개를 홀 방식의 추력기를 선택하게 된 배경해석과 함께 기술하였다.