• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.96-104
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• 2003

Geostationary satellite propulsion system provides satellite with the velocity increment for attitude control operations and sationkeeping operations from satellite launch to de-orbit at the end of life. Today, various types of propulsion system and its thrusters are produced by worldwide manufactures. Therefore, geostationary satellite manufacturers give significant modification to the Mission Analysis Software whenever different type of propulsion system type is adopted. Mission Analysis Software is a tool for planning and verification of satellite mission. For the development of the Generalized Mission Analysis Software, many thrusters are carefully investigated and modeled.

• Proceedings of the KIEE Conference
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• 2007.10c
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• pp.95-97
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• 2007

This paper proposes a mathematical modelling about Leviation Force and Propulsion Force in a system, where Primary and Secondary LSRM air-gap is irregular. This can be a suitable model for Magnetically levitation Train, where Primary and Secondary air-gap mechanically has to control simultaneously Levitation Force and Propulsion Force.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.456-459
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• 2011

The Dual-type Solenoid Valve was developed for a domestic production of a fuel-supply valve on the satellite attitude control thruster system. The satellite valve using a hydrazine as a fuel must fulfill the cycle life, shock, vibration and the environment of an extremely low temperature In addition to the basic performance of the response time, mass flow and leakage etc.. in this paper, the design, production and performance experiment using the nitrogen pneumatic equipment were conducted.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.793-794
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• 2011

In launch process, propellants should be supplied with established temperature range for engine normal operation. In order to satisfy this temperature condition, propellant feeding systems should be considered some effects during operation. This paper studied liquid oxygen filling system operation process and cooling method of liquid oxygen during launch process.

• Proceedings of the KIEE Conference
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• 2001.07b
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• pp.1245-1247
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• 2001

This paper discusses that the maintenance of the propulsion equipment in railway rolling stock. Condition monitoring of railway equipment is the need for integration of remote condition monitoring with maintenance management strategies. The paper outlines research leading to the design and development of a prototype control and monitoring system for propulsion equipment.

• The Journal of Korea Robotics Society
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• v.5 no.3
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• pp.197-208
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• 2010

The ostraciiform swimming mode allows the simplest mechanical design and control for underwater vehicle swimming. Propulsion is achieved via the flapping of caudal fin without the body undulatory motion. In this research, the propulsion of underwater vehicles by ostraciiform swimming mode is explored experimentally using an ostraciiform fish robot and some rigid caudal fins. The effects of caudal fin flapping frequency and amplitude on the cruising performance are studied in particular. A theoretical model of propulsion using rigid caudal fin is proposed and identified with the experimental data. An experimental method to obtain the drag coefficient and the added mass of the fish robot is also proposed.

• Proceedings of the KSR Conference
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• 2005.11a
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• pp.1021-1027
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• 2005

The Diesel Multiple Units (DMU) is a successful mass transportation system, that is being, continuously, on demand by train operators and railway authorities around the globe. One of its advantages is the fact that a diesel engine, along with the correct propulsion and control equipment, could also be used on either Electrified or Non-Electrified Railway Lines. Currently, there are almost 12,000 DM Units being used worldwide and the demand is on the increase. This paper describes the special features as well as the advantages/disadvantages of the different types of the DMUs according to the propulsion systems that are employed, to help establish a trend in the DMU market.

• Proceedings of the KIEE Conference
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• summer
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• pp.1319-1321
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• 2004

This paper presents a model and simulation for the korean type multi-propulsion system consisting of a gas turbine driven synchronous alternator coupled to a rectifier and dc-to-dc converter. The simulation modules include turbine system, alternator and rectifier, dc-to-dc converter, power management module. A modular, system level simulation of the propulsion system prototype is presented in order to confirm stability for loads with uncertain input impedances and uncertain control loop speeds.

• Journal of Electrical Engineering and Technology
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• v.7 no.2
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• pp.200-206
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• 2012

In order to develop a deep-underground great train express (GTX) in South Korea, the specifications decision and development of a traction control system (including an inverter and a traction motor), which considers a variety of route conditions, must be advanced. In this study, we examined the running resistance properties of a high-speed traction system based on a variety of tunnel types and vehicle organization methods. Then, we studied the power requirements necessary for the traction motor to maintain balanced speed in the high-speed traction system. From this, we determined the design criteria for the development of a high-speed traction system for use in the deep-underground GTX. Finally, we designed a linear induction motor (LIM) for a propulsion system, and we used the finite element method (FEM) to analyze its performance as it travelled through deep-underground tunnels.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.5
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• pp.67-74
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• 2019

In this paper, mathematical models of a simulation code are presented. The simulation code was developed for the startup analysis of an open cycle liquid rocket engine (LRE). Most of the components comprising an LRE, including the priming process in the propellant feeding line, were considered. A startup simulation of a 75-tonf LRE, which was used for the KSLV-II test launch vehicle (TLV), was performed. The simulation results showed good agreement with the engine acceptance test results, thus proving the validity of the startup simulation code.