• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.168-171
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• 2007

A technical review of current slurry and gelled propellants is presented. In advanced countries, it is confirmed that these propellants have high specific impulse, density, excellent handling, safety characteristics and thrust controllability through research since 1950s. Substantial researches have been pursued to characterize the rheological properties, spray/combustion phenomena and propulsion system design for the gel propellant characteristics. Slurry and gelled propellants are developing actively to applicate both military and space propulsion fields such as tactical missile, air-breathing ramjet, pulse detonation engine, and combined cycle engine of future propulsion mode.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.6
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• pp.95-108
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• 2019

Electric propulsion is a type of space propulsion with a high specific impulse by accelerating propellant using electrical energy and brings about reduction of the fuel mass and launch costs of satellites so that it is being extensively studied in the world. Electric thrusters are widely used for various purposes from micro satellites to large satellites and from low Earth orbit satellites to spacecraft for exploration. Recently, satellites using full-electric propulsion have been developed, and the number of satellites with electric propulsion is also gradually increasing. In this paper, the current status and trends of research on electric propulsion in the United States, Europe, and Japan will be reported.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.72-78
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• 2005

Considerable achievements on scramjet technology have been performed since the end of 1950's when the improvement of performance on ramjet engine was begun. From the viewpoint of rapid and economic efficiency, scramjet propulsion system is presently regarded as the most promising one considered to be applied to the atmospheric hypersonic airplanes and ballistic weapons and even the space launch vehicles. Histories and current trends on scramjet development of USA and Russia are investigated and suggested in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.79-85
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• 2005

Considerable achievements on scramjet technology have been performed since the end of 1950's when the improvement of performance on ramjet engine was begun. From the viewpoint of rapid and economic efficiency, scramjet propulsion system is presently regarded as the most promising one considered to be applied to the atmospheric hypersonic airplanes and ballistic weapons and even the space launch vehicles. Histories and current trends on scramjet development of france, Germany, Japan and Australia are investigated and suggested in this paper.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.11a
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• pp.301-306
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• 2000

Small passenger and car carrier ships are mainly used as a connection way between land and small islands. And these ships should be designed to enlarge the capacity of passenger and car loading within limited space and draft. So the resonances of various vibrations exist in normal operation range of engine and propulsion shafting. In this paper, hull's superstructure vibration which was especially induced by the 1st order excitation of whirling vibration on the 2-engines and 2-propulsion shafting systems is introduced. Also these are verified via the theoretical analysis using transfer matrix method and FEA software ANSYS and its vibration measurement.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.3
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• pp.76-83
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• 2017

Korea Aerospace Research Institute(KARI) has been developing a new launch vehicle Korea Space Launch Vehicle-II(KSLV-II) with their own technology. Thus, it is required a new launch complex that corresponds to a new propulsion system of launch vehicle. Because widely changing of KSLV-II comparing with KSLV-I such as thrust of engine system, composition of vehicle staging, pneumo-hydraulic scheme of propulsion system, it is important to establishing appropriate ground support equipments for fuel(kerosene) filling. In this critical design process, specific supply line and specification of components are designed and the concept of kerosene filling is determined based on results of preliminary design. Also, plans of supply operation and prerequisite are established and operation algorithms are formed.

• Journal of the Korean Society for Precision Engineering
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• v.22 no.7 s.172
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• pp.102-111
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• 2005

In this paper, we address a position control for a parallel stage, which is levitated and driven by electric magnetic force. This consists of a levitating object (called platen) with 4 permanent magnetic linear synchronous motors in parallel. Each motor generates vertical force for suspension against gravity and propulsion force horizontally as well. This stage can generate six degrees of freedom motion by the vertical and horizontal force. A dynamic equation of the stage system is derived based on Newton-Euler method and it's special Jacobian matrix describing a relation between the limited velocity and Cartesian velocity is done. There are proposed two control methods for positioning which are Cartesian space controller and Actuator space controller. The control performance of the Cartesian space controller is better than the Actuator space controller in task space trajectory while the Actuator space controller is simpler than the Cartesian space controller in controller realization.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.46-58
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• 2010

Hydrogen peroxide(HP) and liquid methane have deserved renewed considerations as green propellants in recent years, because main design concerns in the development of the new generation propulsion system for spacecrafts are concentrated on low operation cost and environmental cleanness. Although HP has a long history of application to aerospace propulsion systems due to high density, mono-propellant characteristics and low toxicity, it had been replaced by hydrazine and liquid oxygen due to extreme performance requirement during the cold war. But HP has received a renewed interest due to its increased stability and many researches have been conducted to develop high performance LREs(Liquid Rocket Engines) using HP. Liquid methane has also received a new interest in rocket propulsion system for the future space exploration according to its possibility of ISRU(In-Situ Resource Utilization).

• 시스템엔지니어링워크숍
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• s.4
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• pp.105-107
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.3
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• pp.279-284
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• 2008

Propellant pressurization system in liquid rocket propulsion system plays a role in supplying pressurant gas at a controlled pressure into the ullage space of propellant tanks. The most important design parameter for such propellant pressurization system is the temperature of pressurant gas fed from pressurant tank, which is placed inside of cryogenic propellant tank. Such pressurant is gaseous state, of which density is very sensitive to the temperature of pressurant. Previous investigation dealt with thermal correlation of pressurant and external fluid at room temperature. This study investigates the temperature variation of cryogenic pressurant (GHe) at the time when the pressurant is coming out of pressurant tank, which is submerged in a liquid oxygen, experimentally as well as numerically.