• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.216-220
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• 2006

In this study, it was investigated that the characteristics of startup and compatibility using several type hot and cold gases. The characteristics of starting LRE by pyro starter was compared with that by a He spinner. The compatibility of pyre gas, a gaseous He, H2+N2 mixture gas, and air was investigated by a simple 1D turbine analysis considered the properties of each gases and turbine efficiency. Most of them were compatible to start up the LRE but air was properly used only when the turbine was low power mode.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.5
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• pp.109-115
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• 2004

A 1-D system design program has been developed for the preliminary design of the turbopump system in liquid rocket engines, which use LOx and kerosene as propellants. Gasgenerator cycle and staged combustion cycle were considered as turbopump type liquid rocket engine systems. In the system analysis, mass flow balance, thrust, specific impulse, mixture ratios, turbopump power, and turbine expansion ratio of engine system were analyzed. Results show that most of the parameters agree well with real engine parameters except gasgenerator. Therefore, the l-D system design program developed in this study can be used to derive the preliminary design parameters of a turbopump with any thrust level liquid rocket engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.71-80
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• 2010

The KSLV-II(Korea Space Launch Vehicle-II) which being a successor of the KSLV-I is a space launch vehicle capable of delivering 1.5 ton-class satellite into a low earth orbit. The development of a 75 tonf-class liquid rocket engine(LRE) is planned on the basis of the technologies mastered through the preceded research of a 30 tonf-class LRE. The thrust chamber of the LRE is required to have higher combustion stability, structural integrity and thermal durability. This paper deals with the design requirements of the 75-tonf thrust chamber and a variety of technical considerations which have been conducted analytically in the course of the design for the realization of the requirements.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.134-140
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• 2007

Since the successful launch of Sputnik 1, a rocket engine was evolved rapidly. The first artificial satellite Sputnik has only 182 lb mass with a size of a basket ball, a modern artificial satellite is over 10 tons. As the size and the mass of an artificial satellite increases, the stronger launch vehicles are required. However, the story is different in the field of the rocket engine development. In the early to mid age of the space race, rocket engine study was focused on the stronger and bigger engine development, but from the 80's the tide has changed. A rocket engine must be strong and also economic. This trend was accelerated from when a rocket launch was used commercially. In this study, a capability of the launch vehicle and engine was investigated to provide a reference for a liquid rocket engine development plan.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.15-18
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• 2009

Technology demonstration for the development of a 75-tonf liquid rocket engine(LRE) thrust chamber for a space launch vehicle has been started on the basis of the previously acquired 30-tonf LRE technologies. For this purpose, a technology demonstration plan was established upon considering the currently available firing test facility in Korea and performance evaluation firing tests were performed on technology demonstration model thrust chambers under a restricted test condition. This paper describes the plan and current status of technology demonstration for a 75-tonf LRE thrust chamber.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.141-146
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• 2002

During dynamic flight by propulsion of rocket engine, in the atmosphere, the attitude control of flight vehicle can be accomplished by the aerodynamic fin actuator. But, in the outer space, the method of TVC(Thrust Vector Control) is only depend on for it. There are many systems which were developed for TVC. In our research, among them we adopted gimbal engine actuation system which could control the vector of thrust by swivelling rocket engine connected by gimbal. There are electro-hydraulic, electro-mechanical and pneumatic system which can be used as gimbal engine actuation system, but the electro-hydraulic system that has high ratio of output power to mass is preferred for the high power system. In this note, we made a mathematical model of the electro-hydraulic gimbal engine actuation system for the TVC of KSR-III in detail and on the base of this model we performed a simulation study. And then, we verified the model by making a comparison between the simulation and the experiments on the real system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1057-1059
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• 2017

In development of liquid-propellant rocket engine, engine gimbaling requires various types of bellows movements and cryogenic insulation is applied with movement-based design and material on each axial and circular bellows. Cryogenic insulation of Bellows for high pressure line and recirculation line are necessary to maintain cryogenic temperature for engien efficiency and protect from heat transfer and radiation of high temperature components during engine gimbaling.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1054-1056
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• 2017

The Preparation for a flight test of the launch vehicle to verify the performance of the liquid rocket engine(LRE) is proceeding. Flight test of liquid rocket engine costs an enormous amount of money, has a restriction on measurement channels, so it requires the optimal measurement plan to check the prelaunch operation and determine the cause of abnormal situation. This paper surveys the foreign sources for LRE flight test. In recent years, as the tendency to eliminate all faults of LRE at the ground test the number of flight test is decreasing and in contrast, the number of measurements and measurement accuracy is increasing. This paper may be used as a reference for the preparation of an LRE flight test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.928-929
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• 2017

A 75 ton class liquid rocket engine has been developed for KSLV II. Ground firing tests of the rocket engine were conducted to characterize and quantify its structural vibration under combustion testing environments. In this study, evaluation of dynamic response characteristics of the engine system was presented to verify its structural integrity and structural design during ground firing tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.6
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• pp.120-125
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• 2020

75 tonf liquid rocket engine combustion test was performed at Naro space center Engine Combustion Test Facility for KSLV-II. A gradual pressure drop was observed during off-design combustion test turbopump inlet condition using cooled kerosene at 271 K. It was found that the water content inside kerosene could cause pressure drop at 40 ㎛ grade filter through the water contests analysis of kerosene, kerosene cooling test and dehydration of kerosene.