• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.572-582
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• 2017

It is definitely important to measure thrust during ground test when developing air-breathing engine, and in case of air-breathing engine, gross thrust should be calculated considering not only the measured thrust but also the force induced by the air flow of engine intake. Also, side thrust like yaw and pitch should be measured and analyzed using multi-component thrust measurement system. Engine performance was accurately evaluated by calculating the gross thrust of air breathing engine precisely which is analyzed from below serial procedure: labyrinth seal isolation, 1-axis gross thrust calculation, develop multi-component thrust measurement system, and side thrust analysis.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.97-108
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• 2018

It is definitely important to measure thrust during ground test when developing air-breathing engine, and in case of air-breathing engine, gross thrust should be calculated considering not only the measured thrust but also the force induced by the air flow of engine intake. Also, side thrust like yaw and pitch should be measured and analyzed using multi-component thrust measurement system. Engine performance was accurately evaluated by calculating the gross thrust of air breathing engine precisely which is analyzed from below serial procedure: labyrinth seal isolation, 1-axis gross thrust calculation, develop multi-component thrust measurement system, and side thrust analysis.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.78-83
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• 2012

Generally, the first stage of a launch vehicle requires high thrust to achieve a mission. We can use one high thrust level engine or a clustered engine system which made of several small thrust level engines to make high thrust. The first stage propulsion system of KSLV-II has 300tf thrust to satisfy the mission. But it is impractical to make high thrust by one engine at this moment in time. So we should cluster four 75tf class engines which can be applied to make a required thrust for the first stage propulsion system. This article deals with the concept of the first stage clustered engine arrangement of KSLV-II.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.55-59
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• 2008

It is very difficult to measure an accurate thrust for the performance test of liquid rocket engine. Liquid rocket engine is attached to the propellant feed system, control valve and many other safety systems. Without considering these effects, thrust data measured from the firing test is not reliable and meaningless. In this research, the modified thrust measurement system, which includes both all these side effects is developed for the verification of low thrust liquid rocket engine performance. In addition, reliability appraisal technique is studied to secure the reliability of thrust measurement system.

• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2006.05a
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• pp.395-398
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• 2006

this paper provides a novel method to start the linear engine coupled linear generator from dead stop to its final steady state operation. This method depends mainly to use the linear generator mounted on the shaft of the linear engine to provide the required thrust force to move and oscillate the linear engine from bottom to top dead centers. It is a cost effective approach to start the internal linear combustion engine using its coupled tubular permanent magnet linear generator proposed here. This linear generator operates in this case in motoring mode, providing the required thrust force by feeding this linear generator phases with currents by using a three phase PWM inverter controlled by position feedback scheme. In order to provide the desired thrust force with specific value and direction, a position feedback is required to control the free piston engine motion through controlling the inverter switches using PWM control scheme.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.1-7
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• 2002

During the preliminary design phase of aircraft development, it is necessary to evaluate many potential engine/airframe combinations to determine the best solution to given set of mission requirements and it is very important to establish a methodology to calculate precisely engine installed performance. It was carried out to calculate turbofan engine installed performance of a supersonic aircraft for a given engine/aircraft configuration. Thus "Thrust minus drag accounting system" was introduced to identify and calculate the elements of installed thrust or installed propulsive force by using the database based on wind tunnel test data. This paper describes the calculated results of installed thrust of turbofan engine for a supersonic aircraft. aircraft.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.4
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• pp.19-27
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• 2021

In this study, a high-pressure subsacle thrust chamber was developed to verify the core technology for KSLV-II performance enhancement. The core technologies are the design of an injector for high-pressure combustion, development of a combustion stabilization device using the additive manufacturing technique, and the design and fabrication of mixing head and regeneratively cooled combustion chamber. The core technologies, which have been verified through the development of high-pressure subscale thrust chamber, will be used to develop large engine liquid rocket engine thrust chamber in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.574-577
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• 2012

Thrust measuring is one of the crucial factor to decide the performance of a liquid rocket engine when the engine development test, especially for the combustion chamber, is implemented. Calculating the thrust from a combustion pressure is used when direct measuring the thrust is impossible, but direct measuring the thrust is necessary and various methods for doing it more precisely should be considered. This paper introduces the preliminary design concept about the new thrust measurement system for the vertical firing test stand, which is introduced domestically for the first time, of a liquid rocket engine combustion chamber.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.1
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• pp.39-46
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• 2002

It is very difficult to measure an exact thrust in liquid rocket engine compared to solid rocket motor, however it is very important to estimate a performance of engine for developing rockets. To get a good result, we have to concern about errors of measurement and find a method of calibration. In this research, we developed new thrust measurement system for liquid rocket engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.3
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• pp.9-19
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• 2009

Accurate thrust measurement is very important when developing an engine of propulsion system. Especially for a low thrust liquid rocket engine(LRE), accuracy of thrust is seriously affected by thrust measurement errors and thurst losses which are caused by propellant supply system. In this study, a new thrust measurement system is developed for accurate thrust measurement of a low thurst LRE by minimizing these effects. Its thrust measurement range is 150~1500N and the maximum error is below 10N. Also, a reliability appraisal technique is investigated to improve reliability and accuracy of the thrust measurement system.