• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.251-254
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• 2008

Ground firing test facility and test field for firing test of hybrid rocket engine were constructed. Ground firing test facility were composed of hybrid rocket engine, thrust stand, oxidizer storage/supply system, control system and data acquisition system. Firing tests of thrust 50 kgf class were conducted. Stable performance data was obtained and operational reliability of ground firing test facility were found.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.165-169
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• 2007

Qualification test range for Lox/Kerosene gas generator cyle liquid rocket engine was determined by considering engine dispersion and flight inlet conditions. With various pump characteristics, the operation range of components and system was investigated through dispersion analysis. The variation of engine performance shows opposite trends in calibration and dispersion.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.6
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• pp.91-97
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• 2011

A test range for a 75tf class gas generator cycle liquid propellant rocket engine is defined. The engine system test range is defined by the performance variation during flight, the dispersion after engine calibration, and additional margin. The component development test range includes the operation range corresponding to the engine system test range and the component performance margin.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.51-56
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• 2011

A test range for a 75tf class gas generator cycle liquid propellant rocket engine is defined. The engine system test range is defined by the performance variation during flight, the dispersion after engine calibration, and additional margin. The component development test range includes the operation range corresponding to the engine system test range and the component performance margin.

• International Journal of Aeronautical and Space Sciences
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• v.3 no.2
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• pp.59-66
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• 2002

A vertical test stand based on launcher propulsion system was constructed and several tests for the determination of cyclogram were carried out. To make an accurate estimation, static and dynamic pressures were measured and analyzed. Especially, static pressure measurements using fast response sensors without extension tubes were used to determine operation sequence more evidently. The standard operation times of final valves were determined in cold flow tests with an engine head, and fire formation time in combustion chamber was checked in an ignition test with an ignitor only. On the basis of these tests, ignition sequence was established and combustion test cyclogram was finally determined. According to combustion test, test results were well matched with the determined cyclogram within 0.05 sec.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.77-80
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• 2006

Insensitive Munitions(IM) of solid propulsion system are defined as munitions that fulfil the performance and operational requirements, but will minimize the violence of a reaction when subjected to inadvertant stimuli. It should be clear that the reaction violence of rocket motor subjected to thermal stimuli can be mitigated by reducing confinement prior to propellant reaction. Devices designed to do this by venting the rocket motor case are commonly referred to as mitigation devices. The objective of this paper is to introduce the technical information related to the pyrotechnic mitigation devices for insensitive munition of solid rocket motor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.352-358
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• 2011

This paper describes on the study of mitigation technique in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. SCO test was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The rocket motor in SCO test was located in an oven at $50^{\circ}C$ for 7 hours. The temperature was regulated to be elevated at the rate of $3.3^{\circ}C$ per hour. Results showed Type V(Burning) reaction in this SCO test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.807-808
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• 2010

To insert payload to the orbit over the 200km-altitude using launch vehicle which has 300sec the Isp, multi staging technique for launch is necessary. The range between the sea-level to the transfer orbit about 200~250km is for operation of 1st and 2nd rocket engines and the higher altitude is for propulsion system of the acceleration block and satellite. The upper stage rocket engine should have the high technology for entering the payload into the orbit precisely more than the performance for high thrust level. With this investigation of the upper stage rocket engines which have been used, we want to understand their development trend and prospect which is going to be references for the development of ours.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.2
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• pp.16-23
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• 2001

For liquid rocket engine test, one of most important design parameters to be measured is thrust. However, not like solid rocket motor, a 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 firing test is not reliable and sometimes almost meaningless. In this research, new thrust measurement system, which includes all these side effects, was designed and fabricated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.53-56
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• 2006

This paper describes performance design of a solid rocket motor on which thrust cut-off system is installed, and evaluates performance of a rocket motor according to a size of TCO ports. TCO system installed on motors was made to carry out firing tests, and the trend of thrust due to various sizes of TCO port was analyzed to find the existence of the port size for maximum reversal thrust. Conservation equations were used to design performance of motors and to analyze test results. This technique for performance design will be usefully applied to the design of similar TCO systems.