• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.1
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• pp.37-43
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• 2008

In order to verify the performance of upper stage propulsion system designed to operate in the upper atmosphere, test facility which can simulate high altitude is needed. Cylindrical supersonic exhaust diffuser, which utilizes the momentum of exhaust gas, provides a simple means for providing a low pressure around the propulsion system. This paper describes sub-systems and specification of high altitude test facility developed for the test of KSLV-I kick motor. Performance of the facility has been successfully verified through five times of hot firing tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.45-48
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• 2007

Vacuum facility is required for high altitude space environment test to develop small thruster. We, at Chungnam National University, developed vacuum test facility up to $10^{-5}$ torr to simulate 100${\sim}$120 km altitude environment. In this paper, we present some preliminary performance test results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.12
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• pp.1195-1201
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• 2010

Performance tests of a supersonic exhaust diffuser were conducted by using a liquid rocket engine for simulating high-altitude environment. The experimental setup consisted of a combustion chamber, a vacuum chamber and a diffuser. The combustion tests for simulating high-altitude environment were carried out at three cases by chamber pressure variation(26, 29, 32barg). The test results showed that the diffuser was started at all case and vacuum chamber pressures were approximately 140torr. The starting pressure using combustion gas was similar with that of cold gas, but the vacuum chamber pressure was relatively high because of high temperature in the vacuum chamber. The results of this test can be used as an essential database for the design of real-scale high-altitude simulation test facility in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1148-1152
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• 2017

To simulate a high altitude for rocket at sea level, the test facility should provide a sufficiently low pressure environment. Center Body Diffuser(CBD) is those applied for high altitude simulation test facility. To elucidate the flow characteristics of center body diffuser with various the center body location, numerical analyses using ANSYS FLUENT were performed. The result of this study is deemed to be valuable as a data base for the operation of the Center Body Diffuser.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.705-708
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• 2011

Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an design procedure on the configuration and operating condition of multi-ejector for the various high altitude simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.647-650
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• 2017

As the necessity of development of supersonic vehicle increases, securing an aerodynamic data from low to high altitude is requested for flying vehicles crusing in various high-tech environment. Therefore our research team built equipment by improving heating device of Model Aerodynamic Facility(MAF) of Konkuk University to simualte a real gas environment. Guided weapon system and temperature and velocity distribution according to the flow that is produced from the pier of supersonic vehicle is planned to be researched by using this equipment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.153-156
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• 2008

Ignition and combustion performance of a gas-turbine engine were changed by various high-altitude condition. A goal of this study is to make the small test facility to simulate high-altitude condition. To perform the low pressure condition, a diffuser was used in various diffuser front of primary nozzle pressure. To perform the low temperature, heat exchanger was used in various mixture ratio of cryogenic air and ambient temperature air. The experimental result shows that high-altitude conditions can be controled by diffuser front of primary nozzle pressure and mixture ratio of cryogenic air and ambient temperature air.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.49-52
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• 2007

Vacuum facility is required for high altitude space environment test to develop small thruster. We, at Chungnam National University, developed vacuum test facility up to $10^{-5}$ torr to simulate $100{\sim}120km$ altitude environment. Prior to operation, we predict vacuum pump performances and present preliminary calculation and experiments.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.827-829
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• 2011

Vacuum facility is required for high altitude space environment test to develop satellites or space launch vehicles. We, at Chungnam, National University, developed turbo molecular pump vacuum test facility up to $1.0{\times}10-6$ torr to simulate 200 km altitude environment. In this paper, we present some preliminary vacuum performance test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.403-404
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• 2008

The 2nd stage Kick Motor under the national aerospace middle and long term plan operates over the height of 300Km. Rocket Motors, designed for operation in high altitude, need nozzles with large expansion ratio to improve thrust efficiency. Hence, to evaluate the performance of such rocket motors on the ground, similar low pressure with the operating condition has to be made for the ground test to prevent flow separation in the nozzle. This study is for the installation of the high altitude test facility and test result for Kick Motor.