• Aerospace Engineering and Technology
• /
• v.6 no.2
• /
• pp.180-187
• /
• 2007

Korea Aerospace Research Institute(KARI) is developing Korea Space Launch Vehicle(KSLV). KSLV-I is composed of liquid propulsion system for the first stage and apogee kick motor as the second stage. Kick motor has a high expansion ratio nozzle and its starting altitude is 300km high. To verify the performance of kick motor, high altitude test facility (HATF) to simulate its operating condition is necessary. This paper contains preliminary design for construction of HATF.

• Proceeding of EDISON Challenge
• /
• 2016.11a
• /
• pp.63-67
• /
• 2016

본 연구에서는 극초음속 추진기관을 위한 고공환경 모사 설비 장치에서 시험부 안에 들어가는 시험 모델의 변수에 대해 고찰하였다. 시험부에 적용할 시험 모델을 대상으로 진행하고, 시험 모델 형상 변화에 따른 유동 특성을 파악하였다. 시험 모델에 대한 주요 변수는 폐색율, 각도, 받음각으로 설정하였으며, 해석은 EDISON_CFD에서 제공하는 정렬격자 기반 2차원 압축성 유동 범용 해석 SW로 진행하였다. 해석 결과를 통해 다양한 형상 변수에 따라 변화 되는 충격파 뒤의 압력층 두께를 확인 하였고, 압력층 두께가 두꺼워 질수록 시험 조건을 모사 할 수 없음을 확인하였다. 본 연구를 통해 형상 변수에 따른 극초음속 추진기관을 위한 고공모사설비에서 시험부에 적용될 시험 모델의 범위를 확인하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.475-478
• /
• 2012

In this study, preliminary design of a high-altitude test facility (HATF) was performed to simulate the high-altitude environment using a rocket engine that liquid oxygen and kerosene were used as the propellant. Experimental facility consists of vacuum chamber, supersonic exhaust diffuser, heat exchanger, ejector and gas generator. The vacuum chamber was simulated and maintained high-altitude environmental pressure by supersonic exhaust diffuser. Combustion gas of the rocket engine was cooled by water at heat exchanger after that the mixed gas was emitted to the air by ejector. The ejector which was operated by the steam generator using 75% ethanol and liquid oxygen as propellants and water for steam maintains a vacuum condition.

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

• Journal of the Korean Society of Propulsion Engineers
• /
• v.19 no.3
• /
• pp.73-82
• /
• 2015

A high altitude test facility which includes supersonic diffuser and ejector has been developed to simulate atmospheric pressure at 25 km using a 500 N class small scale liquid rocket engine. Also high altitude simulation test for the small scale liquid rocket engine was performed to verify the facility's performance. The experimental facility consists of high altitude simulation device, propellants supply system and coolant supply system. Low pressure condition corresponding to about 27 km(0.021 bar) altitude atmosphere was successfully simulated and a small scale liquid rocket engine thrust level was confirmed at the simulated condition by the high altitude test facility verification test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.553-556
• /
• 2009

In this study, ignition tests of a gas turbine combustor were performed to evaluate an ignition loop at low temperature condition. An experimental setup was constructed to simulate low temperature condition with a heat exchanger using dry ice as a coolant. Various low temperature conditions could be created by controlling the amount of air though the heat exchanger. The results showed that ignition limit decreased with air temperature.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.14 no.3
• /
• pp.61-68
• /
• 2010

A small high altitude test facility has been developed to investigate ignition performance of a small gas-turbine combustor under high altitude conditions. Supersonic diffusers and a heat exchanger were used to perform a low pressure and a low temperature condition, respectively. Experimental results showed that the low pressure environment could be controlled by upstream pressure of primary nozzle flow and low temperature environment by mixture ratio of cooled air and ambient air. Ignition performance tests were performed to verify the performance of the facility under simulated high altitude conditions. Conclusively, it was proven that the test facility could be used for ignition performance test of a small gas-turbine combustor under high altitude condition of approximately 6,100m.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2007.11a
• /
• pp.31-34
• /
• 2007

Performance tests of supersonic exhaust diffuser were conducted by using hot combustion gas for simulating high-altitude environment. The test rig consists of a combustion chamber, a vacuum chamber, water cooling ring and diffuser. Before combustion experiments, the preliminary leak tests were carried out on the liquid rocket engine and diffuser by using high pressure nitrogen(30barg) and a vacuum pump. The leak test results showed that there was no leaks at high pressure and vacuum pressure conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.632-636
• /
• 2017

In this study, we design an altitude test facility for hypersonic propulsion engine by constructing a test facility and cold flow test. Cold flow test is performed both with and without test models. The results show that the facility can simulate almost similar altitude condition without any significant change in pressure regardless of test models. We also constructed a database that might be useful for a variable test in the future.

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