• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.24-24
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• 2002

가스터빈 엔진의 공력 성능은 작동 유체인 공기의 물성 변화에 대하여 민감하게 반응하는데, 대기 중에 수증기 형태로 함유되어 있는 수분이 공기의 물성 변화를 야기하는 대표적인 요인이다. 건공기와는 다른 화학적 조성을 가지는 습한 공기가 가스터빈 엔진에 유입되면 엔진의 작동과 성능에 2가지 방법(공기 흡입 도관에서의 응축 그리고 엔진 전체 사이클에 걸친 가스 조성 변화 야기)으로 영향을 미친다. 절대 습도가 높은 지상 조건의 무더운 날에는 습공기 유입으로 인한 가스터빈 엔진의 성능 저하가 두드러지며 지상에서의 고공환경시험에서는 시험 당일의 습도 조건에 따라 성능의 차이를 보인다. 해상에서 운용되는 비행체 추진기관으로 사용되는 가스터빈의 경우 특히 높은 습도 환경에서 작동하므로 습도 보정을 통하여 엔진의 정확한 성능과 운용성을 파악하는 것은 중요하다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.325-328
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• 2007

In this study, intended to high flight condition test, air flow test and environmental condition test of Small-sized Gas Turbine (including auxiliary power utility - APU) improve preexisting large size test stand C-9N(SCIAM) in Russia. In the process of developing C-9N test stand, this study includes conceptual design approach. This test stand consists of environmental condition, thermostat, cooling/drying, thrust measuring system and SAR (system of automatic regulation).

• 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.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.41 no.9
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• pp.563-570
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• 2017

Experimental and numerical studies were performed to investigate the performance and internal flow characteristics of a supersonic second throat exhaust diffuser (STED) with back pressure ($P_a$). An ejector system was used to vary the back pressure ($P_a$) conditions. The operating gas for the STED and the ejector was high pressure nitrogen at room temperature. When the back pressure ($P_a$) at a constant nozzle inlet pressure $P_0$) decreases, the pressure recovery location moves downstream. If the pressure ratio $P_0/P_a$) is the same, even if the nozzle inlet pressures $P_0$) are different, the diffuser's internal flow pattern and starting pressure ratio ($(P_0/P_a)_{st}$) are almost the same.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.189-192
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• 2003

This paper summarizes a satellite program-specific performance requirements and test results for the verification of standard mono-propellant hydrazine thruster (MRE-1) producing 0.95 lbf (4.2 Newtons) nominal steady-state thrust at an inlet pressure of 350 psia (2.41 Mpa). Performance characteristics are shown in terms of thrust behavior at steady state and pulse mode firing. Hot firing test philosophy is briefly introduced, too.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.6
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• pp.56-65
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• 2008

• 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 Korea Water Resources Association Conference
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• 2005.05b
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• pp.1383-1387
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• 2005

사면의 식생이 초기에는 강우에 의해서 표면흐름, 지하수위 증가, 지표수의 침윤에 의해서 성장이 될 수 있으나, 시간이 경과함에 따라 식생에 의한 사면의 안정성을 확보 하는 데에는 큰 영향을 미치지 못한다. 즉, 사면의 식생을 복우언시켜 식물근(뿌리)에 의해서 사면을 안정화 시키기 위해서는 사면의 위치, 고도 및 방향 등에 따라 적응할 수 있는 식물의 선택과 성장에 충분한 수분을 보습할 수 있는 구조의 사면계획과 구조물 설치가 필수적이다. 본 연구에서는 절$\cdot$성토면에서 경사면의 붕괴를 방지하고 식생을 복원하는 방법으로 Mattress Gabion을 제안하였다. 정형화되고 유연성 있는 다공성 Mattress 구조를 통한 식생의 복원은 사면의 안정과 환경친화적인 목적을 모두 만족할 수 있었다. 특히, Gabion 근고공이 설치된 이후에 공극이 큰 Mattress 구조물을 중심으로 식물의 뿌리를 지반에 직접 연결하거나, 식생 활착이 어려운 암반 절취 사면에서도 Mattress 옹벽을 통해서 식물이 양질의 흙에 직접 활착할 수 있도록 설계한 사면 Mattress의 경우는 사면의 안정성 증대와 아울러 지하수의 표면흐름과 투수 및 침윤에 의한 식물의 성장피해를 최소화하고 시간이 지날수록 식생에 의해서 Mattress Gabion 옹벽이 내구성과 유연성을 유지할 수 있었다.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.428-431
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• 2008

Korea Aerospace Research Institute(KARI) is achieving the Korea Space Launch Vehicle(KSLV) program according to National Space Technology Development Program. KSLV-I will be composed to liquid propellant(first stage) and solid propellant(second stage) propulsion system. The propulsion system of KSLV-I second stage is solid kick motor with high expansion ratio and its starting altitude is 300km high. 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. High Altitude Simulation Test Facility is composed to Thrust Measurement System, Control & Measurement system, Diffuser, SKID for cooling water supply to diffuser, CCTV, fire protection system and so on. This paper introduces TMS adapted to High Altitude Simulation Test for KSLV-I Kick Motor Development and results of hot firing test for its performance verification.