• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1996.04a
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• pp.161-161
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• 1996

본 연구에서는 차량(승용차) 시동용 수퍼캐패시터-밧데리 조합시스템에 적용할 시작품 전기이중층 수퍼캐패시터(super-capacitor:SC)를 설계 제작 개발하고 그 성능 특성을 확인하였다. 재래식의 차량용 밧데리의 비동력(specific power)이 100~200 W/kg에 비하여 전기이중층 SC의 경우는 1,000~3,000 W/kg으로 단위 총량당의 동력이 매우 크다. 또한 충방전시의 화학반응이 없는 관계로 인하여 충전식 2차 전지에 비하여 사용수명이 매우 길다. 이러한 SC를 기존의 밧데리와 함께 조합하여 차량 시동용으로 사용하게 되면 밧데리의 사용수명을 2~3배 길게 할 수 있으며 밧데리는 시동에 필요한 큰 전류의 방전이 요구되지 않으므로 그 용량과 크기가 대체로 절반이상 줄어든다. 또한 매우 낮은 온도의 기후조건에서는 밧데리의 방전효율이 급격히 저하되므로 이를 대비하여 필요 이상의 과용량, 과중량 밧데리의 사용이 실제로 행해지고 있으나 조합시스템의 차량 시동시에는 SC가 갖는 특성상 -5$0^{\circ}C$까지의 기후조건에서도 방전효율이 크게 저하되지 않은 채 시동전류를 공급해주므로 혹한지역이나 혹한시의 차량시동에도 탁월한 시동성능을 갖는다. 설계 제작된 SC는 저장에너지 6KJ, 정격전압 12Volt, 설계축전용량 70F 그리고 사용은 도 범위가 섭씨 영하 25도에서 영상 50도이며 무공해성 수용성 전해질을 사용하였으며, 제작된 CS는 사용온도 범위에서 축전용량 65F - 85F, 내부저항 1.8mOhm - 5.2mOhm의 변화를 보였으며, 정상시동에 필요한 방전전류 300Amp의 경우 2.6초의 방전시간, 약 89%의 방전효율을 보였다. 현재까지 상온하에서 30.000회의 충방전 시험결과로서는 방전효율의 저하가 없는 양호한 성능을 보였으며, SC의 시범 작동시험을 실차(소나타 1800cc)에 장착하여 수행한 결과 20회 이상의 연속시동에서도 아무런 문제점 없이 잘 동작하였다.

• The Proceedings of the Korean Institute of Illuminating and Electrical Installation Engineers
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• v.9 no.2
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• pp.117-117
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• 1995

본 논문에서는 콤팩트 형광램프용 Dimming형 전자식 안정기의 설계에 있어서, 인버터 공진탱크의 커패시턴스값을 변화시킬 때 전압이득곡선을 분석하여 최적의 회로정수를 결정하는 방법을 제안하였다. 또한 하프브리지 인버터회로의 회로정수에 대한 PSpice 시뮬레이션을 행하여 램프전압과 전류값을 구하였고, 실제 전자식 안정기를 제가하고 시동특성과 조광특성을 비교분석하였다. 시동특성은 일반 전자식 안정기와 거의 동일하였으며, 조광특성은 전체 광출력의 5%까지 안정동작되어, 제안된 방법이 뛰어남을 확인하였다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.2
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• pp.93-102
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• 2016

An experimental study has been conducted to verify the startup characteristic of a Center Body Diffuser (CBD) for simulating a low pressure environment when at high altitudes. Vacuum chamber pressure and startup characteristics of the CBD were investigated according to various geometries of the center body structure by a cold gas flow test. The test results show that the startup pressure is lowest when the center body contraction angle is approximately $15^{\circ}$. The startup characteristic of the CBDs significantly improves when the diffuser inlet length ($L_d/D_d$) is decreasing and the divergence length ($L_s$) is increasing. Additionally, it is possible to simulate various high altitude, low pressure conditions for various rocket engines that have different nozzle expansion ratios by adjusting the center body's position inside the diffuser.

• 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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• 2008.11a
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• pp.299-304
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• 2008

Starting characteristics of the axi-symmetric second throat exhaust diffuser (STED) with zero-secondary flows are numerically investigated. Renolds-Average Navier-Stokes equations with a standard ${\kappa}-{\varepsilon}$ turbulence model incorporated with enhanced wall treatment are solved to simulate the diffusing evolutions of the nozzle plume. Minimum (optimum) starting pressure difference of 20$\sim$25% between 1-D theory and the measured data validated from previous results[5] is also applied to predict the range of an effective diffuser expansion ratio (Ad/At) in this system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.7-10
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• 2009

The development and evaluation of solid propellant were performed for the turbopump pyro starter, which start up the liquid propellant rocket engine for the Space Launch Vehicle (SLV). Requirements for the turbopump pyro starter propellant include the production of low flame temperature, low burning rate and nontoxic gas to protect the mechanical corrosion or air pollution. This study describes the development of the solid propellant composition which is based on PCP binder. DHG (Dihydroxy glyoxime), which has advantages of oxygen balance and ignition, was used as coolant. The mechanical properties and burning rate of the propellants were measured. Finally, static fired test was performed to prove the possibility of development.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.117-121
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• 2012

Upper stage propulsion system designed for operation in the upper atmosphere should be tested under nozzle full flow conditions to verify its performance on the ground. KARI has carried out high altitude simulation test of KSLV-I kick motor using cylindrical supersonic exhaust diffuser. Also cold and hot flow test for the sub-scaled diffuser have been conducted to verify the design of real scale diffuser and to study its operating characteristics. This paper deals with the results obtained from these high altitude simulation tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.5
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• pp.10-18
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• 2019

In this study, flow characteristics and the starting pressure of a center body diffuser (CBD) were analyzed at various center body (CB) positions and cone angles. According to the CB position, the location of oblique shock moved to the front from behind the CB cone with an increase in the flow momentum. Additionally, when a strong oblique shock occurred, the direction of supersonic flow was affected and induced to diffuser wall. As a function of different cone angles for the oblique shock, the starting pressure of the CBD was significantly affected.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.2
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• pp.15-22
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• 2011

Unlike most aerodynamic wind-tunnel, Scramjet Engine Test Facility(SETF) of Korea Aerospace Research Institute should simulate enthalpy condition at a flight condition. SETF is a blow-down type, high-enthalpy wind tunnel. To attain a flight condition, a highly stagnated air comes into the test cell through a supersonic nozzle. Also, an air ejector of the SETF is used for simulating altitude conditions of the engine, and facility starting. SETF has a free-jet type test cell and this free-jet type test cell can simulate a boundary layer effect between an airplane and engine using facility nozzle, but it is too difficult to predict the nature of the facility. Therefore it is required to understand the starting characteristics of the facility by experiments. In this paper, the starting characteristics of the SETF and modifications of the ejector are described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.451-458
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• 2010

Unlike most aerodynamic wind-tunnel, Scramjet Engine Test Facility(SETF) of Korea Aerospace Research Institute should simulate enthalpy condition at a flight condition. SETF is a blow-down type, high-enthalpy wind tunnel. To attain a flight condition, a highly stagnated air comes into the test cell through a supersonic nozzle. Also, an air ejector of the SETF is used for simulating altitude conditions of the engine, and facility starting. SETF has a free-jet type test cell and this free-jet type test cell can simulate a boundary layer effect between an airplane and engine using facility nozzle, but it is too difficult to predict the nature of the facility. Therefore it is required to understand the starting characteristics of the facility by experiments. In this paper, the starting characteristics of the SETF and modifications of the ejector are described.