• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.579-582
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• 2008

PEM Fuel cell system was designed and constructed to use as a power source of unmanned aerial vehicles(UAV) in the present study. Sodium borohydride was selected as a hydrogen source and was decomposed by catalytic hydrolysis reaction. Fuel cell system consists of a fuel cell stack, a hydrogen generation system(HGS), and power management system(PMS). HGS was composed of a catalytic reactor, micropump, fuel cartridge, and separator. Hybrid power system between lithium-polymer battery and fuel cell was developed. The fuel cell system was integrated and packaged into a blended wing-body UAV. Energy density of the total system was 1,000 $W{\cdot}hr/kg$ and high endurance more than 5 hours was accomplished in the ground tests.

• Asian Journal of Atmospheric Environment
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• 제4권2호
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• pp.63-71
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• 2010

The removal characteristics for aromatic and aliphatic VOCs by electron beam (EB) were discussed in terms of several removal variables such as initial VOC concentration, absorbed dose, background gas, moisture content, reactor material and inlet temperature. It was reviewed that only reactor material was an independent variable among the potential control factors concerned. It was also suggested that main mechanism by EB should be radical reaction for the VOC removal rather than that by primary electrons. It was discussed that the removal efficiency of benzene was lower than that of hexane due to a closed benzene ring. In the case of aromatic VOCs, it was observed that the decomposition of the VOCs with more functional groups attached on the benzene ring was much easier than those with less ones. As for aliphatic VOCs, it was also implied that the longer carbon chain was, the higher the removal efficiency became. An EB-catalyst hybrid system was discussed as an alternative way to remove VOCs more effectively than EB-only system due to much less by-products. This hybrid included supporting materials such as cordierite, Y-zeolite, and $\gamma$-alumina.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.512-521
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• 2017

This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide($H_2O_2$) as an oxidizer and nitrogen gas($N_2$) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The $MnO_2/Al_2O_3$ catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed $H_2O_2$ at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed $H_2O_2$ product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.

• 조명전기설비학회논문지
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• 제25권10호
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• pp.116-124
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• 2011

In this work, the effect of the initial concentration of methanol and ethanol, and the addition of oxygen molecules were discussed to improve the hydrogen generation using non-thermal plasma reactor effectively. In addition, the effect of ozone decomposition catalyst of manganese dioxide and its quantity was investigated. First, hydrogen concentration increased until an initial concentration of about 40,000[ppm] of methanol and thereafter it was saturated. Henceforth, hydrogen concentration decreased with increasing the oxygen percent on the carrier gas of nitrogen about both substances. Related with the effect of catalyst, it increased upto 60[g], but it was not changed largely after that. Consequently, it is confirmed that the hybrid process using plasma process and catalytic surface chemical reaction is a very promising way to increase the efficiency of hydrogen generation as investigated in this work.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.13-16
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• 2007

본 연구에서는 무인기용 추진 시스템으로 연료전지를 사용하였다. 연료전지 추진 시스템은 고항속 무인기를 위한 고에너지 밀도를 갖는 이상적인 대체 동력원이다. 연료전지 동력 시스템은 기폰 배터리의 5배 이상의 에너지 밀도를 제공한다. 액체상태로 저장되는 수소화붕소나트륨을 수소원으로 사용하였다. 수소 생성 시스템은 촉매 반응기, 펌프, 연료, 카트리지, 분리기로 구성된다. 연료전지와 리륨-폴리머 배터리의 하이브리드 동력 관리 시스템이 개발되었다. 모터, 펌프, 팬은 연료전지 시스댐의 피트백 신호에 따라 배터리 동력으로 작동되고 배터리는 연료전지의 잉여 동력으로 재충전되었다.

• 멤브레인
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• 제27권4호
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• pp.328-335
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• 2017

메조포러스 공극구조를 갖는 광촉매 멤브레인은 다양한 환경기술에 적용될 수 있다. 본 연구에서는 $TiO_2$ 층을 형성시킨 광촉매 반응기용 세라믹 멤브레인을 개발하고 이를 염색용액 처리에 적용하였다. 높은 공극률과 균질성을 지닌 $TiO_2$ 광촉매층을 그라프트 공중합체를 사용하여 제조하였다. 멤브레인은 광촉매 반응기와 멤브레인 여과를 결합시킨 하이브리드 광촉매 반응기에 성공적으로 적용하였다. 실험결과 정렬된 구조의 $TiO_2$ 층이 $Al_2O_3$ 지지체에 형성되었다. $TiO_2$ 층 형성 후 제조된 세라믹 분리막의 순수 투과도는 형성된 광촉매 층 저항으로 감소하였다. 정렬된 구조의 $TiO_2$ 층은 UV 결합 시 5시간 안에 완벽한 염색용액 분해를 달성시킬 수 있었다. 광촉매 멤브레인의 염색용액 분해는 Langmuir-Hinshelwood 흡착 모델로 잘 설명할 수 있었다. 또한 $TiO_2$ 층이 고정화된 세라믹 멤브레인의 model Congo Red에 대한 1차 속도상수는 $Al_2O_3$ 지지체 단독인 경우에 비해 약 6배 정도 큰 값을 나타내었다(0.0081 vs. $0.0013min^{-1}$).

• 청정기술
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• 제20권4호
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• pp.375-382
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• 2014

금속산화물이 담지된 허니컴 형상의 플라즈마-촉매 반응기를 이용하여 아이소프로필 알코올(isopropyl alcohol, IPA) 저감 및 부산물 생성 거동에 대해 조사하였다. 허니컴 형상의 다공질 세라믹 지지체(주성분: ${\alpha}-Al_2O_3$)에 금속산화물로 산화철($Fe_2O_3$) 또는 산화구리(CuO)를 담지시킨 후, 이 촉매가 동축 원통형 전극구조 내부에 위치하도록 플라즈마-촉매 반응기를 구성하였다. 플라즈마 반응에 의한 IPA 분해속도가 매우 빨랐기 때문에 IPA 분해효율 자체는 금속산화물 담지 여부 및 금속산화물 종류에 관계없이 유사한 것으로 나타났으나, 부산물 생성거동은 촉매종류에 따라 큰 차이를 보여주었다. 아세톤, 폼알데하이드, 아세트알데하이드, 메테인, 일산화탄소 등의 유해 부산물 농도는 $Fe_2O_3/{\alpha}-Al_2O_3$ < $CuO/{\alpha}-Al_2O_3$ < ${\alpha}-Al_2O_3$ 순으로 높게 나타났다. 유량 $1L\;min^{-1}$, IPA 초기농도 5,000 ppm(산소: 10%), 방전전력 47 W의 조건에서 얻어진 $CO_2$ 선택도는 ${\alpha}-Al_2O_3$, $CuO/{\alpha}-Al_2O_3$, $Fe_2O_3/{\alpha}-Al_2O_3$에 대해 각각 40, 80, 95%로서 $Fe_2O_3/{\alpha}-Al_2O_3$가 플라즈마-촉매를 이용한 IPA의 산화에 가장 효과적인 것으로 나타났다. 플라즈마를 단독으로 사용하여 휘발성유기화합물을 분해할 경우 타르형태의 생성물이 반응기에 퇴적되는 문제점이 있으나, 플라즈마-촉매 공정에서는 이러한 현상이 관찰되지 않았으며 촉매의 활성이 그대로 유지되었다.