• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.212-212
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• 2012

수소화된 실리콘 질화막은 결정질 태양전지 산업에서 반사방지막 과 패시베이션 층으로 널리 사용되고 있다. 또한, 수소화된 질화막은 금속 소성공정과 같은 높은 공정온도를 거친 후에도 결정질 실리콘 태양전지의 표면층으로서 충족되는 특성들이 변하지 않고 유지되어야 한다. 본 연구에서는 PECVD 장치를 이용한 수소화된 실리콘 질화막의 특성 변화에 대한 경향성을 알아보기 위하여 증착조건의 변수(온도, 증착거리, 무선주파수 전력, 가스비율 등.)들을 다양하게 가변하여 증착조건의 최적화를 찾았다. 이후 수소화된 실리콘 질화막의 전구체가 되는 사일렌(SiH4)과 암모니아(NH3) 가스비를 변화시켜가며 결정질 실리콘 태양전지에 사용되기 위한 박막의 광학 전기 화학적 그리고 표면 패시베이션 특성들을 분석하였다. 가스 비율에 따른 수소화된 실리콘 질화막의 굴절률 범위는 1.90-2.20까지 나타내었다. 결정질 실리콘 태양전지에 사용하기 위한 가장 적합한 특성은 3.6(NH3/SiH4)의 가스비율을 나타내었다. 이를 통하여 PECVD 내에서 구현 할 수 있는 가스의 혼합(SiH4+NH3+N2, SiH4+NH3, SiH4+N2)을 달리하여 박막의 광학적 및 패시베이션 특성을 분석하였다. 이후 $156{\times}156mm$ 대면적 결정질 실리콘 태양전지를 제작하여 SiH4+NH3+N2 의 가스 혼합에서 17.2%의 변환 효율을 나타내었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.87-90
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• 2007

Fuel cell power system was developed for high-endurance unmanned aerial vehicle (UAV). Liquid chemical hydride was selected as a fuel due to its high energy density. Liquid storage of the fuel is an ideal alternative solution of the existing compressed hydrogen storage. The fueling system that extracts hydrogen from chemical hydride consists of catalytic reactor, micro-pump, fuel cartridge, separator, and controller. The fuel cell power system including the fueling system and the fuel cell that generates electricity was integrated into a proposed UAV. The performance verification of the fuel cell power system was performed to use as a power plant of the UAV.

• Journal of the Korean Electrochemical Society
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• v.11 no.4
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• pp.289-296
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• 2008

Electrochemical studies were performed by a half-cell test for the nickel hydroxide (cathode) and hydrogen storage alloy(anode) electrodes for the sealed Ni-MH batteries applicable to industrial use. The electrodes were fabricated and checked a charge efficiency and an internal pressure of the battery during charge-discharge cycling. In order to reduce the internal pressure of the sealed Ni-MH battery, cyclic voltammetry (CV) were performed on the electrodes of nickel hydroxide(cathode) and hydrogen storage alloy(anode), respectively. The results of the test showed clearly the oxidation/reduction and oxygen evolution reaction in a nickel hydroxide electrode and the hydrogenation behavior of a hydrogen storage electrode. The sealed Ni-MH battery of 130Ah was fabricated by using nickel hydroxide of a high over-voltage for an oxygen gas evolution and hydrogen storage alloy of a good performance for activation The battery showed a good characteristics such as a high charge efficiency of 98% at 1 C charge current, a low level internal pressure of 4 atm on a continuous over-charging and a large preservation capacity of 95% at 400 cycle.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.627-633
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• 2011

Performance of a hydrogen generator for a fuel cell unmanned aircraft was evaluated as the change of temperature environment. Sodium borohydride ($NaBH_4$) was used as a hydrogen source due to its high hydrogen content and good storability. The hydrogen gas was generated by the hydrolysis reaction using a catalytic reactor. Reaction chambers were set up with the range of temperatures from -20 to $60^{\circ}C$. The hydrogen generation rate and temperatures changes of reactor and separator were measured at the $NaBH_4$ concentrations of 20 and 25wt.%. As a result, the hydrogen generation rate was decreased as the repeated reaction cycles. It showed that the hydrogen generation rate was stable at low temperature, while at high temperature the hydrogen generation rate was rapidly decreased. The performance degradation was mainly caused by the catalyst loss and $NaBO_2$ deposition on the catalyst surface.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.9
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• pp.858-865
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• 2011

This paper describes the characteristics of hydrogen generation from solid-state $NaBH_4$ and fuel cell operation for fuel cell aircraft. The solid-state $NaBH_4$ was used for a high hydrogen storage density, and was reacted with hydrochloric acid to generate hydrogen. The hydrogen generation rate for the solid-state $NaBH_4$ reaction was measured at various conditions. As a result, the hydrogen generation rate was increased with the feed rate and concentration of hydrochloric acid, while not be affected by the reaction temperature. A fuel cell was connected with the solid-state $NaBH_4$ hydrogen generator. The stable power output was obtained at the gradual and sudden increases of electric loads.

• Proceedings of the Korean Vacuum Society Conference
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• 2010.02a
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• pp.177-177
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• 2010

고효율 비정질 실리콘 박막 태양전지 제작을 위해서는 광파장대에서 optical confinement 능력을 최대화할 수 있는 기술이 필수적이다. 효율적인 photon trapping을 위해서는 back reflector를 사용하거나 전면전극인 투명전도성막의 표면에 요철을 형성하여 포획된 태양광의 내부 반사를 증가시키거나 전면 투명전극에서 반사를 감소시켜 태양광의 travel length를 증가시키는 방법이 일반적이며, 이를 통해 흡수층의 효율을 최대화할 수 있다. 이 중 전면전극으로 사용되는 투명전도성막은 불소가 도핑된 tin-oxide가 주로 사용되었으나, 최근 들어 Al이 도핑된 산화아연막을 이용한 비정질 실리콘 박막 태양전지 개발에 대한 연구도 활발히 진행되고 있다. 투명전극 증착후 표면의 유효면적을 증가시키기 위해 염산 용액을 이용하여 표면 텍스쳐링을 수행한다. 그후 흡수층인 p-i-n 층을 플라즈마 화학기상증착법을 이용하여 형성하는 것이 일반적이다. 이때 표면처리 된 투명전극은 수소플라즈마에 대해 특성이 변하지 않아야 고효율 비정질 실리콘 박막 태양전지 제조에 적용될 수 있다. 본 연구에서는 표면처리 된 AZO 투명전극의 수소플라즈마에 의한 특성 변화에 대해 고찰하였다. 먼저 AZO 투명전극은 스퍼터링 공정을 적용하여 $1\;{\mu}m$두께로 증착하였고, 0.5 wt%의 HCl 용액을 이용하여 습식 식각을 수행하였다. 수소플라즈마 처리 조건은 $H_2$ flow rate 30 sccm, working pressure 20 mtorr, RF power 300 W, Temp $60^{\circ}C$ 이며 3분간 진행하였다. 표면형상은 수소플라즈마 전 후에는 큰 차이를 보이지 않았으며 AZO의 grain size는 각각 220 nm, 210 nm로 관찰되었다. 투명전극의 가장 중요한 특성인 가시광선 영역에서의 투과도는 수소플라즈마 처리전에는 90 % 이상의 투과도를 보였으나, 수소플라즈마 처리 후에는 85 %로 약간 저하된 특성을 보였다. 그러나 이는 박막 태양전지용 전면전극으로 사용하기 위한 투과도인 80 % 이상을 만족하는 결과로, 비정질 박막 실리콘 태양전지 제작에 사용될 수 있다. 또 하나의 중요한 특성인 Haze factor 역시 수소플라즈마 처리 전 후 모두 10 이상의 값을 나타냈다. 하지만 고효율 실리콘 박막 태양전지에 적용하기 위해서는 Haze factor를 증가시키는 공정 개발에 대한 추가 연구가 필요하다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.149-152
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• 2012

This paper describes the study of integrated hydrogen supply system for environment friendly propulsion systems of fuel-cell UAV. Diluted hydrochloric acid was used for direct-decomposing solid-state $NaBH_4$ and generating hydrogen. Self-hydrogen pressurized reactor and pressure regulator was introduced for stable hydrogen supply. Prototype of integrated hydrogen supply systems using the solid-state $NaBH_4$ direct-decomposition was designed for performance evaluation and concept demonstration.

• Korean Chemical Engineering Research
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• v.57 no.3
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• pp.413-419
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• 2019

In the recent, as a world demand of energy resources has been transformed from fossil fuels to hydrogen-based clean energy resources, a huge attention has been attracted to increase the performance and decrease a production cost of core materials in fuel cell technology. The utilization of reinforced composite membranes as electrolytes in the polymer electrolyte membrane fuel cells can reduce the use of high cost perfluorosulfonic acid (PFSA), mitigate the cell impedance, and improve the dimensional stability as well as the interfacial stability, giving rise to achieve both an improved performance and a reduction of production costs of the fuel cell devices. In this study, we investigate the effects of physical characteristics and cell performances according to the various ionomer solvents in the solution based manufacturing process of reinforced composite electrolyte membrane.

• 한국신재생에너지학회:학술대회논문집
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• 2008.05a
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• pp.558-559
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• 2008

본 논문은 미 일리노이 주립대 어바나-샴페인 캠퍼스에서 주로 군사용 응용 관련하여 개발 중인 마이크로 PEM 연료전지 시스템 개발에 대한 논문이다. 본 연구는 수소 저장 장치까지 포함하여 1 $mm^3$의 초소형 연료전지 시스템을 목표로 진행 중이며 본 논문은 이러한 진행 과정 중 화학적 하이드라이드 기반의 수소 발생기와 10 $mm^3$의 시스템 개발 과정에 대해 보고한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.3
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• pp.233-239
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• 2013

A 100 W fuel cell system using chemical storage method has been applied for a propulsion system of the SUAV(Small Unmanned Aerial Vehicle). A fuel cell and battery have been combined for both the small/light hydrogen generation control system and the hybrid power supply system. A small hydrogen generation device was implemented to utilize NaBH4 aqueous solution and dead-end type PEMFC system, which were evaluated on the ground and by the flight tests. The system pressurized at a 45kpa stably operates and get higher fuel efficiency. The pressure inside of the hydrogen generation control system was maintained at between 45 kPa and 55 kPa. The 100W fuel cell system satisfies the required weight and power consumption rate as well as the propulsion system, and the fuel cell system performance was demonstrated through flight test.