• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.95-105
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• 2009

Fuel cells are applied to the propulsion system of aircraft based on environmental-friendly characteristics with low noise and zero emission of CO2, currently many kinds of UAV and small manned aircraft equipped with fuel cells are being developed. Fuel cells for aircraft typically classified into PEMFC(Proton Exchange Membrane Fuel Cell) type and SOFC(Solid Oxide Fuel Cell) type and the system is developed to adapt missions and operational conditions of aircraft. For UAV, various types of aircraft mostly based on PEM fuel cell technology are investigated for military or commercial uses, and the stability and endurance of system will be improved. For small manned aircraft, many researches are carried out to substitute the propulsion system by fuel cell, also some developments for the higher performance of APU of large commercial aircraft to apply fuel cells are in progress. In the future, a fuel cell aircraft will be expected to improve the reliability and efficiency with higher power density.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.683-684
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• 2011

연료전지시스템을 항공기 동력원으로 사용하기 위해서는 요구되는 출력에 필요한 스택성능과 한정된 부피 내 연료전지시스템을 탑재하기 위한 운전장치 구성, 그리고 무게를 최소화하기 위한 부품 및 재료 선정이 필요하다. 스택의 기본성능은 MEA(Membrane electrode assembly)와 기체확산층 구조, 분리판 디자인 및 운전조건 등에 의해 결정된다. 스택의 기본성능은 연료전지시스템을 구성하는 운전장치 구성 및 성능에 의해 달라지기 때문에 어떠한 운전장치를 어떠한 구성으로 설계하는가에 따라서 성능이 변한다고 볼 수 있다. 본 연구에서는 연료전지시스템을 항공기 동력원으로 사용하기 위해서 고려되어야할 스택과 운전장치의 구성이 성능에 미치는 영향과 운전환경(스택 경사, 고도)이 연료전지 스택성능에 미치는 영향에 대해 고찰하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.153-156
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• 2012

The optimization and integration of a fuel cell were performed to improve the performance and reliability of the fuel cell in this paper. To improve the performance of the PEMFC, current and voltage of the fuel cell were measured using an electrical load, and the results was compared and analyzed with the data of a commercial fuel cell. Based on the above results, a controller for a fuel cell UAV applications was designed, and the fuel cell control algorithm was developed to optimize the performance of the fuel cell UAV.

• 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 Society of Propulsion Engineers
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• v.13 no.3
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• pp.58-63
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• 2009

The global restriction on pollutant emissions and the soaring of crude oil price are expected to result in the change of future transportation system. Hydrogen is considered to be the leading candidate as an alternative energy source before other new alternative energy sources emerge. Scientists anticipate that hydrogen fuel gas turbine engine and fuel cell will be the power plant of the aircraft in the near future. To realize the aircraft powered by fuel cell system in the future, the technologies such as fuel cell with higher energy density, compressed gas or liquid storage system of hydrogen fuel, and efficient and lightweight electric motor have to be developed first.

• 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.

• The Science & Technology
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• no.4 s.419
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• pp.82-85
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• 2004

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.5
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• pp.391-403
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• 2013

Propeller aircraft propelled by an electric propulsion system is gaining a renewed interest because of ever-increasing environmental concern on harmful emissions emitted from conventional jet engines and national energy security. Traditional aircraft sizing methods are not readily applicable to electric propulsion aircraft that utilize a variety of alternative energy sources and power generation systems. This study showcases an electric propulsion aircraft sizing exercise based on a generalized, power based sizing method. A general aviation aircraft is propelled by an electric propulsion system that comprises of a propeller, a high temperature super conducting motor, a Proton Exchange Membrance(PEM) fuel cell system fuelled with hydrogen, and power conditioning equipment. In order to assess the impact of technology progression, aircraft sizing was conducted for two different sets of technology assumptions for electric components, and the results were compared with conventional baseline aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.7
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• pp.590-600
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• 2012

In this research, generalized sizing methods were studied that can be applied to an aircraft which uses solar cell or fuel cell as energy sources. To consider multiple propulsion systems and energy resources, multiple power paths were modeled and the weight of consumable and non-consumable energy was reflected in the weight change calculation for each mission segments. In the constraint analysis, power to weight ratio was selected instead of thrust to weight ratio and used in the sizing process of balancing power and energy.