• Journal of the Korea Academia-Industrial cooperation Society
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• v.22 no.5
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• pp.15-21
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• 2021

Electrically powered airplanes can reduce CO₂ emissions from fossil fuel use and reduce airplane costs in the long run through efficient energy use. For this reason, advanced aviation countries such as the United States and the European Union are leading the development of innovative technologies to implement the full-electric airplane in the future. Currently, the research and development to convert existing two-seater engine airplanes to electric-powered airplanes are underway domestically. The airplane converted to electric propulsion is the KLA-100, which aims to carry out a 30-minute flight test with a battery pack installed using the engine mounting space and copilot space. The lithium-ion battery installed on the airplane converted to electric propulsion was designed with a specific power of 150Wh/kg, weight of 200kg, and a C-rate 3~4. This study confirmed the possibility of a 30-minute flight with a designed battery pack before conducting a flight test of a modified electrically propelled airplane. The battery performance was verified by dividing the 30-minute flight profile into start/run stage, take-off stage, climbing stage, cruise stage, descending stage, and landing/run stage. The final target of the 30-minute flight was evaluated by calculating the battery capacity required for each stage. Furthermore, the flight performance of the electrically propelled airplane was determined by calculating the flight availability time and navigation distance according to the flight speed.

• The Korean Journal of Air & Space Law and Policy
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• v.28 no.1
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• pp.55-71
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• 2013

By aircraft from Aviation regulations and institutional regulatory framework for ensuring the safety is secured. State-of-the-art aircraft, according to the type of development and diversification, modernization and new types of aircraft are operated. In particular, light aircraft and ultralight flying device such as the gyro-plane and unmanned flying devices is introduced a new device, and the device operates at these flight in accordance with the standards of the Aviation Act regulations may not occur often. Variety of light aircraft and ultra-light aircraft assembly, can be adapted for a person engaged in the business of aviation safety management and to perform the legal basis was established. Depending on the classification of newly introduced aircraft, the biggest change is the introduction of the concept of the LSA. In Korea, the various light aircraft are operating, but these aircraft range not clearly Aviation Regulations had difficulty in ensuring safety. This study examined the differences between international rules and regulations of Korea about the classification of aircraft. The LSA are included in aircraft categories internationally, but LSA will not be included in the aircraft categories, which is one of a range of powered flight device exists in Korea Aviation Act. Limit for maximum continuous power speed in a LSA, it is a limit on the right of the people who want using the high-performance plane. Also it is an international trend does not fit in, and is consistent with the intent of LSA manufacturer. Delete the content from a range of future aviation law revisions and light aircraft-related provisions to limit the maximum continuous power speed is considered to be suitable for the purpose of introducing the light aircraft industry. The laws and regulations set up in order to ensure the safety of ultralight aircraft categories existing in ultralight aircraft that exceeds the purpose of the introduction of LSA technology development at home and abroad, and is intended to reflect. These standards complement of aircraft operation is not appropriate for the situation unless the country is difficult to ensure the safety of operations. Also developed in other countries, the introduction of aircraft operating in the country, so many problems occur early revision is required.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.2
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• pp.1-11
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• 2017

In this study, we surveyed the regulations of the Seaplane base and Sea Lane for the Light Sport Aircraft(LSA), and analyzed the water landing/takeoff roll distance of LSA in Korea. Based on the information, we presented the situation of the Sea Lane and the Sea Lane Protection Zone concept, to ensure the Rectangle type Sea Lane and the Omni direction type Sea Lane. We analyzed the availability elements of the safety of Sea Lane for LSA in Korea. A Rectangle type Sea Lane 350 meters long and 40 meters wide, the diameter 350 meters for the An Omni direction type Sea Lane.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.34-39
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• 2003

Morphing wing sections actuated by piezoceramic actuator LIPCA have been designed and their actuation displacements estimated by using the therml analogy and MSC/NASTRAN based on the linear elasticity. The wing sections are fabricated as the design and tested for evaluation. Measured actuation displacements were larger than the estimated values mainly due to the material non-linearity of the PIT wafer. The morphing wing sections can be used for control surfaces of small scale UAVs or MAVs.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.105-105
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• 2012

본 논문에서는 전세계적으로 차세대 에너지절감 반도체로 각광을 받고 있는 GaN 소자의 연구개발 동향에 관하여 발표하고자 한다. GaN 반도체는 와이드 밴드갭(Eg=3.4eV)과 고온 안정성($700^{\circ}C$)등 재료적인 특징으로 인하여 고출력 RF 전력증폭기와 고전력용 전력반도체 응용에 큰 장점을 가진다. 고출력용 GaN RF 전력증폭 소자의 전력밀도는 기존 Si-기반 LDMOS 트랜지스터보다 10배 이상 높아 제품의 소형화와 경량화를 통하여 30% 이상의 전력절감이 가능하며, 레이더, 위성등 송수신 트랜시버 모듈에 GaN 전력증폭기를 이용할 경우 기존 GaAs-기반 전력증폭기에 비하여 높은 전력밀도(>x8)와 높은 효율(>20%)로 인하여 모듈 크기를 50% 이상 줄임과 동시에 경량화를 이룰 수 있어 비행기, 위성등 탑재체의 에너지 절감에 크게 기여할 수 있다. 고전력용 GaN 전력 스위칭 소자는 기존 Si-기반 IGBT에 비하여 스위칭 손실과 온-저항 손실이 낮아 30% 이상의 에너지 절감이 가능하다. 뿐만 아니라, 일본 도요타 자동차사의 보고에 의하면 HEV등 전기자동차의 DC-DC 부스터 컨버터나 DC-AC 인버터에 GaN 전력반도체를 적용할 경우 경량화, 변환효율 향상, 전용 냉각시스템을 제거할 수 있어 연료소모를 10% 이상 줄일 수 있어 연간 400불 이상의 에너지 절감 효과를 가진다. 이러한 에너지절감 효과는 미국, 유럽, 일본등 선진국을 중심으로 차세대 GaN 반도체의 신시장 개척과 선진입을 위한 치열한 경쟁 구도의 구동력이 될 것이며, 본 논문을 통하여 GaN 반도체의 연구개발 방향과 상용화의 중요성을 함께 생각해보고자 한다.

• Journal of Hydrogen and New Energy
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• v.23 no.2
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• pp.134-142
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• 2012

A bipolar plate is a major component of a fuel cell stack, which occupies 50~60% of the total weight and over 50% of the total cost of a typical fuel cell stack. In this study, a composite bipolar plate is designed and fabricated to develop a compact and light-weight direct methanol fuel cell (DMFC) stack for a small-scale Unmanned Aerial Vehicle (UAV) application. The composite bipolar plates for DMFCs are prepared by a compression molding method using resole type phenol resin as a binder and natural graphite and carbon black as a conductor filler and tested in terms of electrical conductivity, mechanical strength and hydrogen permeability. The flexural strength of 63 MPa and the in-plane electrical conductivities of 191 S $cm^{-1}$ are achieved under the optimum bipolar plate composition of phenol : 18%; natural graphite : 82%; carbon black : 3%, indicating that the composite bipolar plates exhibit sufficient mechanical strength, electrical conductivity and hydrogen permeability to be applied in a DMFC stack. A DMFC with the composite bipolar plate is tested and shows a similar cell performance with a conventional DMFC with graphite-based bipolar plate.

• Journal of Hydrogen and New Energy
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• v.23 no.3
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• pp.243-249
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• 2012

A lightweight 200W direct methanol fuel cell (DMFC) stack is designed and fabricated to power a small scale Unmanned Aerial Vehicle (UAV). The DMFC stack consists of 33-cells in which membrane-electrode assemblies (MEAs) having an active area of 88 $cm^2$ are sandwiched with lightweight composite bipolar plates. The total stack weight is around 3.485 kg and stack performance is tested under various methanol feed concentrations. The DMFC stack delivers a maximum power of 248 W at 13.2 V and $71.3^{\circ}C$ under methanol feed concentration of 1.2 M. In addition, the voltage of individual cell in the 33-cell stack is measured at various current levels to ensure the stability of DMFC stack operations. The cell voltage distribution data exhibit the maximum cell voltage deviation of 28 mV at 15 A and hence the uniformity of cell voltages is acceptable. These results clearly demonstrate that DMFC technology becomes a potential candidate for small-scale UAV applications.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.8
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• pp.699-705
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• 2015

Aircraft needs high lift-to-drag ratio and weight reduction of the structure for long endurance flight with a small power. Generally high aspect ratio wing is applied to HALE(High Altitude Long Endurance) aircraft. Also high modulus, and high strength CFRP(Carbon Fiber Reinforced Plastic) has been used in primary structures. and thin mylar(membrane material) film has been applied to skin of wing. As a result, wing is more flexible than the other structures. and the stiffness of thin mylar film has an affect on dynamic stability. In this study, the membrane characteristic of mylar film has been simulated using nonlinear gap elements. And equivalent modeling method using shell elements is presented using the nonlinear simulation result. The linear equivalent model has verified using the results of nonlinear membrane method. Proposed linear equivalent shell model has applied to mode analysis for estimate the effect of mylar mechanical properties on natural frequency.