• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.4
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• pp.22-29
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• 2009

Development of Moon Explorer-1 (orbiter) is supposed to be commenced in 2017 and launched in 2020. In case of Moon Explorer-2 (lander), it would be slated to start in 2021 and launch in 2025. In this paper conceptual feasibility studies are conducted for the propulsion system applicable to a Moon Explorer. In the first place the availability of monopropellant/bipropellant/electric propulsion system is examined with domestic as well as overseas precedents. Secondly ${\Delta}V$ is estimated by the mission analysis and the propellant budget is calculated accordingly. Subsequently feasibility of a chemical propulsion system for a Moon Explorer is evaluated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.816-819
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• 2010

A study on the required propulsion powers at the EAV2 electric propulsion vehicle using power system such as solar cell, fuel cell and secondary cell is conducted, through which the scenario about available supply power is discussed at the optimum propulsion system weight on the specified flight envelope. In the result, it is noticed that propulsion system weight is 7.06kg and fuelcell 500W and secondary cell 100W are available to flight for glider-type electric vehicle with 6m length, 0.35m width.

• Proceedings of the KIPE Conference
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• 2011.07a
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• pp.234-235
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• 2011

본 논문에서는 직렬형 하이브리드 전기추진 시스템을 탑재한 선박에서 엔진 연료절감 및 동적 운항성능 개선을 위한 에너지 저장장치의 도입 필요성과 운용 방안을 제안하였다. 수MW급 전기추진 선박을 대상 모델로 하여 엔진-발전기 시스템의 전력사용 패턴을 분석하였고, 제안한 시스템의 효용성을 시뮬레이션을 통해 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.10
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• pp.959-965
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• 2011

A modeling and power simulation of a small UAV's electric propulsion systems is described. Each power source is modeled and simulated in Matlab/Simulink and it is compared flight test data during 4 hr 30 min with simulation results about 200 W electric propulsion system using fuel cell and battery as a main power sources. In result, it is properly simulated performance and dynamic characteristic of each electric power source. Through this, it is revealed that the simulation is available as a means of predicting power characteristic variation for electric propulsion systems of different class.

• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.1607-1608
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• 2015

현대사회의 고속 고급 교통수단에 대한 요구에 부응하고, 고유가 및 온실가스 등 원유 기반의 교통 시스템의 문제를 해결하기 위해 교통 수단의 다양화 연구가 활발히 진행되고 있다. 석유문제가 심각한 상황으로 전개될 경우, 대륙과 대륙 그리고 국가와 국가 사이의 장거리 이동을 할 수 있는 교통수단은 전기로 추진되는 철도이다. 현재 대중화 되어있는 바퀴 식 철도차량은 초고속 운전 시 기하급수적으로 증가하는 소음, 공기저항 동력 전달의 한계, 레일의 마모라는 문제를 가지고 있으며 이러한 문제점을 가진 철도차량의 대안으로 선형 추진 시스템 연구가 진행 중이다[1] 국내에서는 LSM(Linear Synchronous motor)에 대한 연구가 활발히 진행되고 있으나 LPM 기반 철도 차량 추진시스템에 대한 연구는 이루어지지 않고 있다. 그러나 LSM 추진 시스템에 비하여 LPM 추진 시스템은 우수한 등판 능력, 광역범위의 주행 가능 영역, 경량화에 따른 높은 에너지 효율, 건설비 저감등 다양한 장점을 가지고 있으며 충분한 전략성을 가지고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.183-186
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• 2011

In this paper, we present some results of power analyses, and weight estimation on electric propulsion systems for Personal Air Vehicles(PAV) applications. When hybrid electric propulsion is adopted, its power performance using fuel cells and batteries is inferior to that of internal combustion engines for 1,000 kg PAV. However, hybrid electric propulsion systems may replace IC engines when energy density and power density is over $0.75kW{\cdot}hr/kg$and 2.5 kW/kg, respectively.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.554-559
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• 2017

Recently, the global attention is focused on the development of the renewal aero-propulsion systems proved in the air pollution, the noise, the great operational cost, safety and risks. Especially, various study are conducting for the development of the advanced high power to weight ratio aircraft through the significant reduction of fuel consumption and upgrade of the propulsion efficiency, using the alternative propulsion system developments such as hydrogen and solar power system. The hybrid propulsion system can be the representative propulsion system which get the power sources by combining the merits of two or more power sources. In this study, the advancement trends, characteristics, design method which can be applied to the renewal future UAV development.

• Journal of the Korean Society of Marine Environment & Safety
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• v.28 no.7
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• pp.1238-1243
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• 2022

The International Maritime Organization is at the forefront of strengthening gas emission regulations for ships globally. The Korean government needs to apply measures to reduce emissions, such as setting a basic roadmap for greenhouse gas reduction. In addition, there is an urgent need to introduce a new efficient propulsion system that can reduce gas emissions. This includes applications to fishing vessels, which account for 90.6% of the greenhouse gas emissions from ships sailing along domestic coasts. In this study, an electric-combined propulsion system applicable to domestic coastal fishing vessels was developed. The target ship to which the electric-combined propulsion system could be applied was selected. A simulation system was constructed using MATLAB/Simulink to compare the expected fuel consumption when applying the developed complex electric propulsion system to the propulsion system mounted on the selected target fishing vessel. Through simulations, the differences in fuel consumption between the mechanical propulsion system and the electric hybrid propulsion system (both when charging and not charging the battery on land) were confirmed. The results show that fuel consumption can be decreased by approximately 13% and 16% when applying the electric-combined propulsion system.

• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.27-34
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• 2023

This paper presents the application of a magnetic gear to the electric propulsion system for an aircraft. Since high torque is required in aircraft electric propulsion systems, combining a speed reducer can amplify the torque. However, mechanical gears have issues, such as friction, vibration, and heat generation, which lead to maintenance challenges. In the case of a direct-drive motor that does not use mechanical gears, the size and weight of the motor increase to achieve high torque. This paper proposes the application of a magnetic gear to solve the maintenance issues of mechanical gears and the weight increase problem of direct-drive motors in aircraft electric propulsion systems. In this paper, a magnetic gear suitable for aircraft electric propulsion systems is designed, and it is compared with a direct-drive motor in terms of performance and the feasibility of applying the magnetic gear is verified.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.4
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• pp.49-55
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• 2013

This paper deals with the flight test of propulsion system of middle size electrically powered UAV (EAV2, Electric Aerial Vehicle 2) which is under development in KARI. EAV2 is low speed endurance type UAV whose wing span is 6.9 m, and weight is 18 kg. The UAV has flown for 22 hours in June of 2012. The flight test result showed that the propulsion system worked well suppling power for any circumstances during the test flight. Each power source worked according to the design purpose.