• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.521-523
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• 2004

The Japan Aerospace Exploration Agency (JAXA) has proposed new vertical take-off and landing (VTOL) aircraft known as the Jet-VTOL aircraft shown in Fig.1. The Jet-VTOL aircraft is based on a canard wing configuration. The aircraft has the clustered lift-fans mounted near the center of gravity for vertical flight, and has the clustered fans mounted beside the vertical tail for cruise flight. Both fans are driven by the core engine mounted inside the aft end of fuselage. The propulsion system is innovative and attractive not to be seen even in the world.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.398-400
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• 2004

The three-dimensional woven fabric C/SiC composites blisk turbine rotor model was evaluated. The spin tests of the blisk model were performed to measure strain distributions at the room temperature. The rotational strength of the blisk model could be improved by the fiber addition. But, there are still more researches to be done.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.601-604
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• 2004

Precise position and attitude control of pico-satellite requires huge number of impulses of the order of 10$^{-6}$ Ns. MEMS solid rocket array is a promising propulsion system but the higher degree of miniaturization causes unreliable operation mainly due to quenching. In order to breakthrough this situation, a novel design of solid micro-rocket is proposed, which generates tiny impulses repetitively from a single rocket not from array. This unique micro-rocket is based on the utilization of quenching, which causes propellant reaction to sustain only in a small area. A test chip of a micro solid propellant tank and micro heater array is fabricated and ignition test is conducted. Obtained results show the feasibility of this concept and future direction of this quenching-based propulsion is discussed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.251-256
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• 2004

A concept in which laser-sustained plasmas (LSPs) are combined with inductively coupled plasmas (ICPs) is proposed. The concept is aiming at extensions of operative conditions of a CW laser thruster due to the fact that the ICP has some characteristics which are in contrast to those of LSPs. An estimation confirmed that the concept would effectively work. And a fundamental experiment was conducted. The results showed that the radio frequency magnetic field induced by a alternate current of 13.56 MHz coupled inductively with LSPs, resulting in the enlargement of the plasma region and the attainment of the enthalpy. It is expected that some improvements will enable to transfer the RF power to the work gas more effectively and to demonstrate the synergy effect between the LSPs and the ICPs.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.485-490
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• 2004

Sawtooth mixing device used in a non-premixed burner is evaluated for flame stabilization and NO$_{x}$ reduction. Three mixers with different blade angles are tested. Methane is delivered through the fuel jet and air passes through the co-flow annulus. The flame mode changes (attached flame, lifted flame and extinction) against the fuel flow speed are measured, and the stability diagram is drawn. Moreover, by traversing thermocouple and sampling probe in the flame, the distribution of temperature and NO$_{x}$ mole fraction are measured. With the change in blade angle, flame shape, flame stabilization, the distribution of temperature and NO$_{x}$ mole fraction are changed considerably.rably.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.340-345
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• 2008

Liquid hydrocarbon fuels are gathering increasing attention as candidates for a scramjet engine fuel. Experimental researches on supersonic combustion of kerosene have been conducted in model scramjet combustors. Through these works, understanding of combustion characteristics of kerosene have been revealed on some level, and so we decided to work on other kinds of liquid hydrocarbon fuels in order to explore effects of fuel properties on supersonic combustion performances, especially self-ignition and flame-holding. In addition, comparing the results of new fuels with kerosene, the relationship between fuel properties and supersonic combustion characteristics was discussed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.182-186
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• 2008

Fundamental experiments with single row heat exchanger were conducted for the purpose of validating new defrosting method using jet impingement. The coolant temperature were varied from 83 to 250 K. We used the jet periodically, once in 50 second and the duration of the jet is 0.1 second. The effect of the coolant temperature in the effectiveness of the jet defrosting was investigated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.574-578
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• 2008

In order to achieve thrust vector control and discharge stabilization in Hall thrusters, the azimuthal nonuniformity of propellant flow rate in an acceleration channel was created. A plenum chamber was divided into two rooms by two walls and propellant flow rate supplied to each section was independently controlled. In a magnetic layer type Hall thruster, steering angle of up to ${\pm}2.3$ degree was achieved. In an anode layer type Hall thruster, discharge current oscillation amplitude was decreased with the normalized differential mass flow rate.

• Proceedings of the Korean Society of Computer Information Conference
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• 2019.01a
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• pp.293-294
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• 2019

본 논문에서는 전기차 파생 IT융합 서비스의 일환으로 원활한 전기차 충전을 지원하기 위한 불법 주차 방지 시스템을 제안한다. 국내 전기차 관련 법에 따르면 전기차 충전소 앞에 전기차가 아닌 일반 차량이 불법으로 주차를 하게 되면 과태료를 내게 되어 있다. 따라서, 제안한 시스템에서는 전기차가 아닌 일반차가 주차를 하면 경광등 작동시켜 운전자에게 경고한다. 제안한 시스템에서는 딥러닝 기반의 영상인식 SW를 적용하였다. 다양한 조도 환경에서 인식 성공률을 분석하였고 어두운 저녁에는 주변 광량에 따라 인식이 잘 이뤄지지 않는 것을 확인하였다. 향후 추가 LED를 더해 광량의 부족함에 따른 인식률 저하를 개선하는 연구를 진행할 계획이다.

• Journal of Aerospace System Engineering
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• v.15 no.2
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• pp.10-15
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• 2021

The propeller wake of tiltrotor-type aircrafts, such as TR-60 and quad tilt propeller (QTP) UAV, in hover substantially impinges the upper surface of the primary wing and generates a downward load. This load is directly proportional to the thrust of the propeller and reduces the available payload. Therefore, wing and nacelle mechanisms should be carefully designed to reduce downward load. This study conducted a numerical analysis of the rotating propeller in hover to predict the downward load of a QTP UAV. An unsteady three-dimensional Navier-Stokes solver was used along with a sliding mesh for the simulation of the rotating propeller. To reduce the downward load, the tilting mechanisms of the partial wing and nacelle were simultaneously introduced and numerically analyzed. Finally, the downward load was predicted by 14% of isolated propeller thrust; further, the downward load could be reduced by adopting the partial wing and nacelle tilting concept.