• Proceedings of the KIPE Conference
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• 2005.07a
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• pp.159-161
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• 2005

본 논문은 회전형 대용량의 진단 X-선 발생장치를 모노 블록 형태로 설계, 병원의 모바일 진단장치나, 산업용 X-선 장치로의 적용이 가능한 16kw급 X-선 발생장치에 관한 연구이다. 본 장치는 X-선 발생을 위한 고전압 발생부에 회전형 Anode 형의 X-선관을 사용하였고, X-선관의 로터를 구동할 수 있는 로터 구동회로를 추가 하였다. 고주파 고전압용 인버터에는 IGBT(600/300A)를 100kHz로 고주파 스위칭 함으로서 고전압 변압기를 비롯한 고전압 발생부의 크기와 무게를 최소화하였다. 또한, 기존의 16kw급 대용량 진단 X-선 발생장치를 X-선관과 고전압부를 일체화한 모노블록 형태로 설계, 제작하여 부하변동에 따른 X-선 관전압과 관전류의 동작특성을 실험을 통하여 입증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.2
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• pp.105-114
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• 2008

In this study, the sizing and performance analysis program is developed for the canard rotor wing(CRW) aircraft which operates in dual modes (fixed wing mode and rotary wing mode). The developed program is verified for both fixed wing and rotary wing modes using the existing aircraft data and the design optimization formulation is made to perform the reconnaissance mission. For the canard rotor wing aircraft optimization , multi-objective function is constructed to consider both the fixed wing mode and rotary wing mode the weighting factor. For six design cases with different weighting factors and different design constraints, the optimization is performed and improved rotor design results are derived.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.78-86
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• 2006

This paper presents the performance test result of the 30-ton class turbopump turbine. Test has been conducted using high pressure cold air, The turbine overall performance has been measured for various pressure ratio and rotational speed settings. The nozzle-rotor clearance effect on turbine performance also has been tested for the four kinds of the nozzle-rotor clearance values. We found that turbine efficiency rated 51.1% at its design velocity ratio and pressure ratio of 13.5. We also found that turbine efficiency can be increased by 3.5% for approximately 1mm decrement of the nozzle-rotor clearance from its nominal value.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2017.11a
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• pp.143-144
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• 2017

에어보트(Air boat)는, 판옥선처럼 선체 밑바닥이 편평한 형태로 되어있어 물위는 물론 일반 선박이 갈 수 없는 얕은 수면, 늪지수풀 위를 달릴 수 있는 모터보트의 한 종류로서, 팬 보트(Fan boat) 혹은 덕 보트(Duck boat)라고 불리기도 한다. 선체상부 뒤쪽에 장착된 로터의 회전에 의한 풍력으로 추진되며, 로터 바로 뒤에 방향키가 있다. 선체 재질로는 스틸, FRP 등이 사용되고 있으나 최근 고부가선박을 대상으로 알루미늄, 탄소섬유 사용이 늘어나고 있다. 주로 수상 크루징, 낚시, 스쿠버 등에 활용되며, 특히 선저의 독특한 형상으로 인해 군사용, 인명구조용, 수산물수송용 등 특수 목적으로도 사용된다. 이 연구에서는 에어보트 국산화 개발을 위해 주요 개발항목을 도출하고, 12인승 보트를 제조하고자 한다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2018.05a
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• pp.185-186
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• 2018

에어보트(Air boat)는, 판옥선처럼 선체 밑바닥이 편평한 형태로 되어있어 물위는 물론 일반 선박이 갈 수 없는 얕은 수면, 개펄, 빙상, 늪지수풀 위를 달릴 수 있는 모터보트의 한 종류이다. 선체상부 뒤쪽에 장착된 로터의 회전에 의한 풍력으로 추진되며, 로터 바로 뒤에 방향키가 있다. 선체 재질로는 스틸, FRP가 주로 사용되고 있으며 최근 알루미늄, 탄소섬유의 적용이 늘어나고 있다. 수상크루징, 낚시, 스쿠버 등에 활용되며, 선저의 독특한 형상으로 인해 군사용, 인명구조용, 수산물수송용 등으로도 사용된다. 이 연구에서는 12인승 비미니탑 에어보트를 설계, 제작하고 해상 시운전을 실시하였다. 또한 소음저감을 위해 머플러를 설계 제작하고, 35노트에서 75~78dB 수준으로 성능을 검증하였다.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.254-262
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• 2008

Several decades have passed since tiltrotor technology became a hot issue of debates between aircraft majors, policy maker and mass-media. Although most of those subjects have been officially probed or answered in objective way, biased articles or argues related with the adequacy of this technology still prevail in the way of tilt-rotor development programs, which are totally irrelevant and out-dated. This paper aims to help understanding on those issues in technically balanced manner and the cases of flight test mishaps.

• Journal of the KSME
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• v.30 no.5
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• pp.450-453
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• 1990

회전축(로터 안 구멍)과 정지부(베어링, 케이싱 등)에 AE 센서를 붙여 이들의 검출신호를 목적 으로 처리하는 것에 의해 회전체 주위의 이상진단을 수행하는 AE 시스템에 대해서 소개하였다. 회전측의 신호검출에는 무선식 전송방식을 이용하는 것이 유효하다고 생각된다. 또한 베어링에 설치한 AE 센서로부터 베어링의 손상진단이 가능하다는 것과 함께 래빙 발생위치도 알아낼 수 있다고 생각된다. 이 글에서는 회전기계의 이상진단에 관하여 극히 일부를 소개하였으나 AE 법을 이용한 각종 응용이 개발되리라고 기대된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.3
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• pp.197-209
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• 2018

In this study, numerical analyses on Quad Tilt Rotor(QTR) are carried out to investigate the interference effect of components and effect of operating condition during forward flight. Actuator Surface Method(ASM) which is implemented in an open source CFD code, OpenFOAM, is used to calculate the flow field around QTR with high computational efficiency. The lift of the front and rear wing is found to increase or decrease depending on the rotation direction of the rotor. At the rear wing, the interference effects of the front and rear rotor appear as a combined manner. Performance change due to the phase difference is found to be insignificant. For both rotors, the locally higher thrust is generated by the blockage effect of the wing. The interference effect of wake from the front nacelle contributes to higher local thrust for the rear rotor compared to the front rotor. And it is observed that the amplitude of thrust oscillation can decrease depending on the phase difference between the rotors. Aerodynamic performances of both rotors and the entire aircraft were compared and analyzed for various operating conditions.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.52-59
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• 2019

The rotor blade is a key component that generates the lift, thrust, and control forces required for helicopter flight by the torque transmitted through the hub and the blade pitch angle control, and should be designed to factor vibration characteristics so that there is no risk of resonance with structural safety. In this study, the structural design of the main rotor blade for MPUH(Multi-Purpose Unmanned Helicopter) was conducted and the sectional stiffness measurement of the fabricated blade was performed. The evaluation of the vibration characteristics of the main rotor system was then conducted factoring the measured stiffness distribution. The interior of the rotor blade comprised of the skin, spar, and torsion box, and carbon and glass fiber composites were applied. The Ksec2D program was applied to predict the stiffness of blade, and the results were compared to the measured data. CAMRADII, a comprehensive rotorcraft analysis program, was applied to investigate the natural frequency trends and resonance risks due to the rotor rotation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.6
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• pp.509-516
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• 2007

Mathematical modeling and vibration control of a tiltrotor aircraft composite wing-rotor system are investigated in this study. A wing-mounted rotor can be tilted from the vertical position to a horizontal one, and vice versa. Effect of vibration control of the wing-rotor system via piezoelectricity is studied as a function of tilt angle, ply angle of composite wing and rotor's spin speed. Composite wing is modeled as a thin-walled box beam having a circumferentially uniform stiffness configuration that produces elastic coupling between flap-lag and between extension-twist behavior. Numerical simulations are provided and pertinent conclusions are outlined.