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배재성,박상혁,김학봉,이수용,홍예선,안일영,김승종 한국항공우주학회 2011 한국항공우주학회 학술발표회 논문집 Vol.2011 No.4
장기 체공 태양광 무인항공기 개발을 위한 소형 태양광 RC 비행기에 대한 선행 연구를 수행하였다. 태양에너지는 태양광 무인항공기의 영구비행을 가능하게 해줄 수 있다. 이를 위해서는 태양전지를 사용하여 태양에너지를 전기에너지로 변환시키고, 변환된 에너지를 무인항공기의 비행동력과 배터리 충전에 사용한다. 태양광 무인항공기의 비행시간을 증가시키기 위해서는 태양전지 시스템의 효율을 높이고, 비행에 필요한 동력은 최소한으로 사용하는 것이다. 따라서, 태양전지 및 콘트롤러, 추진시스템 설계, 무인항공기의 공력 및 구조 설계 등의 전체 시스템에 대한 설계가 매우 중요하다. 본 연구에서는 장기 체공태양광 무인항공기 개발을 위한 선행연구로서 소형 태양광 무인항공기에 대한 설계/제작 및 비행시험을 수행하였다. 이로부터 태양광 무인항공기 개발을 위한 시스템설계 기술을 확보하고, 태양광 무인항공기 개발의 가능성 및 문제점 등을 파악하여 향후 연구에 반영하고자 한다. In the present study, the preliminary study on a small solar-powered RC airplane are performed for the development of a long-endurance solar-powered UAV. Solar energy enables the solar-powered UAV to fly longer or eternally. The solar-powered UAV transfers the solar energy to electric energy and this energy is used for the flight and the battery charge. To increase the flying time, the efficiency of the solar-cell power system must be increased and the required power for flight must be minimized. Hence, the system integration including solar cell and controller, the power system design, and the aerodynamic and structural designs of the UAV is very important. The present study have performed the design, manufacture, and flight test of the small solar-powered UAV for the preliminary study of the long-endurance solar-powered UAV. From this study, the system integration technology of the solar-powered UAV design is established, and the possibility and the issue points for the development of the long-endurance solar-powered UAV are discussed.
열경화성 에폭시를 이용한 가스 절연 개폐기용 절연 스페이서의 사출 성형 최적화 시뮬레이션
배재성,이원창,지홍섭,홍병유,이재형 한국전기전자재료학회 2021 전기전자재료학회논문지 Vol.34 No.6
Injection molding is used in many industrial fields such as home appliances, vehicle parts, and electronic device parts because various resins can be molded, leading to mass production of complex shapes. Generally, the empirical prediction method is used to set the initial processing conditions of injection molding. However, this approach requires a lot of cost and its presented solution is not accurate. In this paper, injection molding was simulated through the MoldflowTM in order to manufacture the spacer for gas insulated switch. Through the simulation, the flow of the resin with respect to the diameter of the inlet was analyzed. It was found that the process was possible at a higher resin temperature as the diameter of the inlet increased. In addition, through thermal analysis during injection of the resin, it was confirmed that a stagnation phenomenon occurred at the insert portion during injection molding, and the temperature of the resin was higher than that of the mold. As in this paper, if the spacer is manufactured by optimizing the injection hole and the temperature of the injection process based on simulation, it is expected that the spacer can be manufactured with high productivity.
배재성,신명승 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.4
여러 분야에서 능동적 비틀림 제어기법에 대한 연구가 활발히 수행되고 있다. 효율적인 비틀림제어를 위해 블레이드는 동일한 비틀림하중에 대해 낮은 응력을 갖는 동시에 큰 비틀림변형을 가져야 한다. 본 연구에서는 능동 비틀림 제어에 용이한 블레이드를 찾기 위해 5 개의 각기 다른 스파를 갖는 블레이드에 대해 2 차원 단면 해석 과 3 차원 유한요소해석을 수행하였다. 2 차원 단면해석에서 얻은 결과들을 이용해 3 차원 유한요소해석을 진행하였다. 이번 연구에서 설정한 조건에서 2 차원 단면해석과 3 차원 유한요소 해석결과들은 동일한 하중조건에서 C 형상의 보를 갖는 블레이드가 능동적 비틀림 제어에 가장 용이한 형상이라는 것을 보여주었다. On wide variety of fields, studies on active twist control are becoming more active. For effective twist control, blades have to have low torsional stresses with high torsional deformations to the same magnitude of torque acting on its crosssection. In this study, 2D sectional analysis and 3D finite element analysis were made for 5 different blades with each having different cross –sections which have different spars. The results from 2D sectional analysis, were then put into 3D blade deformation and stress calculations which lead to analysis. Outcomes from 2D and 3D analysis, showed that on the same torque and concentrated load conditions, the blade with ‘C’ shaped spar was the best of all the blades which were used in this study.
Modeling and experiments on eddy current damping caused by a permanent magnet in a conductive tube
배재성,황재혁,박정삼,곽동기 대한기계학회 2009 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.23 No.11
Eddy currents are induced when a nonmagnetic, conductive material is moving as the result of being subjected to a magnetic field, or if it is placed in a time-varying magnetic field. These currents circulate in the conductive material and are dissipated, causing a repulsive force between the magnet and the conductor. With this concept, eddy current damping can be used as a form of viscous damping. The present study investigates analytically and experimentally the characteristics of eddy current damping when a permanent magnet is placed in a conductive tube. The theoretical model of eddy current damping as the result of a magnet in a copper tube is developed from electromagnetics and is verified from experiments. The experiments include a drop test whereby a magnet is dropped in a copper tube to measure the damping force in a steady-state, and a dynamic test is used to measure the same phenomenon in a dynamic-state. The drop test shows that the present model can accurately predict the force of steady-state damping. From the dynamic test, although predictability is not accurate at high excitation frequencies, the present model can be used to predict damping force at low excitation frequencies.
배재성,현영오,곽동기,박영근,황재혁,Bae, Jae-Sung,Hyun, Young-O,Kwak, Dongi-Gi,Park, Young-Guen,Hwang, Jai-Hyuk 한국항공운항학회 2006 한국항공운항학회지 Vol.14 No.4
In this paper, an experimental study on the robust input shaping for control of the residual vibration of flexible structures has been investigated. Two approaches has been used for the robustness of input shaping: the first method is to increase the number of impulses, and the other includes an EI shaper using vector diagram. The input case designed by the application of the above methods has been applied to a control problem involving residual vibration of a rotating hub with two flexible appendages. It has been found by a series of experiments that the input shaper designed in this paper works well for the residual vibration control of the flexible structure.