• 한국전자통신학회논문지
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• 제13권6호
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• pp.1229-1234
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• 2018

본 논문에서는 풍력발전기 너셀 내부에서 발생 가능한 화재를 예방하거나 신속하게 대응하기 위하여 광대역 전력선통신시스템 기반 화재 예방시스템을 구현하고 실증실험을 수행한 결과를 제시한다. 이를 위하여 고속 전력선통신용 주파수 대역에서 우수한 손실 특성을 가지는 유도성 통신 연결장치도 제작하였다. 구현된 시스템은 터빈 너셀에 설치된 온도, 불꽃, 연기센서 등 다양한 센서 정보와 열화상 이미지를 전력선통신시스템을 통하여 지상관제소에 고속 전송함으로써 너셀 내부의 환경변화를 실시간으로 감시할 수 있음을 확인하였다. 따라서 구현된 시스템은 이미 설치된 기존 안전시스템과 연동하여 풍력발전기 화재감시 및 예방체계의 신뢰성을 크게 향상시킬 수 있을 것으로 기대된다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.301-307
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• 2005

In this study, simplified whirl flutter analyses using quasisteady aerodynamic theory have been performed for a 2-DOF tilt-rotor system with both pitch and yaw motions of a rotor-nacelle. The present dynamic system consists of the rotor (propeller), forming the gyroscopic and aerodynamic element, supported horizontally by a pylon that is pivoted at some wing attachment point. Several design parameters (or rotor-nacelle system are considered and the effect of whirl flutter stability are also investigated for various design parameters.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 춘계 학술대회논문집
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• pp.60-65
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• 2000

An aerodynamic design method has been developed by using a three-dimensional unstructured Euler code and an adjoint code with a discrete approach. The resulting adjoint code is applied to a wing design problem of super-sonic transport with a wing-body-nacelle configuration. Hicks-Henne shape functions are adopted far the surface geometry perturbation, and the elliptic equation method is employed fer the interior grid modification during the design process. Interior grid sensitivities are neglected except those for design parameters associated with nacelle translation. The Sequential Quadratic Programming method is used to minimize the drag with constraints on the lift and airfoil thickness. Successful design results confirm validity and efficiency of the present design method.

• 한국소음진동공학회논문집
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• 제15권7호
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• pp.843-850
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• 2005

In this study, simplified whirl flutter analyses using quasisteady aerodynamic theory have been Performed for a 2-DOF tiIt-rotor system with both pitch and Yaw motions of a rotor-nacelle. The present dynamic system consists of the rotor (propeller) , forming the gyroscopic and aerodynamic element, supported horizontally by a pylon that is pivoted at some wing attachment point. Several design parameters for rotor-nacelle system are considered to practically investigate the effects of whirl flutter stability.

• 대한기계학회논문집B
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• 제32권10호
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• pp.810-815
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• 2008

To enhance aerodynamic efficiency of the Smart Un-manned Aerial Vehicle(SUAV) during the transition period, wingtip fence is attached at the end of wing. The application of wingtip fence is to reduce the effect of the separated flow caused by the nacelle on the wing especially when the tilting angle of nacelle is more than 30 degrees. To compare the effect of with and without wingtip fence, flow visualization and measurement of the aerodynamic coefficients using the pyramidal type external balance are done. Result of forces and moments measurement shows that the slope of lift coefficient is increased 18% and rolling moment of SUAV especially 60 & 90-degree tilting is changed in favorable manners with wingtip fence.

• 항공우주시스템공학회지
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• 제15권2호
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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.

• 한국항해항만학회지
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• 제40권3호
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• pp.159-164
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• 2016

본 연구는 해상풍력발전기에 추가적인 통신전용선로를 확보하지 않고도 자체 전력선을 이용하여 나셀의 상태를 감시할 수 있는 시스템을 구현하는 것을 목표로 한다. MW 급 해상풍력발전기의 내부 전력선을 훼손하지 않고도 통신선로를 확보하기 위하여 유도성 결합기 기반 비접촉식 무배선 통신시스템을 제안하고 성능시험 결과를 보고한다. 페라이트 복합물질을 이용하여 최대 500 A의 고 전류에도 동작할 수 있는 전력선 통신용 유도성 결합기를 개발하였으며 제주도 풍력단지에서 실증시험을 진행하였다. iperf를 이용한 통신성능시험에서 풍력발전기 나셀부와 하단 기저부의 전력변환기간 100 m 길이의 전력선으로 최소 15 Mbps 이상의 통신 속도를 안정적으로 확보할 수 있음을 보였다. 이를 바탕으로 1 주일간의 연속적인 통신상태 시험을 수행하였으며 평균 20 Mbps의 데이터 전송률을 확인하였다. 시험기간 동안 단한번의 통신 불량도 발생하지 않았다. 다음으로 나셀 내부 온도 분포와 변화를 측정하기 위하여 적외선 카메라를 설치하였다. 카메라에서 획득한 실시간 열화상 이미지가 오류 없이 성공적으로 전송됨을 확인하였다.

• 제어로봇시스템학회논문지
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• 제20권11호
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• pp.1103-1111
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• 2014

The results of control law design for a tilt-rotor unmanned aerial vehicle that has a nacelle mounted wing extension (WE) are presented in this paper. It consists of a control surface mixer, stability and control augmentation system (SCAS), hold mode for altitude / speed / heading, and a guidance mode for preprogram and point navigation which includes automatic take-off and landing. The conversion corridor and the control moments derivatives between the original tilt-rotor and its variant of the nacelle mounted WE were compared to show the effectiveness of the WE. The nacelle conversion of the original tilt-rotor starts when the airspeed is greater than 30 km/h but its WE variant starts at 0 km/h in order to reduce the drag caused by the high incidence angle of the WE. The stability margins of the inner loop are presented with the optimization approach. The outer loops for the hold mode are designed with trial and error methods with linear and nonlinear simulation. The main control parameter for altitude control of the helicopter mode is thrust command and it is transferred to the pitch attitude command in airplane mode. Otherwise, the control parameter for the speed of the helicopter mode is the pitch attitude command and it is transferred to the thrust command in airplane mode. Therefore the speed and altitude hold mode are coupled to each other and are engaged at the same time when an internal pilot engages any of the altitude or speed hold modes. The nonlinear simulation results of the guidance control for the preprogrammed mode and point navigation are also presented including automatic take-off and landing in order to prove the full control law.

• 한국전자통신학회논문지
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• 제7권1호
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• pp.81-89
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• 2012

범용적으로 사용되고 있는 수평형 풍력 터빈(HAWT)은 블레이드가 장착된 터빈이 회전부인 너셀에 고정되어 타워의 최상단에 지지되는 구조이다. 터빈에서 생산되는 전력은 너셀 내부에서 증속기를 통하여 발전기로 들어가게 된다. 발전기에서 생산되는 전력은 타워를 통해서 지상과 송전선으로 연결되므로 너셀의 요잉이 발생하는 경우 송전선의 꼬임이 발생하게 된다. 따라서 이를 방지하기 위한 슬립링이나 추가적인 요잉 제어 알고리즘이 필요한 단점이 있다. 제안하는 새로운 구조의 HAWT는 베벨기어와 중공축을 이용하여 송전선 문제를 해결하였다. 또한, 병렬로 접속된 두개의 발전기를 이용하여 요잉이 용이할 뿐 아니라 생산 전력을 분산시킴으로써 인버터의 용량을 줄일 수 있다. MPPT 알고리즘과 요잉 제어를 수행하는 시뮬레이션을 통해서 제안하는 구조가 풍력 발전에 효과적임을 보였다.

• Journal of Mechanical Science and Technology
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• 제15권4호
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• pp.522-530
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• 2001

An experimental study of compressible jet flows has been undertaken in a small transonic wind tunnel. The aim of this investigation was to realize a jet simulator in the framework of wing/nacelle integration research and to characterize the jet flow behavior. First, free jet configuration, and subsequently jet flow in co-flowing air stream configuration were analyzed. Flow conditions were those encountered in a typical flight condition of a generic transport aircraft, i.e. fully expanded sonic jet flows interacting with a compressible external flowfield. Conventional experimental techniques were used to investigate the jet flows-Schlieren visualization and two-component Laser Doppler Velocimetry (LDV). The mean and fluctuating properties were measured along the jet centerline and in the symmetric plane at various downstream locations. The results of two configurations show remarkable differences in the mean and fluctuating components and agree well with the trend observed by other investigators. Moreover, these experiments enrich the database for such flow conditions and verify the feasibility of its application in future aerodynamic research of wing/nacelle interactions.