• Composites Research
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• 제36권1호
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• pp.32-36
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• 2023

최근 탄소 중립 등 지속 가능한 발전을 위한 지구환경 문제가 대두되면서 기존 풍력터빈의 소재인 유리섬유 복합재의 폐기 시 처리 방안이 문제가 되고 있다. 이를 해결하기 위해 본 연구에서는 기존의 유리섬유 복합재를 대체할 수 있는 친환경 복합재인 아마섬유 기반 복합재를 활용하여 30kW 풍력터빈 블레이드를 제조하고 적합성을 평가하였다. 먼저 친환경 천연 아마섬유 복합재의 풍력터빈 블레이드 소재로 활용 가능성을 검증하기 위해 기계적 강도 시험을 수행하였으며, 그 결과 선행 아마섬유 복합재 물성 연구 대비 좀 더 우수한 강도가 측정된 것을 확인하였다. 또한 제작된 30kW 급 아마섬유 복합재 블레이드를 활용하여 아마섬유 복합재 블레이드의 정적강도를 측정하는 정적강도 성능평가 시험을 통하여 적합성을 확인하였다.

• 한국항공우주학회지
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• 제39권8호
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• pp.758-765
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• 2011

최근 화석 에너지의 고갈로 신재생 에너지 중에서 풍력 에너지가 각광받고 있다. 본 연구는 국내 기상과 같이 저 풍속 지역에 적합한 500W급 수직축 풍력 터빈에 관한 연구로서 공력 설계를 통해 저풍속에서도 고효율과 저소음을 가진 형상을 제시하였으며, 복합재료를 적용하여 블레이드의 구조 설계를 수행하였다. 구조 설계 후 유한 요소 모델링을 통하여 응력, 변형, 좌굴, 공진가능성에 관한 해석을 수행 하였다. 또한 피로 수명을 예측 하였으며, 최종 제작된 풍력 터빈은 구조 실험과 성능 시험을 통하여 구조 해석 결과 및 공력 해석 결과와 비교하여 잘 일치함을 확인하였다.

• Wind and Structures
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• 제29권6호
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• pp.431-440
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• 2019

The aim of this study was to explore the influence of structure coupling effect on structural damping of blade based on the blade vibration characteristic. For this purpose, the scaled blade model of NREL 5 MW offshore wind turbine was processed and employed in the wind tunnel test to validate the reliability of theoretical and numerical models. The attenuation curves of maximum displacement and the varying curves of equivalent damping coefficient of the blade under the rated condition were respectively compared and analyzed by constructing single blade model and whole machine model. The attenuation law of blade dynamic response was obtained and the structure coupling effect was proved to exert a significant influence on the equivalent damping coefficient. The results indicate that the attenuation trend of the maximum displacement response curve of the single blade varies more obviously with the increase of elastic modulus as compared to that under the structure coupling effect. In contrast to the single blade model, the varying curve of equivalent damping coefficient with the period is relatively steep for the whole machine model. The findings are of great significance to guide the structure design and material selection for wind turbine blades.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.165-173
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• 2017

The aeromechanics predictions of HART I rotor obtained using a computational structural dynamics (CSD) code are evaluated against the wind tunnel test data. The flight regimes include low speed descending flight at an advance ratio of ${\mu}=0.151$ and cruise condition at ${\mu}=0.229$. A lifting-line based unsteady airfoil theory with C81 table look-up is used to calculate the aerodynamic loads acting on the blade. Either rolled-up free wake or multiple-trailer wake with consolidation (MTC) model is employed for the free vortex wake representation. The measured blade properties accomplished recently are used to analyze the rotor for the up-to-date computations. The comparison results on airloads and structural loads of the rotor show good agreements for descent flight and fair for cruise flight condition. It is observed that MTC model generally improves the correlation against the measured data. The structural loads predictions for all measurement locations of HART I rotor are investigated. The dominant harmonic response of the structural loads is clearly captured with MTC model.

• 항공우주시스템공학회지
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• 제12권5호
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• pp.24-31
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• 2018

항공기의 블레이드 안테나에 대해 더미와 실 안테나의 조류충돌 해석과 시험을 수행하였다. 해석에서 조류는 SPH(Smooth Particle Hydrodynamics) 방법을 이용하여 모델링하였으며, 유체-구조 연성해석 (FSI, Fluid-Structure Interaction) 기법으로 조류와 안테나, 기체 체결부의 거동을 시뮬레이션 하였다. 실제 조류를 사용한 시험을 수행하여 안테나와 동체 사이의 체결부 손상 및 이탈여부를 확인하였으며, 항공기 기체의 구조건전성과 해석 및 시험 결과 사이의 상관성이 있음을 입증하였다.

• 한국자동차공학회논문집
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• 제18권2호
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• pp.83-90
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• 2010

The windshield wiper consists of 4 parts: a blade, an arm, a linkage and a motor. The wiper blade makes contact with the windshield and is designed to be operated normally at an angle of 30~50 degrees to the front glass. If the contact pressure between the wiper blade and windshield surface is too high, noise and wear of the rubber will result. On the other hand, if the contact pressure is too low, the performance will do badly, since foreign substances such as dust and stains will not be removed well. The pressure and friction of the wiper blade has a great influence on its effectiveness in cleaning the front window. This is due to the contact of the rubber with the window. This paper presents the dynamic analysis method to estimate the performance of the flat type blade of the wiper system. The blade has a nonlinear characteristic since the rubber is an incompressible hyper-elastic and visco-elastic material. Thus, Structural dynamic analysis using a complex contact model for the blade is performed to find the characteristics of the blade. The flexible multi-body dynamic model is verified by the comparison between test and analysis result. Also, the optimization using the central composite design table is performed.

• 한국항공우주학회지
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• 제46권3호
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• pp.237-243
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• 2018

본 연구에서는 고 전진비 조건의 로터에 대해 전진비 변화에 따른 허브 진동하중의 변화를 예측하고, 블레이드에서 발생하는 구조하중 예측 및 조화 분석을 통하여 구조하중 변화를 고찰하였다. 로터 전진비는 0.40부터 0.71까지 범위를 가지며, NASA에서 수행한 풍동시험 결과에 대해 수치묘사 연구를 수행하였다. 검증한 결과를 토대로 허브 진동하중 및 블레이드 모멘트를 예측하였다. 허브 진동하중은 최초에 증가하다가 전진비가 0.5 이상의 경우에는 변화가 거의 없음을 보여주었다. 블레이드 구조하중은 전진비가 증가할수록 진폭의 크기가 증가하며, 블레이드 모멘트의 조화 분석을 수행한 결과 플랩 모멘트는 3/rev, 래그모멘트는 4/rev의 영향이 매우 크다는 점을 확인하였다. 이는 전진비가 증가할수록 2차 플랩과 2차 래그 모드의 고유진동수가 각각 3/rev와 4/rev에 근접하기 때문인 것으로 파악되었다.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.498-511
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• 2017

This work conducts a validation study for loads analysis of the UH-60A slowed rotor at high advance ratios. The nonlinear flexible multibody dynamics analysis code, DYMORE II, is used with a freewake model for the rotorcraft comprehensive analysis. Wind tunnel test data of airloads and structural loads of a full-scale UH-60A slowed rotor are used for this validation study. This analysis predicts well the thrust reversal phenomenon at the advance ratio of 1.0. The section airloads such as normal forces and pitching moments and the oscillatory blade structural moments in this analysis are compared well or moderately with the measured data, although the higher harmonics components of blade torsion moments are not captured well. This validation study assesses the prediction accuracy and investigates the unique aeromechanics characteristics of a slowed rotor at high advance ratio.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2014년도 추계학술대회 논문집
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• pp.893-899
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• 2014

X-band antenna has been widely used to effectively transmit the high resolution image data from the observation satellite to the ground station. To achieve above mission, X-band antenna is mainly composed of the 2-axis gimbal system using stepping motors and gears. However, the micro-vibration induced by the stepping motor actuation and the imperfect gear teeth alignment during this on-orbit operation is the main source of image quality degradation. In this paper, X-band antenna combined with a blade gear for micro-vibration isolation was suggested and investigated. The structural safety of the blade gear with low rotational stiffness was confirmed by structure analysis based on the derived torque budget. The isolation performance of the X-band antenna with the blade gear was verified through micro-vibration measurement test using the dedicated micro-vibration measurement device proposed in this study.

• International Journal of Aeronautical and Space Sciences
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• 제13권3호
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• pp.349-360
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• 2012

In this study, the accuracy of CSD (Comprehensive Structural Dynamics) analysis on the evaluation of blade aeroelastic responses and structural loads of HART(Higher harmonic Aeroacoustic Rotor Test) II baseline rotor is assessed using a comprehensive rotorcraft dynamics code, CAMRAD II, and a nonlinear flexible multi-body dynamics analysis code, DYMORE. Considering insufficient measurement data for HART II rotor, prescribed airloads computed by a three-dimensional compressible flow solver KFLOW are used to replace the lifting-line airloads and thereby enhance the prediction capability of the comprehensive analyses. The CSD results on blade elastic deflections using the prescribed airloads indicate more oscillatory behavior than those by lifting-line based approaches, but the wave pattern becomes improved by including artificial damping into the rotor system. It is demonstrated that the structural load predictions are improved significantly by the prescribed airloads approach against the measured data, as compared with an isolated CSD analysis.