• 대한조선학회논문집
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• 제31권3호
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• pp.59-64
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• 1994

본 연구에서는 86,000톤 원유운반선의 프로펠러 날개에서 발생한 singing 현상에 대하여 발생 가능 위치를 조사함으로써 차후 유사문제 발생실 효과적인 방음대책 수립이 가능케 하였다. 조사과정에서는 진동해석과 가진시험으로부터 얻은 프로펠러의 공기중 진동특성을 비교한 후 해석에 의한 접수진동 특성에서 실제 문제 발생가능 모드를 추출하여 실선 계측결과와 비교하였다. 해석결과에 의하면 반경의 95%(0.95R)이상의 날개 끝 뒷날 부분에서 singing이 발생되었을 가능성이 높았으며 방음대책으로 적용된 날개 끝 연삭가공량에 따른 날개의 고유진동수 변화는 거의 없었다.

• 대한치과보철학회지
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• 제31권4호
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• pp.661-678
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• 1993

The purpose of this study was to analyze the stress distribution at supporting bone according to the types of endosseous implants. This investigation evaluated the stress patterns in rectangular photoelastic models produced by four different types of dental implants such as $Br\ddot{a}nemark$, screw type of Steri-Oss, blade type of Steri-Oss, IMZ with IMC and resin tooth using the techniques of quasi-three dimensional photoelasticity. All prostheses were casted in the same nonprecious alloy and were cemented or screwed on their respective implants and abutments. 20 kg of vertical load was applied on the central fossa of casted crown and 16 kg of inclined had was applied on the top third of distal surface of casted crown respectively. The results were as follows : 1. Under the vertical load, screw implants of Steri-Oss and $Br\ddot{a}nemark$ showed increasing stress condition between and around the screw threads along the implant lateral surface and cylindrical implant of IMZ showed the less stress condition along the lateral surface with concentration of stress mostly near the root apex. 2. Under the vertical load, the stress of Steri-Oss blade was distributed uniformly at the alveolar bone under the broad blade. 3. Under the inclined load, the stress concentration of Steri-Oss screw and $Br\ddot{a}nemark$ was developed highly around the mesiocervical bone area on the contralateral side to force application. The stress of $Br\ddot{a}nemark$ with flexible gold glod was more concentrated in the cervical bone area than that of Steri-Oss with stiff screw. 4. Under the inclined load, the stress of Steri-Oss blade broadly was distributed around the mesioceivical bone area and the lower and mesial bone area of the blade. 5. Under the Inclined load, IMZ implant showed the gap between c개wn and fixture due ta deformation of the IMC and IMZ was lower in stress concentration developed around the mesiocervical bone area than $Br\ddot{a}nemark$ and Steri-Oss screw. 6. Under the inclined load, the stress magnitude induced in the mesiocervical bone area of implants was in order of $Br\ddot{a}nemark$, Steri-Oss strew, IMZ and Stsri-Oss blade. 7. Tilting forces as compared to axial forces exerted greater magnitude of stress in the cervical bone area of the implant. 8. In respect of stress distribution, Steri-Oss blade was superior than any other implants and in respect of the stability by horizontal lone, IMB and $Br\ddot{a}nemark$ was inferior than any other implants.

• Journal of Biosystems Engineering
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• 제30권2호
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• pp.75-80
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• 2005

Mechanical characteristics of flower stalks (scapes) of garlic such as shear forces, cutting forces, and modulus of elasticities were investigated as a preliminary research to develop a mechanical harvester of garlic bulbils. The average shear forces of garlic scapes was 0.642 N and the maximum and minimum shear forces were 1.42 and 0.25 N, respectively. The shear forces generally increased as the diameter of garlic scapes increased. There was no correlation between the modulus of elasticity and the diameter of garlic scapes and the average modulus of elasticity of garlic scapes was around $2.40\times10^7\;N/m^2$ There was also no correlation between the cutting force and the diameter of garlic scapes. As the downward speed of blade increased, the cutting force of garlic scapes decreased and reversed to increase. The cutting forces of the lower part garlic scapes were lower than those of the upper part. The range of cutting forces of the lower and the upper part of garlic scapes were 3.88-4.04 N and 4.29-4.93 N, respectively.

• 한국신재생에너지학회:학술대회논문집
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• 한국신재생에너지학회 2007년도 춘계학술대회
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• pp.409-413
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• 2007

To assure the structural integrity for the hub and low speed shaft (LSS) of the drive train, it is necessary to obtain the ultimate aerodynamic loads acting on the wind turbine blade. The aim of this study is to predict the time histories of 3 forces and 3 moments at the hub and the LSS based on the design load case of the IEC 61400-1. From the calculated results most of the load components have rotor revolution frequency whereas thrust and torque of the LSS show blade passage frequency. It turns out that the EWM wind condition involves the maximum ultimate loads at both hub and LSS of the horizontal axis wind turbine.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.115-121
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• 2007

The aeroelastic analysis of rotor blades with trailing edge flaps, focused on reducing vibration while minimizing control effort, are investigated using large deflection-type beam theory in forward flight. The rotor blade aerodynamic forces are calculated using two-dimensional quasi-steady strip theory. For the analysis of forward flight, the nonlinear periodic blade steady response is obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim. The objective function, which includes vibratory hub loads and active flap control inputs, is minimized by an optimal control process. Numerical simulations are performed for the steady-state forward flight of various advance ratios. Also, numerical results of the steady blade and flap deflections, and the vibratory hub loads are presented for various advance ratios and are compared with the previously published analysis results obtained from modal analysis based on a moderate deflection-type beam theory.

• Wind and Structures
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• 제17권6호
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• pp.589-608
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• 2013

A model is proposed to analyse the along-wind dynamic response of upwind turbines with horizontal axis under service wind conditions. The model takes into account the dynamic coupling effect between rotor blades and supporting tower. The wind speed field is decomposed into a mean component, accounting for the well-known wind shear effect, and a fluctuating component, treated through a spectral approach. Accordingly, the so-called rotationally sampled spectra are introduced for the blades to account for the effect of their rotating motion. Wind forces acting on the rotor blades are calculated according to the blade element momentum model. The tower shadow effect is also included in the present model. Two examples of a large and medium size wind turbines are modelled, and their dynamic response is analysed and compared with the results of a conventional static analysis.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 추계학술발표대회 논문집
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• pp.187-190
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• 2000

Cyclocopter is air vehicle to vertically take-off and land like a helicopter. This is an efficient and quiet means of being able to direct thrust compared to a helicopter. The rotor consists of several blades rotating about a horizontal axis perpendicular to the direction of normal flight. The direction of blade span is parallel to rotating axis and both end roots are connected to the hub to resist centrifugal force and to transmit the power. The pitch of the individual blades to the tangent of the circle of the blade's path is varied cyclically to gain thrust. In the paper, the design and manufactures of cyclocopter rotor blades are presented. Stress at the roots of cyclocopter blades is great due to centrifugal and aerodynamic forces and aeroelastic instabilities appear. The blades consist of main spar, front spar, polyurethan foam, weight, and skin and spars and skin are made of glass/epoxy composite.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 추계학술대회논문집
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• pp.106-112
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• 2000

Axial fans are widely used in heavy machines due to their ability to produce high flow rate for cooling of engines. At the same time. the noise generated by these fans causes one of the most serious problems. This work is concerned with the low noise technique of discrete frequency noise. The prediction model. which allowed the calculation of acoustic pressure at the blade passing frequency and it's harmonics. has been developed by Farrasat. This theory is founded upon the acoustic radiation of unsteady forces acting on blade. To calculate the unsteady resultant force over the fan blade. Time-Marching Free-Wake Method are used. The fan noise of fan system having unsymmetric engine-room is predicted. In this paper, the discussion is confined to the performance and discrete noise of axial fan and front part of engine room in heavy equipments.

• 항공우주시스템공학회지
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• 제13권6호
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• pp.52-59
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• 2019

로터 블레이드는 허브를 통해 전달된 토크와 조종장치를 이용한 피치각 제어를 통해 헬리콥터 비행에 필요한 양력, 추력 및 기동력을 발생시킬 수 있는 핵심 구성품이며, 구조적인 안전성과 함께 공진의 위험성이 없도록 진동 특성을 고려하여 설계되어야 한다. 본 연구에서는 다목적 무인 헬리콥터(Multi-Purpose Utility Helicopter)에 적용하기 위한 주로터 블레이드의 구조 설계를 수행하였으며, 제작된 블레이드의 단면 강성 측정 시험을 수행하였다. 이후 측정된 강성 분포를 반영하여 로터 시스템의 진동특성에 대한 평가를 수행하였다. 로터 블레이드 내부는 스킨, 스파 및 토션박스로 구성되며, 탄소 및 유리 섬유 복합소재를 적용하였다. 블레이드 단면 강성 예측을 위해 Ksec2D 프로그램을 활용하였으며, 실험을 통해 측정된 값과 비교한 결과를 제시하였다. 로터 시스템의 회전으로 인한 고유진동수 변화 및 공진 위험 여부를 확인하기 위해 회전익 항공기의 통합 해석 프로그램인 CAMRADII를 활용하였다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2011년도 춘계학술대회 논문집
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• pp.492-497
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• 2011

일반적으로 헬리콥터는 양력, 추력 그리고 힘을 발생시키기 위해 로터 시스템을 사용하기 때문에 공력환경이 매우 복잡하다. 블레이드 와류 간섭과 같은 비정상 공력 환경이 발생한다. 이러한 비정상 공력 환경은 진동하중과 높은 공력소음을 유발한다. 진동하중과 공력소음은 로터 블레이드 회전수에 N 배의 해당하는 주파수 (N/rev)를 갖는다. 하지만 스와시 판과 피치링크로 이루어진 전통적인 로터 조종계통은 블레이드가 1 회 회전하는 동안 한번의 조종 변위를 발생시킬 수 있기 때문에 그러한 진동하중을 조절하기에는 한계가 있다. 이러한 문제를 해결하기 위해 많은 능동 제어 기법들이 개발되었다. 능동 제어기법은 임의의 주파수로 블레이드의 피치 각을 조종할 수 있다. 본 논문에서는 비정상 공력 하중을 변화시키기 위해 능동 제어기법 중 한 가지인 능동 뒷전 플랩 블레이드의 설계를 수행하였다. 능동 뒷전 플랩 블레이드는 에어포일의 캠버를 변화시키기 위해 작동기에 의해 구동되는 뒷전 플랩을 장착한다. 뒷전 플랩을 작동시키기 위해 블레이드 내부에 위치 압전 작동기를 사용하였다.