• 항공우주시스템공학회지
• /
• 제1권3호
• /
• pp.26-31
• /
• 2007

This paper addresses a method for structural optimum design of composite rotor blade. The basic model of a composite helicopter main rotor blade is designed and its parameters determining the structural/dynamic properties are studied. Through the investigation of flap/lag/torsional stiffness, the structural properties of the model are analyzed. In this study, helicopter rotor blades are analyzed by using VABS. The computer program VABS (Variational Asymptotic Beam Section Analysis) uses the variational asymptotic method to split a three-dimensional nonlinear elasticity problem into a two dimensional cross-sectional analysis and a one-dimensional nonlinear beam problem. This is accomplished by taking advantage of certain small parameters inherent to beam-like structures. In addition, the rotational stability of the blade is estimated by the frequency diagram from FE analysis(MSC.Patran/Nastran) to understand its vibrational property. From the result, design parameters to determine and optimize the properties of the model are presented.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2002년도 춘계학술발표대회 논문집
• /
• pp.127-130
• /
• 2002

Vibration analysis of rotating blade is the main purpose of the present study. In this study, general formulation is performed for rotating shell structures including the centrifugal force, Coriolis acceleration and initial twist. Furthermore, simplified equations are derived for the case of an open cylindrical shell. Based on the concept of degenerated shell element with the Reisser-Mindlin's assumptions, the finite element method is adopted for solving the problems. In addition, it is investigated the effect of the stacking sequence of the composites on the vibration characteristics of the blade. The results are summarized for the various parameters such as the speed of rotation and pre-twist of the blade. Also, present results are compared with the previous works and experimental data.

• Journal of Advanced Marine Engineering and Technology
• /
• 제37권1호
• /
• pp.59-65
• /
• 2013

본 논문은 헬리컬 풍력터빈을 이용한 풍력터빈 나무의 구조적 안정성을 검토하는데 목적이 있다. 복합재료를 적용하여 헬리컬 로터 블레이드를 설계하였으며, 유한요소 해석을 통하여 안정성을 검토하였다. 또한 4개의 헬리컬 로터를 지지하고 있는 풍력터빈 나무에 대하여 풍압, 로터의 회전 그리고 자중을 고려한 구조해석을 수행하여 설계 타당성을 검토 하였다.

• 소음진동
• /
• 제7권5호
• /
• pp.819-826
• /
• 1997

The finite element analyses of a composite hingeless rotor blade in forward flight have been performed to investigate the influence of blade design parameters on the blade stability. The blade structure is represented by a single cell composite box-beam and its nonclassical effects such as transverse shear and torsion-related warping are considered. The nonlinear periodic differential equations of motion are obtained by moderate deflection beam theory and finite element method based on Hamilton principle. Aerodynamic forces are calculated using the quasi-steady strip theiry with compressibility and reverse flow effects. The coupling effects between the rotor blade and the fuselage are included in a free flight propulsive trim analysis. Damping values are calculated by using the Floquet transition matrix theory from the linearized equations perturbed at equilibrium position of the blade. The aeroelastic results were compared with an alternative analytic approch, and they showed good correlation with each other. Some parametric investigations for the helicopter design variables, such as pretwist and precone angles are carried out to know the aeroelastic behavior of the rotor.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
• /
• pp.401-407
• /
• 2004

This study proposes a interim development result for the l-㎾ class small wind turbine system, which is applicable to relatively low wind speed regions like Korea and has the variable pitch control mechanism. In the aerodynamic design of the wind turbine blade, parametric studies were carried out to determine an optimum aerodynamic configuration which is not only more efficient at low wind speed but whose diameter is not much larger than similar class other blades. A light composite structure, which can endure effectively various loads, was newly designed. In order to evaluate the structural design of the composite blade, the structural analysis was performed by the finite element method. Moreover both structural safety and stability were verified through the full-scale structural test.

• Advanced Composite Materials
• /
• 제17권1호
• /
• pp.75-87
• /
• 2008

Aerospace structural applications, along with high performance marine and automotive applications, require high-strength efficiency, which can be achieved using metal matrix composites (MMCs). Rotating components, such as jet-engine blades and gas turbine parts, require materials that maximize strength efficiency and metallurgical stability at elevated temperatures. Titanium matrix composites (TMCs) are well suited in such applications, since they offer an enhanced resistance to temperature effects as well as corrosion resistance, in addition to optimum strength efficiency. The overall behavior of the composite system largly depends on the properties of the interface between fiber and matrix. Characterization of the fiber.matrix interface at operating temperatures is therefore essential for the developemt of these materials. The fiber fragmentation test shows good reproducibility of results in determining interface properties. This paper deals with the evaluation of fiber fragmentation characteristics in TMCs at elevated temperature and the results are compared with tests at ambient temperature. It was observed that tensile testing at $650^{\circ}C$ of single-fiber TMCs led to limited fiber fragmentation behavior. This indicates that the load transfer from the matrix to the fiber occurs due to interfacial friction, arising predominantly from mechanical clamping of the fiber by radial compressive residual and Poisson stresses. The present work also demonstrates that composite processing conditions can significantly affect the nature of the fiber.matrix interface and the resulting fragmentation of the fiber.

• 대한조선학회논문집
• /
• 제46권2호
• /
• pp.203-217
• /
• 2009

The researches on the development of composite material propeller with outstanding damping effects have been actively attempted for the reduction of radiation noise of underwater vehicle propeller. Composite material suitable for the flexible propeller has the following advantages, such as high specific strength and specific stiffness, low thermal expansion coefficient, high resistance against environmental deterioration, low possibility of corrosion due to cavitation, nonoccurrence of rapid fracture due to fatigue, easy molding of complicated shape, easy repair maintenance and low production costs, etc. For the confirmation of optimal fiber array structures of composite material for the production of the flexible propeller blades, in this study, mechanical characteristics of its specimens according to materials were obtained and structural characteristics of propeller blade were also examined according to materials and stacking fiber arrays.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2007년도 춘계학술대회A
• /
• pp.136-141
• /
• 2007

This paper introduces an artificial neuron which is a nano composite continuous sensor. The continuous nano sensor is fabricated as a thin and narrow polymer film sensor that is made of carbon nanotubes composites with a PMMA or a silicone matrix. The sensor can be embedded onto a structure like a neuron in a human body and it can detect deteriorations of the structure. The electrochemical impedance and dynamic strain response of the neuron change due to deterioration of the structure where the sensor is located. A network of the long nano sensor can form a structural neural system to provide large area coverage and an assurance of the operational health of a structure without the need for actuators and complex wave propagation analyses that are used with other methods. The artificial neuron is expected to effectively detect damage in large complex structures including composite helicopter blades and composite aircraft and vehicles.

• 비파괴검사학회지
• /
• 제31권4호
• /
• pp.382-390
• /
• 2011

최근 대형화되는 복합재 풍력 블레이드의 운전 중 발생되는 손상을 조기에 모니터링하기 위하여 블레이드 내부에 일제형으로 설치가 가능한 스마트 센서들이 연구되고 있다. 본 연구에서는 광섬유 브래그 격자(FBG: Fiber Bragg grating) 센서를 복합재 모형 블레이드 후연부 시편에 부착하여 균열 또는 접착층 분리를 감지하는 실험을 수행하여 패키징된 광섬유 브래그 격자 센서 탐촉자의 풍력 블레이드에 적용 가능성을 검토하였다. 블레이드 시편에 인가된 연장 하중이 1100 N부터 1260 N 사이에서 노출된 광섬유 브래그 격자 센서의 파장 이동 방향이 급격히 반전되는 결과로부터 전단 웹의 균열과 접착 분리 파손을 확인할 수 있었다. 블레이드에 사용하기 위한 노출된 광섬유 브래그 격자 센서는 깨지가 쉽기 때문에 이 단점을 보완하기 위하여 에폭시로 패키징된 광섬유 브래그 격자 센서 탐촉자를 제작하였다. 블레이드 시편의 스킨 위에 제작된 탐촉자를 설치한 후 인장 시험을 수행한 결과 변형률에 대한 감지도는 약 1.3 ${\mu}{\varepsilon}$/pm으로 노출된 광섬유 브래그 격자 센서의 감지도와 거의 동일한 것으로 확인되었다. 한편 온도 감지도는 $80^{\circ}C$ 까지의 가열 테스트를 통하여 약 48 pm/$^{\circ}C$의 온도 감지도를 보였다.

• 항공우주시스템공학회지
• /
• 제6권4호
• /
• pp.7-11
• /
• 2012

Recently, the renewable energy has been widely used as a wind energy and solar energy resource due to lack and environmental issues of the mostly used fossil fuel. In this situation, the interest in wind power has been risen as an important energy source. For this blade a high efficiency wind turbine blade was designed with the proposing aerodynamic design procedure, and a light and low cost composite structure blade was designed considering fatigue life. Structural analyses including load case study, stress, deformation, buckling, fatigue life and vibration analysis were performed using the Finite Element Method.