• 제목/요약/키워드: Flexible wing

검색결과 46건 처리시간 0.029초

유연 날개 설계 및 돌풍응답완화 수치해석 (Design and Numerical Analysis of Flexible Wing for Gust Response Alleviation)

  • 이상욱;김태욱;김성찬;황인희;하철근
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2006년도 춘계학술대회논문집
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    • pp.203-206
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    • 2006
  • In this study, the method of designing the flexible wing model which will be used for wind tunnel testing of gust response alleviation system was presented. The design concept proposed herein was validated by performing the modal testing of the flexible wing model manufactured for demonstration purpose. In addition, the study on the gust response alleviation using flexible wing control surface was performed. For this purpose, optimal control with output feedback was adopted for designing the control surface controller, and the effects of gust response alleviation was validated by performing the numerical simulation for the representative flexible wing model. The methods proposed and validated in this study can be applied for wind tunnel testing of the flexible wing for gust response alleviation.

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풍동시험을 통한 유연날개 돌풍응답 특성 분석 (Study of Gust Response Characteristics for Flexible Wing by Wind Tunnel Test)

  • 이상욱;김태욱;황인희;임재형;하철근
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2007년도 추계학술대회논문집
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    • pp.1329-1332
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    • 2007
  • In this study, the design method of flexible wing model for gust response measurement wind tunnel test was presented. The design concept proposed herein was validated by modal testing of the flexible wing model manufactured. In addition, aeroservoelastic modeling method for flexible wing model was presented and validated by comparing the gust response analysis results from the method proposed herein with those of commercial software. The gust response characteristics of the flexible wing model was studied by wind tunnel test for measuring the flexible wing gust response due to the induced gust excitation by gust generator. The aeroservoelastic modeling methods proposed and the wind tunnel test results obtained in this study can be applied for wind tunnel testing of the flexible wing for gust response alleviation.

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슬라이딩 모드 제어기법을 이용한 유연날개 동적 응답 제어 (Dynamic Response Control of a Flexible Wing using Sliding Mode Control)

  • 이상욱;석진영
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2013년도 춘계학술대회 논문집
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    • pp.522-527
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    • 2013
  • In this study, dynamic response control of a flexible wing such as gust loads alleviation using sliding mode control method is presented. To achieve this purpose, trailing edge control surface of a flexible wing is used as control means generating the aerodynamic control force. Aeroservoelastic CASE) model consisting of aeroelastic plant, control surface actuator model, and gust model depicting the atmospheric turbulence is formulated in the state space. A sliding mode controller based on the estimated state vector is designed for active dynamic response control of flexible wing aeroservoelastic model. The performance of the controller designed is demonstrated via numerical simulation for the representative flexible wing model under atmospheric turbulence loading.

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슬라이딩 모드 제어기법을 이용한 3차원 유연날개 돌풍응답 제어 (Gust Response Alleviation of a Three-dimensional Flexible Wing using Sliding Mode Control)

  • 이상욱;석진영
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2013년도 추계학술대회 논문집
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    • pp.220-225
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    • 2013
  • In this study, active control system using sliding mode control method is presented to achieve the gust response alleviation of a three-dimensional flexible wing model. For this purpose, aeroservoelastic model which is composed of aeroelastic plant, control surface actuator model, and gust model depicting the atmospheric turbulence is formulated in the state space. The aerodynamic force generated by the motion of a trailing edge control surface of a flexible wing is made use of as control means. An active control system combining state feedback sliding mode controller and state estimator based on measured responses such as wing tip acceleration and wing root strain is designed for gust response alleviation of a flexible wing aeroservoelastic model. The performance of the controller designed is demonstrated via numerical simulation for the representative flexible wing model under gust loading conditions.

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Hydrodynamic characteristics of cambered NACA0012 for flexible-wing application of a flapping-type tidal stream energy harvesting system

  • Sitorus, Patar Ebenezer;Park, JineSoon;Ko, Jin Hwan
    • International Journal of Naval Architecture and Ocean Engineering
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    • 제11권1호
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    • pp.225-232
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    • 2019
  • In recent years, nonlinear dynamic models have been developed for flapping-type energy harvesting systems with a rigid wing, but not for those with a flexible wing. Thus, in this study, flexible wing designs of NACA0012 section are proposed and measurements of the forces of rigid cambered wings, which are used to estimate the performance of the designed wings, are conducted. Polar curves from the measured lift and drag coefficients show that JavaFoil estimation is much closer to the measured values than Eppler over the entire given range of angles of attack. As the camber of the rigid cambered wings is increased, both the lift and drag coefficients increase, in turn increasing the resultant forces. Moreover, the maximum resultant forces for all rigid cambered wings are achieved at the same angle of attack as the maximum lift coefficient, meaning that the lift coefficient is dominant in representations of the wing characteristics.

전기동력무인기 유연날개 플러터 해석 (Flutter Analysis of Flexible Wing for Electric Powered UAV)

  • 이상욱;신정우;최용준
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2014년도 추계학술대회 논문집
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    • pp.189-192
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    • 2014
  • Recently, development of electric powered UAV for high altitude and long endurance mission has been conducted worldwide. Long endurance requirement necessitates high lift over drag (L/D) aerodynamic characteristics and lightweight structures, leading to highly flexible wings with high aspect ratio. These highly flexible wings increase the danger of catastrophic aircraft failure due to flutter, which is a dynamic aeroelastic instability occurring from the interaction of aerodynamic, inertial, and elastic forces acting on the aircraft flying through the air. In this paper, flexible wing for electric powered UAV whose skin is fabricated using mylar film for lightweight design is briefly explained. In addition, flutter analysis procedures and results for the flexible wing in order to substantiate the aeroelastic stability requirements are presented.

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슬라이딩 모드 제어기법을 이용한 유연날개의 플러터 억제 (Flutter Suppression of a Flexible Wing using Sliding Mode Control)

  • 이상욱;석진영
    • 한국항공우주학회지
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    • 제41권6호
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    • pp.448-457
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    • 2013
  • 본 논문에서는 항공기 유연날개의 플러터 억제를 위한 능동 제어시스템을 슬라이딩 모드 제어기법을 이용해 설계하였다. 제어력으로는 유연날개 뒷전 조종면 움직임으로 발생하는 공기력을 이용하였으며, 이를 위해 공탄성 모델, 조종면 작동기 모델, 돌풍 모델로 구성되는 서보 공탄성 모델링을 수행하였다. 플러터 억제를 위한 조종면 제어시스템은 슬라이딩 모드 제어기와 측정값을 이용해 상태 변수를 추정하는 칼만 필터를 조합해 구성하였으며, 수치 시뮬레이션을 통해 유연날개 모델에 대한 플러터 억제 효과를 확인하였다.

날갯짓 초소형 비행체의 앞전 및 시맥 탄성이 공력 성능에 미치는 영향 (Effect of the Leading Edge and Vein Elasticity on Aerodynamic Performance of Flapping-Wing Micro Air Vehicles)

  • 윤상훈;조해성;신상준;허석행;구지훈;유재관;김종암
    • 한국항공우주학회지
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    • 제49권3호
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    • pp.185-195
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    • 2021
  • 본 연구의 날갯짓 초소형 비행체는 실제 생명체의 날개를 모방하여, 매우 유연한 재질의 캠버날개를 활용한다. 캠버 날개는 생명체와 유사하게 앞전, 시맥, 박막과 같이 특성이 서로 다른 세가지 재질로 구성되어 있고 다양한 방식으로 구속되어 있다. 날개의 유연성을 활용한 수동 회전(passive rotation) 방식은 앞전과 시맥의 재질이 날갯짓 궤적에 매우 큰 영향을 미치는 요소이기 때문에 적절한 유연성을 갖는 재질의 선정이 필수적이다. 이러한 날개의 재질들과 복잡한 형상을 사실적으로 모델링하여 정밀하게 해석할 수 있는 유체-구조 연성해석 프로그램을 개발하고, 날개의 앞전과 시맥의 탄성 계수의 변화에 따른 공력탄성학 효과를 정밀하게 분석하였다. 결과적으로 재료의 탄성 계수 변화만으로도 날개의 비틀림각 궤적을 적절히 발생시킴으로써 날갯짓 비행체의 추력 및 효율을 크게 증가시킬 수 있음을 보였다.

신뢰성을 고려한 유연 날개 형상 최적 설계에 대한 연구 (STUDY OF RELIABILITY BASED FLEXIBLE WING SHAPE DESIGN OPTIMIZATION)

  • 김수환;권장혁
    • 한국전산유체공학회지
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    • 제11권1호
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    • pp.21-28
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    • 2006
  • Reliability Based Design Optimization(RBDO) is one of the optimization methods that minimize the product failure due to small changes of operating conditions or process errors. It searches the optimum that satisfies the safety margin of each constraint, and it gives stable and reliable designs. However, RBDO requires many times oj computational efforts compared with the conventional deterministic optimization(DO) to evaluate the probability of failure about each constraint, therefore it is hard to apply directly to large-scaled problems such as a flexible wing shape design optimization. For the efficient reliability analysis, the approximate reliability analysis method with the two-point approximation(TPA) is proposed In this study, the lift-to-drag ratio maximization designs are performed with 3-dimensional Navier-Stokes analysis and NASTRAN structural analysis, and the optimization results about the deterministic, FORM and SORM are compared.

Aerodynamic Design of the Solar-Powered High Altitude Long Endurance (HALE) Unmanned Aerial Vehicle (UAV)

  • Hwang, Seung-Jae;Kim, Sang-Gon;Kim, Cheol-Won;Lee, Yung-Gyo
    • International Journal of Aeronautical and Space Sciences
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    • 제17권1호
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    • pp.132-138
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    • 2016
  • Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53kg, the structure weight is 22kg, and features a flexible wing of 19.5m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, $V_{cr}=6m/sec$, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight because of the EAV-3 is the solar-electric driven UAV. Thus, static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing with the previously designed the EAV-2 and EAV-2H/2H+ to upgrade the flight performance of the EAV-3.