• Composites Research
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• 제15권1호
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• pp.1-8
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• 2002

본 연구에서는 실제 구조형상의 사각형 상자형 날개와 전투기 날개에 대하여 구조재를 표피(skin)부분은 복합재료로 대체하고, 나머지 스파(spar)와 리브(rib)는 알루미늄으로 하여 플러터 해석을 수행하였다. MS/PATRAN을 이용하여 실제 날개 구조에 근사한 3차인 유한 요소 모델이 구축되었고, MSC/NASTRAN을 이용하여 고유진동 해석이 수행되었다. 유한 요소는 멤브레인(membrane)요소, 1차원 막대(rod)요소, 전단패널(shear panel)요소를 사용하였다. 복합재료의 적층은 실제적인 적층각을 이용하여 다양하게 변화시켜 해석하였다. 아음속 영역에서 비정상 공력 해석을 위하여 주파수 영역에서의 선형 공기력 이론인 DLM코드가 적용되었고, 주파수 영역 공탄성 지배방정식의 해법으로 V-g방법 및 p-k방법이 적응되었다.

• 한국소음진동공학회논문집
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• 제19권7호
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• pp.699-709
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• 2009

In this paper, the nonlinear dynamics and the stability of nanopipes conveying fluid and modelled as a thin-walled beam is investigated. Effects of boundary conditions, geometric nonlinearity, non-classical transverse shear and rotary inertia are incorporated in this study. The governing equations and the three different boundary conditions are derived through Hamilton's principle. Numerical analysis is performed by using extend Galerkin method which enables us to obtain more exact solutions compared with conventional Galerkin method. Variations of critical flow velocity for different boundary conditions of carbon nanopipes are investigated and compared with linear case.

• 한국항공우주학회지
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• 제38권11호
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• pp.1075-1080
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• 2010

마찰 감쇠가 있는 공탄성 해석을 위하여, 연계 시간 적분법을 사용하여 아음속/천음속 영역에서 공탄성 응답을 구하였다. 양력면에 발생하는 충격파에 의한 공기역학적 비선형성을 고려하기 위하여 동위상 주기 경계 조건이 적용된 미소교란 방정식을 비정상 공기력 계산에 적용하였다. 변위 종속적인 마찰 감쇠기가 있는 2차원 에어포일 시스템에 대하여 플러터 경계에 대한 수직력의 기울기와 마하수의 영향을 살펴보았다.

• 한국소음진동공학회논문집
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• 제24권1호
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• pp.14-20
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• 2014

Recent developments for high altitude, long endurance conventional UAVs(HALE UAVs) have revealed new issues regarding aircraft structure design and analysis. First of all, due to intensive mission requirements, the structures of HALE UAVs have lightweight and very flexible main wing with high aspect ratio, and slender fuselage. For this kind of structures, aeroelastic characteristics are different from conventional aircrafts. Hence, currently developed analysis methods are not suitable to fully understand strucutral dynamics of the very flexible aircraft, and to guarantee structural reliability. Therefore, various structural studies considering nonlinear behaviors which are generally ignored for the conventional aircraft strucutral analyis have been attracting researchers interests. Nonlinear flutter of the very flexible wing is one of the subject to be studied in combination with strong coupling between aeroelastic characteristics and flight dynamics. Herein, as preliminary study, modeling and nonlinear system analysis of the 2D airfoild with torsional nonlinearity have been discussed.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 추계학술대회 논문집
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• pp.226-231
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• 2013

Recent developments for high altitude, long endurance conventional UAVs (HALE UAVs) have revealed new issues regarding aircraft structure design and analysis. First of all, due to intensive mission requirements, the structures of HALE UAVs have lightweight and very flexible main wing with high aspect ratio, and slender fuselage. For this kind of structures, aeroelastic characteristics are different from conventional aircrafts. Hence, currently developed analysis methods are not suitable to fully understand strucutral dynamics of the very flexible aircraft, and to guarantee structural reliability. Therefore, various structural studies considering nonlinear behaviors which are generally ignored for the conventional aircraft strucutral analyis have been attracting researchers interests. Nonlinear flutter of the very flexible wing is one of the subject to be studied in combination with strong coupling between aeroelastic characteristics and flight dynamics. Herein, as preliminary study, modeling and nonlinear system analysis of the 2D airfoild with torsional nonlinearity have been discussed.