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김성준(Sung Joon Kim),김동현(Dong Hyun Kim),임주섭(Joosup Lim),이상욱(Sang Wook Lee),김태욱(Tae-Uk Kim),김승호(Seungho Kim) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.8
항공기가 적은 동력으로 장시간 체공을 하기 위해서는 높은 양항비(Lift Drag Ratio)와 구조경량화가 요구된다. 일반적으로 고고도 장기체공 비행기에는 가로세로비가 큰 날개가 적용된다. 또한 기체의 주요 구조물에 고강도, 고강성 탄소섬유복합재료를 사용하고, 날개의 표피(Skin)에 박막(Membrane) 소재인 얇은 마일러(Mylar)를 사용된다. 그 결과 날개 구조물이 다른 구조물에 비하여 유연해진다. 그리고 박막 소재인 얇은 마일러의 강성이 동적 안정성에 영향을 미치게 된다. 본 연구에서는 비선형 갭(Gap) 요소를 사용하여 마일러의 박막 특성을 모사하였다. 그리고 비선형해석 결과를 이용하여 등가강성을 갖는 선형쉘(Shell) 요소로 등가모델링 하는 방법을 제시하였다. 선형 등가 쉘 모델은 멤브레인 요소법를 이용한 비선형해석 결과와 비교하여 결과의 타당성을 검증하였다. 제안된 선형등가쉘 모델은 모드 해석에 적용하여 마일러의 기계적 물성이 고유진동수에 미치는 영향을 평가하였다. Aircraft needs high lift-to-drag ratio and weight reduction of the structure for long endurance flight with a small power. Generally high aspect ratio wing is applied to HALE(High Altitude Long Endurance) aircraft. Also high modulus, and high strength CFRP(Carbon Fiber Reinforced Plastic) has been used in primary structures. and thin mylar(membrane material) film has been applied to skin of wing. As a result, wing is more flexible than the other structures. and the stiffness of thin mylar film has an affect on dynamic stability. In this study, the membrane characteristic of mylar film has been simulated using nonlinear gap elements. And equivalent modeling method using shell elements is presented using the nonlinear simulation result. The linear equivalent model has verified using the results of nonlinear membrane method. Proposed linear equivalent shell model has applied to mode analysis for estimate the effect of mylar mechanical properties on natural frequency.
Effect of a Silicone Defoamant on the Motion of Single Air Bubbles Rising in Lubricant
Shim, Joosup,Cho, Wonoh,Chung, Keunwoo,Kim, Woung Woon Korean Tribology Society 2000 KSTLE International Journal Vol.1 No.1
The velocity and motion of single air bubbles rising through lubricant have been experimentally investigated to test the effect of silicon defoamant The investigation reveals that the velocity is markedly retarded by the addition of small amount of silicone defoamant. This retardation of rising velocity of air bubbles is proposed by increasing of Drag force or reducing of Buoyancy force around the surfaces of the bubbles.
비틀림 비선형성을 갖는 2차원 익형의 Limit Cycle Flutter 해석과 Critical Slowing Down
임주섭(Joosup Lim),김태욱(Tae-uk Kim),황인희(In-hee Hwang) 대한기계학회 2013 대한기계학회 춘추학술대회 Vol.2013 No.12
In this paper, limit cycle flutter induced by Hopf bifurcation is studied with nonlinear system analysis approach and observed for the critical slowing down phenomenon. Considering an attractor of the dynamics of a system, when a small perturbation is applied to the system, the dynamics converge toward the attractor at some rate. The critical slowing down means that this recovery rate approaches zero as a parameter of the system varies and the size of the basin of attraction shrinks to nil. Consequently, in the pre-bifurcation regime, the recovery rates decrease as the system approaches the bifurcation. This phenomenon is one of the features used to forecast bifurcation before they actually occur. Therefore, studying the critical slowing down for limit cycle flutter behavior would have potential applicability for forecasting those types of flutter. Herein, modeling and nonlinear system analysis of the 2D airfoil with torsional nonlinearity have been discussed, followed by observation of the critical slowing down phenomenon.