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구조 모델링 특성에 따른 복합재료 무힌지 로터의 공력 탄성학적 안정성 연구
박일주(Il-ju Park),정성남(Sung Nam Jung),김창주(Chang-Joo Kim) 한국항공우주학회 2008 韓國航空宇宙學會誌 Vol.36 No.2
혼합 보 이론과 적정변형 보 이론에 입각한 공탄성 해석 시스템을 결합하여 유연면을 갖는 복합재료 무힌지 로터에 대한 정지 및 전진 비행시의 공탄성 해석을 수행하였다. 블레이드에 작용하는 공기력은 Leishman-Beddoes의 비정상 공력 모델을 이용하여 구했다. 인장, 회전면 내외의 굽힘, 그리고 비틀림이 상호 연계된 블레이드에 대한 운동방정식은 Hamilton의 원리에 입각하여 유도하였다. 헬리콥터 블레이드의 공탄성 해석에 주요한 요소들인 단면 벽의 두께, 탄성연계, 그리고 구성방정식에 대한 적합한 가정과 같은 주요 구조 모델링 문제들에 대한 효과들을 고찰하였다. 이러한 요소들은 블레이드 단면의 복합재료 적충 구조에 민감하게 반응하며, 블레이드 안정성에도 적지 않은 영향을 나타냄을 보였다. The aeroelastic stability analysis of a soft-in-plane, composite hingeless rotor blade in hover and in forward flight has been performed by combining the mixed beam method and the aeroelastic analysis system that is based on a moderate deflection beam approach. The aerodynamic forces and moments acting on the blade are obtained using the Leishman-Beddoes unsteady aerodynamic model. Hamilton's principle is used to derive the governing equations of composite helicopter blades undergoing extension, lag and flap bending, and torsion deflections. The influence of key structural modeling issues on the aeroelastic stability behavior of helicopter blades is studied. The issues include the shell wall thickness, elastic couplings and the correct treatment of constitutive assumptions in the section wall of the blade. It is found that the structural modeling effects are largely dependent on the layup geometries adopted in the section of the blade and these affect on the stability behavior in a large scale.
朴日柱,陳鍾泰,尹漢翼 東義大學校産業技術開發硏究所 1992 産業技術硏究誌 Vol.6 No.-
The vibration problem of a two-dimensional rigid body system on a simple beam is studied. The rigid body system is supported by the suspension units with stiffness and damping, and it has constant velocity on a beam. The deformations of the beams is represented by their corresponding eigenfunction series. The Runge-Kutta method is used in numerical analysis. 1. Regardless of damping, as the speed reduces, the maximum deflection of rigid body system increases, and as the speed increases, the maximum deflection of rigid body system reduces. 2. As the speed reduces, the deflection of rigid body system decreaces at endpoint of the simple beam from C=0 to C=100 N·s/m. And in case of C=1700 N·s/m, the deflection of rigid body system at endpoint of the simple beam is smallest at midspeed 22.22 m/s. 3. In case of undamping(C=O), the maximum deflection of rigid body system is moved from midpoint to endpoint of the simple beam as the speed increases. 4. As the damping coefficient increases, the deflection of rigid body system increases very small at the initial portion of the simple beam, but the maximum deflection reduces. 5. As the damping coefficient increases, the maximum deflection of rigid body system is moved from endpoint to midpoint of the simple beam.