Parametric Studies on Nonlinear Flutter of High-Aspect-Ratio Flexible Wings
High-aspect-ratio flexible wing undergoing large deflection requires nonlinear structure and aerodynamic model to predict accurate aeroelastic behavior.The paper presents a methodology for high-aspect-ratio flexible wings aeroelastic analysis based on geometrically exact,fully intrinsic beam theory and Extended-ONERA dynamic stall aerodynamic model.By finite element discretization,the governing formulas coupled with nonlinear structure and aerodynamic can be described as first-order algebra differential form.Newton-Raphson method and Backward-Differentiation-Formulas (BDF) method are used for the solutions of static equilibrium and time simulation.Aeroelastic stability of Goland wing and the effects of several parameters on flutter velocity are investigated.The results show that the flutter velocity rises as the incidence or sweep angle increases,and declines with the increasing the ratio of flapwise bending stiffness to torsional stiffness.
Y.YAN J.XIANG D.LI Y.REN
School of Aeronautic Science and Engineering, Beihang University, Beijing, China 100191 School of Aeronautic Science and Engineering, Beihang University, Beijing, China100191 School of Aeronautic Science and Engineering, BeihangUniversity, Beijing, China 100191 School of Aeronautic Science and Engineering,Beihang University, Beijing100191
国际会议
Sixth International Conference on Nonlinear Mechanics(第六届国际非线性力学会议)(ICNM-VI)
上海
英文
188-192
2013-08-01（万方平台首次上网日期，不代表论文的发表时间）