A Comparative Study on Rotor Blade Structural Load Calculation Methods
Based on finite rotation hypothesis,a rigid-flexible rotor dynamic model is developed.This model introduces three rigid degrees of freedom compared with classical moderate deflection beam theory.With quasi-steady theory and free wake inflow model,aerodynamic forces and moments are tightly coupled with structural rigid rotations and elastic deflections.Structural loads are computed using three load calculation methods while equations of motions are solved.The loads are examined by analysis results of BO105 model blade and flight test data of SA349/2 Gazelle helicopter.Although force summation method can handle vast range of computation cases,it loses some power at sections near the blade root especially when transient aerodynamic forces are taken into account.The predictions are relatively consistent with other methods at sections where accumulated numerical integrating errors are small.Results from curvature method and reaction force method are generally the same at the nodes of finite element method.Accuracy of reaction force method depends on the response solutions and it cannot predict the loads at points between nodes.Since curvature method simplify considers the bending and torsion deflections,curvatures of sectional bending moments are relatively smooth.
Rotor dynamics structural load vibration force summation reaction force curvature method
Jie Wu Weidong Yang Zhihao Yu
National Key Laboratory of Rotorcraft Aeromechanic s,Nanjing University of Aeronautics and Astronautic s,Nanjing,China
国际会议
南京
英文
1-5
2013-08-20（万方平台首次上网日期，不代表论文的发表时间）