The Effect of Composite Flexures on Aeroelastic Stability of a Hingeless Rotor Blade
The effects of ply orientation angle of composite flexures on stability of hingeless rotor blade system are studied.The composite hingeless rotor blade system is simplified as a hub,a flap flexure and a lag flexure.pitch bearing and main blade.The kinematics formulations are inferred by employing the moderate deflection beam theory.The shear deformation and warping related to torsion are considered.The quasi-steady strip theory with dynamic inflow effects is applied to obtain the aerodynamic loads acting on the blade.Based on these.the set of finite element formulations of a hingeless rotor blade system is worked out.The numerical results show that the ply angle of the composite flexures has great effects on the aeroelastic stability of rotor blade.
作 者： Shi Qinghua 作者单位： Beijing Aeronautical Manufacturing Technology Research Institute 刊 名： 航空制造技术 ISTIC 英文刊名： AERONAUTICAL MANUFACTURING TECHNOLOGY 年，卷(期)： 2007 ""(z1) 分类号： V2 关键词： Aeroelastic Stability Blade Composite Flexure beam