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   作者單位： Beijing Aeronautical Manufacturing Technology Research Institute  刊 名： 航空制造技術(shù)  ISTIC 英文刊名： AERONAUTICAL MANUFACTURING TECHNOLOGY  年，卷(期)： 2007 ""(z1)  分類號(hào)： V2  關(guān)鍵詞： Aeroelastic Stability Blade Composite Flexure beam  

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