A Refined Beam Theory For Advanced Composite Rotor Blade Analysis

Le résumé fourni par la source

An analytical model is presented for accurately determining the three-dimensional response and stress distribution (including interlaminar shear) of advanced composite helicopter rotor blades. This model is developed by formulating Saint-Venant 's elasticity solutions for the extension, bending, torsion, and flexure of a prismatic beam whose cross section is nonhomogeneous and generally anisotropic. The coupled second order elasticity problem is solved based upon the principle of minimum potential energy and a two-dimensional finite element approach. Derivations are also included for calculating the one-dimensional beam-theory properties; the beam twist, Saint-Venant torsion warping distribution, torsion constant, flexural center, moment­curvature relations, and shear correction factors. Numerical results are presented to illustrate the versatility of this model by analyzing both isotropic and advanced composite airfoil sections.

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