B. Paluch

When dimensioning helicopter blade models, it is important to be able to calculate the shear stresses induced by torsion and shearing forces in each section accurately. The method explained here can be used to compute these stresses once the two warping functions are determined that represent the torsional and transverse shear properties of the blade. The finite element formulations associated with these functions are formally identical, except as concerns the boundary conditions. This method can also be used to compute the equivalent torsional stiffness of the sections, their transverse shear coefficients, and the position of their center of torsion. A grid generator method is also discussed, which is a part of the calculation program, and is used to discretize the sections quickly and condition the grid data reliably. After describing the successful validation of the method on a few sections composed of isotropic materials, we apply it to the case of blade model sections made of composite materials. The results are good, compared with experimental data.

17th European Rotorcraft Forum 1991, Berlin

Conference Paper

englisch

21,0 x 29,7 cm, 30 Seiten

DGLR-Bericht, 1991, 1991-08, 17th European Rotorcraft Forum Proceedings; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Dieser Aufsatz ist nicht Teil der Veröffentlichung!

rotor blades, composite materials, helicopters, shear stress

Bestellbar

1991