A dynamic theory of composite unformly rotating helicopter blades modelled as thin-walled beams is presented. The structural model incorporates the anisotropy and heterogeneity, transverse shear, primary and secondary warpings as well as the effects of a centrifugal force field. It is shown that in a special case of ply configuration and when Coriolis terms are neglected the governing system splits exactly and entirely into two independent systems, describing the flapping-lagging-transverse shear and extension-twist motions. Numerical illustrations of the effects played by the ply angle, angular velocity, hub radius on the coupled flap-lag-shear coupled eigenfrequencies are presented and a number of conclusions are outlined.
Free-vibration of composite rotating helicopter blades modelled as thin-wallled beams
Freischwingende, als dünnwandige Balken dargestellte Helikopterschaufeln aus Verbundwerkstoffen
1992
14 Seiten, 5 Bilder, 1 Tabelle, 16 Quellen
Conference paper
English
Resonant vibration of helicopter rotor blades
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