Aeroelastic analysis of bearingless rotors with a composite flexbeam

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An aeroelastic analysis of bearingless rotors is investigated using large deflection beam theory in hover and forward flight. The bearingless configuration consists of a single flexbeam with a wrap-around torque tube and pitch links located at the leading edge and trailing edge of the torque tube. The outboard main blade, flexbeam, and torque tube are all assumed as an elastic beam undergoing arbitrary large displacements and rotations, that are discretized into beam finite elements. In the bearingless rotors, a flexbeam has various sections made of laminate. The sectional elastic constants of a composite flexbeam, including the warping deformations, are determined from a refined cross-sectional finite element method. Numerical results of the static deflections and the aeroelastic modal damping are presented for various configurations of a composite flexbeam and are compared with previously published experimental results and theoretical values obtained from a modal analysis using a moderate deflection-type beam theory. (C) 2008 Elsevier Ltd. All rights reserved.
Publisher
ELSEVIER SCI LTD
Issue Date
2009-05
Language
English
Article Type
Article
Keywords

LARGE DEFLECTION THEORY; BEAM THEORY; INTRINSIC EQUATIONS; BLADES; HOVER; STABILITY; DYNAMICS

Citation

COMPOSITE STRUCTURES, v.88, no.4, pp.570 - 578

ISSN
0263-8223
DOI
10.1016/j.compstruct.2008.06.007
URI
http://hdl.handle.net/10203/94351
Appears in Collection
AE-Journal Papers(저널논문)
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