Aeroelastic analysis of rotor systems using trailing edge flaps

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An aeroelastic analysis of rotor blades with trailing edge flaps was conducted using large deflection-type beam theory for forward flight conditions with a focus on reducing vibration while minimizing control effort. The aerodynamic forces of the rotor blade were calculated using two-dimensional quasi-steady strip theory. For the analysis of forward flight, the nonlinear periodic blade steady response was obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim. The objective function, which includes vibratory hub loads and active flap control inputs, was minimized by an optimal control process. Numerical simulations were performed for the steady-state forward flight of various advance ratios. Numerical results of the steady blade and flap deflections as well as the vibratory hub loads were also presented for various advance ratios and were compared with previously published analysis results obtained from modal analyses based on a moderate deflection-type beam theory. (C) 2008 Elsevier Ltd. All rights reserved.
Publisher
ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD
Issue Date
2009-04
Language
English
Article Type
Article
Keywords

HELICOPTER VIBRATION; STABILITY

Citation

JOURNAL OF SOUND AND VIBRATION, v.321, no.3-5, pp.525 - 536

ISSN
0022-460X
DOI
10.1016/j.jsv.2008.10.029
URI
http://hdl.handle.net/10203/94380
Appears in Collection
AE-Journal Papers(저널논문)
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