Aeroelastic Characteri stics of Rotor Blades with Trailing Edge Flaps

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The aeroelastic analysis of rotor blades with trailing edge flaps, focused on reducing vibration while minimizing control effort, are investigated using large deflection-type beam theory in forward flight. The rotor blade aerodynamic forces are calculated using two-dimensional quasi-steady strip theory. For the analysis of forward flight, the nonlinear periodic blade steady response is 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, is minimized by an optimal control process. Numerical simulations are performed for the steady-state forward flight of various advance ratios. Also, numerical results of the steady blade and flap deflections, and the vibratory hub loads are presented for various advance ratios and are compared with the previously published analysis results obtained from modal analysis based on a moderate deflection-type beam theory.
Publisher
한국항공우주학회
Issue Date
2007-05
Language
English
Citation

KSAS INTERNATIONAL JOURNAL, v.8, no.1, pp.115 - 121

ISSN
1229-9626
URI
http://hdl.handle.net/10203/5718
Appears in Collection
AE-Journal Papers(저널논문)
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