A method recently developed for analyzing the nonlinear behavior of relatively limber rotor blades is used to study nonlinear effects in forward flight forced response. This method is based on the 'Principal Curvature Transformation' and 'Velocity Component Transformation'. It uses the nonrotating, uncoupled natural modes of a flat blade as generalized coordinates to examine the forced response of a YUH-61A blade in forward flight. The aerodynamic loads are taken directly from the Boeing Helicopter Company C-60 computer code and an open loop procedure is used, i.e. the same airloads are used as excitation regardless of the resulting response. Keywords: Helicopter rotors, Rotor blades, Nonlinear analysis, Reprints, Equations, Mathematics. (CP)
Non-Linear Effects in Helicopter Rotor Forward Flight Forced Response
1990
19 pages
Report
Keine Angabe
Englisch
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