Abstract
This paper describes a new methodology for formulating the aeroelastic stability and response problem for helicopter rotor blades. The mathematical expressions for the aerodynamic loads heed not be explicit functions of the blade displacement quantities. The methodology is combined with a finite-element model of the blade and a quasilinearization solution technique. The resulting computer program is used to study the behavior of blades with noncoincident elastic axis, aerodynamic centers, and centers of mass.
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