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Application of the finite element method to rotary-wing aeroelasticityRecent research in rotary-wing aeroelasticity has indicated that all fundamental problems in this area are inherently nonlinear. The non-linearities in this problem are due to the inclusion of finite slopes, due to moderate deflections, in the structural, inertia and aerodynamic operators associated with this aeroelastic problem. In this paper the equations of motion, which are both time and space dependent, for the aeroelastic problem are first formulated in P.D.E. form. Next the equations are linearized about a suitable equilibrium position. The spatial dependence in these equations is discretized using a local Galerkin method of weighted residuals resulting in a finite element formulation of the aeroelastic problem. As an illustration the method is applied to the coupled flap-lag problem of a helicopter rotor blade in hover. Comparison of the solutions with previously published solutions establishes the convergence properties of the method. It is concluded that this formulation is a practical tool for solving rotary-wing aeroelastic stability or response problems.
Document ID
19790034646
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Friedmann, P.
(California, University Los Angeles, Calif., United States)
Straub, F.
(California Univ. Los Angeles, CA, United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Structural Mechanics
Meeting Information
Meeting: European Rotorcraft and Powered Lift Aircraft Forum
Location: Stresa
Country: Italy
Start Date: September 13, 1978
End Date: September 15, 1978
Accession Number
79A18659
Funding Number(s)
CONTRACT_GRANT: NGR-05-007-414
Distribution Limits
Public
Copyright
Other

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