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Application of the finite element method to rotary wing aeroelasticity
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Friedmann, P. P. Straub, F. K. |
| Copyright Year | 1982 |
| Description | A finite element method for the spatial discretization of the dynamic equations of equilibrium governing rotary-wing aeroelastic problems is presented. Formulation of the finite element equations is based on weighted Galerkin residuals. This Galerkin finite element method reduces algebraic manipulative labor significantly, when compared to the application of the global Galerkin method in similar problems. The coupled flap-lag aeroelastic stability boundaries of hingeless helicopter rotor blades in hover are calculated. The linearized dynamic equations are reduced to the standard eigenvalue problem from which the aeroelastic stability boundaries are obtained. The convergence properties of the Galerkin finite element method are studied numerically by refining the discretization process. Results indicate that four or five elements suffice to capture the dynamics of the blade with the same accuracy as the global Galerkin method. |
| File Size | 39844061 |
| Page Count | 233 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820012687 |
| Archival Resource Key | ark:/13960/t1dk0868h |
| Language | English |
| Publisher Date | 1982-02-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Degrees of Freedom Rigid Rotors Helicopters Rotor Aerodynamics Equilibrium Equations Equations of Motion Rotary Wings Finite Element Method Eigenvalues Flutter Galerkin Method Aeroelasticity Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
