| タイトル | Flap-lag damping of an elastic rotor blade with torsion and dynamic inflow in hover from symbolically generated equations |
| 著者（英） | Reddy, T. S. R. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1984-05-01 |
| 言語 | eng |
| 内容記述 | A program written in FORTRAN IV and coded into subroutines for subsequent numerical study is used to derive symbolically the governing equations of motion of the elastic rotor blade and the dynamic inflow equations. By rearranging the coefficients of the equations, the blade and dynamic inflow equations are converted into equations in a multiblade coordinated system. The final multiblade equations can accommodate any number of elastic blade modes. It is noted that with a given data set, the entire process, from the derivation of the equations to the numerical calculations, is computerized and requires only limited user interface. To demonstrate the usefulness of the approach, damping data in hover with and without dynamic inflow effects are presented for various rotor blade models, including flap-lag, flap-lag-torsion, quasi-static torsion, and rigid blade lag-flap. |
| NASA分類 | STRUCTURAL MECHANICS |
| レポートNO | 84A34909
AIAA PAPER 84-0989 |
| 権利 | Copyright |
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