| タイトル | An influence coefficient method for the application of the modal technique to wing flutter suppression of the DAST ARW-1 wing |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820003197 |
| 著者（英） | Pines, S. |
| 著者所属（英） | Analytical Mechanics Associates, Inc. |
| 発行日 | 1981-11-01 |
| 言語 | eng |
| 内容記述 | The methods used to compute the mass, structural stiffness, and aerodynamic forces in the form of influence coefficient matrices as applied to a flutter analysis of the Drones for Aerodynamic and Structural Testing (DAST) Aeroelastic Research Wing. The DAST wing was chosen because wind tunnel flutter test data and zero speed vibration data of the modes and frequencies exist and are available for comparison. A derivation of the equations of motion that can be used to apply the modal method for flutter suppression is included. A comparison of the open loop flutter predictions with both wind tunnel data and other analytical methods is presented. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 82N11070
AMA-81-25
NASA-CR-165772 |
| 権利 | No Copyright |
