| タイトル | Development and demonstration of a flutter-suppression system using active controls |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760007430 |
| 著者（英） | Abel, I.; Gray, D. L.; Sandford, M. C. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1975-12-01 |
| 言語 | eng |
| 内容記述 | The application of active control technology to suppress flutter was demonstrated successfully in the transonic dynamics tunnel with a delta-wing model. The model was a simplified version of a proposed supersonic transport wing design. An active flutter suppression method based on an aerodynamic energy criterion was verified by using three different control laws. The first two control laws utilized both leading-edge and trailing-edge active control surfaces, whereas the third control law required only a single trailing-edge active control surface. At a Mach number of 0.9 the experimental results demonstrated increases in the flutter dynamic pressure from 12.5 percent to 30 percent with active controls. Analytical methods were developed to predict both open-loop and closed-loop stability, and the results agreed reasonably well with the experimental results. |
| NASA分類 | STRUCTURAL MECHANICS |
| レポートNO | 76N14518
L-10446
NASA-TR-R-450 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/187583 |
