| タイトル | Improvement of method for experimental determination of flutter speed by parameter identification |
| 本文（外部サイト） | http://hdl.handle.net/2060/19940008297 |
| 著者（英） | Nissim, E. |
| 著者所属（英） | Technion Research and Development Foundation Ltd. |
| 発行日 | 1993-08-05 |
| 言語 | eng |
| 内容記述 | The method investigated in the current research work is based on the identification of the equations of motion during test flights, followed by the solution of these identified equations to numerically compute the flutter dynamic pressure. The current research work is aimed at overcoming two main difficulties which arise when: (1) A continuous system is truncated into a system with a finite number of degrees of freedom. (2) The desired range of frequencies is wide; in the latter case, numerical difficulties occur that can only partly be overcome by giving relatively more weight to the high frequency modes. Results pertaining to the above first point will be presented under section entitled 'Truncation Effects', and results pertaining to the above second point will be presented under section entitled 'Frequency Range Effects'. The numerical example used herein consists of a continuous simply supported beam. It is further assumed that the object of the identification procedure is to identify the beam's first seven modes. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 94N12769
NASA-CR-193555
NAS 1.26:193555 |
| 権利 | No Copyright |
