| タイトル | Influence of high-order dynamics on helicopter flight-control system bandwidth |
| 著者（英） | Hindson, W. S.; Chen, R. T. N. |
| 著者所属（英） | NASA Ames Research Center|Stanford Univ. |
| 発行日 | 1986-04-01 |
| 言語 | eng |
| 内容記述 | The increasing use of highly augmented digital flight-control systems in modern military helicopters prompted an examination of the influence of the influence of rotor dynamics and other high-order dynamics on control-system performance. A study was conducted at NASA Ames Research Center to correlate theoretical predictions of feedback gain limits in the roll axis with experimental test data obtained from a variable-stability research helicopter. Feedback gains, the break frequency of the presampling sensor filter, and the computational frame time of the flight computer were systematically varied. The results, which showed excellent theoretical and experimental correlation, indicate that the rotor-dynamics, sensor-filter, and digital-data processing delays can severely limit the usable values of the roll-rate and roll-attitude feedback gains. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 86A31660 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/385477 |
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