| タイトル | Development and evaluation of an inverse solution technique for studying helicopter maneuverability and agility |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910022831 |
| 著者（英） | Whalley, Matthew S. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1991-07-01 |
| 言語 | eng |
| 内容記述 | An inverse solution technique for determining the maximum maneuvering performance of a helicopter using smooth, pilotlike control inputs is presented. Also described is a pilot simulation experiment performed to investigate the accuracy of the solution resulting from this technique. The maneuverability and agility capability of the helicopter math model was varied by varying the pitch and roll damping, the maximum pitch and roll rate, and the maximum load-factor capability. Three maneuvers were investigated: a 180-deg turn, a longitudinal pop-up, and a lateral jink. The inverse solution technique yielded accurate predictions of pilot-in-the-loop maneuvering performance for two of the three maneuvers. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 91N32145
NAS 1.15:102889
AD-A241980
A-91020
NASA-TM-102889
AD-A242304
USAAVSCOM-TR-90-A-008 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/130897 |
