| タイトル | Control definition study for advanced vehicles |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840008144 |
| 著者（英） | Sturm, M. J.; Klein, R. W.; Lapins, M.; Martorella, R. P.; Meyer, R. C. |
| 著者所属（英） | Grumman Aerospace Corp. |
| 発行日 | 1983-11-01 |
| 言語 | eng |
| 内容記述 | The low speed, high angle of attack flight mechanics of an advanced, canard-configured, supersonic tactical aircraft designed with moderate longitudinal relaxed static stability (Static Margin, SM = 16% C sub W at M = 0.4) was investigated. Control laws were developed for the longitudinal axis (""G'' or maneuver and angle of attack command systems) and for the lateral/directional axes. The performance of these control laws was examined in engineering simulation. A canard deflection/rate requirement study was performed as part of the ""G'' command law evaluation at low angles of attack. Simulated coupled maneuvers revealed the need for command limiters in all three aircraft axes to prevent departure from controlled flight. When modified with command/maneuver limiters, the control laws were shown to be adequate to prevent aircraft departure during aggressive air combat maneuvering. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 84N16212
NASA-CR-3738
NAS 1.26:3738 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/160654 |
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