| タイトル | Adaptive control laws for F-8 flight tests |
| 著者（英） | Hartmann, G. L.; Stein, G.; Hendrick, R. C. |
| 著者所属（英） | Honeywell, Inc. |
| 発行日 | 1975-01-01 |
| 言語 | eng |
| 内容記述 | An adaptive flight-control-system design for NASA's F-8 Digital Fly-by-Wire research aircraft is described. This design implements an explicit parallel maximum likelihood identification algorithm to estimate key aircraft parameters. The estimates are used to compute gains in simplified quadratic-optimal command augmentation control laws. Design details for the control laws and identifier are presented, and performance evaluation results from NASA Langley's F-8 simulator are summarized. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 77N22811 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/440670 |
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