| タイトル | Preliminary design-lift/cruise fan research and technology airplane flight control system |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770004121 |
| 著者（英） | Lewis, G. E.; Gotlieb, P.; Little, L. J. |
| 著者所属（英） | Boeing Aerospace Co. |
| 発行日 | 1976-11-01 |
| 言語 | eng |
| 内容記述 | This report presents the preliminary design of a stability augmentation system for a NASA V/STOL research and technology airplane. This stability augmentation system is postulated as the simplest system that meets handling qualities levels for research and technology missions flown by NASA test pilots. The airplane studied in this report is a T-39 fitted with tilting lift/cruise fan nacelles and a nose fan. The propulsion system features a shaft interconnecting the three variable pitch fans and three power plants. The mathematical modeling is based on pre-wind tunnel test estimated data. The selected stability augmentation system uses variable gains scheduled with airspeed. Failure analysis of the system illustrates the benign effect of engine failure. Airplane rate sensor failure must be solved with redundancy. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 77N11064
NASA-CR-137971
D180-20216-1 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184074 |
