| タイトル | Development and flight evaluation of an augmented stability active controls concept with a small horizontal tail |
| 本文（外部サイト） | http://hdl.handle.net/2060/19840020736 |
| 著者（英） | Mijares, R. D.; Rakness, W. L.; Kairys, A. A.; Rising, J. J.; Peterson, R. S.; Siegart, C. D.; King, R. W.; Wickson, D.; Hurley, S. R.; Maass, C. A. |
| 著者所属（英） | Lockheed-California Co. |
| 発行日 | 1982-09-01 |
| 言語 | eng |
| 内容記述 | A limited authority pitch active control system (PACS) was developed for a wide body jet transport (L-1011) with a flying horizontal stabilizer. Two dual channel digital computers and the associated software provide command signals to a dual channel series servo which controls the stabilizer power actuators. Input sensor signals to the computer are pitch rate, column-trim position, and dynamic pressure. Control laws are given for the PACS and the system architecture is defined. The piloted flight simulation and vehicle system simulation tests performed to verify control laws and system operation prior to installation on the aircraft are discussed. Modifications to the basic aircraft are described. Flying qualities of the aircraft with the PACS on and off were evaluated. Handling qualities for cruise and high speed flight conditions with the c.g. at 39% mac ( + 1% stability margin) and PACS operating were judged to be as good as the handling qualities with the c.g. at 25% (+15% stability margin) and PACS off. |
| NASA分類 | AIRCRAFT STABILITY AND CONTROL |
| レポートNO | 84N28805
LR-30208-2
NASA-CR-165951
NAS 1.26:165951 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/158949 |
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