| タイトル | Description and test results of a digital supersonic propulsion system integrated control |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760024067 |
| 著者（英） | Arpasi, D. J.; Baumbick, R. J.; Batterton, P. G. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1976-08-01 |
| 言語 | eng |
| 内容記述 | A digitally implemented integrated inlet/engine control system was developed and tested on a mixed compression, Mach 2.5, supersonic inlet and augmented turbofan engine. The control matched engine airflow to available inlet airflow so that in steady state, the shock would be at the desired location, and the overboard bypass doors would be closed. During engine induced transients, such as augmentor lights and cutoffs, the inlet operating point was momentarily changed to a more supercritical point to minimize unstarts. The digital control also provided automatic inlet restart. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N31155 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/569815 |
