| タイトル | The High Stability Engine Control (HISTEC) Program: Flight Demonstration Phase |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980206364 |
| 著者（英） | Gallops, George W.; Orme, John S.; DeLaat, John C.; Southwick, Robert D. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1998-07-01 |
| 言語 | eng |
| 内容記述 | Future aircraft turbine engines, both commercial and military, must be able to accommodate expected increased levels of steady-state and dynamic engine-face distortion. The current approach of incorporating sufficient design stall margin to tolerate these increased levels of distortion would significantly reduce performance. The objective of the High Stability Engine Control (HISTEC) program is to design, develop, and flight-demonstrate an advanced, integrated engine control system that uses measurement-based estimates of distortion to enhance engine stability. The resulting distortion tolerant control reduces the required design stall margin, with a corresponding increase in performance and decrease in fuel burn. The HISTEC concept has been developed and was successfully flight demonstrated on the F-15 ACTIVE aircraft during the summer of 1997. The flight demonstration was planned and carried out in two phases, the first to show distortion estimation, and the second to show distortion accommodation. Post-flight analysis shows that the HISTEC technologies are able to successfully estimate and accommodate distortion, transiently setting the stall margin requirement on-line and in real-time. This allows the design stall margin requirement to be reduced, which in turn can be traded for significantly increased performance and/or decreased weight. Flight demonstration of the HISTEC technologies has significantly reduced the risk of transitioning the technology to tactical and commercial engines. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | AIAA Paper 98-3756
E-11257
NASA/TM-1998-208482
NAS 1.15:208482 |
| 権利 | No Copyright |
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