| タイトル | Flight control actuation system |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080007019 |
| 著者（英） | Gaines, Louie T.; Evans, Paul S.; Kern, James I.; Wingett, Paul T. |
| 著者所属（英） | Honeywell International, Inc. |
| 発行日 | 2004-12-07 |
| 言語 | eng |
| 内容記述 | A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities. |
| NASA分類 | Aircraft Stability and Control |
| 権利 | No Copyright |
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