| タイトル | A Mission-Adaptive Variable Camber Flap Control System to Optimize High Lift and Cruise Lift-to-Drag Ratios of Future N+3 Transport Aircraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/20140006948 |
| 著者（英） | Urnes, James, Sr.; Totah, Joseph; Nguyen, Nhan; Ting, Eric; Ippolito, Corey; Trinh, Khanh |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 2013-01-06 |
| 言語 | eng |
| 内容記述 | Boeing and NASA are conducting a joint study program to design a wing flap system that will provide mission-adaptive lift and drag performance for future transport aircraft having light-weight, flexible wings. This Variable Camber Continuous Trailing Edge Flap (VCCTEF) system offers a lighter-weight lift control system having two performance objectives: (1) an efficient high lift capability for take-off and landing, and (2) reduction in cruise drag through control of the twist shape of the flexible wing. This control system during cruise will command varying flap settings along the span of the wing in order to establish an optimum wing twist for the current gross weight and cruise flight condition, and continue to change the wing twist as the aircraft changes gross weight and cruise conditions for each mission segment. Design weight of the flap control system is being minimized through use of light-weight shape memory alloy (SMA) actuation augmented with electric actuators. The VCCTEF program is developing better lift and drag performance of flexible wing transports with the further benefits of lighter-weight actuation and less drag using the variable camber shape of the flap. |
| NASA分類 | Aircraft Design, Testing and Performance; Aircraft Stability and Control |
| レポートNO | ARC-E-DAA-TN7072 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/80282 |
