The University of Tokyo
The University of Tokyo
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
出版者
宇宙航空研究開発機構(JAXA)
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料
雑誌名(英)
JAXA Special Publication: Proceedings of the First International Symposium on Flutter and its Application
巻
JAXA-SP-16-008E
ページ
457 - 466
発行年
2017-03-15
会議概要（会議名, 開催地, 会期, 主催者等）（英）
First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan
抄録（英）
Recent commercial aircraft have high aspect ratio wings to improve the fuel efficiency. However, it is concerned that the margin of wing strength gets smaller, especially at the wing root. In order to deal with the problem, adaptive wing structure, which can change the lift-to-drag ratio in flight, is considered. By using the adaptive wing structure, the lift distribution can be modified so that the bending moment decreases. The purpose of this paper is to investigate the effectiveness of adaptive wing structure for reducing the bending moment and the stress. For this purpose, static aeroelastic analysis is conducted with a semispan wing model using MSC/NASTRAN. The model is composed of spars, ribs and skins, and has 4 flaps at each of its leading and trailing edges. The set of flap deflection angles is optimized to minimize the wing root bending moment in a 2.5 pull-up maneuver with Response Surface Methodology (RSM) using MATLAB. As a result, the wing root bending moment is successfully reduced by 10 approximately 35% in comparison to that of the original configuration whose flaps have 0 deg deflection angles.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
Numerical study on adaptive wing structure using leading and trailing edge flaps for reduction of bending moment
AA1630046049.pdf
(3.65MB)
