Fundamental Study on Adaptive Wing Structure for Control of Wing Load Distribution
Author:
Affiliation:
1. Department of Aeronautics and Astronautics, The University of Tokyo
2. Japan Aerospace Exploration Agency
Publisher
Japan Society for Aeronautical and Space Sciences
Link
https://www.jstage.jst.go.jp/article/tastj/15/APISAT-2016/15_TJSAS-D-17-00017/_pdf
Reference16 articles.
1. 1) Powers, S. G., Webb, L. D., Friend, E. L. and Lokos, W. A.: Flight Test Results from a Supercritical Mission Adaptive Wing with Smooth Variable Camber, NASA TM-4415, 1992.
2. 2) Rodriguez, D. L., Aftosmis, M. J., Nemec, M. and Anderson, G. R.: Optimized Off-Design Performance of Flexible Wings with Continuous Trailing-Edge Flaps, AIAA Paper 2015-1409, 2015.
3. 3) Nguyen, N., Precup, N., Urnes Sr., J., Nelson, C., Lebofsky, S., Ting, E. and Livne, E.: Experimental Investigation of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap Design, AIAA Paper 2014-2441, 2014.
4. 4) Zink, P. S., Love, M. H. and Youngren, H.: Drag Minimization Through the Use of Mission Adaptive Trailing Edge Flaps and Fuel State Control, AIAA Paper 2004-4365, 2004.
5. 5) Lebofsky, S., Ting, E., Nguyen, N. and Trinh, K.: Optimization for Load Alleviation of Truss-Braced Wing Aircraft with Variable Camber Continuous Trailing Edge Flap, AIAA Paper 2015-2723, 2015.
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