Abstract
One potential solution for a morphing wing concept could make use of a skin panel that incorporates corrugated laminates in a sandwich structure. Located in the trailing edge region it would have low in- and out-of-plane stiffness in the wing chordwise direction in order to achieve large camber and chord length changes on a morphing aerofoil section. This investigation presents experimental and analytical results for a sandwich structure with trapezoidal corrugated skins. Furthermore, a parametric study analyses the effects of corrugation geometry and form on the structural elastic strain and equivalent elastic tensile modulus transversely to the corrugation direction. The results give a good indication of the wide envelope within which corrugated laminates can be designed to meet the requirements for a morphing skin application.
Original language | English |
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Title of host publication | 19th International Conference on Adaptive Structures and Technologies 2008, ICAST 2008 |
Publisher | Swiss Federal Laboratories for Materials Science and Technology (Empa) |
Pages | 313-325 |
Number of pages | 13 |
ISBN (Electronic) | 9781617389870 |
Publication status | Published - 2008 |
Externally published | Yes |
Event | 19th International Conference on Adaptive Structures and Technologies 2008, ICAST 2008 - Ascona, Switzerland Duration: 6 Oct 2008 → 9 Oct 2008 |
Publication series
Name | 19th International Conference on Adaptive Structures and Technologies 2008, ICAST 2008 |
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Conference
Conference | 19th International Conference on Adaptive Structures and Technologies 2008, ICAST 2008 |
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Country/Territory | Switzerland |
City | Ascona |
Period | 6/10/08 → 9/10/08 |
Keywords
- Composites
- Corrugations
- Morphing
- Skins