Abstract
The impact of buckling containment features on the stability of thin-gauge fuselage, metallic stiffened panels has previously been demonstrated. With the continuing developments in manufacturing technology, such as welding, extrusion, machining, and additive layer manufacture, understanding the benefits of additional panel design features on heavier applications, such as wing panels, is timely. This compression testing of thick-gauge panels with and without buckling containment features has been undertaken to verify buckling and collapse behaviors and validate sizing methods. The experimental results demonstrated individual panel mass savings on the order of 9%, and wing cover design studies demonstrated mass savings on the order of 4 to 13%, dependent on aircraft size and material choice.
Original language | English |
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Pages (from-to) | 416-426 |
Number of pages | 11 |
Journal | Journal of Aircraft |
Volume | 53 |
Issue number | 2 |
Early online date | 13 Aug 2015 |
DOIs | |
Publication status | Published - 2016 |
Keywords
- Buckling
- Wing Design
- Metallic material
ASJC Scopus subject areas
- Aerospace Engineering