Assessment of Materials for Fuselage Panels Considering Fatigue Behavior

• Type: Article in International Conference Proceedings Book
• Date: 2013

Authors

tavares, smo (Author) FEUP; camanho, p (Author) FEUP; de castro, pmst (Author) FEUP

Conference proceedings International

Title: ADVANCED MATERIALS FORUM VI, PTS 1 AND 2

Pages: 265-270

6th International Materials Symposium (MATERIALS 2011)/15th Meeting of SPM

Guimaraes, PORTUGAL, APR 18-20, 2011

Indexing

ISI Web of Knowledge - 0 Citations

Scopus - 1 Citation

Scientific classification

FOS: Engineering and technology > Materials engineering

Other information

Authenticus ID: P-005-3N4

DOI: 10.4028/www.scientific.net/msf.730-732.265

Abstract (EN): Minimum-weight designs are frequently too costly to manufacture, whereas less expensive and easy to fabricate and assemble designs are often much heavier. The most efficient design on the basis of both cost and weight often lies between these two extremes. The current trend in structural materials selection consists of the extensive use of composite materials in the airframe. Composite materials have high specific strength, are less prone to fatigue crack initiation and provide enhanced flexibility for structural optimization compared to the aluminum alloys. On the other hand, aluminum alloys display higher toughness and better damage tolerance in the presence of defects. A simple methodology for the weight assessment based on the specific weight for different damage scenarios for an exemplary, simplified fuselage panel, will be presented, in order to quantify the savings under different conditions. The results show that the composites have advantages over the aluminum alloys, although due to low ductility, in parts that are exposed to external damages the aluminum alloys can have better performance due to the better damage tolerant properties.

Language: English

Type (Professor's evaluation): Scientific

No. of pages: 6