Fatigue Analysis and Design of Composite-Metal Joints in Primary Aircraft Structures

Abstract:

Increasingly broader application of composite materials in commercial airplane primary structure has led to a renewed, more in-depth assessment of the effect composite elements in mechanical joints have on the durability of the metal structure to which they are mated. Thermal stresses, clamp-up loss due to composite creep, composite joint properties, and lightning and electrical grounding effects have been found to be some of the parameters most significantly affecting or limiting the fatigue performance of the metallic constituents within these hybrid joints, influencing the way joint design and analysis are approached.

• Periodical: Advanced Materials Research (Volumes 891-892)
• Pages: 588-593
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.891-892.588
• Online since: March 2014
• Authors: Antonio C. Rufin*, Robert L. Jochum
• Keywords: Analysis, Composite, Design, Fatigue, Joining, Metals

References

[1] MMPDS-07, Battelle Memorial Institute (2012).

[2] R.B. Heywood, Designing Against Fatigue of Metals, Reinhold, New York, (1962).

[3] Caccese, V., et al., Detection of bolt preload loss in hybrid composite/metal bolted connections, Eng. Struct. 26 (2004) 895-906.

DOI: 10.1016/j.engstruct.2004.02.008

[4] U.S. Code of Federal Regulations Title 14 Part 25. 981, Fuel Tank Ignition Prevention, amended July 21, (2008).