NDLI: Corrosion and corrosion fatigue of airframe aluminum alloys

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Corrosion and corrosion fatigue of airframe aluminum alloys

Content Provider	NASA Technical Reports Server (NTRS)
Author	Wei, R. P. Harlow, D. G. Gao, M. Chen, G. S.
Copyright Year	1994
Description	Localized corrosion and corrosion fatigue crack nucleation and growth are recognized as degradation mechanisms that effect the durability and integrity of commercial transport aircraft. Mechanically based understanding is needed to aid the development of effective methodologies for assessing durability and integrity of airframe components. As a part of the methodology development, experiments on pitting corrosion, and on corrosion fatigue crack nucleation and early growth from these pits were conducted. Pitting was found to be associated with constituent particles in the alloys and pit growth often involved coalescence of individual particle-nucleated pits, both laterally and in depth. Fatigue cracks typically nucleated from one of the larger pits that formed by a cluster of particles. The size of pit at which fatigue crack nucleates is a function of stress level and fatigue loading frequency. The experimental results are summarized, and their implications on service performance and life prediction are discussed.
File Size	2240273
Page Count	17
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19950008051
Archival Resource Key	ark:/13960/t6f23wb8d
Language	English
Publisher Date	1994-09-01
Access Restriction	Open
Subject Keyword	Metallic Materials Service Life Fatigue Life Nucleation Transport Aircraft Life Durability Aluminum Alloys Commercial Aircraft Crack Propagation Coalescing Degradation Pitting Stress-strain Relationships Corrosion Airframes Crack Geometry Fatigue Materials Predictions Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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