Model for Prediction of Fatigue Lives Based Upon a Pitting Corrosion Fatigue Process

2009 ◽  
pp. 841-841-30 ◽  
Author(s):  
DW Hoeppner
Keyword(s):  
Corrosion Fatigue ◽  
Pitting Corrosion ◽  
Fatigue Process

806 Pit growth during corrosion fatigue process of industrial pure aluminum

2001 ◽  
Vol 2001.38 (0) ◽  
pp. 245-246
Author(s):  
Sotomi ISHIHARA ◽  
Takahito GOSHIMA ◽  
Hitoshi CHIBA ◽  
Sinitirou NOMATA ◽  
Satosi SUNADA
Keyword(s):  
Corrosion Fatigue ◽  
Pure Aluminum ◽  
Fatigue Process

scholarly journals Management of Airframe In-Service Pitting Corrosion by Decoupling Fatigue and Environment

2021 ◽  
Vol 2 (3) ◽  
pp. 493-511
Author(s):  
Loris Molent ◽  
Russell Wanhill
Keyword(s):  
Corrosion Fatigue ◽  
Pitting Corrosion ◽  
Structural Integrity ◽  
Corrosion Damage ◽  
Fatigue Loading ◽  
Cost Driver ◽  
Service Environments ◽  
Corrosion Pits ◽  
The Impact ◽  
Fatigue Corrosion

Corrosion-induced maintenance is a significant cost driver and availability degrader for aircraft structures. Although well-established analyses enable assessing the corrosion impact on structural integrity, this is not the case for fatigue nucleation and crack growth. This forces fleet managers to directly address detected corrosion to maintain flight safety. Corrosion damage occurs despite protection systems, which inevitably degrade. In particular, pitting corrosion is a common potential source of fatigue. Corrosion pits are discontinuities whose metrics can be used to predict the impact on the fatigue lives of structural components. However, a damage tolerance (DT) approach would be more useful and flexible. A potential hindrance to DT has been the assumption that corrosion-induced fatigue nucleation transitions to corrosion fatigue, about which little is known for service environments. Fortunately, several sources indicate that corrosion fatigue is rare for aircraft, and corrosion is largely confined to ground situations because aircraft generally fly at altitudes with low temperature and humidity Thus, it is reasonable to propose the decoupling of corrosion from the in-flight dynamic (fatigue) loading. This paper presents information to support this proposition, and provides an example of how a DT approach can allow deferring corrosion maintenance to a more opportune time.

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