Fatigue Life Enhancement of a D16at Aluminum Alloy for Aircraft Components with Fastener Holes
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21340%2F20%3A00345005" target="_blank" >RIV/68407700:21340/20:00345005 - isvavai.cz</a>
Result on the web
<a href="https://doi.org/10.1007/s11223-020-00144-3" target="_blank" >https://doi.org/10.1007/s11223-020-00144-3</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1007/s11223-020-00144-3" target="_blank" >10.1007/s11223-020-00144-3</a>
Alternative languages
Result language
angličtina
Original language name
Fatigue Life Enhancement of a D16at Aluminum Alloy for Aircraft Components with Fastener Holes
Original language description
D16AT aircraft Al-alloy was evaluated. The friction stir hole expansion (FSHE), solid mandrel cold working and symmetric cold expansion (SCE) methods were compared. The results are summarized on the basis of fatigue tests, S–N curves, X-ray diffraction, and microstructural analysis. Under the high-cycle fatigue, SCE provides more than 66 times longer fatigue life as compared to the solid mandrel method and more than 82 times greater fatigue life in comparison with the FSHE method. Through X-ray diffraction analysis it was found that the higher efficiency of the SCE method was due to symmetric distribution (with respect to the plate middle plane) of residual hoop stresses around the hole. On the other hand, the solid mandrel cold working method causes a significant gradient of the residual stress distribution through the plate thickness, which is a precondition for nucleation and propagation of corner fatigue cracks. The FSHE method efficiency was established to be primarily dependent on generated heat and equivalent plastic strains. The combination of these factors determines the beneficial microeffect of the microstructure modifying in the vicinity of the hole and a useful macroeffect due to residual compressive stresses. It was concluded that SCE method should be used for prestressing of fastener holes in the most loaded components in D16AT aircraft structures – wings and fuselage, while the FSHE one can be applied to processing of fastener holes in less loaded aircraft components.
Czech name
—
Czech description
—
Classification
Type
J<sub>imp</sub> - Article in a specialist periodical, which is included in the Web of Science database
CEP classification
—
OECD FORD branch
20501 - Materials engineering
Result continuities
Project
—
Continuities
I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace
Others
Publication year
2020
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Name of the periodical
Strength of Materials
ISSN
0039-2316
e-ISSN
1573-9325
Volume of the periodical
52
Issue of the periodical within the volume
1
Country of publishing house
US - UNITED STATES
Number of pages
15
Pages from-to
1-15
UT code for WoS article
000528074600001
EID of the result in the Scopus database
2-s2.0-85084061699