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The influence of the environment and corrosion on the structural integrity of aircraft materials
Author(s) -
RUSSO S.,
SHARP P. K.,
DHAMARI R.,
MILLS T. B.,
HINTON B. R. W.,
CLARK G.,
SHANKAR K.
Publication year - 2009
Publication title -
fatigue and fracture of engineering materials and structures
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.887
H-Index - 84
eISSN - 1460-2695
pISSN - 8756-758X
DOI - 10.1111/j.1460-2695.2009.01348.x
Subject(s) - fastener , materials science , corrosion , corrosion fatigue , fretting , aluminium , metallurgy , aluminium alloy , cyclic stress , intermetallic , alloy , composite material
Fatigue results of 1 1 / 2 dog‐bone jointed specimens manufactured from 7075‐T6 aluminium alloy indicated that the application of corrosion preventative compounds (CPCs) at the faying surfaces slightly decreased the log mean fatigue life at 144 MPa, while the effect was not statistically significant at the higher stress level (210 MPa). The addition of the CPC also reduced fretting corrosion at the faying surfaces and shifted the fatigue initiation sites closer to the edge of fastener holes. Scatter in fatigue life was found to be associated with the location and size of the intermetallics at the initiation site. The presence of corrosion in the bores of the countersunk fastener holes reduced the fatigue life by up to one order of magnitude. Fatigue test results for dog‐bone specimens manufactured from 7075‐T651 and 2024‐T351 aluminium alloys indicated that the presence of exfoliation corrosion reduced the fatigue life under dry conditions, with a greater reduction under humid conditions. The application of a CPC to the corroded region eliminated the influence humidity had on fatigue life.