By Hans-Heiri Stapfer
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Chapter 2 will diseuss the applieation of this teehnique for quantifieation and evaluation of eorrosion defeets. Parameters determined by WLIM can be used to ca1culate the stress intensity factors of eorrosion pits, which show an exceIlent correlation to the fatigue life of eorroded test specimens. Micro-focus x-ray teehniques can be employed to quantify hidden corrosion. The gray scale in the x-ray image is analyzed to quantify corrosion depths and thickness loss (Chapter 3). Pixel by pixel comparison between topography ca1culated from x-ray images and measured by white light interference microscopy indieates that neither technique show the complete damage.
1, No. 4: 255 Wallace WW, Hoeppner DW (1985) AGARD Corrosion Handbook, vol. 1, Aircraft Corrosion: Causes and Case Histories. AGARDograph No. 278, NATO, p. 101 Callister WD Jr. (1994) Materials Science and Engineering: An Introduction, 4th ed. Wiley, New York Cooper DC, Kelto CA (1978) Fatigue in machines and structures-Aircraft. Fatigue and microstructure: Materials science seminar, Proc ASM pp. 29-56 Suresh S (1991) Fatigue ofMaterials. Cambridge University Press, Cambridge, p. 10 Finney JM (1994) Fatigue crack growth in metallic military aircraft structures.
Liu JJ, Vincent L (1997) Nucleation and early growth of tribologically transformed structure (TTS) induced by fretting. Wear 212:50-58 40. Antoniou RA, Radtke TC (1997) Mechanisms of fretting-fatigue of titanium alloys. Mat Sci Eng A237:229-240 41. Fouvry S, Kapsa Ph, Vincent L (1995) Analysis of sliding behavior for fretting loadings: determination of transition criteria. B. Shell, M. Khobaib, J. Hoying, L. Simon, C. Kacmar, V. Kramb, M. Donley, D. 1 Introduction In many applications, the onset of damage occurs at the component surface due to plastic deformation, fretting, wear, corrosion, or crack nucleation.