Paper Title:
Damage Tolerance Properties of 2198-T8 Integral Fuselage Panel between Double Friction Stir Weld Joints
  Abstract

Al-Li alloy 2198-T8 was used in the fuselage application. Integral fuselage panels were joined by double friction stir welds. Fatigue tests were conducted in the R=0.1. Notch was made between two welds. Residual stresses were measured and analyzed in the test samples with double welds. Cracks grew from the centre of two welds and across the two welds were observed, and crack growth rates were measured and compared with parent material. It is shown that crack growth rates are lower between double welds, and it is close to parent material after cross the two welds. The virtual crack closure technique (VCCT) method was used to calculate stress intensity factor from residual stress (Kres) in aim to explain the experimental findings.

  Info
Periodical
Chapter
Chapter 2: Material Science and Engineering
Edited by
Honghua Tan
Pages
651-656
DOI
10.4028/www.scientific.net/AMM.138-139.651
Citation
Y. E. Ma, B. Q. Liu , Z. Q. Zhao, "Damage Tolerance Properties of 2198-T8 Integral Fuselage Panel between Double Friction Stir Weld Joints", Applied Mechanics and Materials, Vols. 138-139, pp. 651-656, 2012
Online since
November 2011
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$32.00
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