The paper details the stress characteristics in eccentrically loaded aircraft spliced joints. It is shown that the hoop stress (. σ θθ) around each rivet is characterized by two peak values located at . θ=. (0°,. 90°). The magnitude of (. σ θθ) is then reduced to a minimum value between these two peaks. A sharp increase in the axial stress component (. σ xx) along the vertical splice lines occurs in the vicinity of the rivet centerlines followed by a rapid decrease in the areas between the rivets. It is shown that stresses along the first interior rivet row is the most critical. The axial stress (. σ xx) profile along horizontal rivet lines has a " sinusoidal" pattern. It is observed that the transverse stress profile (. σ yy), along the horizontal lines, has different peak and minimum values between the rivets. The magnitude of the peak/minimum values depends upon the line location within the splice region. It is also shown the bending stress component varies significantly and must be accounted for the analysis of the eccentric aircraft joints. Experimental comparisons are made along several lines in the splice region. The numerical model is utilized for analysis of a full frame-bay/splice of aircraft fuselage. The paper provides valuable information that can be utilized by practicing engineers for analysis and design of joints with large number of rivets. © 2011 Elsevier Inc.
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