An experimental and finite element analysis of a uniform cylindrical shell with a large circular cut-out is presented. In this analysis three hole sizes are considered, namely μ = 2.037, 4.084, and 6.344 (where μ = {[12(1 - y2)]1/4/2} × [a/(Rt)1/2]), for loadings of axial compression, torsion and three point bending. The experimental results are the only ones available for cylindrical shells with large values of μ (except for one graph by Savin (1)†), while for three point bending there is no previously published theoretical or analytical results.
Good agreement is found between the calculated and experimental stresses around the holes.
Get full access to this article
View all access options for this article.
References
1.
SavinG. N.‘Stress distribution around holes’, NASA. Technical Translation, NASA TT F67, 1970.
2.
KolossoffG.PhD Dissertation, Dorpat, 1909.
3.
HoughtonD. S.RothwellA.‘The analysis of reinforced circular and elliptical cut-outs under various loading conditions. College of Aeronautics, Rpt. No. 151, 1961.
4.
HoughtonD. S.RothwellA.‘The effects of curvature on the stress concentration around holes in shells’, College of Aeronautics, Rpt. No. 156, 1962.
