| タイトル | Stability of the cylindrical shell of variable curvature |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930093928 |
| 著者（英） | Marguerre, Karl |
| 著者所属（英） | National Advisory Committee for Aeronautics |
| 発行日 | 1951-07-01 |
| 言語 | eng |
| 内容記述 | This report is a first attempt to devise a calculation method for representing the buckling behavior of cylindrical shells of variable curvature. The problem occurs, for instance, in dimensioning wing noses, the stability of which is decisively influenced by the variability of curvature. The calculation is made possible by simplifying the stability equations (permissible for the shell of small curvature) and by assuming that the curvature 1/R as a function of the arc lengths can be represented by a very few Fourier terms. The formulas for the special case of an ellipse-like half oval with an axis ratio 1/3 ?= e ?= 1 under compression in longitudinal direction,shear, and a combination of shear and compression were evaluated. However, the results can also be applied approximately to an unsymmetrical oval-shell segment under compression, shear, and bending so that the numerical values contained in the diagrams 10 to 12 represent directly dimensioning data for the wing nose. |
| レポートNO | 93R23254
NACA-TM-1302 |
| 権利 | No Copyright |
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