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Stability of the cylindrical shell of variable curvature
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1951 |
| Description | 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. |
| File Size | 2346669 |
| Page Count | 65 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930093928 |
| Archival Resource Key | ark:/13960/t4dn8gn3z |
| Language | English |
| Publisher Date | 1951-07-01 |
| Access Restriction | Open |
| Subject Keyword | Loads AND Stresses, Structural - Bending Loads AND Stresses, Structural - Compression Cylinders Loads AND Stresses, Structural - Shear Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
