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A Simplified Method of Elastic Stability Analysis for Thin Cylindrical Shells

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:06:46Z
date available2017-09-04T17:06:46Z
date copyright01/01/1947
date issued1947
identifier otherYFYHUEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=autho9216AF6769B752731854DD6EFDEC014A/handle/yse/130291
description abstractThis paper develops a new method for determining the buckling stresses of cylindrical shells under various loading conditions. In part I, the equation for the equilibrium of cylindrical shells introduced by Donnell in NACA report no. 479 to find the critical stresses of cylinders in torsion is applied to find critical stresses for cylinders with simply supported edges under other loading conditions. In part II, a modified form of Donnell's equation for the equilibrium of thin cylindrical shells is derived which is equivalent to Donnell's equation but has certain advantages in physical interpretation and in ease of solution, particularly in the case of shells having clamped edges. The question of implicit boundary conditions is also considered.
languageEnglish
titleNACA REPORT 874num
titleA Simplified Method of Elastic Stability Analysis for Thin Cylindrical Shellsen
typestandard
page25
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAEROELASTICITY
subject keywordsANALYSIS (MATHEMATICS)
subject keywordsAXIAL COMPRESSION LOADS
subject keywordsBUCKLING
subject keywordsCOMPARISON
subject keywordsCRITICAL LOADING
subject keywordsCYLINDRICAL SHELLS
subject keywordsDONNELL EQUATIONS
subject keywordsEDGES
subject keywordsELASTIC SHELLS
subject keywordsSHEAR STRESS
subject keywordsSTABILITY
subject keywordsSTRESS ANALYSIS
subject keywordsSTRESSED-SKIN STRUCTURES
subject keywordsSUPPORTS
subject keywordsTHEORIES


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