Accession Number : AD0873254
Title : Effect of Edge Restraint on the Buckling of Axially Compressed Circular Cylindrical Shells
Descriptive Note : Final technical rept.
Corporate Author : STANFORD UNIV CA DEPT OF AERONAUTICS AND ASTRONAUTICS
Personal Author(s) : Rehfield, L W
PDF Url : AD0873254
Report Date : Jun 1970
Pagination or Media Count : 45
Abstract : A broad analytical study of the effect of edge restraint on the buckling stress of geometrically perfect, axially compressed circular cylindrical shells, based on linear elastic theory, is presented. An overall evaluation of this effect is made by studying the 16 limiting cases, 7 of which are studied for the first time, it is found that 8 permit buckling to occur at stresses less than the classical theoretical value of theory and experiments indicate that the effect of shell length on the buckling stress can usually be disregarded is used in the analysis. This fact suggests that shells may be assumed to be semi-infinite; as a consequence, formulas for buckling stresses are determined in essentially closed form.
Descriptors : *BUCKLING, *SHELLS(STRUCTURAL FORMS), CYLINDRICAL BODIES, DYNAMICS, EQUATIONS, STRAIN(MECHANICS)
Subject Categories : Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE