Creep Buckling of Cylindrical Shells in Axial Compression,
Abstract
Tests have been made of 56 QQ-M-44H magnesium alloy circular cylinders in axial compression. The test temperatures ranged from 75F to 600F and the loading program included stresses increasing linearly with time in addition to constant stresses. A semiempirical formula was obtained which correlates, through the use of basic elastic and creep properties, the buckling stress and time as influenced by temperature and the stress history in the ranges tested. The statistical variation of the data as correlated has been used to establish allowable buckling stresses of the material used in the GAR-3/GAR-4 Falcon missile fuselages as a function of desired probability of failure. The buckling correlation equation has been expressed in terms of the elastic and generalized secant moduli of the cylinder material and has been used to predict creep buckling stresses for other materials. Methods of applying these results to creep buckling under transient stress and temperature conditions have been analyzed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1957
- Accession Number
- ADA951882
Entities
People
- C. H. Tsao
- J. M. Bozajian
Organizations
- Hughes Aircraft Company