Thermal Buckling Analysis for Stiffened Orthotropic Cylindrical Shells.
Abstract
A theory for thermal buckling of an orthotropic, multilayered, stiffened cylindrical shell is presented. The theory includes the effects of eccentricity of layers and stiffening, and deformations prior to buckling. It is sufficiently general to account for discrete rings and averaged properties of longitudinal stiffening, as well as arbitrary temperature distributions through the thickness of the shell and depth of the stiffeners. Two computer programs are described corresponding to solutions for buckling obtained by using finite differences and determinant plotting or modal iteration. Computed results for thermal buckling of unstiffened and ring-stiffened shells are presented and are in reasonable agreement with published results. The interaction of thermal loading and axial compression in two large-diameter stiffened shells representative of a launch vehicle interstage and a preliminary supersonic transport fuselage design is investigated. Results indicate that buckling can occur in both structures at a realistic temperature under thermal loading alone.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1971
- Accession Number
- ADA309606
Entities
People
- L. K. Chang
- Michael F. Card
Organizations
- Langley Research Center