Accession Number : ADA309606

Title :   Thermal Buckling Analysis for Stiffened Orthotropic Cylindrical Shells.

Descriptive Note : Technical note,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Chang, L. K. ; Card, Michael F.

PDF Url : ADA309606

Report Date : APR 1971

Pagination or Media Count : 91

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.

Descriptors :   *THERMAL ANALYSIS, *BUCKLING, *THERMAL STRESSES, STRESS STRAIN RELATIONS, COMPUTER PROGRAMS, MATHEMATICAL MODELS, LOAD DISTRIBUTION, STRESS ANALYSIS, STRUCTURAL ANALYSIS, DEFORMATION, MODULUS OF ELASTICITY, STIFFENING, SHELLS(STRUCTURAL FORMS), FINITE DIFFERENCE THEORY, TEMPERATURE GRADIENTS, CYLINDRICAL BODIES, FUSELAGES, COMPRESSIVE STRENGTH, SKIN(STRUCTURAL), LAUNCH VEHICLES, AXIAL LOADS, BENDING STRESS, RADIAL STRESS, STRESS CONCENTRATION, SUPERSONIC TRANSPORT AIRCRAFT, RING STIFFENED CYLINDERS.

Subject Categories : Mechanics
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE