THERMAL STRESS DETERMINATION TECHNIQUES FOR SUPERSONIC TRANSPORT AIRCRAFT STRUCTURES. PART II DESIGN DATA FOR SANDWICH PLATES AND CYLINDERS UNDER APPLIED LOADS AND THERMAL GRADIENTS

Abstract

Structural design data are presented for various applied load and thermal gradient conditions for flat rectangular sandwich panels and sandwich cylinders. The flat panel solutions pertain to instability under nonuniform stress, and also to the stresses and displacements resulting from normal pressures and temperature gradients across the panel thickness in the presence of uniform midplane compression. Sandwich cylinder design data are given for buckling under nonuniform circumferential and axial stress, respectively, and for stresses due to radial or axial temperature gradients. The range of stiffness parameters extend, at one limit, to the isotropic forms of construction.