Abstract: This study presents a closed-form solution, utilizing a classical stress formulation approach to carry out elasto-electro-thermo analysis of generalized plane-strain of a right circular cylindrical shell. The present analytical solution holds good for thin as well as thick cylindrical shells made of metallic/composite/piezoelectric/incompressible materials. Standard finite elements are not suitable for modelling the incompressible nature of the solid propellant grains in rocket motors. An efficient axisymmetric hybrid-stress displacement formulation for compressible/nearly incompressible materials will provide accurate results for solid propellant rocket motors. The finite element analysis results for a propellant grain reinforced with a thin metallic casing under thermal and pressure loads are found to be in good agreement with the present analytical solution. Stress analysis results are also presented for a piezoelectric cylindrical shell to examine piezoelectric effects when the shell is subjected to internal pressure. These analytical solutions can provide not only a validation for the finite element model but also provide a means of parametric study, which is useful in the preliminary design stage.