Conceptual Design and Structural Analysis of Solid Rocket Motor Casing

This paper is concern with theoretical design of the 100 kg solid rocket motor with predefined values of the burning rate is 100 mm/ sec, specific impulse is 240 sec and chamber pressure is 1000 psi. confined with selection of the material and basic concept of the rocket motor and its aspect during static test. Rocket motor is a highly complex aerospace component that consists of a metal casting, ablative liner and propellant grain. Also to determine the design pressure and burst pressure of a solid rocket motor casing .Preliminary design provided key propulsion outputs that would later be refined and assessed in the final design.