Design and Analysis of Composite Rocket Motor Casing

Rocket motors are extensively used to produce thrust or impulsive force to impart a preferred velocity to flight vehicle to convey its shipment to the proposed target. The working principle of the Rocket motor is mostly Newton's 2 nd and 3rd laws. Rocket motors are non-air inhalation propulsion class i.e., won't involve oxygen from the atmosphere for combustion of the fuel which is stored in the rocket motor. Through the operating situation of the motor hardware, it will be subjected to high temperatures and pressure loads. Structural and thermal design has to be carried out for a given input parameters and analysis to be carried out to check the stress levels and temperatures on the rocket motor. This research work has been accepted out with structural design of motor hardware. The main input parameters measured are the maximum working pressure and maximum diameter of the motor hardware. For design, the motor hardware is measured as a pressure vessel. To calculate parameters like thickness some initial assumptions were finished. 2D drawing has urbanized using solid works software and for structural and thermal analysis is approved out in ANSYS. This software employs finite element analysis techniques to generate the solution. Hence the displacement magnitude, von Mises stress and strain developed within the motor. From this analysis the suitable material can be proposed, suggested for the future work.