Abstract
Abstract: Rocket motors are widely employed to provide thrust, or impulsive force, which gives the flight vehicle a chosen velocity and facilitates delivery to the intended destination. Newton's second and third principles make up the majority of the rocket motor's operating principle. As a non-air inhalation propulsionclass, rocket motors do not require atmospheric oxygen for the combustion of the fuel that is stored inside of them. The motor hardware is going to be exposed to high temperatures and pressure loads during operation. In order to verify the rocket motor's temperatures and stress levels, structural and thermal design must be completed for the specified input parameters. This study has been approved for publication with structural
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