ABSTRACT
A rocket motor is designed based on the burning rate of 10mm/sec with the burning index of 0.4, which shall be useful to fire at sea level to perform its objective at the maximum altitude of 2 km. Thickness of the shell will be calculated based on the maximum operating pressure of the rocket motor and its throat area, based on the mass flow rate, chamber pressure, and characteristic velocity of propulsion. Propellant composition shall provide its characteristic velocity. Based on the burning rate, chamber pressure shall be evaluated and also operational range will be helpful in evaluating its maximum thrust generated at the time of its operation. A suitable material shall be selected to withstand internal pressure of the rocket motor generated during operation.
