Development of a Solid Propellant Motor for High- Powered Model Rockets

Abstract

High powered rocketry involves rockets with a total mass of more than 1,500 grams, a fuel mass of more than 125 grams and a propellant of more than 160 Newton-seconds of total impulse or a motor with an average thrust of 80 Newtons or more. Such rockets require high powered propulsion systems to be developed in order to achieve the required thrust and apogee. This paper highlights the design, simulation, and development of a high-powered propulsion system for the Nakuja-2 rocket with a desired apogee of 500 m. The design process was done with the goal to ensure the required thrust is achieved while ensuring safety. During the process, data was collected remotely by means of a developed data acquisition system and the developed solid propellant motor was able to generate an average thrust of 151.7 Newtons, getting the rocket to an apogee of 280 m. Keywords— Solid rocket propellant, Model rocket, Thrust