Nanosatellites, such as Cubesats, are becoming increasingly popular for research purposes, especially among universities. However, these satellites do not typically carry propulsion systems, limiting their missions and relegating such satellites to the orbit of the primary payload with which they are launched. The purpose of this paper is to evaluate the performance of a proof-of-concept small-scale vortex-flow end-burning hybrid rocket motor intended as a propulsion system for such spacecraft. The motor has a length to diameter ratio of 0.79 which is much lower than the traditional hybrid average of 8. This allows it to be mounted on the end of a satellite, rather than through the satellite's center. The motor was designed for a thrust of 1 Newton to prevent overwhelming a potential spacecraft's attitude control system. The thruster burns gaseous oxygen and polyethylene and was fired twice. An average operational thrust of 0.72±0.05 Newtons was measured, and an average I_(sp) of 170±10 sec was calculated. Significant heating of the motor case was observed. A CFD study was also conducted, and predicted that I_(sp) would be between 162 and 184 seconds, supporting the experimental results. This thruster, when paired with more energetic propellants, could be a viable competition for monopropellant liquid thrusters.
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