Design and Analysis of a Self-Propelled Nanosatellite for a Mission Beyond Low Earth Orbit

Recent advances in miniaturised electric propulsion have shifted the paradigm for small satellite missions. Enabled by the high fuel efficiency of electric thrusters, self-propelled nanosatellites hold the potential to unlock high delta-V manoeuvres. This paper explores the feasibility of an advanced orbit-raising nanosatellite mission. Systems-level analysis and mission simulation allowed the identification and analysis of two optimised missions. The characteristics of the optimal propulsion system that would enable such missions are also presented. The results of the work show a constant thrust manoeuvre with 2 mN of thrust and a specific impulse of 1250 s for 30 W of input power to the electric thruster could reach altitudes near geostationary orbit in less than 100 days. These simulation results were compared with an alternative mission scenario with thrust impulse only at perigee. The findings indicate that such an approach is not only feasible for a 3U, but also has the potential to significantly save propellant and power, thus saving mass and volume. By providing mass-power requirements for possible mission scenarios, this work has quantified the applicability of electric propulsion for small satellites. Resulting optimal thruster characteristic is compared with commercially available technologies, leading to the conclusions on the direction of future directions of development.