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

Recent advances in miniaturized electric propulsion are broadening the horizons of small satellite missions. Enabled by the high fuel efficiency of electric thrusters, self-propelled nanosatellites hold the potential to unlock high Δ�� maneuvers. This paper explores the feasibility of an advanced orbit-raising nanosatellite mission. Systems-level analysis and mission simulation in NASA’s General Mission Analysis Tool allowed the identification of two orbit raising missions, one with constant thrust, resulting in a a spiral trajectory and the other using thrust-at-perigee, creating a highly elliptical orbit. A gradient descent search algorithm is presented to derive the characteristics of an optimal propulsion system to meet mission specifications. The results of the work show a constant thrust maneuver with 2 mN of thrust and a specific impulse of 1500 s for 30 W of input power to the electric thruster could reach altitudes near geostationary orbit in 110 days. Comparison with the alternative mission scenario with thrust impulse only at perigee indicate both that thrust-at-perigee is feasible for a 3U CubeSat mission, and has the potential to significantly save propellant and power, thus maximizing mission potential. By providing mass-power requirements for possible mission scenarios, this work has quantified the applicability of electric propulsion for small satellites. The resulting specifications for an optimal thruster is compared with commercially available technologies, leading to conclusions on the direction of future development to make high Δ�� self-propelled small satellite missions a reality.