Feasibility of a Deep-Space CubeSat Mission with a Stage-Based Electrospray Propulsion System
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ieee_aeroconf_2020_hispeed.pdf
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Author(s)
Jia-Richards, Oliver
Lozano, Paulo C
Sternberg, David C.
Grebow, Daniel
Mohan, Swati
Date Issued
August 2020
Journal
2020 IEEE Aerospace Conference
Publisher
Institute of Electrical and Electronics Engineers (IEEE)
Citation
Jia-Richards, Oliver et al. "Feasibility of a Deep-Space CubeSat Mission with a Stage-Based Electrospray Propulsion System." 2020 IEEE Aerospace Conference, March 2020, Big Sky, Montana, Institute of Electrical and Electronics Engineers, August 2020. © 2020 IEEE
Version
Author's final manuscript
Abstract
Independent deep-space CubeSat missions require efficient propulsion systems capable of delivering several km/s of ΔV. The ion Electrospray Propulsion System under development at MIT's Space Propulsion Laboratory is a high ΔV propulsion system that is a promising technology for propulsion of independent deep-space CubeSat missions due to its mechanical simplicity and small form factor. However, current electrospray thrusters have demonstrated lifetimes up to an order of magnitude lower than the required firing time for a mission to a near-Earth asteroid starting from geostationary orbit. A stage-based concept is proposed where the propulsion system consists of a series of electrospray thruster arrays. When a set of thrusters reaches its lifetime limit, it is ejected from the spacecraft exposing new thrusters thereby increasing the overall lifetime of the propulsion system. Such a staging strategy is usually not practical for in-space thrusters. However, the compactness of micro-fabricated electrospray thrusters means that their contribution to the overall spacecraft mass and volume is small relative to other subsystems. Mechanisms required for this stage-based approach are proposed and demonstrated in a vacuum environment. In addition, missions to several near-Earth asteroids with orbital elements similar to those of Earth are analyzed with a particular focus on the escape trajectory. With a stage-based approach, independent deep-space CubeSat missions become feasible from a propulsion standpoint.
MIT Department
Massachusetts Institute of Technology. Space Propulsion Lab
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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Creative Commons Attribution-Noncommercial-Share Alike
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DOI of Published Version
https://doi.org/10.1109/aero47225.2020.9172544
