Abstract
Multi-mode spacecraft micro propulsion systems which include a high-thrust chemical mode and high-specific impulse electric mode are assessed with specific reference to cube sat-sized satellite applications. Both cold gas Freon-14 propellant and ionic liquid chemical monopropellant modes were investigated alongside pulsed plasma, electrospray, and helicon electric thruster modes. Systems involving chemical monopropellants have the highest payload mass fractions for a reference mission of a 500 m/s delta-V and 6U sized cube sat for electric propulsion usage below 55% of total delta-V. For higher electric propulsion usage, cold gas thrusters delivered a higher payload mass fraction due to lower system inert mass. Due to the combination of utilizing a common propellant for both propulsive modes, low inert mass, and high electric thrust, the cold-gas chemical/helicon-type electric combination had the highest mission flexibility, able to achieve a delta-V 10% lower than that of the largest delta-V system, but at roughly 500 days less burn time. A System utilizing a monopropellant thruster and electrospray thruster can achieve the largest delta-V, but with a burn time of over 600 days. This same system, however, can achieve the largest delta-V for missions requiring a thrust time of less than roughly 10 days.
Recommended Citation
S. P. Berg and J. L. Rovey, "Assessment of Multi-Mode Spacecraft Micropropulsion Systems," 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, American Institute of Aeronautics and Astronautics, Jan 2014.
The definitive version is available at https://doi.org/10.2514/6.2014-3758
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
International Standard Book Number (ISBN)
978-162410303-2
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 2014
