Abstract
Multimode spacecraft micro propulsion systems that include a high-Thrust chemical mode and high-specific impulse electric mode are assessed with specific reference to CubeSat-sized satellite applications. Both cold-gas butane propellant and ionic liquid chemical monopropellant modes are investigated alongside pulsed plasma, electrospray, and ion electric thruster modes. These systems are studied by varying electric propulsion usage percent and calculating the payload mass fraction and thruster burn time for missions requiring 250, 500, and 1000 m/s delta-V. Systems involving chemical monopropellants have the highest payload mass fractions for a reference mission of 500 m/s delta-V and 6U-sized CubeSat, where 1U is a 10 cm x 10 cm x 10 cm volume, for electric propulsion usage below 70% of total delta-V; whereas for higher electric propulsion usage, cold-gas thrusters deliver a higher payload mass fraction due to lower system inert mass. Due to the combination of a shared propellant for both propulsive modes, low inert mass, high electric thrust, and specific impulse near optimum for the system, the monopropellant/ electrospray system has the highest mission capability in terms of delta-V for missions lasting less than 150 days.
Recommended Citation
S. P. Berg and J. L. Rovey, "Assessment of Multimode Spacecraft Micropropulsion Systems," Journal of Spacecraft and Rockets, vol. 54, no. 3, pp. 592 - 601, American Institute of Aeronautics and Astronautics, Jan 2017.
The definitive version is available at https://doi.org/10.2514/1.A33649
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
International Standard Serial Number (ISSN)
1533-6794; 0022-4650
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 2017
