A Solar Thermal Steam Propulsion System Using Disassociated Steam for Interplanetary Exploration
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Final Published Version
Affiliation
Aerospace and Mechanical Engineering Department, University of ArizonaSchool of Energy, Matter and Transport Engineering, Arizona State University
Issue Date
2024-01-17
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Vance, L.; Espinoza, A.; Martinez Dominguez, J.; Rabade, S.; Liu, G.; Thangavelautham, J. A Solar Thermal Steam Propulsion System Using Disassociated Steam for Interplanetary Exploration. Aerospace 2024, 11, 84. https://doi.org/10.3390/aerospace11010084Journal
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© 2024 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).Collection Information
This item from the UA Faculty Publications collection is made available by the University of Arizona with support from the University of Arizona Libraries. If you have questions, please contact us at repository@u.library.arizona.edu.Abstract
Sustainable space exploration will require using off-world resources for propellant generation. Using off-world-generated propellants significantly increases future missions’ range and payload capacity. Near Earth Objects (NEOs) contain a range of available resources, most notably water-ice and hydrated minerals. However, water-bearing regolith needs to be excavated and the water extracted. Water is a compelling choice for fuel as it is readily available in interplanetary space and easily stored. In this paper, we propose using solar concentrators, which can efficiently convert incident sunlight into heat without the need for moving parts. When water is heated up to 4000 K, a value consistent with high-performance refractive materials, it experiences significant disassociation into H2, O2, OH, H, and O components, providing a path for adding considerable additional chemical energy per degree of temperature increase, and producing theoretical specific impulse (Isp) values in the range of 643 s to 659 s. © 2024 by the authors.Note
Open access journalISSN
2226-4310Version
Final Published Versionae974a485f413a2113503eed53cd6c53
10.3390/aerospace11010084
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Except where otherwise noted, this item's license is described as © 2024 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).