A linear magnetic reconnection based plasma thruster for spacecraft propulsion
A linear magnetic reconnection based plasma thruster for spacecraft propulsion
Magnetic reconnection offers a potential mechanism to improve the performance of in-space propulsion, reducing transit times between destinations and increasing access to deep space for manned and un-manned missions. This work documents the theory behind and design on a linear reconnecting plasma thruster with theoretical specific impulse of 35000 s and thrust of 1.0 N, at an input power of less than 1000 kW, placing the performance of the thruster an order of magnitude higher than current, state-of-the-art, high power electric propulsion. Limited experimental testing has been conducted, verifying that the assembled electromagnets generate the desired magnetic field profile and magnitude for the thruster mechanism. Magnetohydrodynamic simulations of the proposed thruster have been attempted,with the initial step of the thruster mechanism towards forming a reconnection region being seen but evidence of the full process remains inconclusive due to computation time constraints and boundary condition issues, which could not be solved within the time allocated for the project. However, potential solutions to these issues have been identified and improved simulations will be conducted in future work
Everett, Christopher N.
e7e90931-efb3-46a5-bef9-e7d348736793
Ryan, Charles
3627e47b-01b8-4ddb-b248-4243aad1f872
24 January 2023
Everett, Christopher N.
e7e90931-efb3-46a5-bef9-e7d348736793
Ryan, Charles
3627e47b-01b8-4ddb-b248-4243aad1f872
Everett, Christopher N. and Ryan, Charles
(2023)
A linear magnetic reconnection based plasma thruster for spacecraft propulsion.
AIAA SciTech 2023 Forum, Gaylord National Resort & Convention Center, National Harbor, United States.
23 - 27 Jan 2023.
30 pp
.
(doi:10.2514/6.2023-0448).
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Conference or Workshop Item
(Paper)
Abstract
Magnetic reconnection offers a potential mechanism to improve the performance of in-space propulsion, reducing transit times between destinations and increasing access to deep space for manned and un-manned missions. This work documents the theory behind and design on a linear reconnecting plasma thruster with theoretical specific impulse of 35000 s and thrust of 1.0 N, at an input power of less than 1000 kW, placing the performance of the thruster an order of magnitude higher than current, state-of-the-art, high power electric propulsion. Limited experimental testing has been conducted, verifying that the assembled electromagnets generate the desired magnetic field profile and magnitude for the thruster mechanism. Magnetohydrodynamic simulations of the proposed thruster have been attempted,with the initial step of the thruster mechanism towards forming a reconnection region being seen but evidence of the full process remains inconclusive due to computation time constraints and boundary condition issues, which could not be solved within the time allocated for the project. However, potential solutions to these issues have been identified and improved simulations will be conducted in future work
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In preparation date: 23 January 2023
Published date: 24 January 2023
Venue - Dates:
AIAA SciTech 2023 Forum, Gaylord National Resort & Convention Center, National Harbor, United States, 2023-01-23 - 2023-01-27
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Local EPrints ID: 474513
URI: http://eprints.soton.ac.uk/id/eprint/474513
PURE UUID: a2452a93-ad7f-444b-ab88-a016086caca1
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Date deposited: 23 Feb 2023 17:46
Last modified: 17 Mar 2024 01:03
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Author:
Christopher N. Everett
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