2026-09-19T19:07:39Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/728412022-01-13T07:54:36Zcom_1721.1_7582com_1721.1_7581col_1721.1_131024
Paulo Lozano.
Conte, Joseph Richard, III
Massachusetts Institute of Technology. Dept. of Mechanical Engineering.
Massachusetts Institute of Technology. Department of Mechanical Engineering
2012-09-13T18:55:36Z
2012-09-13T18:55:36Z
2012
2012
http://hdl.handle.net/1721.1/72841
807127388
Thesis (S.B.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2012.
Pages 46-85 printed landscape format. Cataloged from PDF version of thesis.
Includes bibliographical references (p. 44-45).
A plasma space propulsion thruster has been designed. It is classified as a Cusped Field Thruster (CFT), which refers to the geometry of the magnetic field that influences the flow of electrons and ions. The thruster was modeled after an original Diverging Cusped Field Thruster (DCFT) developed at MIT's Space Propulsion Laboratory. There are several improvements (including a flat downstream separatrix) that are aimed at increasing performance. In general, plasma thrusters have applications in satellite trajectory adjustment and deep space probes because of their superior fuel efficiency compared to chemical thrusters.
by Joseph Richard Conte, III.
S.B.
85 p.
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by
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http://dspace.mit.edu/handle/1721.1/7582
Mechanical Engineering.
Design of a cusped field plasma thruster
Thesis
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