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A tandem mirror plasma source for a hybrid plume plasma propulsion conceptThis paper describes a tandem mirror magnetic plasma confinement device to be considered as a hot plasma source for the hybrid plume rocket concept. The hot plasma from this device is injected into an exhaust duct, which will interact with an annular layer of hypersonic neutral gas. Such a device can be used to study the dynamics of the hybrid plume and to experimentally verify the numerical predictions obtained with computer codes. The basic system design is also geared toward being lightweight and compact, as well as having high power density (i.e., several kW/sq cm) at the exhaust. This feature is aimed toward the feasibility of 'space testing'. The plasma is heated by microwaves. A 50 percent heating efficiency can be obtained by using two half-circle antennas. The preliminary Monte Carlo modeling of test particles result reported here indicates that interaction does take place in the exhaust duct. Neutrals gain energy from the ion, which confirms the hybrid plume concept.
Document ID
19860026265
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Yang, T. F.
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Miller, R. H.
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Wenzel, K. W.
(Massachusetts Inst. of Tech. Cambridge, MA, United States)
Krueger, W. A.
(MIT Cambridge, MA, United States)
Chang, F. R.
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 12, 2013
Publication Date
September 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-2054
Accession Number
86A11003
Distribution Limits
Public
Copyright
Other

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