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  • Other Sources  (2)
  • 1985-1989  (2)
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  • 1
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    A tandem mirror plasma source for hybrid plume plasma studies (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: A tandem mirror device to be considered as a hot plasma source for the hybrid plume rocket concept is discussed. The hot plamsa from this device is injected into an exhaust duct, which will interact with an annular hypersonic layer of neutral gas. The device can be used to study the dynamics of the hybrid plume, and to verify the numerical predictions obtained with computer codes. The basic system design is also geared towards low weight and compactness, and high power density at the exhaust. The basic structure of the device consists of four major subsystems: (1) an electric power supply; (2) a low temperature, high density plasma gun, such as a stream gun, an MPD source or gas cell; (3) a power booster in the form of a tandem mirror machine; and (4) an exhaust nozzle arrangement. The configuration of the tandem mirror section is shown.
    Keywords: PLASMA PHYSICS
    Type: AFOSR The 1985 AFOSR(AFRPL Chem. Rocket Res. Meeting; 3 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A tandem mirror plasma source for a hybrid plume plasma propulsion concept (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This 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.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 85-2054
    Format: text
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    NASA TECHNICAL REPORTS
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