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  • 1
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    Thrust for interorbital propulsion - A question of lifetime (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The most promising operational window for the use of magnetoplasmadynamic (MPD) thrusters is identified to be at megawatt power levels for orbital maneuvering. For such applications, the operation of a steady-state MPD thruster system imposes stringent requirements on the lifetime of thruster surfaces which will erode due to interactions with the plasma working fluid. Basic erosion mechanisms are presented and the problems associated with measuring the erosion rates are discussed. An experimental approach that would allow the development of a phenomenological model for erosion is proposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    NASA TECHNICAL REPORTS
  • 2
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    Ion thruster charge-exchange plasma flow (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: (Previously cited in issue 07, p. 996, Accession no. A82-19802)
    Keywords: SPACECRAFT PROPULSION AND POWER
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental and computer model results on an ion thruster charge-exchange plasma (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 354-359
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    NASA TECHNICAL REPORTS
  • 4
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    Ion thruster charge-exchange plasma flow (1982)
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    Publication Date: 2019-07-13
    Description: The electron bombardment ion thruster has been under development for a number of years and during this time, studies of the plasmas produced by the thrusters and their interactions with spacecraft have been evaluated, based on available data. Due to diagnostic techniques used and facility effects, there is uncertainty as to the reliability of data from these early studies. This paper presents data on the flow of the charge-exchange plasma produced just downstream of the thruster's ion optics. The 'end-effect' of a cylindrical Langmuir probe is used to determine ion density and directed ion velocity. Results are compared with data obtained from a retarding potential analyzer-Faraday cup.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-0403 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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  • 5
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    A comparison of experimental and computer model results on the charge-exchange plasma flow from a 30 cm mercury ion thruster (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Ion thrusters can be used in a variety of primary and auxiliary space-propulsion applications. A thruster produces a charge-exchange plasma which can interact with various systems on the spacecraft. The propagation of the charge-exchange plasma is crucial in determining the interaction of that plasma with the spacecraft. This paper compares experimental measurements with computer model predictions of the propagation of the charge-exchange plasma from a 30 cm mercury ion thruster. The plasma potentials, and ion densities, and directed energies are discussed. Good agreement is found in a region upstream of, and close to, the ion thruster optics. Outside of this region the agreement is reasonable in view of the modeling difficulties.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1946 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 6
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    Energy storage systems for MPD thrusters (1981)
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    Publication Date: 2019-07-13
    Description: Because of its high thrust density, the magnetoplasmadynamic (MPD) thruster is a promising candidate for many advanced space missions. Its high power requirements lead to operation in a pulsed mode using an intermediate energy storage device. The characteristics of a system consisting of a solar array, energy storage capacitor, and MPD thruster are studied for array powers in the range 25-375 kw. Assuming simple analytic models for the circuit components, the circuit charge and discharge equations are solved numerically, resulting in the system efficiency and capacitance. The system efficiency is inversely proportional to array power and decreases with circuit resistance. Alternative methods of energy storage such as a pulse forming network and a homopolar generator, are presented, and an overall comparison between all of the methods is given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-0142 , Aerospace Sciences Meeting; Jan 12, 1981 - Jan 15, 1981; St. Louis, MO
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  • 7
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    Alfven propulsion at Jupiter (1988)
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    Publication Date: 2019-07-13
    Description: The operation of an electrodynamic tether at Jupiter is investigated. The pertinent Jupiter environments are investigated, and analytic expressions are derived for the induced electric field and the voltage, current, and force for an electrodynamic tether as a function of the radial distance from Jupiter. The formulas are combined with environmental models to arrive at quantitative values for the above parameters. The results are used to investigate propulsion applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Intl. Conference on Space Tethers for Science in the Space Station Era; Oct 04, 1987 - Oct 08, 1987; Venice; Italy
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