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  • Other Sources  (11)
  • 1
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    The Effects of Magnetic Nozzle Configurations on Plasma Thrusters (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Over the course of eight years, the Ohio State University has performed research in support of electric propulsion development efforts at the NASA Lewis Research Center, Cleveland, OH. This research has been largely devoted to plasma propulsion systems including MagnetoPlasmaDynamic (MPD) thrusters with externally-applied, solenoidal magnetic fields, hollow cathodes, and Pulsed Plasma Microthrusters (PPT's). Both experimental and theoretical work has been performed, as documented in four master's theses, two doctoral dissertations, and numerous technical papers. The present document is the final report for the grant period 5 December 1987 to 31 December 1995, and summarizes all activities. Detailed discussions of each area of activity are provided in appendices: Appendix 1 - Experimental studies of magnetic nozzle effects on plasma thrusters; Appendix 2 - Numerical modeling of applied-field MPD thrusters; Appendix 3 - Theoretical and experimental studies of hollow cathodes; and Appendix 4 -Theoretical, numerical and experimental studies of pulsed plasma thrusters. Especially notable results include the efficacy of using a solenoidal magnetic field downstream of a plasma thruster to collimate the exhaust flow, the development of a new understanding of applied-field MPD thrusters (based on experimentally-validated results from state-of-the art, numerical simulation) leading to predictions of improved performance, an experimentally-validated, first-principles model for orificed, hollow-cathode behavior, and the first time-dependent, two-dimensional calculations of ablation-fed, pulsed plasma thrusters.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-CR-202341 , NAS 1.26:202341 , E-10721
    Format: application/pdf
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  • 2
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    A first-principles model for orificed hollow cathode operation (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A theoretical model describing orificed hollow cathode discharge is presented. The approach adopted is based on a purely analytical formulation founded on first principles. The present model predicts the emission surface temperature and plasma properties such as electron temperature, number densities and plasma potential. In general, good agreements between theory and experiment are obtained. Comparison of the results with the available related experimental data shows a maximum difference of 10 percent in emission surface temperature, 20 percent in electron temperature and 35 percent in plasma potential. In case of the variation of the electron number density with the discharge current a maximum discrepancy of 36 percent is obtained. However, in the case of the variation with the cathode internal pressure, the predicted electron number density is higher than the experimental data by a maximum factor of 2.
    Keywords: PLASMA PHYSICS
    Type: AIAA PAPER 92-3742
    Format: text
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  • 3
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    Qualitative spectroscopic study of magnetic nozzle flow (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The physics of the magnetic nozzle flow for a 100-kW-level quasi-steady MPD thruster was studied by photographic spectroscopy focusing on the plasma model in the flow and the acceleration mechanism. Spectroscopic visualization for the flow-species analysis indicates that the plasma-exhaust flow dominated by NII species were confined by the magnetic nozzle effect to collimate the flow for the better thruster performance. Inside the nozzle, the plasma flow was found to be in nonhomogeneous collisional-radiative condition. There appears to be a substantial flow acceleration from the magnetic nozzle inlet to the outlet with slight expansion. This suggests that the flow resembles that of constant area supersonic duct flow with cooling.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3161
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  • 4
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    Some Considerations on the Pulsed Electromagnetic Acceleration of Plasma (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: In applying pulsed electromagnetic acceleration of plasma to space propulsion (known as pulsed plasma thrusters in the community), the mode of acceleration used has been mostly in the collisionless or near-collisionless regime. The preparation of the initial plasma is given scant attention. Collisional regime of accelerating the plasma, however, have been encountered in a variety of plasma accelerating devices. Both of these modes of acceleration are reviewed in a companion paper. In this paper, we discuss the considerations governing the controlled introduction and preparation of the initial plasma, so that the collisional mode of accelerating the plasma may be suitably enhanced.
    Keywords: Plasma Physics
    Type: American Physical Society Division of Plasma Physics Annual Meeting; Nov 11, 2002 - Nov 15, 2002; Orlando, FL; United States
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  • 5
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    Conceptual Design of an MTF Space Propulsion System (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Most fusion propulsion concepts that have been investigated in the past employ some form of inertial or magnetic confinement separately, and are encumbered by the need for advanced drivers (e.g. laser) or steady-state magnetic confinement systems (e.g. superconductors) that have historically resulted in large, massive spacecraft designs. Here we present a comparatively new approach, Magnetized Target Fusion (MTF), which offers a nearer-term avenue for realizing the tremendous performance benefits of fusion propulsion. MTF attempts to combine the favorable attributes of both inertially and magnetically confined fusion to achieve both efficient and low-cost compressional plasma heating and energy confinement. The key advantage of MTF is its less demanding requirements for driver energy and power processing. Additional features include: 1) very low system masses and volumes, 2) relatively low waste heat, 3) substantial utilization of energy from product neutrons, 4) efficient, low peak-power drivers based on existing pulsed power technology, 5) very high Isp , specific power and thrust, and 6) relatively affordable R&D pathways. MTF overcomes many of the problems associated with traditional fusion techniques, thus making it particularly attractive for space applications. Isp greater than 50,000 seconds and specific powers greater than 20 kilowatts/kilogram appear feasible using relatively near-term pulse power and plasma gun technology.
    Keywords: Spacecraft Propulsion and Power
    Type: DOE Innovative Confinement Concepts; Jan 22, 2002 - Jan 24, 2002; College Park, MD; United States
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  • 6
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    Plasma Liner Research for MTF at NASA Marshall Space Flight Center (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The current research effort at NASA Marshall Space Flight Center (MSFC) in MTF is directed towards exploring the critical physics issues of potential embodiments of MTF for propulsion, especially standoff drivers involving plasma liners for MTF. There are several possible approaches for forming plasma liners. One approach consists of using a spherical array of plasma jets to form a spherical plasma shell imploding towards the center of a magnetized plasma, a compact toroid. Current experimental plan and status to explore the physics of forming a 2-D plasma liner (shell) by merging plasma jets are described. A first-generation coaxial plasma guns (Mark-1) to launch the required plasma jets have been built and tested. Plasma jets have been launched reproducibly with a low jitter, and velocities in excess of 50 km/s for the leading edge of the plasma jet. Some further refinements are being explored for the plasma gun, Successful completion of these single-gun tests will be followed by an experimental exploration of the problems of launching a multiple number of these jets simultaneously to form a cylindrical plasma liner.
    Keywords: Spacecraft Propulsion and Power
    Type: DOE Innovative Confinement Concepts; Jan 22, 2002 - Jan 24, 2002; College Park, MD; United States
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  • 7
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    Acceleration patterns in quasi-steady MPD arcs (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Quasi-steady coaxial MPD arcs characteristics, studying Ar ion velocities, electrostatic ion acceleration mechanism and arc voltage gradient
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 70-165 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 8
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    The cathode region of a quasi-steady magnetoplasmadynamic arcjet, supplement 8 (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Electric and magnetic field measurements in cathode region of quasi-steady magnetoplasmadynamic arcjet
    Keywords: PHYSICS, PLASMA
    Type: NASA-CR-117040 , REPT-940-SUPPL-8
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  • 9
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    Conceptual Design of an MTF Space Propulsion System (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Most fusion propulsion concepts that have been investigated in the past employ some form of inertial or magnetic confinement separately, and are encumbered by the need for advanced drivers (e.g. laser) or steady-state magnetic confinement systems (e.g. superconductors) that have historically resulted in large, massive spacecraft designs. Here we present a comparatively new approach, Magnetized Target Fusion (MTF), which offers a nearer-term avenue for realizing the tremendous performance benefits of fusion propulsion. MTF attempts to combine the favorable attributes of both inertially and magnetically confined fusion to achieve both efficient and low-cost compressional plasma heating and energy confinement. The key advantage of MTF is its less demanding requirements for driver energy and power processing. Additional features include: 1) very low system masses and volumes, 2) high gain and relatively low waste heat, 3) substantial utilization of energy from product neutrons, 4) efficient, low peak-power drivers based on existing pulsed power technology, and 5) very high I(sub sp), specific power and thrust. MTF overcomes many of the problems associated with traditional fusion techniques, thus making it particularly attractive for space applications. I(sub sp) greater than 50,000 seconds and specific powers greater than 20 kilowatts/kilogram appear feasible using relatively near-term pulse power and plasma gun technology.
    Keywords: Plasma Physics
    Type: 2nd International MTF Workshop; Aug 07, 2001 - Aug 09, 2001; Reno, NV; United States
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  • 10
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    The cathode region of a quasi-steady MPD arcjet (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Arc luminosity in cathode region of quasi-steady MPD arc jet, using high speed photography and electric and magnetic field probes
    Keywords: PHYSICS, PLASMA
    Type: AIAA PAPER 70-1094
    Format: text
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