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  • 1
    Electronic Resource
    Electronic Resource
    Low voltage drop plasma switch for inverter and modulator applications (1993)
    [S.l.] : American Institute of Physics (AIP)
    Review of Scientific Instruments 64 (1993), S. 2312-2319 
    Details
    ISSN: 1089-7623
    Source: AIP Digital Archive
    Topics: Physics , Electrical Engineering, Measurement and Control Technology
    Notes: A low forward voltage drop plasma switch has been developed for high-efficiency inverter and modulator applications. The switch, called the HOLLOTRON, is based on a grid-controlled, thermionic hollow-cathode discharge. A low forward voltage drop (10–20 V) is achieved by operating the hollow-cathode discharge in a static gas pressure of xenon. The dense plasma generated in the Ba-oxide dispenser hollow cathode is spread over a relatively large control grid area by a diverging magnetic field superimposed on the discharge. Interruption of the discharge current at high current densities ((approximately-greater-than)4 A/cm2) over the grid area is achieved by biasing the control grid sufficiently negative with respect to the plasma. The HOLLOTRON switch has demonstrated voltage stand-off of up to 20 kV, switching times of ≤0.3 μs, and pulse repetition frequencies of 20 kHz at 50% duty.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1063/1.1143927
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Low voltage drop plasma switch for inverter and modulator applications (1993)
    American Institute of Physics
    Details
    Publication Date: 1993-08-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 3
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    INSTABILITY OF PLASMA SHEATH ROTATION AND ASSOCIATED MICROWAVE GENERATION IN A PENNING DISCHARGE (1963)
    American Institute of Physics
    Details
    Publication Date: 1963-10-01
    Print ISSN: 0003-6951
    Electronic ISSN: 1077-3118
    Topics: Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 4
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    Development of advanced inert-gas ion thrusters (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Inert gas ion thruster technology offers the greatest potential for providing high specific impulse, low thrust, electric propulsion on large, Earth orbital spacecraft. The development of a thruster module that can be operated on xenon or argon propellant to produce 0.2 N of thrust at a specific impulse of 3000 sec with xenon propellant and at 6000 sec with argon propellant is described. The 30 cm diameter, laboratory model thruster is considered to be scalable to produce 0.5 N thrust. A high efficiency ring cusp discharge chamber was used to achieve an overall thruster efficiency of 77% with xenon propellant and 66% with argon propellant. Measurements were performed to identify ion production and loss processes and to define critical design criteria (at least on a preliminary basis).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168206 , NAS 1.26:168206
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Retrofit and verification test of a 30-cm ion thruster (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Twenty modifications were found to be necessary and were approved by design review. These design modifications were incorporated in the thruster documents (drawings and procedures) to define the J series thruster. Sixteen of the design revisions were implemented in a 900 series thruster by retrofit modification. A standardized set of test procedures was formulated, and the retrofit J series thruster design was verified by test. Some difficulty was observed with the modification to the ion optics assembly, but the overall effect of the design modification satisfies the design objectives. The thruster was tested over a wide range of operating parameters to demonstrate its capabilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165233
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Electric propulsion - characteristics, applications, and status (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparative review of the principles of ion thruster and chemical rocket operations is presented. The 30cm mercury ion thruster development and the specifications imposed on it by the Solar Electric propulsion System program are discussed. The 30cm thruster operating range, efficiency, wear out lifetime, and interface requirements are described.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-81630 , E-640
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Characteristics of the LeRC/Hughes J-series 30-cm engineering model thruster (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: As a consequence of endurance and structural tests performed on 900-series engineering model thrusters (EMT), several modifications in design were found to be necessary for achieving performance goals. The modified thruster is known as the J-series EMT. The most important of the design modifications affect the accelerator grid, gimbal mount, cathode polepiece, and wiring harness. The paper discusses the design modifications incorporated, the condition(s) they corrected, and the characteristics of the modified thruster.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    30-cm mercury ion thruster technology (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The LeRC/Hughes 30-cm mercury ion thruster has been developed to a state of maturity such that is has become meaningful to formulate models for describing the performance characteristics of the major subassemblies. The thruster hollow cathode and the ion optics subassemblies have been investigated with this objective and conceptual, semiquantitative models have been formulated for relating lifetime and performance capabilities to design and operating parameters. This paper summarizes the investigations, discusses the factors considered for inclusion in the models, and describes the status of the models.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Extended performance solar electric propulsion thrust system study. Volume 1: Executive summary (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several thrust system design concepts were evaluated and compared using the specifications of the most advanced 30 cm engineering model thruster as the technology base. The extensions in thruster performance required for the Halley's comet mission were defined and alternative thrust system concepts were designed. Confirmation testing and analysis of thruster and power-processing components were performed, and the feasibility of satisfying extended performance requirements was verified. A baseline design was selected from the alternatives considered, and the design analysis and documentation were refined. A program development plan was formulated that outlines the work structure considered necessary for developing, qualifying, and fabricating the flight hardware for the baseline thrust system within the time frame of a project to rendezvous with Halley's comet. An assessment was made of the costs and risks associated with a baseline thrust system as provided to the mission project under this plan. Critical procurements and interfaces were identified and defined. Results are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-135281-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A 30-cm-diameter, low specific impulse, hollow cathode mercury thruster (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Low specific impulse hollow cathode mercury thrustor for deep space electric propulsion, using SERT 2 configuration
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 70-1099
    Format: text
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    NASA TECHNICAL REPORTS
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