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  • 1
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    Space Power Management and Distribution Status and Trends (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: An overview of space power management and distribution (PMAD) is provided which encompasses historical and current technology trends. The PMAD components discussed include power source control, energy storage control, and load power processing electronic equipment. The status of distribution equipment comprised of rotary joints and power switchgear is evaluated based on power level trends in the public, military, and commercial sectors. Component level technology thrusts, as driven by perceived system level trends, are compared to technology status of piece-parts such as power semiconductors, capacitors, and magnetics to determine critical barriers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 205-218
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development of a multikilowatt ion thruster power processor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A feasibility study was made of the application of silicon-controlled, rectifier series, resonant inverter, power conditioning technology to electric propulsion power processing operating from a 200 to 400 Vdc solar array bus. A power system block diagram was generated to meet the electrical requirements of a 20 CM hollow cathode, mercury bombardment, ion engine. The SCR series resonant inverter was developed as a primary means of power switching and conversion, and the analog signal-to-discrete-time-interval converter control system was applied to achieve good regulation. A complete breadboard was designed, fabricated, and tested with a resistive load bank, and critical power processor areas relating to efficiency, weight, and part count were identified.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120928
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Electrical Prototype Power Processor for the 30-cm Mercury electric propulsion engine (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An Electrical Prototpye Power Processor has been designed to the latest electrical and performance requirements for a flight-type 30-cm ion engine and includes all the necessary power, command, telemetry and control interfaces for a typical electric propulsion subsystem. The power processor was configured into seven separate mechanical modules that would allow subassembly fabrication, test and integration into a complete power processor unit assembly. The conceptual mechanical packaging of the electrical prototype power processor unit demonstrated the relative location of power, high voltage and control electronic components to minimize electrical interactions and to provide adequate thermal control in a vacuum environment. Thermal control was accomplished with a heat pipe simulator attached to the base of the modules.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-684 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Extended performance electric propulsion power processor design study. Volume 2: Technical summary (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Electric propulsion power processor technology has processed during the past decade to the point that it is considered ready for application. Several power processor design concepts were evaluated and compared. Emphasis was placed on a 30 cm ion thruster power processor with a beam power rating supply of 2.2KW to 10KW for the main propulsion power stage. Extension in power processor performance were defined and were designed in sufficient detail to determine efficiency, component weight, part count, reliability and thermal control. A detail design was performed on a microprocessor as the thyristor power processor controller. A reliability analysis was performed to evaluate the effect of the control electronics redesign. Preliminary electrical design, mechanical design and thermal analysis were performed on a 6KW power transformer for the beam supply. Bi-Mod mechanical, structural and thermal control configurations were evaluated for the power processor and preliminary estimates of mechanical weight were determined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-135358 , TRW-31526.000-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Extended performance electric propulsion power processor design study. Volume 1: Executive summary (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several power processor design concepts were evaluated and compared. Emphasis was placed on a 30cm ion thruster power processor with a beam supply rating of 2.2kW to 10kW. Extensions in power processor performance were defined and were designed in sufficient detail to determine efficiency, component weight, part count, reliability and thermal control. Preliminary electrical design, mechanical design, and thermal analysis were performed on a 6kW power transformer for the beam supply. Bi-Mod mechanical, structural, and thermal control configurations were evaluated for the power processor, and preliminary estimates of mechanical weight were determined. A program development plan was formulated that outlines the work breakdown structure for the development, qualification and fabrication of the power processor flight hardware.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-135357 , TRW-31526.000-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Electric prototype power processor for a 30cm ion thruster (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An electrical prototype power processor unit was designed, fabricated and tested with a 30 cm mercury ion engine for primary space propulsion. The power processor unit used the thyristor series resonant inverter as the basic power stage for the high power beam and discharge supplies. A transistorized series resonant inverter processed the remaining power for the low power outputs. The power processor included a digital interface unit to process all input commands and internal telemetry signals so that electric propulsion systems could be operated with a central computer system. The electrical prototype unit included design improvement in the power components such as thyristors, transistors, filters and resonant capacitors, and power transformers and inductors in order to reduce component weight, to minimize losses, and to control the component temperature rise. A design analysis for the electrical prototype is also presented on the component weight, losses, part count and reliability estimate. The electrical prototype was tested in a thermal vacuum environment. Integration tests were performed with a 30 cm ion engine and demonstrated operational compatibility. Electromagnetic interference data was also recorded on the design to provide information for spacecraft integration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-135287 , TRW-28014-6001-TU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Power processor for a 30cm ion thruster (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A thermal vacuum power processor for the NASA Lewis 30cm Mercury Ion Engine was designed, fabricated and tested to determine compliance with electrical specifications. The power processor breadboard used the silicon controlled rectifier (SCR) series resonant inverter as the basic power stage to process all the power to an ion engine. The power processor includes a digital interface unit to process all input commands and internal telemetry signals so that operation is compatible with a central computer system. The breadboard was tested in a thermal vacuum environment. Integration tests were performed with the ion engine and demonstrate operational compatibility and reliable operation without any component failures. Electromagnetic interference data were also recorded on the design to provide information on the interaction with total spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-134785 , TRW-20384-6002-RU-01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    High voltage series resonant inverter ion engine screen supply (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A high-voltage, high-power LC series resonant inverter using SCRs has been developed for an Ion Engine Power Processor. The inverter operates within 200-400Vdc with a maximum output power of 2.5kW. The inverter control logic, the screen supply electrical and mechanical characteristics, the efficiency and losses in power components, regulation on the dual feedback principle, the SCR waveforms and the component weight are analyzed. Efficiency of 90.5% and weight density of 4.1kg/kW are obtained.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Power Electronics Specialists Conference; Jun 10, 1974 - Jun 12, 1974; Murray Hill, NJ
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thyristor power processor for the 30 cm mercury electric propulsion engine (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-433 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Power processor for a 20CM ion thruster (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A power processor breadboard for the JPL 20CM Ion Engine was designed, fabricated, and tested to determine compliance with the electrical specification. The power processor breadboard used the silicon-controlled rectifier (SCR) series resonant inverter as the basic power stage to process all the power to the ion engine. The breadboard power processor was integrated with the JPL 20CM ion engine and complete testing was performed. The integration tests were performed without any silicon-controlled rectifier failure. This demonstrated the ruggedness of the series resonant inverter in protecting the switching elements during arcing in the ion engine. A method of fault clearing the ion engine and returning back to normal operation without elaborate sequencing and timing control logic was evolved. In this method, the main vaporizer was turned off and the discharge current limit was reduced when an overload existed on the screen/accelerator supply. After the high voltage returned to normal, both the main vaporizer and the discharge were returned to normal.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-121160 , TRW-20384-6002-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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