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  • 1
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    Operation of high power converters in parallel (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Three different unequal power sharing approaches for parallel operation of converters - droop, master-slave, and proportional adjustment - are discussed. The approaches have been incorporated in the breadboard dc-dc converter units used in the space station power management and distribution dc test bed at the Lewis Research Center, where the system operation has been verified.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: In: IECEC '92; Proceedings of the 27th Intersociety Energy Conversion Engineering Conference, San Diego, CA, Aug. 3-7, 1992. Vol. 6 (A93-25851 09-44); p. 6.49-6.53.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Operation of high power converters in parallel (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High power converters that are used in space power subsystems are limited in power handling capability due to component and thermal limitations. For applications, such as Space Station Freedom, where multi-kilowatts of power must be delivered to user loads, parallel operation of converters becomes an attractive option when considering overall power subsystem topologies. TRW developed three different unequal power sharing approaches for parallel operation of converters. These approaches, known as droop, master-slave, and proportional adjustment, are discussed and test results are presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA-CR-191096 , E-7685 , NAS 1.26:191096
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Versatile digital signal processor for dc to dc converters (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Digital signal processor (DSP) for dc-to-dc converters, processes all incoming signals and transmits correct signal to operate power switch.
    Keywords: ELECTRONIC COMPONENTS AND CIRCUITS
    Type: LEW-13020 , NASA Tech Briefs (ISSN 0145-319X); 4; 2; P. 170
    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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    Development of a standardized control module for dc-to-dc converters (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The electrical performance of a power processor depends on the quality of its control system. Most of the existing control circuits suffer one or more of the following imperfections that tend to restrict their respective utility: (1) inability to perform different modes of duty cycle control; (2) lack of immunity to output filter parameter changes, and (3) lack of capability to provide power component stress limiting on an instantaneous basis. The three lagging aspects of existing control circuits have been used to define the major objectives of the current Standardized Control Module (SCM) Program. Detailed information on the SCM functional block diagram, its universality, and performance features, circuit description, test results, and modeling and analysis efforts are presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA-CR-135072 , TRW-26629.000
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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