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  • 1
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    Electrical/electronics working group summary (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The electrical/electronics, technology area was considered. It was found that there are no foreseeable circuit or component problems to hinder the implementation of the flywheel energy storage concept. The definition of the major component or technology developments required to permit a technology ready date of 1987 was addressed. Recommendations: motor/generators, suspension electronics, power transfer, power conditioning and distribution, and modeling. An introduction to the area of system engineering is also included.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Langley Research Center An Assessment of Integrated Flywheel System Technol.; p 29-38
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    ASDTIC: A feedback control innovation (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ASDTIC (Analog Signal to Discrete Time Interval Converter) control subsystem provides precise output control of high performance aerospace power supplies. The key to ASDTIC operation is that it stably controls output by sensing output energy change as well as output magnitude. The ASDTIC control subsystem and control module were developed to improve power supply performance during static and dynamic input voltage and output load variations, to reduce output voltage or current regulation due to component variations or aging, to maintain a stable feedback control with variations in the loop gain or loop time constants, and to standardize the feedback control subsystem for power conditioning equipment.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TM-X-68153 , E-7184
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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    The application of the analog signal to discrete time interval converter to the signal conditioner power supplies (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Analog Signal to Discrete Time Interval Converter microminiaturized module was utilized to control the signal conditioner power supplies. The multi-loop control provides outstanding static and dynamic performance characteristics, exceeding those generally associated with single-loop regulators. Eight converter boards, each containing three independent dc to dc converter, were built, tested, and delivered.
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-CR-120906
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Design, development, and fabrication of a electronic analog microminiaturized electronic analog signal to discrete time interval converter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The microminiaturization of an electronic analog signal to discrete time interval converter is presented. Discrete components and integrated circuits comprising the converter were assembled on a thin-film ceramic substrate containing nichrome resistors with gold interconnections. The finished assembly is enclosed in a flat package measuring 3.30 by 4.57 centimeters. The module can be used whenever conversion of analog to digital signals is required, in particular for the purpose of regulation by means of pulse modulation. In conjunction with a precision voltage reference, the module was applied to control the duty cycle of a switching regulator within a temperature range of -55 C to +125 C, and an input voltage range of 10V to 35V. The output-voltage variation was less than + or - 300 parts per million, i.e., less than + or - 3mV for a 10V output.
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-CR-120905
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Development of a uninterrupted power system: ac and dc to dc converter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This program covered the design, fabrication and testing of an advanced development model uninterrupted power system. The input and output requirements imposed on the power processor were specified such that the unit is electrically interchangeable with existing power systems used by the Federal Aviation Administration in installations which have a history of failure due to electrical transient conditions. Input power is from either of two single-phase ac power sources or batteries with electronic selection and transfer between power sources. Battery reconditioning is automatic when either ac source is present. The output power is rated at 84OW; the nominal output is 24V at 35A. Within the 84OW limit, the regulated output voltage is adjustable from 22V to 30Vdc. Protection against continuous overloading or short circuit is provided. The unit is packaged in a standard 19-inch rack mount configuration with 7-inch panel height. Controls are on the front panel with power input and output through connectors on the rear surface. Cooling is by free convection from fin areas located on the side and rear panels. The packaged unit weighs 52.8 lbs., which can be reduced significantly if a three-phase ac power source is used.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-134497
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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
  • 8
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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
  • 9
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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
  • 10
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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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