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  • 1
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    NPSS Electrical Port Development (2019)
    In:  CASI
    Details
    Publication Date: 2019-05-22
    Description: No abstract available
    Keywords: Computer Programming and Software; Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN65942
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Proposal and Development of a High Voltage Variable Frequency Alternating Current Power System for Hybrid Electric Aircraft (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of ultra-efficient commercial vehicles and the transition to low-carbon emission propulsion are seen as strategic thrust paths within NASA Aeronautics. A critical enabler to these paths comes in the form of hybrid electric propulsion systems. For megawatt-class systems, the best power system topology for these hybrid electric propulsion systems is debatable. Current proposals within NASA and the Aero community suggest using a combination of alternating current (AC) and direct current (DC) for power generation, transmission, and distribution. This paper proposes an alternative to the current thought model through the use of a primarily high voltage AC power system, supported by the Convergent Aeronautics Solutions (CAS) Project. This system relies heavily on the use of doubly-fed induction machines (DFIMs), which provide high power densities, minimal power conversion, and variable speed operation. The paper presents background on the activity along with the system architecture, development status, and preliminary results.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN46211 , Incorporating Strathclyde Fault Management Technology; Aug 22, 2017; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Electrical Power System Sizing Within the Numerical Propulsion System Simulation (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Electrified aircraft propulsion seeks to address ambitious goals in the commercial airline industry, including significant decreases in fuel burn, emissions, noise, and takeoff field length. In order to move these electrified propulsion concepts forward, analysis tools are needed that can model propulsion systems containing both gas turbine and power system components. This work presents the definition of an electric port, a set of electrical power systems tools, and simulation examples for the Numerical Propulsion System Simulation (NPSS) software. NPSS is the industry standard modeling and simulation package for aircraft propulsion systems, and the ability to design, size, integrate, and analyze electric power systems will enable industry efforts towards the development of electrified aircraft propulsion.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN70658 , AIAA Propulsion and Energy Forum and Exposition; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Control Demonstration of Multiple Doubly-Fed Induction Motors for Hybrid Electric Propulsion (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Convergent Aeronautics Solutions (CAS) High Voltage-Hybrid Electric Propulsion (HVHEP) task was formulated to support the move into future hybrid-electric aircraft. The goal of this project is to develop a new AC power architecture to support the needs of higher efficiency and lower emissions. This proposed architecture will adopt the use of the doubly-fed induction machine (DFIM) for propulsor drive motor application.The Convergent Aeronautics Solutions (CAS) High Voltage-Hybrid Electric Propulsion (HVHEP) task was formulated to support the move into future hybrid-electric aircraft. The goal of this project is to develop a new AC power architecture to support the needs of higher efficiency and lower emissions. This proposed architecture will adopt the use of the doubly-fed induction machine (DFIM) for propulsor drive motor application. DFIMs are attractive for several reasons, including but not limited to the ability to self-start, ability to operate sub- and super-synchronously, and requiring only fractionally rated power converters on a per-unit basis depending on the required range of operation. The focus of this paper is based specifically on the presentation and analysis of a novel strategy which allows for independent operation of each of the aforementioned doubly-fed induction motors. This strategy includes synchronization, soft-start, and closed loop speed control of each motor as a means of controlling output thrust; be it concurrently or differentially. The demonstration of this strategy has recently been proven out on a low power test bed using fractional horsepower machines. Simulation and hardware test results are presented in the paper.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN43482 , AIAA/SAE/ASEE Joint Propulsion Conference; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Proposal and Development of a High Voltage Variable Frequency Alternating Current Power System for Hybrid Electric Aircraft (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The development of ultra-efficient commercial vehicles and the transition to low-carbon emission propulsion are seen as thrust paths within NASA Aeronautics. A critical enabler to these paths comes in the form of hybrid-electric propulsion systems. For megawatt-class systems, the best power system topology for these hybrid-electric propulsion systems is debatable. Current proposals within NASA and the Aero community suggest using a combination of AC and DC for power transmission. This paper proposes an alternative to the current thought model through the use of a primarily high voltage AC power generation, transmission, and distribution systems, supported by the Convergent Aeronautics Solutions (CAS) Project. This system relies heavily on the use of dual-fed induction machines, which provide high power densities, minimal power conversion, and variable speed operation. The paper presents background on the project along with the system architecture, development status and preliminary results.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN33090 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 25, 2016 - Jul 27, 2016; Salt Lake City, UT; United States
    Format: application/pdf
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  • 6
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    A Generalized Power System Architecture Sizing and Analysis Framework (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The aeronautics industry has been challenged to increase efficiency, reduce noise and emissions, and decrease dependency on carbon-based fuels. To address these needs, NASA has identified and begun to pursue electrified aircraft as a possible solution. The power system for an electric aircraft can exist in many different forms, however; at the early design stage the engineer(s) must identify whether a hybrid- or turbo- electric solution may be best, whether the power transmission system is to be AC or DC, and to ultimately answer the question: does the electric solution provide a net system benefit compared to the fully mechanical solution? This paper describes a generalized power system architecture sizing and analysis framework to provide a mechanism to answering these questions, along with an example based on the STARC-ABL Architecture.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN57588 , AIAA Propulsion and Energy Forum; Jul 07, 2018 - Jul 13, 2018; Cincinnati/Ohio; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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