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A Generalized Power System Architecture Sizing and Analysis FrameworkThe 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.
Document ID
20180005332
Document Type
Conference Paper
Authors
Sadey, David J. (NASA Glenn Research Center Cleveland, OH, United States)
Csank, Jeffrey T. (NASA Glenn Research Center Cleveland, OH, United States)
Hanlon, Patrick A. (NASA Glenn Research Center Cleveland, OH, United States)
Jansen, Ralph H. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 17, 2018
Publication Date
July 7, 2018
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
GRC-E-DAA-TN57588
Meeting Information
AIAA Propulsion and Energy Forum(Cincinnati/Ohio)
Funding Number(s)
WBS: WBS 664817.02.03.02.03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Hybrid-Electric
Turbo-Electric
STARC-ABL Architecture

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