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Turboelectric and Hybrid Electric Aircraft Drive Key Performance ParametersNASA has been investigating electrified aircraft propulsion as a means of furthering its goals of reducing fuel burn, emissions, and noise. However, the electric drive components required introduce weight and efficiency penalties at odds with these goals. The purpose of this paper is to propose electric drive specific power, electric drive efficiency, and electric propulsion fraction as the key performance parameters for fully turboelectric, partially turboelectric, and parallel hybrid electric aircraft power systems. The impact of these parameters on overall aircraft performance are investigated. Range equations for each aircraft type are described. The benefits and costs that may result from the electrified propulsion systems are enumerated. A breakeven analysis is conducted to find the minimum allowable electric drive specific power and efficiency, for a given electrical propulsion fraction and battery specific energy, that can preserve the range, payload weight, input energy, and ratio of operating empty weight to initial weight of the conventional aircraft.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Duffy, Kirsten P.
(Toledo Univ. Toledo, OH, United States)
Jansen, Ralph H.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
November 1, 2018
Publication Date
July 13, 2018
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: AIAA/IEEE Electric Aircraft Technologies Symposium
Location: Cincinnati, OH
Country: United States
Start Date: July 9, 2018
End Date: July 11, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 081876.
Distribution Limits
Public Use Permitted.
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