The purpose of this paper is to propose specific power and efficiency as the key performance parameters for a turboelectric aircraft power system and investigate their impact on the overall aircraft. Key functional requirements are identified that impact the power system design. Breguet range equations for a base aircraft and a turboelectric aircraft are found. The benefits and costs that may result from the turboelectric system are enumerated. A break-even analysis is conducted to find the minimum allowable electric drive specific power and efficiency that can preserve the range, initial weight, operating empty weight, and payload weight of the base aircraft.
Turboelectric Aircraft Drive Key Performance Parameters and Functional Requirements
AIAA Propulsion & Energy 2015 ; 2015 ; Orlando, FL, United States
2015-07-27
Conference paper
No indication
English
Turboelectric Aircraft Drive Key Performance Parameters and Functional Requirements (AIAA 2015-3890)
British Library Conference Proceedings | 2015
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