TY - GEN
T1 - Co-design of an integrated direct-drive electric motor and ducted propeller for aircraft propulsion
AU - Balachandran, Thanatheepan
AU - Reband, John David
AU - Xiao, Jianqiao
AU - Sirimmana, Samith
AU - Dhilon, Ranbir
AU - Haran, Kiruba S.
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - This paper discusses the co-design of an electric aircraft propulsion system for minimum weight and maximum power-to-thrust efficiency. The system under consideration for preliminary exploration of the methodology consists of a fully superconducting synchronous motor and a ducted, fixed-pitch propeller. In order to ensure a viable propulsor, a minimum required thrust bound is imposed on the system design. Both analytical methods and finite-element analysis (FEA) are used to size the motor, and a blade-element momentum (BEM) model is implemented for predicting performance of the ducted propeller. A genetic algorithm optimization scheme is applied on a hydrogen-powered electric aircraft propulsion system proposed for the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA) project. Sensitivity of the combined system efficiency to motor weight is evaluated.
AB - This paper discusses the co-design of an electric aircraft propulsion system for minimum weight and maximum power-to-thrust efficiency. The system under consideration for preliminary exploration of the methodology consists of a fully superconducting synchronous motor and a ducted, fixed-pitch propeller. In order to ensure a viable propulsor, a minimum required thrust bound is imposed on the system design. Both analytical methods and finite-element analysis (FEA) are used to size the motor, and a blade-element momentum (BEM) model is implemented for predicting performance of the ducted propeller. A genetic algorithm optimization scheme is applied on a hydrogen-powered electric aircraft propulsion system proposed for the Center for High-Efficiency Electrical Technologies for Aircraft (CHEETA) project. Sensitivity of the combined system efficiency to motor weight is evaluated.
UR - http://www.scopus.com/inward/record.url?scp=85091297961&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85091297961&partnerID=8YFLogxK
U2 - 10.2514/6.2020-3560
DO - 10.2514/6.2020-3560
M3 - Conference contribution
AN - SCOPUS:85091297961
SN - 9781624106026
T3 - AIAA Propulsion and Energy 2020 Forum
SP - 1
EP - 11
BT - AIAA Propulsion and Energy 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy 2020 Forum
Y2 - 24 August 2020 through 28 August 2020
ER -