Co-design of an integrated direct-drive electric motor and ducted propeller for aircraft propulsion

Thanatheepan Balachandran, John David Reband, Jianqiao Xiao, Samith Sirimmana, Ranbir Dhilon, Kiruba S. Haran

Research output: Chapter in Book/Report/Conference proceedingConference contribution


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.

Original languageEnglish (US)
Title of host publicationAIAA Propulsion and Energy 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Number of pages11
ISBN (Print)9781624106026
StatePublished - 2020
EventAIAA Propulsion and Energy 2020 Forum - Virtual, Online
Duration: Aug 24 2020Aug 28 2020

Publication series

NameAIAA Propulsion and Energy 2020 Forum


ConferenceAIAA Propulsion and Energy 2020 Forum
CityVirtual, Online

ASJC Scopus subject areas

  • General Energy
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering


Dive into the research topics of 'Co-design of an integrated direct-drive electric motor and ducted propeller for aircraft propulsion'. Together they form a unique fingerprint.

Cite this