Abstract
Developing more electric, hybrid, and full electric aircraft became one of the most important research directions today. The available and emerging technologies, mainly due to the low specific energy of batteries, have not yet allowed the development of full electric aircraft with performance similar to existing conventional ones. This paper deals with the adaptation of conceptual design methodologies to electric/hybrid aircraft development. It introduces the analysis of energy fractions of flight mission stages into the conceptual design, the definition of extra constraints for optimisation, and the implementation of the hybridisation factor and power split. The applicability of the adapted method is demonstrated through the development case studies of a full electric small aircraft and a cargo hybrid UAV.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
