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Impact of electric propulsion technology and mission requirements on the performance of VTOL UAVs

  • One of the engineering challenges in aviation is the design of transitioning vertical take-off and landing (VTOL) aircraft. Thrust-borne flight implies a higher mass fraction of the propulsion system, as well as much increased energy consumption in the take-off and landing phases. This mass increase is typically higher for aircraft with a separate lift propulsion system than for aircraft that use the cruise propulsion system to support a dedicated lift system. However, for a cost–benefit trade study, it is necessary to quantify the impact the VTOL requirement and propulsion configuration has on aircraft mass and size. For this reason, sizing studies are conducted. This paper explores the impact of considering a supplemental electric propulsion system for achieving hovering flight. Key variables in this study, apart from the lift system configuration, are the rotor disk loading and hover flight time, as well as the electrical systems technology level for both batteries and motors. Payload and endurance are typically used as the measures of merit for unmanned aircraft that carry electro-optical sensors, and therefore the analysis focuses on these particular parameters.

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Metadaten
Author:Felix FingerORCiD, Carsten BraunORCiD, Cees Bil
DOI:https://doi.org/10.1007/s13272-018-0352-x
ISSN:1869-5582 print
ISSN:1869-5590 online
Parent Title (English):CEAS Aeronautical Journal
Publisher:Springer
Document Type:Article
Language:English
Year of Completion:2018
Date of the Publication (Server):2018/12/18
Volume:10
Issue:3
Length:827
First Page:843
Link:https://doi.org/10.1007/s13272-018-0352-x
Zugriffsart:weltweit
Institutes:FH Aachen / Fachbereich Luft- und Raumfahrttechnik
collections:Verlag / Springer
Open Access / Hybrid