Parametric analysis of battery-electric rotorcraft configurations to fly on Mars

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dc.contributor.authorYouhanna, Vishal
dc.contributor.authorFelicetti, Leonard
dc.contributor.authorIgnatyev, Dmitry
dc.date.accessioned2023-08-05T09:57:25Z
dc.date.available2023-08-05T09:57:25Z
dc.date.issued2023-07-13
dc.description.abstractThe success of NASA’s Ingenuity Helicopter promises that the future exploration of Mars will include aerobots in line with rovers and landers. However, Ingenuity lacks long-range endurance and scientific payload capacity because of its small and elementary design. In the series of optimised Martian drone concepts development, we introduced in this paper - an initial sizing of rotary eVTOL design configurations based on the performed parametric analysis for hover and vertical climb using simplified rotorcraft momentum theory, for a set of more challenging requirements for a Martian aerobot mission and sized to fit into the maximum spacecraft aeroshell limit. A tandem rotor configuration was found to be the most efficient configuration, whereas a conventional single main rotor configuration with small diameters manifested the poorest performance.en_UK
dc.identifier.citationYouhanna V, Felicetti L, Ignatyev D. (2023) Parametric analysis of battery-electric rotorcraft configurations to fly on Mars. In: Aerospace Europe Conference Joint 10th EUCASS - 9th CEAS Conference 2023, 9-13 July 2023, Lausanne, Switzerlanden_UK
dc.identifier.urihttps://www.eucass.eu/conferences-and-publications/conference-papers
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/20046
dc.language.isoenen_UK
dc.publisherCouncil of European Aerospace Societies (CEAS)en_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.titleParametric analysis of battery-electric rotorcraft configurations to fly on Marsen_UK
dc.typeConference paperen_UK

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