Dokument-ID Dokumenttyp Verfasser/Autoren Herausgeber Haupttitel Abstract Auflage Verlagsort Verlag Erscheinungsjahr Seitenzahl Schriftenreihe Titel Schriftenreihe Bandzahl ISBN Quelle der Hochschulschrift Konferenzname Bemerkung Quelle:Titel Quelle:Jahrgang Quelle:Heftnummer Quelle:Erste Seite Quelle:Letzte Seite URN DOI Zugriffsart Link Abteilungen OPUS4-9251 Konferenzveröffentlichung Quitter, Julius, quitter@fh-aachen.de; Marino, Matthew, ; Bauschat, J.-Michael, bauschat@fh-aachen.de Highly Non-Planar Aircraft Configurations: Estimation of Flight Mechanical Derivatives Using Low-Order Methods 2019 10 Seiten Deutscher Luft- und Raumfahrtkongress 2019, DLRK 2019. Darmstadt, Germany weltweit https://www.researchgate.net/publication/336313155 Fachbereich Luft- und Raumfahrttechnik OPUS4-10981 Wissenschaftlicher Artikel Hammer, Thorben, ; Quitter, Julius, quitter@fh-aachen.de; Mayntz, Joscha, mayntz@fh-aachen.de; Bauschat, J.-Michael, bauschat@fh-aachen.de; Dahmann, Peter, dahmann@fh-aachen.de; Götten, Falk, goetten@fh-aachen.de; Hille, S., ; Stumpf, E., Free fall drag estimation of small-scale multirotor unmanned aircraft systems using computational fluid dynamics and wind tunnel experiments New European Union (EU) regulations for UAS operations require an operational risk analysis, which includes an estimation of the potential danger of the UAS crashing. A key parameter for the potential ground risk is the kinetic impact energy of the UAS. The kinetic energy depends on the impact velocity of the UAS and, therefore, on the aerodynamic drag and the weight during free fall. Hence, estimating the impact energy of a UAS requires an accurate drag estimation of the UAS in that state. The paper at hand presents the aerodynamic drag estimation of small-scale multirotor UAS. Multirotor UAS of various sizes and configurations were analysed with a fully unsteady Reynolds-averaged Navier-Stokes approach. These simulations included different velocities and various fuselage pitch angles of the UAS. The results were compared against force measurements performed in a subsonic wind tunnel and provided good consistency. Furthermore, the influence of the UAS`s fuselage pitch angle as well as the influence of fixed and free spinning propellers on the aerodynamic drag was analysed. Free spinning propellers may increase the drag by up to 110%, depending on the fuselage pitch angle. Increasing the fuselage pitch angle of the UAS lowers the drag by 40% up to 85%, depending on the UAS. The data presented in this paper allow for increased accuracy of ground risk assessments. Wien Springer 2023 14 Seiten CEAS Aeronautical Journal Corresponding author: Thorben Hammer 10.1007/s13272-023-00702-w weltweit https://doi.org/10.1007/s13272-023-00702-w Fachbereich Luft- und Raumfahrttechnik