S. Gul, H. Yeo

A family of generic hingeless hub distributed tiltrotor configurations was modeled in RCAS and studied for whirl flutter. Also modeled was a baseline conventional configuration for comparison. A sensitivity study was carried out using the baseline model to provide a fundamental understanding. Wing torsion and rotor flap stiffness significantly impacted the instability speed. Reducing wing beam stiffness stabilized the system due to lower participation of wing torsion motion in this mode. Various distributed tiltrotor configurations were analyzed. Adding a same-size rotor to 40% wing span only slightly decreased the instability speed. On the other hand, utilizing two small rotors with half the disk area greatly stabilized the system. Placing these rotors at the wing tip in a coaxial configuration is also beneficial, but not as much as distributing them over the wing. Hence, eVTOL configurations appear to exhibit better stability characteristics than traditional tiltrotor aircraft; however, analysis for a real aircraft is necessary. Impact of rotor-rotor and rotor-wing aerodynamic interactions was studied using Viscous Vortex Particle Method (VVPM). Predictions show that the effect of rotor wake on the wing may be important if wing beam is the unstable mode.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 18 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-18; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023