A rotor blade (200) for a rotary wing aircraft includes a leading edge (204) and a trailing edge (206) defining a chordwise direction. The leading edge defines a forward end of the rotor blade and the trailing edge defines an aft end of the rotor blade. The rotor blade has a center of gravity (224) and an aerodynamic center (226) along the chordwise direction. The center of gravity is aft of the aerodynamic center.
METHOD OF STABILIZING ARTICULATED ROTOR BLADE
VERFAHREN ZUR STABILISIERUNG EINES GELENKIGEN ROTORBLATTS
PROCÉDÉ DE STABILISATION D'UNE PALE DE ROTOR ARTICULÉE
06.03.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Articulated rotor systems with blade-to-blade damping
Europäisches Patentamt | 2020
|ARTICULATED ROTOR SYSTEMS WITH BLADE-TO-BLADE DAMPING
Europäisches Patentamt | 2020
|