Vibration control systems, devices, and methods are provided for a rotary wing aircraft having a rotor including a plurality of blades (20) each attached to a hub (10) at its root end and capable of pitching with respect to the hub (10). The systems, devices, and methods include a blade pitch adjuster (100) that is passively adjustable in response to aerodynamic loading on the plurality of blades (20) to adjust a pitch of one of the plurality of blades (20) with respect to the hub (10) based on a frequency of the aerodynamic loading. The blade pitch adjusters (100) can be configured to exhibit relatively high stiffness at the rotor rotating frequency and tailored dynamics at frequencies higher than the rotor rotating frequency such that hub loads at one or more higher harmonics are reduced.
DYNAMIC PITCH ADJUSTMENT DEVICES, SYSTEMS, AND METHODS
2016-08-18
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |