An aircraft rotor assembly (217) has a central hub (221) and a plurality of rotor blades (215) coupled to the hub (221) for rotation with the hub (221) about an axis (242), each blade (215) having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade (215) is formed by a flexure (219) coupling the associated blade (215) to the hub (221). Each pivot is a radial distance from the axis (242) and allows for in-plane lead-lag motion of the associated blade (215) relative to the hub (221), each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure (219) produces a biasing force for biasing the associated blade (215) toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade (215).
ROTOR ASSEMBLY WITH HIGH LOCK-NUMBER BLADES
ROTORANORDNUNG MIT BLAETTERN MIT HOHER LOCK-ZAHL
ENSEMBLE ROTOR À PALES À NOMBRE DE LOCK ÉLEVÉ
2017-09-13
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |