Helicopter rotor and blade connection
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
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May 20, 1980
Grant Date -
N/A
app pub date -
Sep 7, 1978
filing date -
Sep 7, 1977
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
This invention relates to helicopter rotors in which the rotor blades are supported by flexure members and resilient means to permit flap and lead/lag movements. Hitherto such support means have been subjected to centrifugal forces thus complicating their design and requiring compromises such that optimum properties in flap and lead/lag planes have been unattainable. In this invention, each blade is attached by an individual spindle 19 supported in an elastomeric bearing 21 secured in a hollow rotor hub 12. Arms 26, flexible in a flapping plane, extend from the rotor hub 12 and a bearing 46 at the outer end of each spindle is attached to its associated arms through resilient means 30 to permit lead/lag movement of the spindle 19 relative the arms 26. In operation, centrifugal loads are transmitted to the hub 12 so that the arms 26 and resilient means 30 can be designed to provide optimum properties in the flap and lead/lag planes. Furthermore, bending of the spindles 19 due to such blade movements significantly reduces corresponding deflections of the elastomeric bearing 21.
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