Elastomeric bearing elements for droop stop mechanisms
AssigneeSikorsky Aircraft Corporation
InventorDavid A. Zinni
Life of this patent
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Abstract
An elastomeric bearing element having an outer race, an inner race, and at least two elastomeric segments secured between the inner and outer races is provided. The elastomeric segments are spaced from one another by a corresponding number of expansion segments. The elastomeric segments provide a first spring rate when a first force applied to the outer race places the elastomeric segments in compression and a second spring rate when a second force applied to the outer race places the elastomeric segments in shear. The second spring rate is lower than the first spring rate.
Claims11
A droop stop mechanism, comprising:
- an elastomeric bearing element moveable between a static position and a dynamic position;
- a first support area secured to said elastomeric bearing assembly, said first support area contacting a rotor blade assembly in said static position;
- and
- a second support area secured to said elastomeric bearing assembly, said second support area being positioned for impact by the rotor blade assembly in said dynamic position, said elastomeric bearing element having a first spring rate in said static position and a second spring rate in said dynamic position, said second spring rate being lower than said first spring rate.
A rotor hub comprising:
- a hub body;
- a plurality of rotor blade assemblies depending from said hub body;
- and
- a droop stop mechanism pivotally secured to said hub body by an elastomeric bearing element for movement of said droop stop mechanism and said elastomeric bearing element between a static position and a dynamic position, said elastomeric bearing element having a first spring rate in said static position and a second spring rate in said dynamic position, said second spring rate being lower than said first spring rate, wherein said droop stop mechanism comprises a first support area configured to contact a respective one of said plurality of rotor blade assemblies in said static position and a second support area configured to contact said respective one of said plurality of rotor blade assemblies in said dynamic position.
Dependencies are inferred from the claim text.