Lord Corporation

Brian McGill

Peter M Jones

Peter J Jones

Keith R Ptak

David M Catanzarite

Dampers (), assemblies, and methods are provided for lead-lag damping for an articulated rotor and includes a lead-lag damper () having a first end connector () configured to be coupled to a rotor hub (H), a second end connector () configured to be coupled to one of a plurality of rotor blades (B), and a body portion () coupled to the first end connector () and to the second end connector (). The body portion () includes one or more elastomeric material layers () arranged in a lengthwise direction between the first end connector () and the second end connector (), with each of the elastomeric material layers () having a substantially chevron-shaped profile in a crosswise direction.

Lead-lag dampers and assemblies for an articulated rotor and methods for operation

Rotary dampers and systems for use and installation within a rotary winged aircraft, and related methods, are provided herein. In some aspects, a rotary damper includes a housing having a rotor assembly positioned inside the housing. The rotary damper may further include at least one resilient member disposed adjacent to an outer portion of the housing. The at least one resilient member is externally visible from outside of the rotary damper. In some aspects, the resilient member includes a torsional spring of the rotary damper. In certain aspects, the resilient member is disk shaped and slidable within a portion of the rotary damper. In some aspects, at least one primary liquid orifice is provided in a portion of the at least one rotor member. In some aspects, at least one pressure equalization port is disposed within a portion of the rotor assembly.

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Erie, PA, United States of America

Brian McGill