Lockheed Martin Corporation

John C Cox

David H Hunter

Emmett Emile Menair

John Devin Carroll

Steven P Lozano

Jacob Adam Fehrman

A tunable mass damper assembly is attachable to a rotor blade. The tunable mass damper assembly comprises a base configured to be attached to the rotor blade and a pendulum mass structure movably attached to the base and configured to move relative to the base in accordance with a rotational speed of the rotor blade about a rotor axis. The pendulum mass structure is configured to reduce vibratory forces of the rotor blade induced by a rotation of the rotor blade about the rotor axis. An entirety of the pendulum mass structure being configured to be contained within and enclosed by the rotor blade.

Tunable mass damper assembly for a rotor blade

An adjustable control link for transferring rotor shaft rotation to a rotating swashplate, the adjustable control link includes an elongate element rotatable with the rotor shaft, the elongate element having a first end. A structure has an opening and a second end. At least one cam component is disposed within the opening and is rotatable relative to the structure about a central axis of the opening. A pin is configured to couple the elongate element to the at least one cam component. The pin is eccentrically rotatable about the central axis to move the first end of the elongate element relative to the second end of the structure.

Eccentrically adjusted rotating scissor pitch control link

A swashplate assembly of a rotary wing aircraft includes a first component, a second component arranged concentrically with the first component, and a bearing disposed between the first component and the second component. The bearing includes a spherical bearing and at least one bearing roller element and is operable to transmit torque between the first component and the second component.

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Jupiter, FL, United States of America

John C Cox