Lockheed Martin Corporation

Sikorsky Aircraft Corporation

Eric Dunn

Sven Roy Lofstrom

Keith M Schenone

Frank M Caputo

Joseph Nathan Hull

A system includes a mandrel having an exterior surface configured to receive composite material, a first end, and a second end opposite the first end, an end support coupled to the first end of the mandrel such that the mandrel is rotatable about an axis of rotation, and an intermediate support configured to support the mandrel between the first end and the second end such that at least a portion of the exterior surface is exposed while the mandrel is supported by the intermediate support, a vertical distance between the intermediate support and the axis of rotation defining a support distance, and the intermediate support being adjustable between a first position having a first support distance and a second position having a second support distance greater than the first support distance.

Mandrel support system and method

According to an aspect, a method of assembling a mandrel includes assembling a plurality of members via interlocking features arranged at opposing edges of each member of the plurality of members to form a compartment, the assembled members having a collective outer surface that conforms to an inner surface of the spar. A support member is inserted into the compartment formed radially inward from the assembled members, the support member making contact with a portion of each member of the plurality of members.

Collapsible spar mandrel

A pitch beam movable by a pitch change shaft to adjust a pitch of at least one rotor blade of a rotor system via a pitch linkage includes a first surface having a generally planar configuration, a smooth second surface disposed opposite the first surface, and a sidewall extending between the first surface and the second surface. A pitch linkage connection point is disposed at the sidewall to which the pitch linkage is attachable. An interior is defined between the first surface and the second surface and an opening extends through the first and second surface at a rotational axis of the rotor system to which the pitch change shaft is attached. Movement of the pitch change shaft moves the pitch beam and adjusts the pitch of the at least one rotor blade via the pitch linkage attached at the pitch linkage connection point.

Lightweight low drag rotor pitch beam

An aircraft rotor blade assembly includes a rotor blade rotatable about an axis of rotation and a weighted assembly mounted to the aircraft rotor blade. The weighted assembly includes an actuator which moves a mass to adjust a moment of the rotor blade assembly when the rotor blade is rotated about the axis of rotation.

Blade moment adjustment system

A bushing assembly for receiving a fastener includes a first bushing portion and a second bushing portion arranged coaxially with the first bushing portion. The second bushing portion defines at least part of an opening for receiving the fastener. The second bushing portion is rotatable relative to the first bushing portion about an axis of rotation to adjust a position of the opening about a first axis and a second axis independently relative to the first bushing portion and the second bushing portion. The first axis is coplanar with and perpendicular to the second axis.

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Trumbull, CT, United States of America

Eric Dunn