Textron Innovations Inc.

Bell Helicopter Textron Inc.

Bell Textron Inc.

Keith Alan Stanney

George Ryan Decker

James Everett Kooiman

Frank B Stamps

Richard Erler Rauber

Patrick R Tisdale

David Popelka

Andrew G Baines

James Braswell, Jr

Thomas C Campbell

Matthew Carl VanBuskirk

Robert Mark Chris

Mark E Wasikowski

David A Popelka

James L Braswell

Steven Ray Ivans

John R McCullough

Brent Chadwick Ross

Bryan Kenneth Baskin

Paul Branson Sherrill

David Gordon Carlson

Douglas K Wolfe

John James Corrigan

Tom Donovan

Troy Thomas Bushmire

Ron Measom

Michael J Southerland

Tricia Hiros

Tim Ledbetter

Ryan Smith

John J Corrigan, Iii

James Lee Braswell

John J Iii Corrigan

Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

Centerline tiltrotor

A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.

Composite wing structure and methods of manufacture

An airframe assembly for an aircraft includes a first airframe member having first and second skins with a large cell core and a solid insert joined therebetween. The solid insert has a side surface at least a portion of which is adjacent to the large cell core. The first airframe member has a first set of openings extending through the first skin, the solid insert and the second skin. The airframe assembly also includes a second airframe member having a second set of openings operable to be aligned with the first set of openings of the first airframe member. Each of a plurality of fasteners extends through one of the openings of the first set of openings and one of the openings of the second set of openings securably coupling the first airframe member to the second airframe member.

Mechanically Joining airframe members at solid insert

An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.

Adhesively joining airframe members at solid insert

A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.

Tiltrotor aircraft having journal bearing mounted pylon assemblies

A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub () and a plurality of step-over arms () connected to the hub and capable of pivoting relative to the hub about a pivot axis. Each of a plurality of pitch links () connects one of the step-over arms () to a flight control system for pivoting the connected step-over arm () about the pivot axis and relative to the hub in response to inputs from the control system. Each of a plurality of step-over links () connects one of the step-over arms () to one of the blades for rotating the associated blade about the pitch axis in response to pivoting of the associated step-over arm.

Step-over blade-pitch control system

An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

Assembly for providing flexure to blade system

Growing community of inventors

Dallas, TX, United States of America

Keith Alan Stanney