Textron Innovations Inc.

Bell Helicopter Textron Inc.

Bell Textron Inc.

Mark Loring Isaac

Brent Chadwick Ross

James Everett Kooiman

Frank B Stamps

John R McCullough

David A Elliott

Robert W Roe

Brian J Cox

Steven Ray Ivans

John Richard Mccullough

David Russell Bockmiller

John Elton Brunken, Jr

Andrew Paul Haldeman

Michael Scott Seifert

Jared Mark Paulson

Albert Gerard Brand

Michael E Rinehart

Aaron Alexander Acee

Michael Christopher Burnett

Russell Lee Mueller

Glenn Alan Shimek

Andrew Thomas Carter

Alan Carl Ewing

Lynn Francis Eschete

Matthew Carl VanBuskirk

Eric Ricardo Gonzalez

Steven Allen Robedeau, Jr

Charles David Hogue

Kent E Donaldson

Jason Paul Winter

Derek Ray Eddins

Clegg Benjamin Brian Smith

Frank Bradley Stamps

Jr John Elton Brunken

Matthew Carl Van Buskirk

David A Elliot

A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.

Wing design for removable battery

An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.

Landing gear with caster and variable shimmy damping

A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.

Adjustable landing gear assembly for use in aircraft

A retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.

Contouring retractable landing gear systems

Aircraft landing gear

Aircraft

A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.

Dual rotor propulsion systems for tiltrotor aircraft

A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.

Extended range quad tiltrotor aircraft

According to one embodiment, an aircraft features a fuselage, a wing member, and two fuselage beam. The fuselage features a first plurality of structural supports, a second plurality of structural supports, a first opening disposed between the first plurality of structural supports, and a second opening disposed between the second plurality of structural supports. The wing member is disposed above the first opening and above the second opening. The wing features a plurality of ribs including a first rib and a second rib. The first fuselage beam couples the first rib of the wing member to the fuselage and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam couples the second rib of the wing member to the fuselage and features an elongated body portion extending across the second plurality of structural supports.

Fuselage to wing attachment

According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.

Tail spar spring

A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed position on a wing member, and a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member. The engine is disposed adjacent a fuselage of the tilt rotor aircraft, and the prop-rotor pylon is configured to selectively rotate between a vertical position and a horizontal position. The prop-rotor pylon is coupled to a plurality of rotor blades.

Tiltrotor aircraft with inboard wing mounted fixed engine arrangement

The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

Tilt rotor aircraft with fixed engine arrangement

A rotor system for tilt rotor aircraft comprises an engine disposed at a first fixed location on a wing member; a prop-rotor pylon mechanically coupled to the engine along a drive path, and a gearbox disposed in the drive path. The prop-rotor pylon is rotatably mounted on a spindle, and the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle between a vertical position and a horizontal position. The gearbox comprises a rotational axis aligned with the rotational axis of the spindle.

Spindle mounted tiltrotor pylon with fixed engine arrangement

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Fort Worth, TX, United States of America

Mark Loring Isaac