Textron Innovations Inc.

Bell Helicopter Textron Inc.

Joseph Daniel Leachman

William Anthony Amante

Timothy Brian Carr

Joshua Allan Edler

Troy S Caudill

Richard Theodore Perryman

Bobby Howard Mosier

Jeffery S Greenwood

William David Dennison

Darrell W Wilkerson

Jeffery W Erwin

Danielle Vann

Jedediah Bryce Goodell

Ernest Edward Senn, Jr

Adrienne Ruth Sullivan

Mark Adam Wiinikka

Thomas Mast

John Robert Wittmaak, Jr

Kevin Knott

Eric Christopher Terry

David Platz

Sarah R Villanueva

Chyau J Tzeng

Edith Richard

Daniel John Burns

Bob Thornton

Brian Mesing

William D Dennison

An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with first and second pylons coupled therebetween. A distributed thrust array is coupled to the airframe including a plurality of propulsion assemblies coupled to the first wing and a plurality of propulsion assemblies coupled to the second wing. A cargo pod is coupled between the first and second pylons. The cargo pod is rotatable between a loading configuration, substantially perpendicular to the wings and a transportation and deployment configuration, substantially parallel to the wings. A flight control system is configured to independently control each of the propulsion assemblies and to autonomously deploy a payload from the cargo pod at a desired location.

Autonomous payload deployment aircraft

In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; one or more puck fasteners in the floor panel, wherein each puck fastener comprises an attachment fitting and a plurality of internal flanges, wherein the plurality of internal flanges within each puck fastener are adjacent; and one or more seating fixtures coupled to the floor panel using the one or more puck fasteners.

Flexible aircraft seat configurations

The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.

Rotorcraft fall restraint protection attach points and mechanism systems

The present invention includes an emergency egress system of a vehicle, including: a rope compartment, wherein the rope compartment is located on or near a vertical plane along a longitudinal axis of the vehicle, within reach of one or more occupant seats; a rope, wherein at least a portion of the rope is stored within the rope compartment and is securely tethered to a portion of a structure of the vehicle; and a rope compartment cover to secure the rope in the rope compartment.

Integrated emergency egress equipment

In an example, a puck configured to be embedded in a structure of a rotorcraft creates a cavity in the structure and includes an attachment post for coupling a component to the structure in which the puck is embedded. A puck cover can be configured to cover the cavity in the structure and the puck cover can include a top cover surface to cover the cavity, a center support, and plurality of extensions, where the plurality of extensions coupled with the attachment post.

Puck cover

A storage system is provided in one example embodiment and may include a storage device that may include a plurality of outer walls; and a liner that covers one or more of the outer walls, wherein the liner comprises a woven material that is puncture-resistant. A storage device is provided in another example embodiment and may include a plurality of outer walls, wherein at least one of the outer walls comprises a woven material that is puncture-resistant. A vehicle is provided in another example embodiment and may include a fuel system that includes a fuel cell. The fuel cell may include a plurality of outer walls, and at least one of: a puncture-resistant liner covers one or more of the outer walls; and one or more of the outer walls comprises a woven material that is puncture resistant.

Puncture-resistant storage systems and devices

An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

Fume tight sock collector/box

One example of an aircraft fuel line assembly clamp member includes a c-shaped outer shell and a plurality of spokes. The c-shaped outer shell is sized to be positioned within an outer tube of an aircraft fuel line assembly. The plurality of spokes is arranged on an inner surface of the outer shell. The plurality of spokes protrudes from the inner surface towards a center of the outer shell to define a shape to receive an inner tube of the aircraft fuel line assembly. The plurality of spokes is also spaced apart on the inner surface.

Adapter for aircraft fluid transmission lines

One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft.

Fluid transfer chamber for aircraft fluid transmission lines

Cockpit center console

Main cockpit control panel

Growing community of inventors

Keller, TX, United States of America

Joseph Daniel Leachman