Textron Innovations Inc.

Bell Helicopter Textron Inc.

Carl A May

James Donn Hethcock, Jr

John R McCullough

Paul K Oldroyd

John Richard Mccullough

David Gordon Carlson

Suvankar Mishra

Richard Theodore Perryman

Rodney H Jones

Kenneth E Nunn, Jr

William D Dennison, Ii

Ronald K Cox

Ross D Cosby

James Donn Hethcock

James D Hethcock

James Everett Kooiman

William Anthony Amante

Joshua Andrew Emrich

Ramesh Thiagarajan

Robert Mark Chris

Michael Stephen Deslatte

Jesse J Wrabel

Theodore W Ingram, Iii

Randall Willnow

William D Dennison

Kenneth E Nunn

James E Kooiman

In one embodiment, an apparatus may comprise an attachment device configured to be embedded in a structure, wherein the attachment device comprises: a body comprising a first flange and a second flange, wherein the body is configured such that the first flange and the second flange are coupled together internally within the body when the attachment device is embedded in the structure; an attachment fitting for coupling a component to the structure in which the attachment device is embedded.

Puck attachment mechanism for flexible aircraft configuration

In one embodiment, an apparatus may comprise: a floor panel for a rotorcraft; and a plurality of passenger seats coupled to the floor panel, wherein: the plurality of passenger seats is arranged into a plurality of seating rows; and the plurality of passenger seats comprises one or more foldover seats arranged to facilitate access to one or more exits of the rotorcraft.

Flexible foldover seat configurations for emergency egress of aircraft

An aircraft includes a composite structure, comprising an outer skin formed from a composite material and having a first thickness, an inner skin formed from a composite material and having a second thickness, the second thickness being greater than the first thickness, and a core structure positioned between the inner and outer skins to increase bending stiffness of the composite structure. During use a structural load carried by the inner skin exceeds a structural load carried by the outer skin.

Shielded structure for aircraft

In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.

Composite rib assembly

A method of making a core-stiffened structure includes the steps of providing a honeycomb core having an adhesive disposed on first and second surfaces thereof, providing a first skin and a second skin, and assembling the first skin, the second skin, and the honeycomb core to form the core-stiffened structure. The method further includes the steps of curing the core-stiffened structure and inhibiting at least one of the first skin and the second skin from protruding into at least one cell of the honeycomb core during the step of curing the core-stiffened structure.

Method of making core-stiffened structure

An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.

Apparatus for attaching a member to a core-stiffened structure and a combination thereof

A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.

Method of repairing, splicing, joining, machining, and stabilizing honeycomb core using pourable structural foam and a structure incorporating the same

A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

Multi-directional load joint system

A method of repairing a core stiffened structure can include removing a damaged portion of the core stiffened structure; creating a cutout in a portion of a repair core member; fitting the repair core member onto an existing core member such that the cutout mates with a portion of the existing core member; bonding the repair core member to the existing core member; and placing a skin patch over the repair core member.

Method of repairing a core stiffened structure

An apparatus for joining a first member and a second member includes fasteners for joining the first member and the second member, a shear transfer layer for transferring shear loads between the first member and the second member separate from the fasteners for joining the first member and the second member. An assembly includes a first member, a second member, and fasteners for joining the first member and the second member. The assembly further includes a shear transfer layer for transferring shear loads between the first member and the second member separate from the fasteners for joining the first member and the second.

Apparatus for joining members and assembly thereof

According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Growing community of inventors

Mansfield, TX, United States of America

Carl A May