Textron Innovations Inc.

Bell Helicopter Textron Inc.

Jonathan Alexander Freeman

James Everett Kooiman

James Donn Hethcock, Jr

David Gordon Carlson

Douglas K Wolfe

Paul K Oldroyd

Joseph Richard Carpenter, Jr

Daniel C Burns

Charles David Hogue

David M Carlson

Robert G Pierce

James D Hethcock

An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

Beaded composite structural web

A method of fabricating a panel includes laying up a first laminate on a tooling surface, laying a first layer of thermoplastic on an inner surface of the first laminate, laying a large cell carbon core on the first layer of thermoplastic, laying a second layer of thermoplastic across the large cell carbon core, laying a second laminate on the second layer of thermoplastic, creating a sealed core pocket by bonding the edges of the first and second layers of the thermoplastic surrounding a perimeter of the core, increasing pressure within the core pocket, increasing pressure on the outer surface of the second laminate, heating the panel to a desired curing temperature, and maintaining the increased pressures and temperature for a desired curing duration.

Large cell carbon core sandwich panel and method of manufacturing same

A method of carving a contour surface on a composite core can include positioning a first edge of the composite core against a first tooled member; locating a first magnet within an outer cell member along the first edge of the composite core so that the first edge of the composite core is magnetically drawn to the first tooled member; locating a second magnet along a second edge of the composite core such that the second edge of the composite core is magnetically drawn to a second tooled member; and carving a first contour of the composite core.

Method of securing composite core during a manufacturing process

A method of assembling a core stiffened structure that includes bonding a composite core to a substructure by utilizing magnetic force to create pressure between a flat surface of the composite core the substructure, and bonding a face sheet onto a surface network of the composite core.

Method of manufacturing net edge core and a method of bonding net edge core to a substructure

A method of splicing together a first composite core and a second composite core can include: positioning a first flange of the first composite core adjacent to a second flange of the second composite core, applying an adhesive, and locating a first magnet and a second magnet to provide a pressure on the adhesive.

Growing community of inventors

North Richland Hills, TX, United States of America

Jonathan Alexander Freeman