Gulfstream Aerospace Corporation

Aerodynamic Composites, LLC

Charles Aitken

Brenden Autry

John McGuire

Michael McKee

John Mcguire

Michael Mckee

David Charles Hornick

Andrew Foose

Bryan Williams

John Everett Reighley

Kevin Andrew Shea

Muneer Bakhsh

Travis Cope

Susan Daggett

A safety seat for an occupant includes a front shell secured to a bulkhead. The front shell has an outer edge and an inner edge. The inner edge defines an opening. The safety seat includes a seat base having a first side and a second side opposite the first side. The seat base has a first position and a second position. In the first position, the first side is flush with the inner edge and in the second position; the second side supports the occupant.

Integrated safety seat for infants and small children

Apparatuses and methods for making reinforcement structures are provided. In one example, an apparatus for making a reinforcement structure includes a rigid mandrel and a flexible bladder. The flexible bladder at least partially surrounds the rigid mandrel for supporting a reinforcement structure-forming material during fabrication of the reinforcement structure. The flexible bladder is configured to apply a force to the reinforcement structure-forming material in a direction opposite the rigid mandrel in response to a pressure differential between inside and outside of the flexible bladder.

Apparatuses and methods for making reinforcement structures

Methods for fabricating composite tools and composite tools are provided. In an exemplary embodiment, a method for fabricating a composite tool includes providing a master mold and forming a low temperature cured resin laminate overlying the master mold. The low temperature cured resin laminate is heated and compressed to form a cured low temperature cured resin laminate, the low temperature cured resin laminate heated to a first temperature. The cured low temperature cured resin laminate is removed from the master mold and a high temperature cured resin laminate is formed overlying the cured low temperature cured resin laminate. The high temperature cured resin laminate is heated and compressed to form a cured high temperature cured resin laminate. The high temperature cured resin laminate is heated to a second temperature, wherein the second temperature is higher than the first temperature.

Composite tools and methods for fabricating composite tools

Stiffening structures, wing structures and methods for manufacturing stiffening structures are provided. In accordance with an exemplary embodiment, a stiffening structure includes a first longitudinal member, a second longitudinal member, and a first rib that extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall and a joining wall that joins the first wall and second wall. The first wall, the second wall and the joining wall form a space having a trapezoidal shape.

Stiffening structures, wing structures, and methods for manufacturing stiffening structures

Methods for manufacturing a reinforced composite structure for an aircraft and devices used in such methods are provided. A device includes a base, a first support member fixedly attached to the base, and a second support member fixedly attached to the base and aligned longitudinally with the first support member. The first support member and the second support member are spaced a first distance apart. Two pinching wheels are spaced a second distance apart. The two pinching wheels are positioned proximate to ends of the first support member and the second support member. The second distance is less than the first distance. The two pinching wheels are configured to receive a composite material layout between them and to cause two lengths of the composite material layout to contact each other.

Methods for manufacturing an I-stringer of an aircraft and devices for use in such methods

Methods for manufacturing a reinforced composite structure for an aircraft and devices used in such methods are provided. A method includes advancing a composite material layout through a cap-forming device. The advancing results in a preformed cap section, a first length of the layout and a second length of the layout. The layout is removed from the cap-forming device and the preformed cap section of the layout is arranged within a cavity of a flexible mandrel with a foot portion of the first length and a foot portion of the second length remaining outside the cavity of the flexible mandrel. The foot portion of the first length and the foot portion of the second length contact a skin structure. The layout is heated and pressurized using the flexible mandrel to cure the layout and form the reinforced composite structure affixed to the skin structure.

Methods for manufacturing an i-stringer of an aircraft and devices for use in such methods

Embodiments of reinforced composite structures for aircrafts and methods for making such reinforced composite structures are provided herein. A reinforced composite structure for an aircraft comprises a fiber reinforced composite stringer. The fiber reinforced composite stringer comprises a beam body portion and a runout portion that extends from the beam body portion in a first direction. The beam body and runout portions are defined by projection of a variable I-shaped cross-section in the first direction along at least a portion of an entire combined length of the beam body and runout portions. The variable I-shaped cross-section has a cap section, a foot section, and a web section that extends between the cap and foot sections. The variable I-shaped cross-section is configured such that a height of the web section tapers in the first direction along at least a portion of an entire length of the runout portion.

Growing community of inventors

Savannah, GA, United States of America

Charles Aitken