The Boeing Company

Flodesign Sonics, Inc.

Sgg Patents LLC

Thomas Joseph Kennedy

William Thomas Kline

Jeffrey D Kendall

Bart Lipkens

David A Fucci

Jason Dionne

Ronald P Laliberty

Joseph Warren

Dane Mealey

Dan Dresskell Day

Geoffrey Allen Butler

Mark Ronald McLaughlin

Erik Lund

Jason Barnes

Lyle Ray Deobald

Luis A Perla

Ben Ross-Johnsrud

Charles Yuanxin Hu

David Bruce Smith

Michael Robert Rush

Nihar Ashokkumar Desai

Robert G Meyer

John D Harrison

Colin Lee Farr

Joseph E Absalonson

Shane Frank Cuda

Peter J VanVoast

Joshua Amory Ross

Ken Schomburg

Charles J Nelson

Thang D Phung

Curtis M Groth

Richard A Ransom

Justin L Holland

Joseph F Warren

Brian Mccarthy

Walter Presz

Mark Ronald Mclaughlin

A stiffened panel comprises a composite panel, and a stiffener including a base flange on the composite panel. The base flange is tapered towards the panel. The stiffened panel further comprises a composite overwrap layer on only the composite panel and a tapered surface of the base flange.

Stiffened composite panels

A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

Aircraft skin attachment system

A heated tool assembly for forming a structural member may include a heated tool and a pressure bladder for mounting the structural member. The tool may have an inner surface, a liner in thermal contact with the inner surface of the tool, and a heating system for heating the tool. The heating system may include a heater for heating a heated medium, a blower for blowing the heated medium, and a plurality of nozzles for directing the heated medium over the tool liner.

Heated tool assembly for forming a structural member

A bow wave in a composite laminate generated during part consolidation is reduced by transmitting atmospheric pressure loads to a region of the part having low compaction pressure due to bridging of a vacuum bag at an edge of the part.

Device for compressing a composite radius

Method and device for compressing a composite radius

An apparatus for forming a structural member includes a tool platform and a pressure platform that may be movable relative to one another between an open position and a closed position. The apparatus may include a tool against which the member may be pressed. The tool may be supported by the tool platform and may have an inner surface. The apparatus may include a pressure bladder configured to be pressurized for applying pressure to the member. The pressure bladder may be supported by the pressure platform for pressing the member against the tool. Also included may be a heating system for heating the tool and a tool liner in thermal contact with the inner surface for distributing heat thereto.

Method for joining composite structural members using thermal spreader

Apparatus for curing a composite structural member

A method of assembling a composite structure is disclosed. An illustrative embodiment of the method includes receiving and positioning at least two composite structure subassemblies on a structure assembly table by operation of at least one first device and at least one second device and compacting the at least two composite structure subassemblies into a composite structure by operation of a third device.

Method of assembling composite structure

Growing community of inventors

Bonney Lake, WA, United States of America

Thomas Joseph Kennedy