The Boeing Company

Geo2 Technologies, Inc.

The Boeing Corporation

Ge02 Technologies, Inc.

The Boeiog Company

Robert A DiChiara

Gordon S Alward

Vann Heng

Richard W Burns

MaryAnn S Muench

William Ryan Harrigan

Kevin R Lenihan

Francis J Samalot Rivera

Leanne L Lehman

Creed E Blevins

Peter A Hogenson

Conley Siddoway Thatcher

Edward A Zadorozny

Robert E French

Elizabeth Chu

Dave Zorger

Jerry Denham

David Zorger

Bilal Zuberi

Jonathan David Embler

Thomas R Pinney

David Thomas Misciagna

Keith Allan Etling

Michael J Best

Michael D Nevinsky

Holly M O'Brien

Franklin K Myers

Brian L Muench

David S Blum

Marc Daniel Spiccia Karasek

Joseph Orso

Glenn B Godinho

Frank W Zok

Susan Saragosa

Carlos G Levi

A thermal transfer blanket includes a flexible container comprising a thermally insulating material. A thermal energy storage media is disposed within the flexible container.

Thermal transfer blanket system

In a first example, a radome includes a shell including a ceramic matrix composite, the shell forming a first hole at a forward end of the shell and a second hole at an aft end of the shell. The radome also includes a fluid impervious coating on the shell. In a second example, a vehicle includes a main body, the radome, and an attachment assembly that couples the radome to the main body. In a third example, a method includes forming a shell comprising a ceramic matrix composite using a wet layup process, applying a fluid impervious coating onto the shell, and curing the shell and the fluid impervious coating.

Radome with ceramic matrix composite

The present disclosure is directed to a method of repairing an aircraft. The method comprises charging a thermal transfer blanket comprising a thermal energy storage media with thermal energy from a heat source. The method further comprises positioning a thermally curable patch on an exterior surface of an aircraft. The thermally curable patch comprises an uncured polymer having a first temperature. The thermal transfer blanket is applied to the thermally curable patch. Thermal energy is transferred between the thermal transfer blanket and the thermally curable patch to increase the first temperature of the uncured polymer to a cure temperature for a sufficient amount of time to cure the polymer.

Method of using a thermal transfer blanket system

A system and method for mitigating thermal loading between engine exhaust structures having different coefficients of thermal expansion. The engine exhaust structure comprises a metallic duct portion, a ceramic duct portion, and a double bipod fitting joining the metallic duct portion to the ceramic duct portion. The double bipod fitting is capable of flexing and taking up the thermal expansion differences between the joined metallic and ceramic ducts across the full temperature spectrum that an engine exhaust structure will experience in service.

Double bipod fitting to mitigate thermal loading of engine exhaust structures

A method of dissipating heat from a surface of a first thermoplastic composite (TPC) being inductively welded with a second thermoplastic composite (TPC) includes flexing a heat sink during placement to conform to the surface of the first TPC, cooling the heat sink, applying inductive heat to a weld interface area between the first TPC and the second TPC, and drawing off heat via the heat sink from the surface of the first TPC.

Induction welding using a heat sink and/or cooling

A heat sink for use in induction welding includes a number of tiles, wherein the tiles are electrically non-conductive and have a thermal diffusivity of greater than about 25 mm2/sec. A joint flexibly joins the tiles together.

A method of induction welding a first thermoplastic composite (TPC) to a second thermoplastic composite (TPC) includes inductively heating a weld interface area between the first TPC and the second TPC, and cooling a surface of the first TPC opposite the weld interface area while inductively heating the weld interface area.

A heat sink for use in induction welding includes a number of tiles, where the tiles are electrically non-conductive and thermally conductive, a joint flexibly joining the tiles together, and a fluid path formed through the heat sink for communicating a coolant therethrough.

A heat sink for use in induction welding includes a flexible backing and a number of tiles disposed on the flexible backing in a single layer, wherein the tiles are electrically non-conductive and thermally conductive.

A method of induction welding a first thermoplastic composite (TPC) to a second thermoplastic composite (TPC) using an induction coil includes forming a weld interface area between the first TPC and the second TPC, cooling the first TPC with a cooling apparatus before heating by the induction coil, and inductively heating the weld interface area with the induction coil after cooling the first TPC.

A high temperature fastener including a bolt and a nut, where the bolt and the nut are constructed of an aluminum oxide ceramic material reinforced with silicon-carbide crystal whiskers or silicon nitride.

Method of making whisker reinforced high fracture toughness ceramic threaded fasteners

A method of induction welding a first carbon fiber thermoplastic composite (TPC) to a second carbon fiber thermoplastic composite (TPC) using an induction coil includes aligning the first TPC with the second TPC to form a weld interface area, flexing a heat sink onto a surface of the first TPC between the weld interface area and the induction coil, and inductively heating the weld interface area with the induction coil.

Provided are stacks including CMC structures and capping layers deposited on surfaces of these CMC structures. Also provided are methods for hermetically sealing the surfaces of the CMC structures with the capping layers. These stacks may be used to construct walls of radomes that enclose antennas and other equipment of aerospace vehicles. The capping layers may form smooth external surfaces of the radomes and may hermetically seal the underlying CMC structures. The dielectric properties of these stacks may be configured to minimize interference with operations of the antennas and other equipment deposited within the radome.

Stacks having hermetic capping layers over porous ceramic matrix composite structures

Provided are methods for hermetically sealing the surfaces of the CMC structures with the capping layers, comprising depositing a slurry onto the surface of a CMC structure and treating the CMC structure with the deposited slurry in an oxygen containing environment, thereby forming a stack. These stacks may be used to construct walls of radomes that enclose antennas and other equipment of aerospace vehicles. The capping layers may form smooth external surfaces of the radomes and may hermetically seal the underlying CMC structures. The dielectric properties of these stacks may be configured to minimize interference with operations of the antennas and other equipment deposited within the radome.

A fastener system includes a fastener including a fastener first end and a longitudinally opposed fastener second end, and an anchor configured to receive and capture the fastener upon rotation of the fastener in a first direction, wherein the anchor is further configured to engage the fastener first end upon complete rotation of the fastener in the first direction, and the anchor is further configured to prohibit further rotation in a second direction, opposite the first direction, upon engagement with the fastener first end.

Growing community of inventors

Carlsbad, CA, United States of America

Robert A DiChiara