Abstract: A method and apparatus are present for manufacturing a part. The part is comprised of a metal alloy and is positioned to form a positioned part. An electromagnetic field is generated that heats the positioned part. A surface of the positioned part is exposed to an inert gas, while the electromagnetic field is generated to create an inverse thermal gradient between an exterior of the positioned part and an interior section of the positioned part to form a heat treated part.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A method and apparatus are present for manufacturing a part. The part is comprised of a metal alloy and is positioned to form a positioned part. An electromagnetic field is generated that heats the positioned part. A surface of the positioned part is exposed to an inert gas, while the electromagnetic field is generated to create an inverse thermal gradient between an exterior of the positioned part and an interior section of the positioned part to form a heat treated part.

Abstract: A method and apparatus are present for manufacturing a part. The part is comprised of a metal alloy and is positioned to form a positioned part. An electromagnetic field is generated that heats the positioned part. A surface of the positioned part is exposed to an inert gas, while the electromagnetic field is generated to create an inverse thermal gradient between an exterior of the positioned part and an interior section of the positioned part to form a heat treated part.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A method to join a first structure to a second structure comprises aligning a first hole in the first structure with a second hole in the second structure and inserting a fastener into the first hole and the second hole. The fastener comprises a shape memory alloy which was formed into a first shape having a diameter slightly larger than a diameter of the first hole and the second hole when the shape memory alloy was in an austenite state and reduced to a second shape having a diameter less than the diameter of the first hole and the second hole when the shape memory alloy was in a martensite state. The method further comprises heating the fastener above an austenite start transition temperature.

Abstract: A solid oxide fuel cell (SOFC) interconnect comprises a metal sheet with an air side and a fuel side in accordance with an embodiment of the present invention. The metal sheet comprises a metallic composite having a matrix. The matrix comprises a first metal. The metal sheet also comprises a plurality of discontinuous, elongated, directional reinforcement wires. The reinforcement wires comprise a second metal that is immiscible in the first metal. An oxidation protection layer is disposed on the air side of the metal sheet.

Abstract: In one embodiment a method to join a first structure to a second structure, comprises aligning a first hole in the first structure with a second hole in the second structure and inserting a fastener into the first hole and the second hole. The fastener comprises a shape memory alloy which was formed into a first shape having a diameter slightly larger than a diameter of the first hole and the second hole when the shape memory alloy was in an austenite state and reduced to a second shape having a diameter less than the diameter of the first hole and the second hole when the shape memory alloy was in a martensite state.

Abstract: In one embodiment method to form a composite part from a metallic composite powder, comprises positioning a metallic composite powder preform in a mold cavity formed by a first susceptor and a second susceptor, heating the mold cavity to a first processing temperature, applying a pressure to the mold cavity, and applying a thermal oscillation cycle to the mold cavity, wherein the thermal oscillation cycle oscillates the temperature of the mold cavity between a first temperature in which the metallic composite powder is in a first phase and a second temperature in which the metallic composite powder is in a second phase, different from the first phase.

Abstract: In one embodiment a method to join a first structure to a second structure, comprises aligning a first hole in the first structure with a second hole in the second structure and inserting a fastener into the first hole and the second hole. The fastener comprises a shape memory alloy which was formed into a first shape having a diameter slightly larger than a diameter of the first hole and the second hole when the shape memory alloy was in an austenite state and reduced to a second shape having a diameter less than the diameter of the first hole and the second hole when the shape memory alloy was in a martensite state.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A method and apparatus are present for manufacturing a part. The part is comprised of a metal alloy and is positioned to form a positioned part. An electromagnetic field is generated that heats the positioned part. A surface of the positioned part is exposed to an inert gas, while the electromagnetic field is generated to create an inverse thermal gradient between an exterior of the positioned part and an interior section of the positioned part to form a heat treated part.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A solid oxide fuel cell (SOFC) interconnect comprises a metal sheet with an air side and a fuel side in accordance with an embodiment of the present invention. The metal sheet comprises a metallic composite having a matrix. The matrix comprises a first metal. The metal sheet also comprises a plurality of discontinuous, elongated, directional reinforcement wires. The reinforcement wires comprise a second metal that is immiscible in the first metal. An oxidation protection layer is disposed on the air side of the metal sheet.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: An apparatus and method for forming a composite workpiece are provided. An electromagnetic field generator induces a current in a susceptor, thereby heating the workpiece in a die cavity. An elastomeric bladder in the cavity is inflated and urges the workpiece against a contour surface corresponding to a desired configuration of the workpiece. Coolant fluid can also be circulated through the die cavity to cool the workpiece. Thus, the workpiece can be heated, formed, and cooled quickly and without substantial heating of other components, thereby reducing the time and energy relative to conventional forming methods.

Abstract: An apparatus and method for forming a composite workpiece are provided. An electromagnetic field generator induces a current in a susceptor, thereby heating the workpiece in a die cavity. An elastomeric bladder in the cavity is inflated and urges the workpiece against a contour surface corresponding to a desired configuration of the workpiece. Coolant fluid can also be circulated through the die cavity to cool the workpiece. Thus, the workpiece can be heated, formed, and cooled quickly and without substantial heating of other components, thereby reducing the time and energy relative to conventional forming methods.

Abstract: A die liner for use in a die having a die body wherein the die body is configured to form a workpiece. The die liner is a discrete structure that is configured to be used in conjunction with the die body. The die liner defines a forming surface for forming the workpiece and is configured to have at least one characteristic that is different than a corresponding characteristic of the die body such that the die liner increases the durability of the die.

Abstract: A single or multilayer smart susceptor for temperature control of part fabrication in an induction processing system generally consists of single layer or laminated layers of ferromagnetic material susceptible to heating by induction. The use of the susceptors in fabrication at elevated temperatures causes oxidation damage to the surface. The susceptor may be coated with a nickel aluminide surface coating to minimize oxidation of the susceptor outer surface.