Abstract: A method for manufacturing a part including steps of (1) casting an ingot, (2) scalping the ingot to yield a scalped ingot, (3) homogenizing the scalped ingot to yield a homogenized ingot, (4) breakdown of the homogenized ingot to yield a slab, (5) rolling the slab to yield a rolled aluminum material, (6) annealing the rolled aluminum material to yield an aluminum starting material, (7) cold working the aluminum starting material to obtain an aluminum cold worked material, and (8) forming the part from the aluminum cold worked material.

Abstract: A method for manufacturing a part including steps of (1) casting an ingot, (2) scalping the ingot to yield a scalped ingot, (3) homogenizing the scalped ingot to yield a homogenized ingot, (4) breakdown of the homogenized ingot to yield a slab, (5) rolling the slab to yield a rolled aluminum material, (6) annealing the rolled aluminum material to yield an aluminum starting material, (7) cold working the aluminum starting material to obtain an aluminum cold worked material, and (8) forming the part from the aluminum cold worked material.

Abstract: A method for manufacturing a part including steps of providing an aluminum starting material, wherein the aluminum starting material is in an anneal temper, cold working the aluminum starting material to obtain an aluminum cold worked material, and forming the part from the aluminum cold worked material.

Abstract: A method for manufacturing a part including steps of providing an aluminum starting material, wherein the aluminum starting material is in an anneal temper, cold working the aluminum starting material to obtain an aluminum cold worked material, and forming the part from the aluminum cold worked material.

Abstract: A selectively reinforced hybrid metal-composite structural element can include a metal element and a composite material. The composite material can be bonded to the metal element by an adhesive layer including a polymer matrix using a radiation curing process, resulting in insubstantial or negligible residual stresses at the bond line between the metal element and the composite element. The structural element also can include a metal closeout cap to provide a barrier from a corrosive atmosphere, and the adhesive layer can encapsulate the composite element to provide a corrosion-resistant barrier between the composite element and the surrounding metal.

Abstract: A monolithic structure for use as a pressure bulkhead for an aircraft includes a first web, a redundant second web spaced from the first web, stiffeners disposed between and connecting the webs to each other, and first and second outer attachment rings respectively provided on the outer peripheries of the first and second webs for attaching the bulkhead to fuselage structure. One of the webs comprises a pressure web for supporting pressure loading, and the other web defines at least one aperture therethrough. The stiffeners are integrally fabricated along with at least one of the webs and associated attachment ring as a one-piece monolithic part.

Abstract: A monolithic structure for use as a pressure bulkhead for an aircraft includes a first web, a redundant second web spaced from the first web, stiffeners disposed between and connecting the webs to each other, and first and second outer attachment rings respectively provided on the outer peripheries of the first and second webs for attaching the bulkhead to fuselage structure. One of the webs comprises a pressure web for supporting pressure loading, and the other web defines at least one aperture therethrough. The stiffeners are integrally fabricated along with at least one of the webs and associated attachment ring as a one-piece monolithic part.

Abstract: A monolithic structure for use as a pressure bulkhead for an aircraft includes a first web, a redundant second web spaced from the first web, stiffeners disposed between and connecting the webs to each other, and first and second outer attachment rings respectively provided on the outer peripheries of the first and second webs for attaching the bulkhead to fuselage structure. One of the webs comprises a pressure web for supporting pressure loading, and the other web defines at least one aperture therethrough. The stiffeners are integrally fabricated along with at least one of the webs and associated attachment ring as a one-piece monolithic part.

Abstract: A method for making gate dielectrics for MOS devices includes first forming a silicon oxynitride layer, and then forming a silicon dioxide layer that underlies the oxynitride layer. The oxynitride layer functions as a membrane for controlled diffusion of oxygen to the oxidation region of the silicon substrate.