Abstract: A method of forming an aircraft component includes providing an aluminum alloy. The method further includes mixing a shape memory alloy (SMA) with the aluminum alloy to form a combination of the SMA and the aluminum alloy. The method further includes forming the aircraft component with the combination of the SMA and the aluminum alloy.

Abstract: An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

Abstract: A metal lattice for a carbon dioxide scrubber includes a metal lattice body defining a plurality of intersecting ligaments, wherein nodes are formed at intersections of the plurality of intersecting ligaments, wherein a node density of the metal lattice body varies.

Abstract: Systems for and methods of manufacturing a ceramic matrix composite include introducing a gaseous precursor into an inlet portion of a reaction furnace having a chamber comprising the inlet portion and an outlet portion that is downstream of the inlet portion, and delivering a mitigation agent, such as water vapor or ammonia, into an exhaust conduit in fluid communication with and downstream of the outlet portion of the reaction chamber so as to control chemical reactions occurring with the exhaust chamber. Introducing the gaseous precursor densifies a porous preform, and introducing the mitigation agent shifts the reaction equilibrium to disfavor the formation of harmful and/or pyrophoric byproduct deposits within the exhaust conduit.

Abstract: A hybrid torque bar for a brake assembly may comprise a base portion, a pin extending from a first end of the base portion, and a rail extending between the first end of the base portion and a second end of the base portion opposite the first end. The base portion may be formed using a first manufacturing process. At least one of the pin or the rail may be formed using a second manufacturing process. The second manufacturing process may comprise an additive manufacturing technique.

Abstract: A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.

Abstract: An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

Abstract: An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

Abstract: A method of forming an aircraft component includes providing an aluminum alloy. The method further includes mixing a shape memory alloy (SMA) with the aluminum alloy to form a combination of the SMA and the aluminum alloy. The method further includes forming the aircraft component with the combination of the SMA and the aluminum alloy.

Abstract: Systems for and methods of manufacturing a ceramic matrix composite include introducing a gaseous precursor into an inlet portion of a reaction furnace having a chamber comprising the inlet portion and an outlet portion that is downstream of the inlet portion, and delivering a mitigation agent, such as water vapor or ammonia, into an exhaust conduit in fluid communication with and downstream of the outlet portion of the reaction chamber so as to control chemical reactions occurring with the exhaust chamber. Introducing the gaseous precursor densifies a porous preform, and introducing the mitigation agent shifts the reaction equilibrium to disfavor the formation of harmful and/or pyrophoric byproduct deposits within the exhaust conduit.

Abstract: The present disclosure provides a heat shield. The heat shield may comprise a first layer comprising a first material, a second layer radially outward of the first layer comprising a second material, and a third layer radially outward of the second layer comprising a third material, wherein the first layer is coupled to the second layer by at least one post and at least one support extending from a radially outer surface of the first layer.

Abstract: A method of manufacturing a ceramic matrix composite component may include introducing a gaseous precursor into an inlet portion of a chamber that houses a porous preform and introducing a gaseous mitigation agent into an outlet portion of the chamber that is downstream of the inlet portion of the chamber. The gaseous precursor may include methyltrichlorosilane (MTS) and the gaseous mitigation agent may include hydrogen gas. The introduction of the gaseous precursor may result in densification of the porous preform(s) and the introduction of the gaseous mitigation agent may shift the reaction equilibrium to disfavor the formation of harmful and/or pyrophoric byproduct deposits, which can accumulate in an exhaust conduit 340 of the system.

Abstract: Systems for and methods of manufacturing a ceramic matrix composite include introducing a gaseous precursor into an inlet portion of a reaction furnace having a chamber comprising the inlet portion and an outlet portion that is downstream of the inlet portion, and delivering a mitigation agent, such as water vapor or ammonia, into an exhaust conduit in fluid communication with and downstream of the outlet portion of the reaction chamber so as to control chemical reactions occurring with the exhaust chamber. Introducing the gaseous precursor densities a porous preform, and introducing the mitigation agent shifts the reaction equilibrium to disfavor the formation of harmful and/or pyrophoric byproduct deposits within the exhaust conduit.

Abstract: A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.

Abstract: A metal lattice for a carbon dioxide scrubber includes a metal lattice body defining a plurality of intersecting ligaments, wherein nodes are formed at intersections of the plurality of intersecting ligaments, wherein a node density of the metal lattice body varies.

Abstract: A hybrid torque bar for a brake assembly may comprise a base portion, a pin extending from a first end of the base portion, and a rail extending between the first end of the base portion and a second end of the base portion opposite the first end. The base portion may be formed using a first manufacturing process. At least one of the pin or the rail may be formed using a second manufacturing process. The second manufacturing process may comprise an additive manufacturing technique.

Abstract: A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.

Abstract: A metal lattice for a carbon dioxide scrubber may comprise a metal lattice body defining a plurality of intersecting ligaments, wherein nodes are formed at said intersections. In various embodiments, the metal lattice may be manufactured using an additive manufacturing process. A node density of the metal lattice may vary. A ligament thickness of the metal lattice may vary. The metal lattice may comprise liner defining a channel extending through the metal lattice.

Abstract: A hybrid torque bar for a brake assembly may comprise a base portion, a pin extending from a first end of the base portion, and a rail extending between the first end of the base portion and a second end of the base portion opposite the first end. The base portion may be formed using a first manufacturing process. At least one of the pin or the rail may formed using a second manufacturing process. The second manufacturing process may comprise an additive manufacturing technique.

Abstract: A method of forming an aircraft component includes providing an aluminum alloy. The method further includes mixing a shape memory alloy (SMA) with the aluminum alloy to form a combination of the SMA and the aluminum alloy. The method further includes forming the aircraft component with the combination of the SMA and the aluminum alloy.