Abstract: An air management system of a vehicle having a conditioned area includes at least one duct defining a flow path for delivering air to the conditioned area and a sterilization system associated with the at least one duct. The sterilization system including at least one light source operable to emit a germicidal ultraviolet light into the flow path defined by the at least one duct to sterilize the air to be provided to the conditioned area.

Abstract: A method of forming an adhesively bonded structure may comprise applying a primer compound to a first substrate, wherein the primer compound comprises a functionalized nanomaterial dopant, drying the primer compound on the substrate to form a primer layer comprising the functionalized nanomaterial dopant, applying an adhesive compound over the primer layer to form an adhesive layer, wherein the adhesive compound comprises the functionalized nanomaterial dopant, contacting the adhesive layer with a second substrate and curing the adhesive layer to form an adhesively bonded structure, wherein the first substrate is metallic and the second substrate is at least one of metallic or composite.

Abstract: A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.

Abstract: An attachment system for an exhaust component is disclosed. In various embodiments, the attachment system includes a radial attachment flange of the exhaust component; and a radial ring having at least one of a radially outer surface configured for engagement with a radially inner surface of the radial attachment flange or a radially inner surface configured for engagement with a radially outer surface of the radial attachment flange.

Abstract: A component is provided for an aircraft. This aircraft component includes an object and a multi-layer coating. The object includes an object surface. The multi-layer coating includes a barrier layer and a laminar flow layer. The covers at least a portion of the object surface. The barrier layer a fluoropolyether, a silicon rubber and/or a polyurethane. The laminar flow layer covers the barrier layer and forms an exterior surface of the component. The laminar flow layer includes a sol-gel siloxane, a rare-earth oxide and/or a phosphate.

Abstract: A method of corrosion inhibition on a substrate may comprise: applying a sealing solution to an anodized surface of the substrate, wherein the sealing solution may comprise a nanomaterial dopant and a corrosion inhibiting compound, wherein the nanomaterial dopant may comprise at least one of graphene nanoplatelets, carbon nanotubes, and carbon nanofibers, and wherein the corrosion inhibiting compound may comprise at least one of a trivalent chromium compound, a trivalent praseodymium compound, nickel acetate, cobalt acetate, siloxanes, silicates, orthophosphates, molybdates, or a compound comprising at least one of elemental or ionic praseodymium, cerium, cesium, lanthanum, zinc, lithium, magnesium, or yttrium; and drying the sealing solution on the substrate to form a sealing layer comprising the nanomaterial dopant and the corrosion inhibiting compound.

Abstract: An additive for reducing corrosion and increasing hydrophobicity having oxidized graphene nanoplatelets; and a pendant group represented by the following formula: R1, R2, and R3 are selected from a group consisting of alcohols, ethers, halogens, and amines. A is an unsubstituted chain of at least 1 and no more than 4 atoms wherein at least one atom is carbon. m is an integer from 1 to 12, X1 and X2 are selected from a group consisting of hydrogen, halogens, and alkyls of 1 to 5 carbon atoms. X3, X4, and X5 are selected from a group consisting of hydrogen and halogens, and at least one of X3, X4, and X5 is fluorine. At least one of R1, R2, and R3 is covalently bonded to one of the graphene nanoplatelets.

Abstract: A method includes beginning an additively manufactured build by depositing initial layers of the build on a build plate, and additively manufacturing a temperature control channel as part of the build in progress. The method also includes controlling temperature in the temperature control channel while continuing to additively manufacture the build to provide temperature control for the build in progress. The method also includes completing additive manufacture of the build. The method can include removing the temperature control channel from the build after completion of the build.

Abstract: A drain mast is provided that includes a unitary structure having a first housing, a second housing, and a plurality of tubes extending between the first housing and the second housing. The unitary structure is configured to provide a plurality of fluid paths through the drain mast, each fluid path extending through the first housing, one of the plurality of tubes, and the second housing.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, a nozzle extending from the nozzle body, an eductor shroud at least partially surrounding the nozzle, the eductor shroud configured to focus a first flow of ambient air towards a first flow of hot gas exiting the first nozzle.

Abstract: An apparatus for aircraft anti-icing includes a nozzle body, at least one nozzle extending from the nozzle body, and at least one vane disposed in at least one of the nozzle(s), the at least one vane configured to impart rotational movement of a hot gas moving through the nozzle(s).

Abstract: An apparatus for aircraft anti-icing includes a nozzle head including an inner wall and an outer wall, the inner wall defining a through-hole extending through the nozzle, the outer wall circumscribing the inner wall, wherein a plenum is disposed between the inner wall and the outer wall, and a neck extending from the outer wall of the nozzle head, the neck configured to supply a flow of hot gas to the plenum, wherein a maximum width of the inner surface of the neck is less than a maximum width of the through-hole.

Abstract: A method of coating a metal article is disclosed that includes immersing a metal article having an exterior anodized layer in a bath containing a chemically active corrosion inhibitor, and applying a voltage to the article during the immersing, the voltage driving the chemically active corrosion inhibitor from the bath into the exterior anodized layer. An article is also disclosed that has a substrate comprising a metal, and a porous anodized layer formed on an exterior surface of the substrate that is infiltrated with a chemically active corrosion inhibitor, the anodized layer having an inward-facing region and an outward-facing region, the anodized layer having a greater concentration of chemically active corrosion inhibitors in the inward-facing region than in the outward-facing region.

Abstract: A mechanical connection system is provided that includes a ceramic skin panel, at least one bushing, and at least one bolt. The ceramic skin panel includes a first surface, a second surface, and at least one aperture extending between the first surface and the second surface. The aperture has an axial centerline, a chamfered portion contiguous with the first surface, and an axial portion contiguous with the second surface. The chamfered portion includes a tapered surface disposed at a first angle such that a line extending along the tapered surface intersects the axial centerline at a plane of the second surface. The bushing has a housing and a collar. The housing is configured to mate with the chamfered portion of the aperture disposed within the ceramic skin panel. The collar is configured for engagement with the housing.

Abstract: A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket.

Abstract: A component is provided for an aircraft. This aircraft component includes an object and a multi-layer coating. The object includes an object surface. The multi-layer coating includes a barrier layer and a laminar flow layer. The covers at least a portion of the object surface. The barrier layer a fluoropolyether, a silicon rubber and/or a polyurethane. The laminar flow layer covers the barrier layer and forms an exterior surface of the component. The laminar flow layer includes a sol-gel siloxane, a rare-earth oxide and/or a phosphate.

Abstract: Systems and methods for lightning strike materials are disclosed. The material may include a carbon fiber tow. Carbon nanotubes may be grown on carbon fibers within the carbon fiber tow. The carbon nanotubes may cause the carbon fibers to separate, decreasing a carbon tow fiber volume fraction of the tow. The growth of the carbon nanotubes may be controlled to select a tow fiber volume fraction of the tow. The lightning strike material may transmit electricity to decrease damage to the composite structure in case of a lightning strike.

Abstract: A laminar flow coating for aerodynamic surfaces is provided. The laminar flow coating may comprise a base composition, such as an epoxy composition, a fluoropolyurethane composition, or a polyurethane composition. A filler composition may be dispersed within the base composition. The filler composition may comprise at least one of a nanomaterial composition or a microfiller composition. The filler composition may be doped with a hydrophobic surface modifier prior to being dispersed within the base composition.

Abstract: A method of coating a metal article is disclosed that includes immersing a metal article having an exterior anodized layer in a bath containing a chemically active corrosion inhibitor, and applying a voltage to the article during the immersing, the voltage driving the chemically active corrosion inhibitor from the bath into the exterior anodized layer. An article is also disclosed that has a substrate comprising a metal, and a porous anodized layer formed on an exterior surface of the substrate that is infiltrated with a chemically active corrosion inhibitor, the anodized layer having an inward-facing region and an outward-facing region, the anodized layer having a greater concentration of chemically active corrosion inhibitors in the inward-facing region than in the outward-facing region.

Abstract: A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit.