Abstract: An ice protection system may include a rotary blade, an electrothermal heater, and a low ice adhesion surface. The low ice adhesion surface may include an adhesion strength below 100 kPa. The rotary blade may be disposed between the electrothermal heater and the low ice adhesion surface. The electrothermal heater may be disposed between the low ice adhesion surface and the rotary blade. The low ice adhesion surface may include a coating or a surface treatment.

Abstract: A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

Abstract: A method for forming a deicer includes forming a body of the deicer. The method further includes forming an outer layer of the deicer through extrusion of an elastomeric material. The method further includes coupling the outer layer of the deicer to the body of the deicer.

Abstract: A method of manufacturing a cured vessel is disclosed herein. The method comprises wrapping a first bladder in a first composite laminate, wrapping a second bladder in a second composite laminate. The method further comprises joining the first composite laminate and the second composite laminate by wrapping them both in a third composite laminate to form an un-cured vessel. The un-cured vessel is cured by heating the uncured vessel and pressurizing the bladder while the uncured vessel is in a vessel mold.

Abstract: A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer.

Abstract: A heated floor panel assembly with an impact layer is made to absorb blunt force and protect a heating element inside the assembly. The assembly further includes a plurality of structural layer made of a reinforced polymer matrix, one or more core layer with a honeycomb or foam structure for absorbing shear stress, and a heating layer containing the heating element. The impact layer is a composite layer with a resin impregnated fiber matrix.

Abstract: A heated floor panel assembly for aircraft includes structural layers made of a fiber matrix and a high temperature thermoplastic resin. The structural layers are within the heated floor panel assembly to protect the other assembly components from damage and absorb stress. The heated floor panel assembly further includes a heating layer with a heating element, an impact layer, and a core layer to take shear stress exerted on the assembly.

Abstract: An aircraft may include a fuselage and a wing extending away from the fuselage to a wing tip. The wing may have a leading edge portion, a suction side portion, and a pressure side portion. A thermoelectric element may be coupled to an inner surface of the wing. A chemical adhesive may be disposed on a thermoelectric inner surface. A structural rib may be adhesively bonded to the thermoelectric element by curing the chemical adhesive. The structural rib may be mechanically fastened to a suction side of the wing and to a pressure side of the wing.

Abstract: An ice protection heater element includes a carbon allotrope heater with micro-perforations across up to about sixty percent of the carbon allotrope heater's surface. The micro-perforations allow uniform heating across the heating element and tailored electrical resistances for ice protection.

Abstract: A method of making a blind hole in a wall of a multi-section tank during manufacture includes inserting a thin, flexible composite spacer ring in a hole in a composite material between mating parts of a soluble tool. The composite spacer ring is cured to the composite material during curing and maintains the hole between sections of the tank once completed.

Abstract: A conformable tank includes a body with a plurality of composite walls formed around a cavity, and an internal support connected to one of the plurality of composite walls and positioned in the cavity. The plurality of composite walls includes a flat side wall disposed opposite a curved side wall. A first section of one of the plurality of composite walls includes an exterior facing, an interior facing, and a core positioned between the exterior facing and the interior facing.

Abstract: A method of making an adhesive for an ice protection assembly includes mixing ferrous nanoparticles into the adhesive. Removal of the adhesive for ice protection assembly inspection or repair includes heating the ferrous nanoparticles in the adhesive to soften the adhesive and allow for easy removal or repositioning of the ice protection assembly.

Abstract: A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

Abstract: An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.

Abstract: Additively manufactured heating elements for tubes are made from a positive temperature coefficient heater ink printed on the tube. A bus bar is likewise printed onto the tube using a conductive ink. The positive temperature coefficient heater ink and bust bar conductive ink are encapsulated with a closing adhesive.

Abstract: A heating element includes a first bus bar disposed to receive current from a power source, and a second bus bar non-adjacent to the first bus bar. The heating element further includes a polymer ink section extending between the first and second bus bars, and the section includes a plurality of PTC polymer inks each different from one another. The second bus bar is electrically connected to the first bus bar via the polymer ink section.

Abstract: A heated floor panel assembly for aircraft includes an impact layer made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer can further include woven metallic fibers. The assembly also includes a stack of structural layers, a heating layer, and a core layer for absorbing shear stress.

Abstract: A heated floor panel assembly with an impact layer is made to absorb blunt force and protect a heating element inside the assembly. The assembly further includes a plurality of structural layer made of a reinforced polymer matrix, one or more core layer with a honeycomb or foam structure for absorbing shear stress, and a heating layer containing the heating element. The impact layer is a composite layer with a resin impregnated fiber matrix.

Abstract: A heated floor panel assembly for aircraft includes structural layers made of a fiber matrix and a high temperature thermoplastic resin. The structural layers are within the heated floor panel assembly to protect the other assembly components from damage and absorb stress. The heated floor panel assembly further includes a heating layer with a heating element, an impact layer, and a core layer to take shear stress exerted on the assembly.

Abstract: A heated floor panel assembly contains a positive temperature coefficient heater secured in the assembly through a number of welded joints through a thermoplastic dielectric layer. The positive temperature coefficient heater is on a thermoplastic substrate, which is bonded to the thermoplastic dielectric layer. The assembly further includes an impact layer, a core layer, and structural layers.