Abstract: A de-icing assembly for a surface of an aircraft includes: a carcass with a first layer, a second layer, and a carcass centerline and a plurality of seams sewn into the carcass, wherein the plurality of seams join the first and second layers of the carcass together. The assembly includes a plurality of inflation passages formed by the plurality of seams and disposed between the first and second layers of the carcass. The system also includes a manifold fluidly connected to and disposed beneath the carcass, the manifold comprising a width and a manifold centerline oriented approximately perpendicular or parallel to the carcass centerline. The seams are sown by a stitchline formed of carbon nanotube yarn.

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: A conformable tank includes a body with a plurality of walls defining a cavity in the body, and an internal support structure connected to an internal surface of one of the plurality of walls and protruding into the cavity of the body. The plurality of walls are formed of a first 3D woven composite material. The internal support structure is formed of a second composite material.

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: A conductive ink may comprise a high temperature thermoplastic polyurethane (TPU) and a plurality of conductive particles disposed in the high temperature TPU. The plurality of conductive particles may comprise between 60% and 95% of the conductive ink by weight. The high temperature TPU may include a melting point between 120° C. and 200° C. The conductive ink may be used for external heated composite structures, such as rotor blades, fixed wings, faring, engine lip electrothermal ice protection, or the like. The conductive ink may have enhanced mechanical fatigue resistance.

Abstract: An internal heating trace assembly may include a first bus bar, a second bus bar, a plurality of ceramic positive temperature coefficient (PTC) elements, and an insulator. The ceramic PTC elements may be disposed in parallel between the first bus bar and the second bus bar. The insulator may include a heat-shrink tubing. The ceramic PTC element may include a PTC strip or a PTC bead.

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: 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: A method of coating a high-pressure fluid vessel comprises filling a high-pressure fluid vessel with a coating solution, draining the coating solution, and drying a remainder of the coating solution in the high-pressure fluid vessel. The coating solution may include a thermoplastic elastomer that is hard with a low glass transition temperature and a high melting temperature. Drying the remainder of the coating solution may form a food grade coating within the high-pressure fluid vessel.

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 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 tuning an electrical resistance of a laser-induced graphene heater is provided. The method includes forming a base carbon heating element, and determining a target electrical resistance of a laser-induced graphene (LIG) heater to be fabricated from the base carbon heating element. The method further includes determining a targeted LIG pattern that provides the target electrical resistance, and directing laser energy on to the base carbon heating element based on the targeted LIG pattern to form one or more LIG regions. The one or more LIG regions define a LIG pattern to from the LIG heater having the target electrical resistance.

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 method for reducing the resistivity of a carbon nanotube nonwoven sheet includes providing a carbon nanotube nonwoven sheet comprising a plurality of carbon nanotubes and applying pressure to the carbon nanotube nonwoven sheet to reduce air voids between carbon nanotubes within the carbon nanotube nonwoven sheet.

Abstract: A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.

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: A multilayer heating structure for controlling ice accumulation on a surface of an aircraft includes a carbon nano-tube (CNT) heater. The heater includes: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material.

Abstract: A system for controlling ice accumulation on a surface of an aircraft, the system includes a carbon nano-tube (CNT) heater comprising: a CNT layer; a first encapsulation layer disposed on a first side of the CNT layer formed of a first encapsulation layer thermoplastic material; and a second encapsulation layer disposed on a second side of the CNT layer formed of a second encapsulation layer thermoplastic material. The system also includes a fore composite structure that includes a fore composite structure thermoplastic material disposed on the first side of CNT heater, an aft composite structure that includes an aft composite structure thermoplastic material disposed on the first side of CNT heater and a sensor layer disposed between the CNT heater and the one of the fore and aft composite structures.

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: Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.