Abstract: A carbon allotrope heating element includes an electrical resistivity between 0.005 ohms per square (?/sq) and 3.0 ?/sq. A heating system includes a component and a carbon allotrope heating element having an electrical resistivity between 0.005 ?/sq and 3.0 ?/sq. A method includes modifying a carbon allotrope heating element to have an electrical resistivity between 0.005 ?/sq and 3.0 ?/sq and applying the carbon allotrope heating element to a component of an aircraft.

Abstract: Disclosed is an attachment between a bus bar and a nano-carbon heater used for de-icing and/or anti-icing in an aircraft or other vehicle. The attachment between the bus bar and the heater is created through a coupling agent, a pre-preg glass fabric, and a conductive adhesive. This attachment allows for electrical connections to be made to the heater via the bus bar, and the attachment is strong enough to withstand stress from thermal cycles.

Abstract: A heating element includes a bottom layer, a web consisting of a carbon nanotube (CNT) yarn wherein the web is affixed to a first side of the bottom layer, and an encapsulating layer positioned on the web and the first side of the bottom layer. A method for making a heating element includes providing a bottom layer, inserting a plurality of pegs into the bottom layer such that a portion of each peg protrudes from the bottom layer, weaving a CNT yarn around the protruding portions of the plurality of pegs to form a CNT web, affixing the CNT web to the bottom layer, and encapsulating the CNT web and the bottom layer to form the heating element.

Abstract: A floor panel assembly includes an insulating layer which protects a sheet heater, first and second structural layers, and a honeycomb layer for support. The floor panel assembly allows for heating of the cabin of an aircraft without mechanical damage to the sheet heater.

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

Abstract: A composite sandwich structure for heating an environment includes a first core layer made from a first cellular material and having a first thickness, and a second core layer made from a second cellular material and having a second thickness less than the first thickness. The structure further includes a heating layer having a thermoelectric heating element and disposed between the first and second core layers. The first core layer is positioned between the heating layer and the environment.

Abstract: An ice protection assembly on an airfoil includes a heater positioned on the leading edge, and one or more ice phobic layers positioned to inhibit runback ice formation on the surface of the airfoil downstream of the heater.

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 heater assembly includes both a carbon allotrope heating element for ice protection and a metallic carrier material for lightning strike damaged protection. The carbon allotrope heating element is formed on the metallic carrier material to create an integrated heating and lighting protection assembly.

Abstract: A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

Abstract: One example of a heating element includes a first carbon nanotube (CNT) layer and a second CNT layer. At least a portion of the first CNT layer overlaps at least a portion of the second CNT layer, and the first CNT layer includes a first perforated region having a plurality of perforations. Another heating element includes a CNT sheet with a first perforated region having a plurality of perforations and a first perforation density and a second perforated region having a plurality of perforations and a second perforation density different from the first perforation density. A method of forming a heating element includes perforating a first CNT layer so that it includes a perforated region and stacking the first CNT layer with a second CNT layer such that at least a portion of the first CNT layer overlaps at least a portion of the second CNT layer.

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 pneumatic deicer includes a base layer, a forming layer, a first chamber, and a first sensor. The base layer has an inlet, a first side, and a second side. The forming layer is connected to the base layer along at least two seams and has inner side and an outer side with the outer side being distant from the base layer. The first chamber is formed between the base layer and the forming layer and configured to be inflated by air passing into the first chamber through the inlet in the base layer. The first sensor is situated within the first chamber.

Abstract: Apparatus and associated methods relate to providing redundant heating elements to a surface of an aircraft skin for the purpose of controlling ice accretion thereon. Each of the redundant heating elements can be used alone or in conjunction with the other(s) of the redundant heating elements. In some embodiments, a second heating element can be used if or when a first heating element fails and/or is insufficient to perform the heating task. In some embodiments, the first and second heating elements can be controlled so as to create a heating profile of the surface of the aircraft skin. A heat controller provides electrical control signals to the first and second heating element. In some embodiments, the heat controller can provide such electrical control signals in response to detected ice accretion, flight conditions, and/or detected atmospheric conditions.

Abstract: Pre-fabric, flexible and thermally stable plastic sheets are loaded with carbon additives such as carbon nanotubes (CNTs), graphene, nano carbon fibers, graphite powders, or other carbon allotropes to adjust the resistivity of the sheets as desired for ice protection. These sheets are both conformable to desired surfaces and prevent the carbon debris migration issues in traditional CNT heaters.

Abstract: A method of making monolithic carbon nanotube heater elements with geometric shape with multiple, complex curvatures is disclosed. The method includes depositing carbon nanotubes on to a forming surface, draining the carbon nanotubes, and drying the carbon nanotubes. Alternatively, the method includes thermoforming carbon nanotube sheets containing thermoplastic binders. The resulting carbon nanotube heater element is a thin, monolithic carbon nanotube heater sheet having a geometric shape with complex curvatures.

Abstract: A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

Abstract: A heating element includes an electrode array having first and second interdigitated electrodes. The first electrode is configured to have a first polarity, and the second electrode is configured to have a second polarity. The electrode array substantially encloses a plurality of regions. The heating element further includes a heating surface including a layer of a carbon allotrope material having a first electrical resistance. The electrode array is in electrical communication with the carbon allotrope material.

Abstract: A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

Abstract: An erosion shield assembly includes an erosion shield, a carbon allotrope heater attached to an inner surface of the erosion shield, and an adhesive layer between the carbon allotrope heater and the erosion shield. The carbon allotrope heater includes at least one layer of a carbon allotrope material.