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.

Abstract: A deicing assembly includes a pneumatic deicing apparatus configured for attachment to a leading edge of an aircraft surface, the pneumatic deicing assembly having a plurality of inflatable chambers, and a carbon allotrope heater having at least one sheet of a carbon allotrope material.

Abstract: A method of making a carbon nanotube heater includes impregnating a dry carbon nanotube fiber matrix with a conductive resin, the conductive resin is made of an organic resin and a conductive filler material. The carbon nanotube heater is lightweight, strong, and maintains appropriate electrical conductivity and resistance for use as a heater.

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 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 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.

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 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: A method for reducing the resistivity of a thermoplastic film containing carbon nanotubes includes connecting an electric power supply to the thermoplastic film containing carbon nanotubes and passing electric current through the thermoplastic film containing carbon nanotubes to heat the thermoplastic film to an elevated temperature and align carbon nanotubes within the thermoplastic film. The thermoplastic film is solid at room temperature.

Abstract: A method of making a carbon nanotube heater assembly for a large area requiring ice protection includes using a connection material to join first and second carbon nanotube heaters. The assembly includes a carrier material and an encapsulating material surrounding the carbon nanotube heaters and connection material.

Abstract: A method for creating a carbon nanotube heater assembly includes creating a carbon nanotube heater with varying resistances and attaching the carbon nanotube heater to both carrier and encapsulating materials. Creating the carbon nanotube heater with varying resistances is accomplished by applying a carbon nanotube mixture to a substrate, adjusting the thickness or width of the carbon nanotube mixture, and drying the nanotube mixture.

Abstract: Disclosed is the use of a boron nitride nanotube (BNNT) fabric as a skin for protection of nano-carbon heaters used for de-icing aircrafts or other vehicles. This allows the heaters to be resistant to hail, bird, and other mechanical striking damages, and can be applied to parts of aircraft that require acoustic protection.

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 nano alumina fabric protects heaters used for de-icing aircraft or other vehicles. This allows heaters to withstand mechanical foreign object damage (FOD), is environmentally safe, and is a cost-efficient alternative to other protection fabrics.

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 aircraft ice protection system (10) comprises an ice protection device (21), an onboard power source (30), a supply line (31) from the power source (30) to the device (21), a controller (41) which controls the line (31), and an optimizer (50) which conveys operation-optimizing instructions (51) to the controller (41). An ice detector (60) provides an input (70) to the optimizer (50) and this ice-condition input (70) is used to generate the operation-optimizing instructions (51).

Abstract: An electric heater (40) for integration into an acoustic panel (20) having sound-penetrating pores (30) communicating with a sound-canceling medium. The heater (40) includes an electrically conductive layer (53) with resistance-setting apertures (63) filled with sealant (73). Openings (83), which contribute to the sound-penetrating pores (30), extend through the sealant-filled apertures (63). The acoustic panel (20) can be assimilated into an aircraft component, such as a nacelle inlet lip, which requires both noise-reducing and ice-protecting features.

Abstract: An aircraft ice protection system (10) comprises an ice protection device (21), an onboard power source (30), a supply line (31) from the power source (30) to the device (21), a controller (41) which controls the line (31), and an optimizer (50) which conveys operation-optimizing instructions (51) to the controller (41). An ice detector (60) provides an input (70) to the optimizer (50) and this ice-condition input (70) is used to generate the operation-optimizing instructions (51).

Abstract: An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.

Abstract: An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends.