Abstract: A humidity protection shield assembly for a carbon nanotube (CNT) fabric composite heater assembly. The humidity protection shield assembly includes a first portion and a second portion. The CNT assembly is disposed between the first portion and the second portion. The first portion includes at least one of one or more first di-electric layers or one or more first thermoplastic/thermoplastic composite di-electric layers; at least one of a first carbon fiber layer or a first composite carbon fiber layer; and at least one of a first metal humidity layer or a first metalized film humidity layer. The second portion includes at least one of one or more second di-electric layers or one or more second thermoplastic/thermoplastic composite di-electric layers; at least one of a second carbon fiber layer or a second composite carbon fiber layer; and at least one of a second metal humidity layer or a second metalized film humidity layer.

Abstract: A low clearance fluid coupling is provided. The low clearance fluid coupling includes a sleeve/fitting body; a tube, a ferrule, and an elastomeric O-ring seal. An end of the tube is configured to be inserted within an end of the sleeve/fitting body. The ferrule is configured to surround an outer circumference of the tube and is further configured to interface with the sleeve/fitting body. The elastomeric O-ring seal configured to prevent or reduce liquid from passing through to the ferrule.

Abstract: A potted cavity fitting. The potted cavity fitting includes a fitting, a first cavity configured within the fitting, and a second cavity configured within the fitting. The fitting is configured to receive an end of a tube and a portion from the end of the tube. The first cavity is configured to retain a first mechanism the prevent or reduce liquid from passing through. The second cavity is configured to retain a second mechanism at least one of coupled to or formed within the tube.

Abstract: A low clearance fluid coupling is provided. The low clearance fluid coupling includes a sleeve/fitting body; a tube, a ferrule, and an elastomeric O-ring seal. An end of the tube is configured to be inserted within an end of the sleeve/fitting body. The ferrule is configured to surround an outer circumference of the tube and is further configured to interface with the sleeve/fitting body. The elastomeric O-ring seal configured to prevent or reduce liquid from passing through to the ferrule.

Abstract: A hybrid deicing system is disclosed herein. The hybrid deicing system includes a first deicing system coupled to a high critical zone of a control surface, the first deicing system providing thermal energy to the high critical zone of the control surface to remove ice from the control surface, a second deicing system coupled to a low critical zone of the control surface, the second deicing system configured to vibrate the control surface to remove ice from the control surface, and a controller configured to control the first deicing system and the second deicing system.

Abstract: Aircraft ice protection systems and methods include an aircraft component having an internal layer and an external layer, a piezoelectric actuator element embedded within the aircraft component between material of the internal layer and the external layer, and a control system operably connected to the piezoelectric actuator element and configured to drive actuation of the piezoelectric actuator element to at least one of remove ice formed on the aircraft component and prevent the formation of ice on the aircraft component.

Abstract: A sustainable hybrid piezoelectric matrix ice protection system is provided. The system includes at least one energy harvester and anti-icing device and an energy storage device. Responsive to electrical power generated by the at least one energy harvester and anti-icing device being greater than a first threshold, the at least one energy harvester and anti-icing device stores the electrical power in the energy storage device. Responsive to the electrical power generated by the at least one energy harvester and anti-icing device being less than the first threshold, the at least one energy harvester and anti-icing device generates continuous, low-frequency vibrations for anti-icing.

Abstract: A hybrid deicing system is disclosed herein. The hybrid deicing system includes a first deicing system coupled to a high critical zone of a control surface, the first deicing system providing thermal energy to the high critical zone of the control surface to remove ice from the control surface, a second deicing system coupled to a low critical zone of the control surface, the second deicing system configured to vibrate the control surface to remove ice from the control surface, and a controller configured to control the first deicing system and the second deicing system.

Abstract: A piezoelectric deicing system is disclosed herein. The piezoelectric deicing system includes a flexible piezoelectric patch array including a plurality of piezoelectric devices, the plurality of piezoelectric devices configured to vibrate in response to a voltage applied at a frequency, an protective material surrounding the flexible piezoelectric patch array, wherein the protective material and the flexible piezoelectric patch array are configured to conform to a surface, and a controller operatively coupled to each of the plurality of piezoelectric devices, wherein the controller is configured to operate the plurality of piezoelectric devices over a frequency range for a period of time, the frequency applied to each of the plurality of piezoelectric devices changing by a sweep rate.

Abstract: A sustainable hybrid piezoelectric matrix ice protection system is provided. The system includes at least one energy harvester and anti-icing device and an energy storage device. Responsive to electrical power generated by the at least one energy harvester and anti-icing device being greater than a first threshold, the at least one energy harvester and anti-icing device stores the electrical power in the energy storage device. Responsive to the electrical power generated by the at least one energy harvester and anti-icing device being less than the first threshold, the at least one energy harvester and anti-icing device generates continuous, low-frequency vibrations for anti-icing.

Abstract: An ice protection system may include a blade and an electrothermal heater including a carbon nanotube (CNT) element and a metal element. The CNT element may be a CNT fabric or a CNT yarn. The metal element may be coupled to the CNT element via a metallization process, or the like. The electrothermal heater element may include an electric sheet resistivity between 0.01 and 0.5 ohms/square.

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: The present disclosure provides for heater failure detection assemblies/systems and related methods of fabrication and use. More particularly, the present disclosure provides for heater failure detection assemblies/systems for aircraft or the like, with the heater failure detection assemblies/systems utilizing thermal images to detect the operation or failure of an aircraft heater.

Abstract: The present disclosure provides for composite tank assemblies and related methods of fabrication and use. More particularly, the present disclosure provides for linerless composite tank assemblies for aircraft or fuel or the like, and related modular manufacturing methods. The present disclosure uses a multi-section manufacturing method and carbon fiber or equivalent material with epoxy or the like to fabricate the linerless composite tank assemblies (e.g., thermosetting epoxy; thermoplastic).

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: The present disclosure provides for heater failure detection assemblies/systems and related methods of fabrication and use. More particularly, the present disclosure provides for heater failure detection assemblies/systems for aircraft or the like, with the heater failure detection assemblies/systems utilizing thermal images to detect the operation or failure of an aircraft heater.

Abstract: The present disclosure provides for ice protection heater assemblies, and related methods of fabrication and use. More particularly, the present disclosure provides for chordwise ice protection heater assemblies for aircraft or the like. The heater assemblies provide that the heater zones for the ice protection heater assembly are designed such that the electricity mainly flows along the chord of the aircraft component (e.g., wing). This puts the electrical connection points above and below as well as behind the stagnation point of the aircraft component. The electrical connection points are thus behind the area to be protected from icing via the heater assembly.

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 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 heated floor panel may comprise a base assembly and a heating element located on a first surface of the base assembly. A panel skin may be located over the heating element and the first surface of the base assembly. The panel skin may extend from the first surface of the base assembly to a second surface of the base assembly opposite the first surface of the base assembly.