Goodrich Corporation

Brandon Hein

Casey Slane

Jin Hu

Nathaniel Ching

James A Mullen

Galdemir Cezar Botura

Daniel Waina

George F Owens

Wenping Zhao

Peter J Carini

Reid Philip Beery

Melissa Leigh Patterson

Casey M Slane

Provided are embodiments for method and system for performing an integrated ice protection with prognostics and health management using fiber optic sensors. Embodiments can include reading a signal from each sensor of an array of sensors installed on a surface of a structure or equipment, wherein each sensor is a fiber optic sensor, and generating a map based on reading the signal from each sensor, wherein the map monitors a condition of the surface detected by each sensor. Embodiments can also include determining at least one of an abnormal condition or a failure based at least in part on reading the signal from each sensor; and performing at least one of adjusting power control for the structure or equipment or communicating the abnormal condition or failure of the structure or equipment.

Integrated ice protection with prognostics and health management

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.

Metallized carbon nanotube elements for electrothermal ice protection

An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro-thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.

Systems and methods for an ice runback control zone in an electrothermal ice protection system

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.

Panel skin for heated floor panels

A method of making a resistance temperature detector includes additively manufacturing a conductive ink on a flexible substrate and applying the resistance temperature detector to a geometrically complex surface of a component requiring heating, or directly additive manufacturing the resistance temperature detector onto that surface.

Additive manufactured resistance temperature detector

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.

Heated floor panel with impact layer

A panel assembly for use in an aircraft includes a surface. The panel assembly further includes a body portion including a honeycomb material having multiple body volumes oriented perpendicular to the surface. The panel assembly further includes an edge portion extending around an edge of the panel assembly and including the honeycomb material having multiple edge volumes oriented parallel to the surface in order to increase edge strength of the panel assembly.

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Stow, OH, United States of America

Brandon Hein