Goodrich Corporation

James A Mullen

Jin Hu

Galdemir Cezar Botura

Nathaniel Ching

Wenping Zhao

Zaffir A Chaudhry

Mark R Gurvich

William A Veronesi

Casey Slane

Michael John Giamati

Peter J Walsh

Mark James Didyk

Reid Philip Beery

Tommy Maurice Wilson, Jr

Jon Shearer

Brandon Hein

George F Owens

Alan John Fahrner

Brad Hartzler

Richard J Carpino, Ii

Kevin Edward Roach

Daniel Waina

Danielle L Grolman

James Thomas Hindel

Adam George

Andrew Taylor

Lindsay Miller

Gregory Schroeder

Joseph Winesdoerffer

Richard J Carpino

David L Brittingham

Tommy M Wilson Jr

James V Twisk

Tom Wilson

Jason Gesner

Richard J Ii Carpino

Melissa Leigh Patterson

John J Gangloff, Jr

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.

Heater design for carbon allotrope ice protection systems

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

An additively manufactured strain gauge resides on the surface of a component to monitor component fatigue. The strain gauge is additively manufactured, and applied to the curvature of the component surface through either a flexible substrate or through direct printing.

Additive manufactured strain gauge on component surfaces for predictive failure monitoring

An ice detector apparatus for an aircraft includes a heater strip and a temperature sensor. The heater strip is configured to be mounted to an external surface of an aircraft and the temperature sensor is coupled to the heater strip. The temperature sensor is configured to detect a temperature profile of the heater strip, wherein the temperature profile is indicative of an extent of icing. The temperature profile may be indicative of whether the aircraft is operating in an appendix C icing-envelope or an appendix O icing-envelope. The temperature sensor may include a plurality of temperature sensors coupled along a length of the heater strip, such that the temperature profile comprises a spatial temperature map of the heater strip.

Ice detector apparatus, system, and method

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

An additively manufactured heating element is printed on a flexible substrate and attached to an aircraft component having a complex geometric surface. The heating element is made of a plurality of layers of a conductive ink, which is electrically connected to a controller through one or more leads.

Additive manufactured heater elements for propeller ice protection

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 carbon allotrope heating element includes an electrical resistivity between 0.005 ohms per square (&#x3a9;/sq) and 3.0 &#x3a9;/sq. A heating system includes a component and a carbon allotrope heating element having an electrical resistivity between 0.005 &#x3a9;/sq and 3.0 &#x3a9;/sq. A method includes modifying a carbon allotrope heating element to have an electrical resistivity between 0.005 &#x3a9;/sq and 3.0 &#x3a9;/sq and applying the carbon allotrope heating element to a component of an aircraft.

Carbon allotrope heater material with resistivity ranges suited for aircraft ice protection

A protective enclosure for an electrically-conductive element disposed along a component surface includes a base, a first side with an electrical connector, and a second side with an aperture for receiving a potting material. The base, the first side, and the second side at least partially define an internal void, and the internal void communicates with an external environment via the aperture.

Integrally bonded and installed protective enclosure

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.

Adjusting CNT resistance using perforated CNT sheets

A rotary blade includes a blade tip assembly with a first bus bar segment and a main blade assembly with second bus bar segment. The first bus bar segment is connected to the blade tip assembly and the second bus bar segment is connected to the main blade assembly. The blade tip assembly is connected to the main blade assembly such that the first and second bus bar segments are longitudinally offset from one another. A low-profile interconnect spans the first and second bus bar segments for resistively generating less heat than the bus bar segments for a predetermined current flow.

Electrical interconnects for ice protection systems

An ice protection system () comprising electrothermal devices (-) having zones (P-P,L-L,S-S,T-T) associated with respective surface regions of rotor blades. Each zone involves electric load (R) which converts supplied electrical power from one phase of a three-phase power system into heat. The combined load of the A-phase zones, the combined load of the B-phase zones, and the combined load of the C-phase zones are approximately equal.

Ice protection system

An electrical resistance heating element of the sort suitable for use in de-icing an aircraft surface includes a foil patterned with a plurality of holes. The holes are in a first patterned region that extends in a first direction from a first end to an opposite second end. The holes define multiple electrical paths between the two ends. The holes, which may vary in size, are configured and dimensioned such that the multiple electrical paths in areas away from lateral edges of said first patterned region are all non-parallel to the first direction. In other words, the electrical paths do not follow a straight line from the first and second ends, but rather must wend their way around the overlapping holes.

Foil heating element for an electrothermal deicer

A patterned foil sheet heating element has a first discrete region patterned with a first plurality of holes forming multiple conductive ribbons and having a first sheet resistivity. It also has a second discrete region patterned with a second plurality of holes forming multiple conductive ribbons and having a second sheet resistivity. At least some of the multiple conductive ribbons in the first discrete region are in electrical continuity with at least some of the multiple conductive ribbons in the second discrete region, and the first discrete region and the second discrete region both adjoin a first junction strip of the foil heating element. An electrothermal heating assembly may be formed using such a patterned foil sheet sandwiched between two layers of material which may be thermally conductive and electrical insulative.

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Wadsworth, OH, United States of America

James A Mullen