Goodrich Corporation

Michigan Molecular Institute

United Technologies Corporation

Raytheon Technologies Corporation

Dow Corning Corporation

Jin Hu

Casey Slane

Galdemir Cezar Botura

Robert M Nowak

Wenping Zhao

Brandon Hein

Zaffir A Chaudhry

Rhushikesh Patil

Wayde R Schmidt

Mark R Gurvich

John P Wesson

William A Veronesi

Nathaniel Ching

Petar Radivoj Dvornic

Dale J Meier

James A Mullen

Daniel Waina

Peter J Walsh

David B Sweet

Sugumaran Selvaraj

Ioannis Alvanos

Jonathan Jeffery Eastwood

Sameh Dardona

Eric A Grover

Thomas J Praisner

Michael John Giamati

Daniel V Viens

Antonio M Vincitore

Susan Victoria Perz

Tommy Maurice Wilson, Jr

Michael James Owen

Michael Paul Humbert

Rajendra K Agrawal

Jon Shearer

Phi Doan

George F Owens

Mark James Didyk

Paul L Parham

Timothy Charles Nash

Brad Hartzler

Kevin Edward Roach

Hector M Pinero

Gary A Zess

Claire Hartmann-Thompson

Richard Roy Hamm

David Louis Brittingham

Shyam Kumar Dattatri

Andrew Taylor

Mauro J Atalla

James Michael Roman

Quiyun Xu

Rakesh Sachdeva

Agnes M De Leuze-Jallouli

Scott Daniel Reeves

Paul Lane Parham

Joseph Winesdoerffer

Ramesh Achutha Rao

Curtis L Memory

Tom Wilson

Tommy Wilson

Jason Gesner

James Roman

Peter Radivoj Dvornic

Robert Michael Nowak

Dale Joseph Meier

Melissa Leigh Patterson

James M Roman

David L Brittingham

Zhao Wenping

James V Twisk

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.

Hybrid ice protection system

Disclosed is a method of manufacturing a stainless steel component, the method including texturizing a stainless steel substrate by bead blasting to provide a texturized stainless steel. The stainless steel substrate includes grade 316 austenitic stainless steel. The method also includes treating the texturized stainless steel with a passivation solution to provide a passivated stainless steel. The method further includes treating the passivated stainless steel with an oxidizing solution including sulfuric acid and hydrogen peroxide at a temperature of about 130 to about 200 degrees Fahrenheit for at least 50 minutes to provide an antimicrobial stainless steel surface that is free of a separate coating. The method includes obtaining at least 99.9%reduction as measured by JIS Z 2801:2010 test on the antimicrobial stainless steel without a separate coating.

Coating-free antimicrobial stainless steel surfaces

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.

Sustainable hybrid piezoelectric matrix ice protection system

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.

Extruded elastomeric surface or erosion plys

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

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.

System for detecting heater failure by thermal image

A method of manufacturing a metal component with an anti-microbial molecular layer may comprise: disposing the metal component in a piranha solution; washing the metal component; and grafting a surface of the metal component with a Si-Quat or hybrid Si-Quat molecular layer.

Antimicrobial surface treatment systems and methods for aircraft faucets

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.

Composite structure with blind hole

A method of manufacturing an aircraft metallic faucet with an anti-microbial coating may comprise: disposing the aircraft metallic faucet in a piranha solution; washing the aircraft metallic faucet; and coating a surface of the aircraft metallic faucet with a Si-Quat based coating. A method of manufacturing an aircraft metallic faucet with a hybrid anti-microbial coating with cross-linkers may comprise: disposing the aircraft metallic faucet in a piranha solution; washing the aircraft metallic faucet; coating a surface of the aircraft metallic faucet with a hybrid Si-Quat coating with crosslinkers; and curing the hybrid Si-Quat coating at a temperature between 60° C. (140° F.) and 100° C. (212° F.).

Antimicrobial coating surface treatment systems and methods for aircraft faucets

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 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.

Selectively meltable adhesives for bonding of deicers

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 system for inductive heating of an aircraft surface includes a conductive outer layer configured to be located on an outer portion of the aircraft surface. The system further includes a carbon nanotube (CNT) yarn configured to receive and conduct electrical current. The system further includes an insulator located between the conductive outer layer and the CNT yarn such that the electrical current flowing through the CNT yarn generates induction heating on the conductive outer layer.

Carbon nanotube (CNT) or carbon allotrobe based induction heating for aircraft ice protection

A conformable tank includes a body with a plurality of walls defining a cavity in the body, and an internal support structure connected to an internal surface of one of the plurality of walls and protruding into the cavity of the body. The plurality of walls are formed of a first 3D woven composite material. The internal support structure is formed of a second composite material.

3D woven conformable tank

A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

Z-CNT filled meltable adhesives for bonding of deicers

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Hudson, OH, United States of America

Jin Hu