Goodrich Corporation

Rohr, Inc.

Hamilton Sundstrand Corporation

Galdemir Cezar Botura

Jin Hu

Casey Slane

Nathaniel Ching

Wenping Zhao

Zaffir A Chaudhry

Tommy Maurice Wilson, Jr

James A Mullen

Brad Hartzler

Daniel Waina

Claude Marc Hubert

Rhushikesh Patil

Vincent R LoPresto

Brandon Hein

Timothy Olson

Joseph Christopher Zecca

Sugumaran Selvaraj

David Cenit Flosdorf

Mark James Didyk

Michael James Krenz

Michael John Layland

Peter J Carini

David B Sweet

Darren Glenn Jackson

Alan John Fahrner

Jeffrey Martin Werbelow

Milan Mitrovic

Guangqing Shen

Daniel Paul Christy

James Thomas Hindel

George F Owens

Kurt M Tauscher

David Louis Brittingham

David L Brittingham

Brian Burkett

James Michael Roman

Dimitrios Papaioannou

David Bert Sweet

Shyam Kumar Dattatri

Andrew Taylor

Mauro J Atalla

Tommy Wilson

Alex Zadell

Samual Steven Riczo Schomer

Karthik Debbadi

Richard J Cole

James R Hunter

Alan J Fahrner

Chris Cojocar

Anthony Paul Digiacomo

Robert Dodson

Dave Bert Sweet

Melissa Leigh Patterson

Timothy Robert Olson

Casey M Slane

Zhao Wenping

El Hassan Ridouane

Tommy M Wilson

Tommy M Wilson Jr

Brian Bobby Burkett

Jr Tommy M Wilson

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

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

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

An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

Adjustable ice protection system parting strip

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

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

Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

Control of electric pump-driven deicer

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 de-icing assembly for a surface of an aircraft includes: a carcass with a first layer, a second layer, and a carcass centerline and a plurality of seams sewn into the carcass, wherein the plurality of seams join the first and second layers of the carcass together. The assembly includes a plurality of inflation passages formed by the plurality of seams and disposed between the first and second layers of the carcass. The system also includes a manifold fluidly connected to and disposed beneath the carcass, the manifold comprising a width and a manifold centerline oriented approximately perpendicular or parallel to the carcass centerline. The seams are sown by a stitchline formed of carbon nanotube yarn.

Carbon nanotube yarn for pneumatic de-icer stitching

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 heated floor panel assembly for aircraft includes an impact layer made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer can further include woven metallic fibers. The assembly also includes a stack of structural layers, a heating layer, and a core layer for absorbing shear stress.

Impact and knife cut resistant pre-impregnated woven fabric for aircraft heated floor panels

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.

Pressurized reduction of CNT resistivity

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

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Akron, OH, United States of America

Galdemir Cezar Botura