Goodrich Corporation

Hamilton Sundstrand Corporation

George F Owens

Jin Hu

Mark R Gurvich

Wenping Zhao

William A Veronesi

Galdemir Cezar Botura

Nathaniel Ching

James A Mullen

Kevin Edward Roach

Brandon Hein

Casey Slane

Jon Shearer

Robert William Hyde

Daniel Waina

Kurt M Tauscher

Carl Aeschliman

Michael J Dorsey

Richard B Yori

Joseph Winesdoerffer

Melissa Leigh Patterson

Jason Gesner

David L Brittingham

James V Twisk

Tom Wilson

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 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 heating arrangement has a positive temperature coefficient ('PTC') heater. A resistor is electrically in series with the PTC heater sized and configured to limit current through the PTC heater and the resistor below a selected value.

PTC heater with autonomous control

An aircraft heated floor panel includes a first support layer, a second support layer, and a heating layer located between the first support layer and the second support layer. An aircraft floor panel includes a floor panel body and a removal feature that provides a mechanism for the aircraft floor panel to be removed from an attached aircraft structure.

Aircraft floor panel

A valve assembly () for an aircraft water supply system. The valve assembly () comprises a valve member (), an electrical motor (), and a mechanical returning mechanism (). When electrical power is provided, the motor () can be controlled to move the valve member () from a first position and to a second position. The mechanism () is operably connected to the valve member () and mechanically biases it towards the first position. If a power loss occurs when the valve member () is in the second position, the returning mechanism () non-electrically (e.g., mechanically) returns the valve member () to the first position.

Valve assembly for aircraft water supply system

Growing community of inventors

Akron, OH, United States of America

George F Owens