Goodrich Corporation

The B. F. Goodrich Company

Hamilton Sundstrand Corporation

Alan John Fahrner

Norbert A Weisend, Jr

Lubomir A Ribarov

Galdemir Cezar Botura

Stephen Michael Bortoli

Michael John Giamati

James C Putt

David B Sweet

William E Seidel

James A Mullen

Richard L Rauckhorst

James Thomas Hindel

Kurt M Tauscher

Robert N Hohenshil

Andrew Taylor

Steven Charles Brooker

Thomas S Betchel

Gregory C Hopkins

Samual Steven Riczo Schomer

Rick Pudoka

Mark Walter Corcoran

James R Hunter

Thomas A Waples

Donald E Butler

Geoffrey D Fenelon

Steven C Brooker

A de-icer is provided and includes first and second structural layers that each include centerline and a non-inflatable edge angled with respect to the centerline, edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area and stitching. The stitching is disposed to stitch the first and second structural layers together in the central area to form tubes. The tubes include an outermost tube which is closest to and parallel with the non-inflatable edge.

Pneumatic de-icer with reduced non-inflatable area at de-icer edge

A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

Sewn alternate inflate pneumatic de-icer

A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.

Sewn reinforcement features for prevention of stitch breakage in a pneumatic de-icer

A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Ice-shedding spinner for ram air turbine

A valve includes a body with an inlet at a first end of the body, and an outlet at a second end of the body. A first electrically resistive heating element is located in the inlet and heats a first fluid source to a temperature above 0 degrees C. A second electrically resistive heating element is located in the outlet and heats a second fluid source to a temperature above 0 degrees C.

Heated valve

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

An electrical-power-transfer assembly () transferring electrical power from an onboard power source to electrical deicers () on propeller blades (). The assembly () comprises a first race structure () mounted to the aircraft, a second race structure () mounted to the propeller assembly (), and rolling elements () caged in raceway(s) () situated between the race structures (). The current path established by the assembly () passes through the raceway(s) () and the rolling elements () caged therein.

Aircraft propeller assembly

A pneumatic deicing system includes a deicer assembly comprised of an outer layer, an inner ply, and a plurality of inflatable members provided therebetween. The deicer assembly is disposed directly on top of and bonded to an airfoil. The deicer assembly is inflated through an inflation port. Fluid is drained from the deicer assembly through a drain valve.

Pneumatic deicing system with drain valve

A pneumatic deicing system for deicing an airfoil includes a flexible deicing member having inflatable tube-like passages provided therein for being inflated with a pressurized fluid, wherein the deicing member is bonded to a shell having a snap type connector for mating with another connector either on the airfoil or integrated into another part of the shell. An air connector extends through the shell and is utilized for putting the deicing member in fluid connection with the fluid source. Radar absorptive material may be disposed between the shell and the deicing member for reducing the radar cross section of the airfoil.

Pneumatic deicer assembly having a self connecting shell

A pneumatic deicing distribution valve 10 includes a body 12, a cap assembly 14 and a rotary member 30 contained therein. Rotary member 30 selectively connects an input port 18 with a plurality of output ports 20 for selectively pressurizing one of a number of deicing apparatuses. A vacuum port 24 places all output ports not being pressurized under vacuum.

Pneumatic deicing distribution valve and system

A pneumatic deicer assembly 32 for attachment to an airfoil includes a pair of plies 52, 54 which are stitched together with a zig-zag stitch line which periodically crosses over the airfoil leading edge.

Leading edge pneumatic deicer assembly

A hand tool for the preparation of an off-set bore relative to a countersunk recess in a structural plate member wherein a pilot sleeve with a central bore slidably support an upper hollow sleeve that is spring biased away from the pilot sleeve. A bushing secured to the upper portion of said hollow sleeve also retains a drill bit that extends in to the pilot sleeve while the shank end is connectable to a drill for rotation and axial movement with the hollow sleeve relative to the pilot sleeve to drill a through bore in the plate member whose axis is off-set relative to a tapered countersunk conical recess in the plate member. The lower end of the pilot sleeve has a tapered annular surface or conical recess whose central axis is off-set relative to the axis of the central bore of said pilot sleeve, and a handle is secured to the pilot sleeve to position and hold the hand tool in the countersunk recess of the plate member as it is drilled.

Growing community of inventors

Canton, OH, United States of America

Alan John Fahrner