Otis Elevator Company

Goodrich Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Hamilton Sundstrand Corporation

Crane Composites, Inc.

Raytheon Company

B/e Aerospace, Inc.

Sikorsky Aircraft Corporation

Rohr, Inc.

United Technologies Research Center

Wenping Zhao

John P Wesson

Daniel A Mosher

Andrzej Ernest Kuczek

Ellen Y Sun

Scott Alan Eastman

Paul F Croteau

Zaffir A Chaudhry

Michael Paul Humbert

Galdemir Cezar Botura

Jin Hu

Brad Guilani

Gopal R Krishnan

Tommy Maurice Wilson, Jr

Richard N Fargo

Mark R Gurvich

Nathaniel Ching

Daniel V Viens

Justin R Hawkes

Tahany Ibrahim El-Wardany

Jagadeesh Kumar Tangudu

Casey Slane

Paul Papas

James A Mullen

Richard J Ericson

Mark Steven Thompson

Matthew E Lynch

Thomas J Garosshen

Abbas A Alahyari

Matthew Robert Pearson

John A Sharon

Walter Thomas Schmidt

Michael A Klecka

Bart Antonie Van Hassel

Kimberly Rae Saviers

Mary K Herndon

Chen Qian Zhao

Steven M Kestler

Daniel O Ursenbach

Nathaniel John Herrmann

Kyle B Martin

Huan Zhang

Robert L Hancock

Zhigang Wang

Xiaomei Fang

Brad Hartzler

Douglas E Logan

John J Gangloff, Jr

Danielle L Grolman

Eric Jay Amis

David Wayne Mckee

William Eaton Holden, Iii

Robert A Barney

Nathaniel M Gray

Aritra Sur

Steven W Gronda

Jeffrey P King

Daniel Waina

Brandon Hein

Theresa A Hugener

George F Owens

Abhijit Chakraborty

Sameh Dardona

Danielle Grolman

Orlando Mijares

Sridhar Siddhamalli

Lei Xing

Todd B Irick

Callum Bailey

Melissa Leigh Patterson

Jr John J Gangloff

Iii William Eaton Holden

Micheal Paul Humbert

Tommy M Wilson

Tommy M Wilson Jr

Tommy Wilson

Iii William Holden

A rotor is provided. The rotor includes a central hub, an outer ring assembly and back-to-back curved webs. The outer ring assembly includes magnetic elements. The back-to-back curved webs are_radially interposed between the central hub and the outer ring assembly. The back-to-back curved webs can be circumferentially continuous about the central hub or circumferentially non-continuous about the central hub.

Lightweight rotor design with composite structure

A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.

Composite pressure vessel assembly and method of manufacturing

An aircraft brake insulator assembly for a brake mechanism of an aircraft includes a torque barrel assembly and a multi-layer insulator. The torque barrel assembly includes a torque plate and a torque barrel coupled to the torque plate. The multi-layer insulator is configured to be located between a piston housing of the brake mechanism and the torque plate. The multi-layer insulator includes a first insulator layer and a second insulator layer contacting the first insulator layer.

Multi-layer aircraft brake insulator

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 load bearing member for a lifting and/or hoisting system includes a plurality of tension members arranged along a width of the load bearing member. Each tension member includes a plurality of load carrying fibers arranged to extend in a direction parallel to a length of the load bearing member and a matrix material in which the plurality of load carrying fibers are arranged. The load bearing member further includes a lateral layer and a jacket material at least partially encapsulating the plurality of tension members.

Load bearing member including lateral layer

A joint between dissimilar thermoplastic materials comprising a first thermoplastic material layer; a second thermoplastic material layer having a melting point temperature different from a melting point temperature of the first thermoplastic material layer; and an interface layer coupled between the first thermoplastic material layer and the second thermoplastic material layer; wherein the interface layer is configured to join the first thermoplastic material layer and the second thermoplastic material layer together to form the joint, wherein the interface layer comprises a melting point temperature having a value selected from the group consisting of between the melting point temperature of the first thermoplastic material layer and the melting point temperature of the second thermoplastic material layer; or lower than the melting point temperature of the first thermoplastic material layer and the melting point temperature of the second thermoplastic material layer.

Multi-functional interface/surface layer for thermoplastic components

An end effector for welding composite components includes an end effector housing and a welding member mounted to the end effector housing. The end effector further includes a leading roller mounted to the end effector housing forward of the welding member and at least one follower roller mounted to the end effector housing aft of the welding member. The end effector further includes at least one first cooling air jet positioned to direct a first stream of cooling air toward the at least one follower roller.

End effector, welding system, and method for welding composite components

A method of manufacturing a composite vessel assembly () includes the steps of filling a first chamber defined by a first liner () with a first granulated material () through a first orifice () in the first liner. A vacuum is then applied to the first chamber, and the first orifice is plugged. The first liner may then be enveloped with a first layer () for structural rigidity followed by relief of the vacuum.

Method of manufacturing a composite vessel assembly

A composite pressure vessel assembly includes a plurality of lobes, each of the lobes having at least one interior wall and at least one curved wall, the plurality of lobes being positioned in a side by side arrangement and extending in a longitudinal direction from a first end to a second end. Also included is a plurality of end caps disposed at the ends of the lobes, wherein the plurality of lobes and end caps are formed of at least one fiber-reinforced polymer. A method of manufacturing a composite pressure vessel assembly is provided. The method includes forming a plurality of lobes consisting of at least one fiber-reinforced polymer. The method also includes forming a main body with the plurality of lobes, the lobes disposed in a side by side arrangement.

A first composition is disclosed that includes a fire-resistant thermoplastic resin. The fire-resistant thermoplastic resin includes 1-20 wt % of an aryl phosphate, includes 1-20 wt % of a phosphate polymer, and 60%-98% of a (meth)acrylic polymer, including units from at least one monomer, wherein the monomer is chosen from methyl methacrylate, acrylic acid, methacrylic acid, acrylic acid esters, methacrylic acid esters, acrylonitrile and maleic anhydride. The first composition may further include a fabric or a composite material that is embedded with the fire-resistant thermoplastic resin. In some instances, the aryl-phosphate and the phosphonate polymer synergistically reduce an effective heat of combustion, a peak heat release, or a flame time as compared to a second composition that contains only one of the aryl phosphate or the phosphonate polymer.

Fire resistant thermoplastic-based resin for fiber-reinforced composites

A tension member for a lifting and/or hoisting system includes a core including a plurality of load carrying fibers arranged in a matrix material, and an outer layer secured to the core including a plurality of outer fibers arranged around a perimeter of the core. The outer layer includes one or more outer fibers arranged off-axis relative to the load carrying fibers of the core. A method of forming a tension member for an elevator system includes arranging a plurality of load carrying fibers along a length of the tension member, retaining the plurality of load carrying fibers in a matrix material to define a core, and enclosing the core in an outer layer including a plurality of outer fibers arranged around a perimeter of the core. The outer layer includes one or more outer fibers arranged off-axis relative to the load carrying fibers of the core.

Overbraided non-metallic tension members

Aircraft electric motors are described. The electric motors include an annular rotor sleeve having an inner wall, a connecting wall, and an outer wall, wherein the inner wall, the connecting wall, and the outer wall define a U-shaped channel configured to receive a U-shaped magnet structure and a sleeve inner cavity defined radially inward from the inner wall, a hub connector extending radially inward from the inner wall into the sleeve inner cavity, a hub arranged in the sleeve inner cavity and fixedly connected to the hub connector, wherein the hub is configured to rotate with rotation of the rotor sleeve, and a U-shaped magnet structure arranged within the U-shaped channel of the rotor sleeve. At least one of the rotor sleeve, the hub connector, and the hub are formed from a composite material.

Aircraft electric motor

An illustrative example assembly for making an elevator load bearing member includes a fabric having a plurality of fibers arranged with some of the fibers transverse to others of the fibers. A plurality of cords are configured to support a load associated with an elevator car. The cords are included in the fabric and have respective coatings. The coatings include a first coating material and a second coating material, or include different coating thicknesses such that some of the coatings have a different coating thickness than others of the coatings, or the coatings include the first coating material and the second coating material and some of the coatings have a different coating thickness than others of the coatings.

Elevator load bearing member having a fabric structure

Aircraft electric motors are described. The aircraft electric motors include a cooling system comprising an annular heat exchanger, a motor housing arranged radially inward from the heat exchanger, the motor housing defining a rotor-stator cavity and a gear assembly cavity, a rotor sleeve arranged within the rotor-stator cavity, a gear assembly arranged within the gear assembly cavity, a first shaft operably coupled to the rotor sleeve and configured to be rotationally driven by the rotor sleeve to drive rotation of a portion of the gear assembly, and a second shaft operably coupled to the gear assembly and configured to be rotationally driven by the gear assembly.

A sensor array system includes a skin. The sensor array system includes a lattice network coupled to a portion of the skin. The lattice network includes a plurality of interconnects and a plurality of nodes. The plurality of nodes are respectively defined by an intersection of two or more interconnects of the plurality of interconnects. The sensor array system includes a first sensor electrically connected to the lattice network at a first node of the plurality of nodes.

Flexible sensor system for prognostic health monitoring of composite aerostructures

Growing community of inventors

Glastonbury, CT, United States of America

Wenping Zhao