Honeywell International Inc.

Louie Timothy Gaines

Donald Jeffrey Christensen

Paul T Wingett

Brent Bristol

David Lane Charles

Kellan P Geck

Glenn H Lane

David M Mathis

Paul S Evans

John Brian Dempster

Casey Hanlon

Calvin C Potter

Todd Langston

James I Kern

David M Eschborn

William Facinelli

Yogendra Y Sheoran

Wayne T Pearson

Larry A Portolese

Dwayne Michael Benson

William Lee Giesler

Eric Blumer

James Neil Quitmeyer

Gary A Farnsworth

Charles Michael Royalty

Dori Marshall

Mingfong Hwang

Arun Kumar

John Thurston

Chris D Eick

Doug Smith

Mitchell Laidlaw

Albert G Selder

Craig M Goodman

James A Wissinger

Jennifer L Zonneveld

Ben Ho

Peter J Auer

Jeff C Philips

Jeff S Rayner

Anthony Mendoza

Mike Kolic

Med Osman

Brian L Flaherty

Christopher D Eick

Michael J Laidlaw

A motor-driven landing gear apparatus for taxiing an aircraft includes a motor attached to a bogie. A wheel-driving device is attached to an axle of the landing gear apparatus. A telescoping shaft provides a torque-transmitting interconnection between the motor and the wheel-driving device during taxiing of the aircraft. The telescoping shaft includes an internally-splined shaft rotatably supported within a housing attached to the bogie.

Between-wheel bogie mounted taxi system

An aircraft taxi drive system includes a motor that is configured to transfer power to an aircraft wheel via a drive chain, such that the motor rotates the aircraft wheel via the drive chain. In some examples, the drive chain is movable between first and second positions. In the first position, the drive chain, such as an exterior surface of the drive chain, is engaged with a driven sprocket that is mechanically connected to an aircraft wheel. In the second position, the drive chain is disengaged from the driven sprocket.

Aircraft taxi system including drive chain

A method of taxing an aircraft with an electric taxi system (ETS) comprising of drive units producing airflow through rotors to pre-cool drive motors and produce rotation of aircraft wheels. The drive motors may be used to produce reverse motion of the aircraft and of operating the drive motors independently of one another so one can operate at a rate of speed and/or direction that is different from the second one of the drive units which may provide enhanced maneuverability of the aircraft during taxing. The drive motors may be controlled to produce regenerative power producing a deceleration of the aircraft that does not shift a center of gravity of the aircraft.

Compact electric taxi assembly for installation on an aircraft

A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.

A roller bearing assembly includes an annular outer ring with first and second outer ring shoulders that define a first raceway in the outer ring. An annular inner ring may be disposed substantially concentrically within the outer ring, the inner ring including a base portion and first and second inner ring shoulders that extend from and are integral with the base portion to define a second raceway in the inner ring. A plurality of rolling elements may be arranged between the inner ring and outer ring and within the first and second raceways to rotatably couple the outer ring to the inner ring.

Roller bearing assemblies and roller bearing assembly methods

A valve actuator is provided for use in conjunction with a drive motor and a valve. In one embodiment, the valve actuator includes a housing assembly, a first power screw rotatably mounted in the housing assembly and configured to be rotated by the drive motor, a first rack translatably mounted in the housing assembly, and a pinion rotatably mounted in the housing assembly and mechanically linked to the valve. The first rack is threadably coupled to the first power screw and is configured to move linearly as the first power screw rotates. The pinion engages the first rack and is configured to rotate as the first rack moves linearly to move the valve to a desired position.

Low profile valve actuator having high torque output

Butterfly valves assemblies are provided that include a flowbody, a butterfly plate, an actuator and an upper chimney and a lower chimney disposed within the flowbody. The flowbody has an inner surface defining a channel. The butterfly plate is disposed in the channel, is rotationally mounted to the flowbody, and has an outer periphery. The actuator has an actuator output shaft that is coupled to the valve shaft via a serrated spline coupling. The upper chimney and the lower chimney are configured to include bearing assemblies that constrain radial loads and thrust loads exerted upon the valve shaft and minimize misalignment of the serrated spline coupling.

Butterfly valve assembly including a bearing assembly for serrated spline constraint

A wind turbine energy conversion device that can take advantage of the higher speed and more persistent winds at higher altitudes is hereinafter disclosed. The wind turbine energy conversion device includes an unmanned aerial vehicle (UAV) connected to one end of a tether (which may include multiple shorter tethers), the other end being connected to a terrestrial anchorage point. The UAV flies at altitudes where wind speeds can reach 40 mph or higher. The UAV comprises a flying wing with one or more trailing wind power turbines and flies airborne maneuvers designed to increase relative wind speed up to about four times the true wind speed.

Tethered autonomous air vehicle with wind turbines

A linear actuator includes a thrust bearing that is integral to the actuation member. The actuator includes a translation member and an actuation member. The actuation member is responsive to a drive force to rotate. The translation member is configured to translate in response to actuation member. The thrust bearing is coupled to the actuation member and includes an inner race, an outer race, and a plurality of balls. The thrust bearing is configured as a zero lead ballscrew, with the inner race integrally formed on the actuation member, and the plurality of balls disposed between the inner and outer races.

Ballscrew with an integral high-efficiency thrust bearing

A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting/loading sharing systems that use clutches and gear assemblies to share and/or shift load between the turbines.

More electric aircraft power transfer systems and methods

A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.

More electric aircraft starter-generator multi-speed transmission system

An actuator that at least inhibits the deleterious effects of corrosive fluids, such as seawater, does not rely on relatively expensive materials, and is capable of operation and relatively high pressures includes two sealed buffer chambers. One buffer chamber is supplied with a buffer fluid, and the other buffer chamber is maintained at a vacuum pressure. The buffer fluid in the first buffer chamber helps remove any residual corrosive fluid that may remain on the actuator translation member as it moves into the actuator housing, and any fluid that leaks into the second chamber will boil as a result of the vacuum pressure therein.

Self-contained sea water linear actuator

A lubrication system for supplying lubricants between two environments is provided. The first environment is disposed within a first housing and the second environment is disposed within a second housing having a supply opening and an exhaust opening. The system includes a lubricant supply tube disposed within the supply opening and configured to supply lubricant from the first environment to the second environment. The system also includes a receptacle disposed within the second housing and configured to receive lubricant supplied from the supply tube and to hold a predetermined volume of the lubricant. A check valve is disposed within the second housing and is in fluid communication with the exhaust opening. The check valve is configured to receive overflow lubricant from the receptacle, if the lubricant exceeds the predetermined volume and to provide a seal between the first and second environments in response to a pressure differential therebetween.

Accessory lubrication system for a turbine plant

A seal pressure vent system for a waterjet propulsion apparatus including a water intake section and a pumping unit. The pumping unit is designed such that in operation the seal pressure vent system provides a fluidic path for the flow of high pressure water away from a lip seal assembly toward a near ambient pressure region. The seal vent system includes a plurality of fluid passageways formed in a stator structure in conjunction with a water barrier ring, a tail cone including an extended flange, or a modified stator web structure.

Seal pressure vent system for a waterjet apparatus

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Phoenix, AZ, United States of America

Louie Timothy Gaines