Textron Innovations Inc.

Bell Helicopter Textron Inc.

Bell Textron Inc.

Other

St. Jude Medical, Cardiology Division, Inc.

St Jude Medical, Atrial Fibrillation Division, Inc

St. Jude Medical International Holding S.a.r.l.

Eric Stephen Olson

Troy Terrance Tegg

Carlos Alexander Fenny

James V Kauphusman

James Everett Kooiman

Jeffrey A Schweitzer

David Andrew Prater

Charles Eric Covington

Lev Abramovich Koyrakh

Eric Jon Voth

George Ryan Decker

Alon Izmirli

Colton James Gilliland

Jeffrey Matthew Williams

Michael E Rinehart

Mark B Kirschenman

David Russell Bockmiller

Ryan Thomas Ehinger

Carlos D Carbonera

Daniel Richard Starks

Mark Alan Przybyla

Clegg Smith

Michael David Trantham

Trenton Allen Hamm

David Bryan Roberts

Chia-Wei Su

Douglas Andrew Goodwin

Aaran Ashley Barnes

Joseph J Gerardi

Ron Woods

Monte McGlaun

Guy Hevel

Ezra M Tiprigan

Vasily Vylkov

Gregory Alan Spruce

Charles J Ott

Andrea Chavez

Jacob P Speed

Bradford Jeffrey Ekstrom

David R Bockmiller

Ron L Woods

Linda K Nemec

One embodiment is a rotorcraft including a rotor system and a transmission system for providing rotational power to the rotor system, the transmission system comprising a housing and a planetary pinion gear disposed in the housing. The rotorcraft further includes a restraint assembly associated with the planetary pinion gear, the restraint assembly configured to restrict radial deflection of the planetary pinion gear during operation thereof subsequent to a crack-through failure of the planetary pinion gear.

Planetary pinion gear deflection restraint device

A rotorcraft includes a drive shaft coupled to an engine; a sprag clutch coupled the drive shaft; and an output shaft coupled to the sprag clutch, wherein the sprag clutch physically contacts a first contact surface of the output shaft during operation, wherein a first cross-sectional thickness of the output shaft near the middle of the first contact surface is greater than a second cross-sectional thickness of the output shaft near a first edge of the first contact surface.

Sprag clutch system for rotorcraft

A method includes measuring a first rotational speed of a first element of a sprag clutch of a rotorcraft, measuring a second rotational speed of a second element of the sprag clutch, determining if the sprag clutch is in an overrunning condition, wherein the determining is based on the first rotational speed and the second rotational speed, generating an estimation of an instantaneous wear rate of the sprag clutch, wherein the estimation of the instantaneous wear rate is generated based on the first rotational speed and the second rotational speed, and displaying an indication of the estimation of the instantaneous wear rate of the sprag clutch. The method includes generating an estimation of an accumulated wear of the sprag clutch, wherein the estimation of the accumulated wear is based on the estimation of the instantaneous wear rate, and displaying an indication of the estimation of the accumulated wear.

System and method for monitoring clutch wear

A drive system for an aircraft includes a first gearbox assembly and a second gearbox assembly that is in mechanical communication with the first gearbox assembly. A first pressurized lubrication system is configured to circulate a first lubricant through the first gearbox assembly. A second pressurized lubrication system is configured to circulate a second lubricant through the second gearbox assembly. An emergency lubrication system is configured to autonomously supply a portion of the first lubricant to the second gearbox assembly responsive to a loss of pressure in the second pressurized lubrication system. The emergency lubrication system is also configured to autonomously supply a portion of the second lubricant to the first gearbox assembly responsive to a loss of pressure in the first pressurized lubrication system.

Autonomous emergency lubrication of aircraft gearboxes

A tail rotor isolation system for rotorcraft includes a secondary engine, first and second freewheeling units, an isolation assembly and a tail rotor system. The secondary engine is coupled to the input race of the first freewheeling unit. A main rotor system is coupled to the output race of the second freewheeling unit. The isolation assembly is coupled to the output race of the first freewheeling unit and has a fully engaged position coupling the input and output races of the second freewheeling unit and a partially engaged position coupled to the input race but decoupled from the output race of the second freewheeling unit. The tail rotor system is coupled to the input race of the second freewheeling unit such that in the partially engaged position of the isolation assembly, the overrunning mode of the second freewheeling unit isolates the tail rotor system from the main rotor system.

Tail rotor isolation systems for rotorcraft

A bearing raceway for a shaft includes a tubular sleeve comprising a raceway section and a clamp section, the raceway section having a hardened outer surface and a first, axially linear, inner surface, and the clamp section having first threads and a second, axially non-linear, inner surface, where the first threads are configured to mate with second threads on a nut to clamp the tubular sleeve to the shaft.

Bearing-raceway systems and methods

An exemplary passive oil system includes a reservoir housing configured in operation to rotate around a rotational axis, the reservoir housing defining a reservoir between a top wall, a bottom wall, innermost side, and an outer sidewall; and an outlet positioned adjacent the outer sidewall to discharge a lubrication fluid contained in the reservoir in response to the reservoir housing rotating around the rotational axis.

Passive oil system for planetary bearings

A failsafe multimode clutch assembly positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly uses pressurized lubricating oil to shift the bypass assembly between the engaged position and a disengaged position. A lock assembly enables and disables actuation of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit enables a unidirectional torque transfer mode of the clutch assembly. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.

Failsafe multimode clutch assemblies for rotorcraft

A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.

Multimode clutch assemblies having engagement status sensors

Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes an engine reduction gearbox having a retractable driveshaft that selectively engages the mid-wing gearbox via axially translatable motion along a rotation axis when the wing assembly is in the flight position. The mid-wing gearbox includes a plunger seal that is displaced in response to contact with the retractable driveshaft. Displacement of the plunger seal allows lubricant to flow through an inner bore in the retractable driveshaft, across splines of the retractable driveshaft and the mid-wing gearbox, and through lubrication ports in the mid-wing gearbox to lubricate the engine reduction gearbox, splines of the retractable driveshaft and the mid-wing gearbox, and the mid-wing gearbox via a single lubrication system.

Plunger seal for driveshaft connection

A ring gear assembly includes a ring gear, a gear box case, and a set of bolts. The ring gear includes a set of gear teeth inside the ring gear and arranged in a circle around the ring gear axis. The ring gear further includes a set of flanges arranged along at least one side of the ring gear. Each flange has a respective flange bolt hole therethrough, and each flange bolt hole has a respective bolt axis that is oriented perpendicular to the ring gear axis. The gear box case has a set of gear box bolt holes therethrough, each gear box bolt hole corresponding to a respective one of the flange bolt holes. Each of the bolts passes through a respective one of the gear box bolt holes and its corresponding flange bolt hole to fasten the ring gear to the gear box case.

Diameter saving ring gear flexure

Briefly, implementations of claimed subject matter relate to methods and devices for coupling a first rotating shaft to a second shaft. In a particular implementation, an end of a plurality of resilient fingers of a resilient structure may be radially displaced to permit positioning of the resilient structure over a first shaft. An inwardly-directed portion of each of the plurality of the resilient fingers of the resilient structure may be secured to a channel located on an inner surface of a second shaft. After securing the resilient structure to the second shaft, the one or more resilient fingers of the resilient structure may be positioned within a slotted ladder ring encircling the first shaft.

Shaft coupler

An exemplary tiltrotor aircraft with a hybrid drive system includes a first propulsion system having a first engine and a first supplemental driver operably coupled to a first proprotor that is operable between a helicopter mode and an airplane mode and a second propulsion system having a second engine and a second supplemental driver operably coupled to a second proprotor that is operable between a helicopter mode and an airplane mode.

Hybrid tiltrotor drive system

A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located below the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.

Engine and rotatable proprotor configurations for a tiltrotor aircraft

Growing community of inventors

Fort Worth, TX, United States of America

Eric Stephen Olson