US Pat. No. 9,399,513

CONSTANT VELOCITY JOINT WITH CONTROL MECHANISM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub;
a rotor blade coupled to the hub; and
a constant velocity (CV) joint coupled between the drive shaft and the hub, the CV joint comprising:
a first yoke rotatably coupled to the drive shaft about a first axis and configured to receive the drive shaft through a first
opening;

a second yoke rotatably coupled to the first yoke about a second axis and rotatably coupled to the hub about a third axis;
and

a control mechanism adapted to constrain the first yoke and the second yoke so as to achieve a substantially CV characteristic
between the drive shaft and the hub, the control mechanism comprising a positioning portion adapted to position the first
and second yokes such that the second axis substantially resides on a bisector of an angle between the drive shaft and the
hub.

US Pat. No. 9,333,684

METHOD OF REPAIRING, SPLICING, JOINING, MACHINING, AND STABILIZING HONEYCOMB CORE USING POURABLE STRUCTURAL FOAM AND A STRUCTURE INCORPORATING THE SAME

Bell Helicopter Textron I...

1. A method of manufacturing a machined core member, the method comprising:
providing a cavity having a first depth preselected to correlate with a first desired density of an expanded foam and having
a second depth preselected to correlate with a second desired density of the expanded foam, the second depth being less than
the first depth, and the second desired density being greater than the first desired density;

pouring a foam mixture into the cavity and expanding the poured foam mixture to rise upwardly into cells of a stock core member
and to become the expanded foam having both the first density and the second density extending laterally across the stock
core member, the stock core member being arranged entirely over the cavity during said expanding, and the first and second
densities of the foam within the stock core member corresponding to first and second cavity depth locations respectively;
and

machining the stock core member with the expanded foam in the cells.

US Pat. No. 9,585,198

VARIABLE STIFFNESS BLANKET WITH VARIABLE HEATING

Bell Helicopter Textron I...

1. A heater system, comprising:
a first bag forming a cavity;
a fluid bladder carried within the cavity and forming a fluidly sealed chamber, the fluid bladder being configured to store
electrorheological fluid within a fluidly sealed chamber;

an electrical wire in fluid communication with the electrorheological fluid; and
a heater blanket carried within the cavity;
a second bag secure to and placed adjacent to the first bag;
wherein current passing through the electrical wire changes the fluid properties of the electrorheological fluid; and
wherein the heater system creates heat, which in turn warms an object that the heater system is placed thereon.

US Pat. No. 9,334,048

ELASTOMERIC BEARING HAVING TAPERED LAYERS

Bell Helicopter Textron I...

1. A rotor hub for an aircraft, the rotor hub comprising:
a yoke;
a rotor mast; and
a hub spring assembly, comprising:
an upper outer member;
an upper inner member; and
an upper spring member having a plurality of elastomeric layers and shim layers sandwiched between the upper outer member
and the upper inner member, the shim layers being tapered such that a thickness of each shim layer is smaller at a side portion
as compared to the thickness at a center portion;

wherein the shim layers are shaped with an arc taper such that the most interior portions of the shim layers and the most
exterior portions of the shim layers have smaller thickness as compared to a center portion of the shim layers.

US Pat. No. 9,334,920

HYBRID FLUID ELASTOMERIC DAMPER

Bell Helicopter Textron I...

1. A system, comprising:
a damper, having:
a housing forming a fluidly sealed cavity; and
a fluid disposed within the cavity and configured to change fluid properties as electrical energy is induced;
a piston elastically attached to an inner surface of the housing;
a first fluid chamber and a second fluid chamber positioned within the housing and position at opposing ends of the piston;
a fluid passage ending through the piston and in fluid communication with the first chamber and the second chamber;
wherein fluid channeled between the first chamber and the second chamber travel solely through the fluid passage;
a plurality of coils positioned within the second chambers and configured to provide electrical energy to the fluid; and
a control subsystem operably associated with the electrical subsystem and configured to regulate the electrical energy induced
into the fluid.

US Pat. No. 9,341,217

BEARING RACEWAY HEAT DISTRIBUTION USING HEAT PIPES

Bell Helicopter Textron I...

1. A cooling system for a bearing having an inner ring rotatably carried within an outer ring, the system comprising:
a heat pipe extending through a thickness of the inner ring from a first surface to an opposing second surface, the heat pipe
being configured to protrude from the first surface; and

a cooling lubricant in fluid communication with the first surface;
wherein the heat pipe is configured to come into contact with the cooling lubricant and configured to transfer heat energy
from the first surface to the second surface.

US Pat. No. 9,334,060

INFRARED SUPPRESSING EXHAUST SYSTEM

Bell Helicopter Textron I...

1. A method of managing aircraft exhaust, comprising:
receiving hot air from an exhaust aircraft engine at a hot air mass flow rate, the aircraft engine configured to drive a rotor
of the aircraft;

providing the hot air at the hot air mass flow rate to a mixer duct of an exhaust system attached to the exhaust duct;
receiving cold air from outside the aircraft at a cold air mass flow rate through a first duct connecting the outside of the
aircraft to a distributor disposed within the mixer duct, wherein a first fan is positioned within the first duct, and wherein
the first fan is separate from the rotor;

providing the cold air at the cold air mass flow rate to the distributor; and
mixing the hot air and the cold air within the mixer duct at a variable hot air mass now rate to cold air mass flow rate ratio,
wherein the hot air mass flow rate is varied using the aircraft engine and the cold air mass flow rate is varied by controlling
a speed of the first fan positioned within the first duct, wherein the variable hot air mass flow rate to cold air mass flow
rate ratio is selectively maintained independent of at least one of (1) a variation in the hot air mass flow rate and (2)
a variation in a translational speed of the aircraft.

US Pat. No. 9,340,279

FLUID TRANSFER CHAMBER FOR AIRCRAFT FLUID TRANSMISSION LINES

Bell Helicopter Textron I...

1. An aircraft fuel transfer chamber to transfer aircraft fuel, the chamber comprising:
a chamber housing including:
a first sub-chamber defining a first inlet to the chamber housing to be connected to an outer tube of a first aircraft fuel
line assembly passing through a first portion of an aircraft, the first sub-chamber to receive fuel leaked into the outer
tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly; and

a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to the chamber housing
to be connected to an outer tube of a second aircraft fuel line assembly passing through a second portion of the aircraft,
the second sub-chamber to receive fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner
tube of the second aircraft fuel line assembly, the chamber housing defining an outlet connected to the first inlet and the
second inlet to transfer leaked fuel from the first portion and the second portion toward a drain of the aircraft.

US Pat. No. 9,550,580

STRAPPED WINDSHIELD ASSEMBLY FOR ROTORCRAFT

BELL HELICOPTER TEXTRON I...

1. A rotorcraft, comprising:
an airframe;
a windshield, wherein the windshield comprises polycarbonate; and
a plurality of independent straps connected to the airframe and the windshield and extending between the airframe and the
windshield configured to hold the windshield, the straps operative to move independently with respect to each other and to
flex with respect to the windshield and the airframe;

wherein each strap is coupled to the windshield by a connector comprising a grommet extending through the windshield and a
fastener extending through the grommet, the connector operative to allow movement of the windshield relative to the strap.

US Pat. No. 9,399,512

HYBRID SLIDING ELEMENT AND ELASTOMERIC BEARING

Bell Helicopter Textron I...

7. A bearing, comprising:
a housing having a first opening therethrough;
a first member disposed within the first opening and having a second opening therethrough, the first member having at least
one substantially curved surface;

an elastomeric bearing disposed within the second opening and having a third opening therethrough configured to receive a
shaft; and

a sliding element bearing disposed between the elastomeric bearing and the first member.

US Pat. No. 9,457,897

ROTOR SYSTEM SHEAR BEARING

Bell Helicopter Textron I...

1. A system, comprising:
a rotor system comprising:
a flexural yoke; and
a shear bearing configured to perform at least one of transmitting forces to the flexural yoke and receiving forces from the
flexural yoke, wherein the shear bearing comprises:

a four bar linkage comprising a first set of opposing links including a forward link and a rear link and a second set of opposing
links including an upper link and a lower link, the forward link being connected to the upper link with a first pin and to
the lower link with a second pin, the rear link being connected to the upper link with a third pin and to the lower link with
a fourth pin, the forward link being rotatable about the first pin and the second pin, the rear link being rotatable about
the third pin and the fourth pin, the upper link being rotatable about the first pin and the third pin, and the lower link
being rotatable about the second pin and the fourth pin; and

a grip connected between the first set of opposing links of the four bar linkage, wherein the grip retains the flexural yoke.

US Pat. No. 9,463,541

SELECTIVELY COMPLIANT CLAMP

Bell Helicopter Textron I...

1. A clamp to retain an aircraft component, the clamp comprising:
a base comprising a curved portion shaped to complement a curvature of the aircraft component, the base being attached to
a table;

a datum backstop attached to the table and positioned longitudinally rearward of the base, wherein the base is registered
relative to a datum on the datum backstop, the datum backstop configured to abut a rearward end portion of the aircraft component;
and

a first selectively compliant component carried by the base, the first selectively compliant component being selectively operable
between a substantially compliant state and a substantially rigid state;

wherein when the selectively compliant component is operated in the substantially compliant state, the selectively compliant
component is configured to selectively assume a first profile in response to forces being applied to an exterior surface of
the selectively compliant component while the selectively compliant component selectively opposes the forces being applied
to the exterior surface of the selectively compliant component with reactionary forces;

wherein when the selectively compliant component is operated in the substantially rigid state, the selectively compliant component
is configured to selectively maintain the first profile;

wherein the selectively compliant component is configured to selectively return to the substantially compliant state; and
wherein the selectively compliant component is configured to transition between the substantially compliant state and the
substantially rigid state without substantially altering the reactionary forces.

US Pat. No. 9,296,483

DISTRIBUTED ICE PROTECTION CONTROL SYSTEM

Bell Helicopter Textron I...

1. An ice protection control system for an aircraft, the system comprising:
a plurality of ice protection elements configured for removing ice and/or preventing the formation of ice on a surface;
a generic control core comprising:
a master server;
a control module; and
a standby server configured to act as redundant server for the master server;
wherein the master server is configured to receive a sensor data and send the sensor data to the control module;
wherein the control module is configured to be programmable with functional software from the master server, the control module
being configured to functionally operate the plurality of ice protection elements after being programmed with the functional
software from the master server;

wherein the standby server and the master server are each configured to maintain a health status of itself on the other.

US Pat. No. 9,126,678

SPINDLE MOUNTED TILTROTOR PYLON WITH FIXED ENGINE ARRANGEMENT

Bell Helicopter Textron I...

1. A rotor system for tilt rotor aircraft, the rotor system comprising:
an engine disposed at a first fixed location on a wing member;
a prop-rotor pylon mechanically coupled to the engine along a first drive path, wherein the prop-rotor pylon is rotatably
mounted on a spindle, wherein the prop-rotor pylon is configured to selectively rotate about a rotational axis of the spindle
between a vertical position and a horizontal position;

a gearbox disposed in the first drive path, wherein the gearbox comprises a rotational shaft configured to at least partially
transmit a rotation of the engine to the prop-rotor pylon, wherein a rotational axis of the rotational shaft is aligned with
the rotational axis of the spindle; and

an interconnect drive shaft passing through the wing member, wherein the prop-rotor pylon is mechanically coupled to the interconnect
drive shaft along a second drive path, wherein a rotational axis of the interconnect drive shaft is aligned with the rotational
axis of the spindle;

wherein the interconnect drive shaft is disconnected from the rotational shaft included in the gearbox causing the first drive
path and the second drive path to independently engage a prop-rotor gearset.

US Pat. No. 9,090,027

SYSTEM AND METHOD OF CONSTRUCTING COMPOSITE STRUCTURES

Bell Helicopter Textron I...

1. A method of constructing a composite component, comprising:
longitudinally aligning each of a plurality of material strips relative to a concavity of a layup tool, wherein each of the
plurality of material strips is substantially rectangular;

longitudinally extending the material strip to a predetermined location relative to the layup tool by:
measuring a longitudinal distance of each of the plurality of material strips, and aligning a longitudinal end of at least
one of the plurality of material strips with a longitudinal distance indicium;

vertically abutting each of the plurality of material strips to the concavity of the layup tool to form a stack of material
strips; and

machining the stack of material strips using a router traversing longitudinally over the stack of material strips and using
a bit assembly rotating in a direction causing the router to be pulled toward a rear of the layup tool.

US Pat. No. 9,090,334

MECHANICAL AND MAGNETIC CONTROL SYSTEM FOR MAGNETORHEOLOGICAL ACTUATORS

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a main rotor system coupled to the power train, the main rotor system comprising at least one main rotor blade;
a pilot input device; and
a boost actuator in mechanical communication between the pilot input device and the main rotor system, the boost actuator
comprising:

an input member configured to receive an input from the pilot input device;
a driving member configured to receive mechanical energy from a power source;
a driven member;
a magnetorheological (MR) fluid disposed between the driving member and the driven member and configured to transmit a variable
amount of mechanical energy from the driving member to the driven member;

an output member coupled to the driven member; and
a magnetic field system comprising a first device coupled to one of the input member and the output member, a second device
coupled to the other of the input member and the output member, and a magnetic component configured to deliver a magnetic
field towards the MR fluid, the strength of magnetic field delivered to the MR fluid varying based on the relative positions
of the first and second devices.

US Pat. No. 9,067,676

CONVERTIBLE HELICOPTER RING MEMBER

Bell Helicopter Textron I...

1. A helicopter ring member comprising:
a ring member comprising an inner circumference, the ring member to be oriented substantially in-plane with a tail rotor of
a helicopter during a first mode of helicopter operation, wherein the first mode of helicopter operation is a hover mode,
the ring member to be oriented substantially off-plane with the tail rotor of the helicopter during a second mode of helicopter
operation that is different from the first mode.

US Pat. No. 9,156,545

FOLDING OF ROTORCRAFT ROTOR BLADES

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a wing coupled to the body;
a power train coupled to at least one of the body or the wing and comprising a power source and a shaft in mechanical communication
with the power source;

a tiltrotor assembly pivotally coupled to the wing and in mechanical communication with the shaft, the tiltrotor assembly
comprising:

a hub in mechanical communication with the shaft;
a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation;
a swashplate comprising a rotating portion and a non-rotating portion;
a pitch link coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade; and
an actuator coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position
to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

US Pat. No. 9,255,482

ELECTRICAL WIRING SYSTEM FOR A ROTOR HUB

Bell Helicopter Textron I...

16. A rotor hub for an aircraft, the rotor hub, comprising:
a rotor mast;
a yoke coupled to the rotor mast;
a rotor blade coupled to the yoke, the rotor blade having a recessed portion at a root end portion; and
a first connector mounted to a wall of the recessed portion;
a harness coupled to a second connector, the second connector mountable to the first connector;
wherein a trailing edge portion of the recessed portion provides a housing for a slack portion of the harness as operational
centrifugal forces act to press the slack portion of the harness into the recessed portion.

US Pat. No. 9,218,693

DRIVE SYSTEM POWER MEASUREMENT AND DIAGNOSTIC SYSTEM

Bell Helicopter Textron I...

11. An apparatus comprising:
a housing;
a gearing system disposed within the housing and comprising:
a plurality of epicyclic gears rotating about a corresponding plurality of posts; and
a plurality of targets, wherein a respective target is mounted to each post, each target configured to rotate as each post
rotates;

a plurality of sensors mounted to the housing, each sensor configured to remain stationary and to sense a respective target
mounted to each post as the respective target rotates past each sensor;

a processor in electrical signal communication with the sensors; and
a user interface in signal communication with the processor.

US Pat. No. 9,086,016

FUEL DRAIN VALVE FOR A TURBINE ENGINE

Bell Helicopter Textron I...

1. A valve assembly for an engine, the valve assembly comprising:
a housing;
an in-flow port configured for connection with a drain line;
a first out-flow port configured for connection with a fuel line;
a second out-flow port configured for connection with a disposal line;
a passageway that is rotatable with a handle, the passageway being operable to redirect a flow of a fluid between the fuel
line and the disposal line; and

a water wash connection;
wherein the handle impedes attachment of the fluid source to the water wash connection when the passageway is in a position
to direct the flow of the fluid from the drain line to the fuel line.

US Pat. No. 9,156,237

ATTACHABLE ELASTOMERIC PAD

Bell Helicopter Textron I...

2. A method comprising:
calendering an elastomeric material into an elastomeric layer having a thickness that is more uniform than the elastomeric
material prior to the calendering;

vulcanizing the elastomeric layer to a composite shim comprising at least one reinforcement layer in a matrix and at least
one layer of adhesive, wherein the at least one layer of adhesive of the composite shim is on a side of the composite shim
opposed to the elastomeric layer; and

bonding the composite shim to a composite part;
wherein the composite part comprises a second matrix and at least one layer of woven fiberglass and the composite shim has
a higher elastic limit than the composite part.

US Pat. No. 9,090,026

METHOD OF SPLICING COMPOSITE CORE

Bell Helicopter Textron I...

1. A method of splicing together a first composite core and a second composite core, the method comprising:
positioning the first composite core adjacent to the second composite core, the first composite core and the second composite
core each having a plurality of enclosed cell members extending between an upper surface network and a lower surface network,
the first composite core and the second composite core each also having a plurality of flanges that are unenclosed extensions
of the plurality of enclosed cell members, the plurality of flanges extend between the upper surface network and the lower
surface network, wherein the positioning the first composite core adjacent to the second composite core includes overlapping
the first flange and the second flange so as to define bond surfaces on the first flange and the second flange as the portions
on the first flange and the second flange that overlap;

applying an adhesive to at least one of the bond surfaces of the first flange and the and the second flange; and
locating a first magnet adjacent to the first flange and locating a second member adjacent to the second flange, the first
magnet and the second member being located opposite to the bond surfaces of the first flange and the second flange, the first
magnet and the second member positioned to provide a pressure on the adhesive as the first magnet and the second member are
magnetically attracted to each other.

US Pat. No. 9,156,239

METHOD OF MANUFACTURING NET EDGE CORE AND A METHOD OF BONDING NET EDGE CORE TO A SUBSTRUCTURE

Bell Helicopter Textron I...

1. A method of manufacturing a net edge composite core, the method comprising:
wrapping a plurality of full size mandrels with a composite material to form wrapped full size mandrels;
wrapping a plurality of partial mandrels with the composite material to form wrapped partial mandrels;
assembling the wrapped full size mandrels and the wrapped partial mandrels;
locating a supplemental partial mandrel next to each wrapped partial mandrel;
curing the wrapped full size mandrels and the wrapped partial mandrels in a tool; and
removing full size mandrels and the partial mandrels.

US Pat. No. 9,157,372

SERIES BATTERY START CONTROLLER

Bell Helicopter Textron I...

1. An apparatus, comprising:
a series switching logic;
a relay control switch electrically coupled to the series switching logic;
a series-parallel relay electrically coupled to the relay control switch, wherein the series-parallel relay is configured
to selectively configure a plurality of batteries between a series and parallel connection; and

a cutoff switch, wherein the cutoff switch is electrically coupled to the relay control switch and series switching logic,
and wherein the cutoff switch is electrically coupled to a battery relay input.

US Pat. No. 9,157,474

SYSTEM AND METHOD OF MONITORING WEAR IN A BEARING

Bell Helicopter Textron I...

1. A bearing, comprising:
a ball member;
a race;
a liner located on an interior surface of the race, the liner having a first surface bonded to an interior surface of the
race, the liner having a second surface that is adjacent to the ball member; and

a wafer having a wear surface that is aligned with the second surface of the liner, the wafer being an electrically conductive
member with an initial resistance;

wherein a wear inducing operation causes the wafer to wear along with the liner, thus causing a decrease of the initial resistance
such that an amount of the decrease of the initial resistance is indicative of an amount of wear of the liner.

US Pat. No. 9,151,162

PREVENTING ROTATION OF A FIXED RING OF A SWASHPLATE

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a gearbox surrounding a portion of the drive shaft;
a hub;
a rotor blade coupled to the hub;
an anti-rotation sleeve coupled to the gearbox and featuring an outer recess portion;
a tilt sleeve positioned about the anti-rotation sleeve and having an opening therethrough, wherein the tilt sleeve is configured
to slide in a strictly axial direction relative to the anti-rotation sleeve;

a first swashplate ring positioned about the tilt sleeve and featuring an inner recess portion;
an anti-rotation mechanism disposed through the opening and at least partially in the outer recess portion and the inner recess
portion, the anti-rotation mechanism operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve,
the anti-rotation mechanism comprising:

a pin disposed through the opening and at least partially in the outer recess portion and the inner recess portion;
a key disposed at least partially in the outer recess portion and the opening and configured to receive the pin; and
a nut at least partially disposed in the outer recess portion and coupling the pin to the key; and
a second swashplate ring positioned about the first swashplate ring and rotatable about the anti-rotation sleeve with rotation
of the plurality of rotor blades.

US Pat. No. 9,090,329

LOW PROFILE JETTISONABLE DOOR SYSTEM

Bell Helicopter Textron I...

1. A jettisonable door system for an aircraft, the jettisonable door system comprising:
a door;
an upper hinge having a forward portion that is hingedly coupled to an airframe of the aircraft, the upper hinge having an
aft portion that is releasably secured to an upper outboard plate of the door with an upper pin;

a lower hinge having a forward portion that is hingedly coupled to the airframe of the aircraft, the lower hinge having an
aft portion that is releasably secured to a lower outboard plate of the door with a lower pin, the lower pin having a lobe
member that forms an oblong extension from an axis of rotation of the lower pin; and

a handle operably associated with the upper pin, such that a rotation of the handle causes the upper pin to rotate;
an upper wire having a length extending between a first end portion and a second end portion, the first end portion coupled
to the handle at an upper point offset from a handle axis of rotation, the second end portion being coupled to the lobe member
at a lower point offset from the axis of rotation of the lower pin, such that a rotation of the handle translates the upper
wire and rotates the lobe member about the axis of rotation of the lower pin, thus simultaneously causing both the upper hinge
and the lower hinge to release from the door.

US Pat. No. 9,376,206

TILTROTOR AIRCRAFT WITH INBOARD WING MOUNTED FIXED ENGINE ARRANGEMENT

Bell Helicopter Textron I...

1. A rotor system for tilt rotor aircraft, the rotor system comprising:
an engine disposed at a first fixed position above a wing member, wherein the engine is disposed adjacent to and above a fuselage
of the tilt rotor aircraft, wherein the wing member is rotatable coupled to the fuselage, and the wing member is configured
to rotate relative to the fuselage and align a width of the wing member with a longitudinal axis of the fuselage; and

a prop-rotor pylon mechanically coupled to the engine along a drive path extending through the wing member, wherein the prop-rotor
pylon is configured to selectively rotate between a vertical position and a horizontal position, and wherein the prop-rotor
pylon is coupled to a plurality of rotor blades.

US Pat. No. 9,365,022

SYSTEM AND METHOD OF POST-CURE PROCESSING OF COMPOSITE CORE

Bell Helicopter Textron I...

14. A method processing a first bulk composite core and a second bulk composite core, the method comprising the steps of:
applying an adhesive to a first surface network of the first bulk composite core, the first surface network being an exposed
surface at a first termination end of a plurality of cell members of the first bulk composite core;

inserting a plurality of mandrels into the plurality of cell members of the first bulk composite core and a plurality of cell
members of the second bulk composite core, thereby aligning the cell members of the first bulk composite core to the cell
members of the second bulk composite core, the second bulk composite core having a second surface network that is an exposed
surface at a first termination end of a plurality of cell members of the second bulk composite core;

pressing together the first surface network of the first bulk composite core and the second surface network of the second
bulk composite core together with the adhesive located therebetween;

curing the adhesive;
removing the plurality of mandrels; and
cutting through at least one of the first bulk composite core and the second bulk composite core so as to create a wafer therefrom.

US Pat. No. 9,327,831

ROTORCRAFT FLAPPING LOCK

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a wing coupled to the body;
a power train coupled to at least one of the body or the wing and comprising a power source and a shaft in mechanical communication
with the power source;

a tiltrotor assembly pivotally coupled to the wing and
in mechanical communication with the shaft, the tiltrotor assembly comprising:
a hub in mechanical communication with the shaft;
a rotor blade in mechanical communication with the hub;
a flapping lock deployable in a locked position in an unlocked position, the flapping lock operable in the locked position
to prevent at least some flapping movement of the hub relative to the shaft, the flapping lock operable in the unlocked position
to allow the at least some flapping movement of the hub relative to the shaft; and

the flapping lock comprising an actuator, a downstop in mechanical communication with the shaft, and a flapping stop in mechanical
communication with the hub.

US Pat. No. 9,156,567

SYSTEM AND METHOD FOR ECONOMIC USAGE OF AN AIRCRAFT

Bell Helicopter Textron I...

1. A system for an aircraft, the system comprising:
a processor for calculating a rate of damage of a component of the aircraft by analyzing a usage data in an algorithm; and
an output device for communicating an operational change that affects the rate of damage of the component of the aircraft;
wherein the rate of damage is a rate of maintenance inducing operation.

US Pat. No. 9,051,986

HYBRID FLUID ELASTOMERIC DAMPER

Bell Helicopter Textron I...

1. A system, comprising:
a damper, having:
a housing;
a piston elastically attached to an inner surface of the housing via an elastomeric material; and
a first fluid chamber and a second fluid chamber positioned within the piston, and on opposing ends of the piston, and in
fluid communication with each other via a fluid passage;

a heater configured to provide heat energy to the the first fluid chamber, the heater being in fluid communication with the
first fluid chamber; and

a control subsystem operably associated with the heater and configured to regulate heat energy to the first fluid chamber.

US Pat. No. 9,353,820

ELASTOMERIC DAMPER WITH HEATER

Bell Helicopter Textron I...

1. A damper system, comprising:
a damper having:
a first fluid chamber and a second fluid channel fluidly connected to each other via a fluid passage;
a housing; and
a piston disposed within the housing;
wherein the piston is configured to dampen a force exerted on the damper;
wherein the piston forms the first fluid chamber and the second fluid chamber; and
wherein fluid passages between the first fluid chamber and the second fluid chamber as the piston moves within the housing;
a heater having a plurality of coils operably associated with the damper, the plurality of coils being positioned with in
the first chamber; and

a control subsystem operably associated with the heater;
wherein the heater is configured to provide heat energy to a fluid passing between the first fluid chamber and the second
fluid chamber; and

wherein the control subsystem is configured to regulate the amount of heat energy to the damper.

US Pat. No. 9,376,205

RADIAL FLUID DEVICE WITH VARIABLE PHASE AND AMPLITUDE

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train, the rotor system comprising a rotor blade;
an actuator coupled to and operable to move the rotor blade; and
a radial fluid device in fluid communication with the actuator, the radial fluid device comprising:
a cylinder block comprising a first plurality of radially extending cylinders and a second plurality of radially extending
cylinders, wherein the cylinder block, the first plurality of radially extending cylinders, and the second plurality of radially
extending cylinders are rotatable;

a first plurality of pistons each slidably received within a different one of the first plurality of radially extending cylinders;
a second plurality of pistons each slidably received within a different one of the second plurality of radially extending
cylinders;

a first cam disposed about the first plurality of radially extending cylinders and rotatable in a first direction and in a
second direction opposite the first direction; and

a second cam disposed about the second plurality of radially extending cylinders and rotatable in the first direction and
the second direction, wherein the direction of rotation of the second cam is independent of the direction of rotation of the
first cam.

US Pat. No. 9,327,832

ELASTOMERIC BEARING WITH TAPERED SHIMS

Bell Helicopter Textron I...

1. A bearing comprising:
a base member;
a cap member;
alternating separate non-continuous layers of shim members and elastomeric members between the base member and a support member,
the shim members being tapered;

wherein the bearing is a centrifugal force bearing for a rotor hub; and
wherein the shim members are tapered such that a narrow portion is located near an outer portion of the bearing.

US Pat. No. 9,267,561

ROTOR BRAKE CONTROL SYSTEM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a main rotor system coupled to the power train, the main rotor system comprising at least one main rotor blade;
a rotor brake system coupled to the power train, the rotor brake system comprising at least one caliper, at least one brake
pad, and a rotor brake in mechanical communication with the drive shaft; and

a rotor brake control system comprising:
a temperature sensor operable to measure an operating temperature of the rotor brake; and
a rotor brake control unit operable to instruct the at least one caliper to adjust, based on the measured operating temperature,
an amount of friction generated between the at least one brake pad and the rotor brake by instructing the at least one caliper
to increase the amount of friction generated between the at least one brake pad and the rotor brake if the measured operated
temperature is less than a preferred value and instructing the at least one caliper to decrease the amount of friction generated
between the at least one brake pad and the rotor brake if the measured operated temperature is greater than the preferred
value.

US Pat. No. 9,096,327

AIRCRAFT HEALTH ASSESSMENT SYSTEM

Bell Helicopter Textron I...

1. A system for assessing health of a rotorcraft, comprising:
a rotorcraft comprising a body, a power train coupled to the body and comprising a power source and a drive shaft coupled
to the power source, a hub, a rotor blade coupled to the hub, and one or more flight measurement sensors operable to provide
a plurality of measurements associated with two or more flight parameters, the plurality of measurements comprising measurements
spanning at least one period of time, the two or more flight parameters comprising a first parameter and a second parameter;
and

a health assessment system comprising:
a flight spectrum analyzer operable to determine, based on a comparison of the plurality of measurements to a plurality of
flight spectrum definitions, an amount of time the rotorcraft spent in each flight spectrum of a plurality of flight spectrums
during the at least one period of time by:

organizing the plurality of measurements spanning the at least one period of time into a plurality of time segments;
eliminating, for each time segment, at least some flight spectrums based on the received measurements associated with the
first flight parameter to yield a smaller subset of potential flight spectrums; and

assigning each time segment to a flight spectrum within the smaller subset of potential flight spectrums based on the measurements
associated with the second flight parameter; and

a health assessment analyzer operable to assess a change in health of the rotorcraft over the at least one period of time
based on the determination of the amount of time the rotorcraft spent in each flight spectrum and a plurality of spectrum
health profiles, each spectrum health profile defined for a corresponding flight spectrum.

US Pat. No. 9,346,561

MEASUREMENT OF COUPLING MISALIGNMENT OF A DRIVESHAFT

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a rotor system comprising a pylon, a hub disposed adjacent to the pylon, and a rotor blade in mechanical communication with
the hub;

an engine;
a drive shaft in mechanical communication with the power hub and the engine and configured to rotate the hub in response to
receiving rotational energy from the engine;

a flexible coupling coupled to the drive shaft and disposed between the engine and the pylon, the flexible coupling configured
to rotate with the drive shaft and comprising a flexure portion configured to flex in response to a difference in alignment
between the a rotational axis associated with the engine and a rotational axis associated with the pylon, the difference in
alignment occurring when the engine and the pylon are positioned such that the rotational axis associated with the engine
and the rotational axis associated with the pylon are not coaxial; and

a measurement system configured to measure the difference in alignment occurring when the engine and the pylon are positioned
such that the rotational axis associated with the engine and the rotational axis associated with the pylon are not coaxial,
the measurement system comprising:

a reference device;
a sensor situated opposite the flexure from the reference device and configured to receive a signal from the reference device
indicative of a distance between the reference device and the sensor; and

a misalignment measurement system configured to generate, in response to the signal, a misalignment value that represents
the difference in alignment occurring when the engine and the pylon are positioned such that the rotational axis associated
with the engine and the rotational axis associated with the pylon are not coaxial.

US Pat. No. 9,120,255

COMPOSITE CORE AND METHOD OF MAKING SAME

Bell Helicopter Textron I...

1. A method of wrapping a plurality of mandrels with a composite material, the method comprising:
rotating each mandrel at a rotational speed;
translating each mandrel at a translational speed;
positioning each mandrel back to back such that an aft face of a preceding mandrel is approximate to a forward face of a trailing
mandrel;

sequentially wrapping each mandrel with the composite material in a helical orientation by selectively positioning a feed
head at a wrap angle relative to a translation axis of the plurality of mandrels;

compacting the composite material of each mandrel via a compactor that includes pads that travel in an axial direction of
the mandrel and rotate at the same speed as the mandrel, the pads of the compactor pressing against external surfaces of the
composite material near aft and forward portions of the mandrel prior to a cutting of the composite material in order to prevent
the composite material from unraveling; and

moving the compactor back to align with the next wrapped mandrel.

US Pat. No. 9,269,147

VISUAL SIGNATURE DETERMINATION SYSTEM FOR MOVING TARGETS

Bell Helicopter Textron I...

1. A method for measuring a visual signature of a moving target, comprising:
measuring, using a visual-band photometer, an optical property of a moving target while the target moves along a path from
a start position to an end position in front of a background, wherein the optical property of the moving target is an optical
property in the visual-light band, wherein measuring the optical property of the moving target while the target moves along
the path from the start position to the end position in front of the background comprises:

measuring the optical property of the moving target at desired trigger points while the target moves along the path from the
start position to the end position in front of the background; and

recording the measurements at the desired trigger points as a function of time;
repositioning the visual-band photometer to measure optical properties of the background at the start position;
measuring, using the visual-band photometer, the optical property of the background along the path between the start position
and the end position, wherein the optical property of the background is an optical property in the visual-light band; and

determining the visual signature of the moving target by comparing the measured optical property of the moving target along
the path to the measured optical property of the background along the path.

US Pat. No. 9,068,908

SYSTEM AND METHOD FOR IMPROVING A WORKPIECE

Bell Helicopter Textron I...

1. A method of modifying a workpiece, comprising:
providing a workpiece;
determining a tensile load stress profile associated with a tensile load condition, the tensile load stress profile comprising
a tensile load stress beyond a tensile stress limit of the workpiece;

determining a compressive load stress profile associated with a compressive load condition, the compressive load stress profile
comprising a compressive load stress within a compressive stress limit of the workpiece;

determining a residual stress profile, the residual stress profile comprising a residual stress within the tensile stress
limit of the workpiece, wherein a sum of the tensile stress and the residual stress is within the tensile stress limit and
a sum of the compressive stress and the residual stress is within the compressive stress limit of the workpiece; and

providing the workpiece with the residual stress profile.

US Pat. No. 9,056,675

PILOT CONTROL SYSTEM WITH HAND REST

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train and comprising a plurality of rotor blades;
a control assembly, comprising:
a post having a top, a bottom, and a body joining the top to the bottom;
a grip positioned at least partially above the post, the grip being movable along at least one arc; and
a hand rest covering the top of the post and situated at least partially under the grip without physically contacting the
grip, the hand rest comprising an upper surface having a profile corresponding to the at least one arc;

a rotorcraft control system operable to communicate commands to the rotor system based on movements of the grip; and
at least one linkage disposed at least in part within the body;
a shaft having a first end coupled to the at least one linkage proximate to the body below the top and a second end opposite
the first end coupled to the grip, the shaft positioning at least part of the grip directly over the to of the post.

US Pat. No. 9,108,395

SINGLE VACUUM DEBULK COMPOSITE PANEL REPAIR

BELL HELICOPTER TEXTRON I...

1. A method of attaching a composite member to a structure, comprising:
applying heat at a first temperature to an impregnated laminate within a single vacuum enclosure, the impregnated laminate
being formed by impregnating with resin a fabric laminate;

applying a partial vacuum at a first vacuum pressure within the single vacuum enclosure to the impregnated laminate to degas
the resin in the impregnated laminate and form a degassed,? impregnated laminate;

positioning the degassed, impregnated laminate on a structure; and
curing the degassed, impregnated laminate on the structure by applying heat at a second temperature and by applying vacuum
at a second vacuum pressure within the single vacuum enclosure, the second vacuum pressure greater than the first vacuum pressure.

US Pat. No. 9,051,055

SYSTEM AND METHOD OF ADAPTIVELY GOVERNING ROTOR SPEED FOR OPTIMAL PERFORMANCE

Bell Helicopter Textron I...

15. A system for adaptively governing a speed of a rotor assembly in an aircraft, the system comprising:
a processor;
a plurality of sensors configured for measuring the receivable data; and
an actuator system configured for making a collective pitch change to a plurality of rotor blades in the rotor assembly;
wherein the processor is configured to:
calculate a first power available by comparing at least one of:
an actual transmission torque to a transmission torque limit; and
an actual rotor speed to a rotor speed limit;
calculate a second power available by comparing at least one of:
an actual engine exhaust temperature to an engine exhaust temperature limit; and
an actual engine gas generator speed to an engine gas generator speed limit;
wherein the processor is also configured make a collective pitch change command when the first power available is less than
the second power available, and wherein the processor is configured to make an engine power change command when the first
power available is greater than the second power available.

US Pat. No. 9,145,946

ACTIVE VIBRATION ISOLATION SYSTEM

Bell Helicopter Textron I...

1. An apparatus comprising:
an active vibration isolation system, comprising:
a vibration isolator to flow a tuning fluid;
a dual fluid pump in fluid communication with the vibration isolator to flow the tuning fluid through the vibration isolator;
an electro-hydraulic servo valve in fluid communication with the dual fluid pump to provide a hydraulic fluid to drive he
dual fluid pump, the dual fluid pump to segregate the tuning fluid from the hydraulic fluid; and

a hydraulic system configured to provide the hydraulic fluid to the electro-hydraulic servo valve.

US Pat. No. 9,069,372

CUSTOMIZABLE PEDAL SYSTEM

BELL HELICOPTER TEXTRON I...

1. A pedal system comprising:
a support base;
a first lever comprising a root portion and a terminal portion formed such that the terminal portion interfaces with the root
portion at a bend in the first lever of a first predetermined angle, the root portion of the first lever being pivotally mounted
to the support base such that the first lever is rotatable in a first plane of rotation about an axis of rotation at or near
the support base;

a second lever comprising a root portion and a terminal portion formed such that the terminal portion interfaces with the
root portion at a bend in the second lever of a second predetermined angle, the root portion of the second lever being pivotally
mounted to the support base such that the second lever is rotatable in a second plane of rotation about the axis of rotation,
wherein the second plane of rotation is substantially parallel to the first plane of rotation and wherein the first plane
of rotation is separate from the second plane of rotation;

a first pedal configured to be engaged by a foot of a user to rotate the first lever about the axis of rotation, the first
pedal being attached to the first lever to extend therefrom in a direction that is (i) away from the second lever, and (ii)
substantially parallel to the axis of rotation, the first pedal being attached to the first lever such that the position of
the first pedal is adjustable along the terminal portion of the first lever;

a second pedal configured to be engaged by a foot of the user to rotate the second lever about the axis of rotation, the second
pedal being attached to the second lever to extend therefrom in a direction that is (i) away from the first lever, and (ii)
substantially parallel to the axis of rotation, the second pedal being attached to the second lever such that the position
of the second pedal is adjustable along the terminal portion of the second lever separate from the adjustment of the first
pedal along the terminal portion of the first lever,

wherein, if no external force is applied to the first lever, the first lever is held at a default rotational orientation about
the axis of rotation and, if no external force is applied to the second lever, the second lever is held at the same default
rotational orientation about the axis of rotation, the pedal system further comprising an adjustment assembly that enables
the user to adjust the same default rotational orientation of the first and the second lever.

US Pat. No. 9,290,266

SPEED CONTROL ASSEMBLY AND METHODS OF USING SAME

Bell Helicopter Textron I...

1. A speed control assembly, comprising:
an input drive shaft coupled to a first gear subassembly comprising a rotatable gear;
a second gear subassembly coupled to an output drive shaft; and
a linkage coupling the first gear subassembly to the second gear subassembly,
wherein the input drive shaft, the first gear subassembly, the second-gear subassembly, and the linkage are configured such
that a rotational speed of the rotatable gear adjusts a ratio of a speed of the output drive shaft to a speed of the input
drive shaft; and

wherein the second gear subassembly comprises a second epicyclic gear subassembly comprising a sun gear coupled to the output
drive shaft, one or more planet gears, and a fixed ring gear.

US Pat. No. 9,248,759

VEHICLE CREWSTATION SEAT ASSEMBLY

Bell Helicopter Textron I...

1. A movable seat assembly for a vehicle, the moveable seat assembly comprising:
a first and second predetermined paths located on a floor of the vehicle, each having an operational location at a first end,
and an ingress/egress location at a second, the first and second predetermined paths being substantially adjacent in position
and substantially mirrored in orientation;

a first and second seats that travel along the first and second predetermined paths, respectively, between the operational
location and the ingress/egress location;

wherein each of the first and second seats has an operational orientation at the operational location of its respective predetermined
path, and an ingress/egress seat orientation at the ingress/egress location of its respective predetermined path; each ingress/egress
seat orientation being substantially angled relative to its respective operational seat orientation;

wherein at least one of the first and second predetermined paths comprises a substantially straight track and two or more
other tracks each having a curved portion;

a mounting plate provided to translate aft along the substantially straight track during egress; and
an end of the substantially straight track including an endstop, the endstop defining a pivot point about which the mounting
plate rotates according to a path defined by the two or more other tracks each having a curved portion.

US Pat. No. 9,464,532

SYSTEM AND METHOD FOR REDUCING ROTOR BLADE NOISE

Bell Helicopter Textron I...

1. A rotor blade, comprising:
an active flap; and
an airflow disturber disposed at least partially on the active flap and selectively extending from a surface profile of the
active flap, the airflow disturber comprising a wedge disturber having a triangular profile, wherein a point of the triangular
profile points toward a leading edge of the rotor blade, the airflow disturber configured to selectively alter airflow across
the active flap; and

wherein the airflow disturber is selectively extendible between a first stowed position that does not extend beyond the surface
profile of the active flap, a second deployed position of the airflow disturber that extends beyond the surface profile of
the active flap, and a third partially deployed position of the active flap between the first stowed position and the second
deployed position.

US Pat. No. 9,254,914

HELICOPTER TRANSMISSION MOUNT SYSTEM

Bell Helicopter Textron I...

1. An Aircraft transmission restraint system, wherein the restraint system comprising: a first strut having a first piston
resiliently coupled to a first housing with a first elastomeric member, wherein the first housing, the first piston, and the
first elastomeric member form a first fluid chamber; a second strut having a second piston resiliently coupled to a second
housing with a second elastomeric member, wherein the second housing, the second piston, and the second elastomeric member
form a second fluid chamber; a fluid line placing the first fluid chamber and the second fluid chamber in fluid communication;
a fluid in the first fluid chamber, the second fluid chamber, and the fluid line; wherein an actuation of the first piston
and the second piston in a first direction causes a portion of the fluid to move into one of the first fluid chamber and the
second fluid chamber.

US Pat. No. 9,180,965

ACTUATION SYSTEM FOR AN ACTIVE ELEMENT IN A ROTOR BLADE

Bell Helicopter Textron I...

1. An actuation system configured for actuating a moveable airfoil surface on a rotor blade, the actuation system comprising:
a first bearing and a second bearing;
an upper drive tape and a lower drive tape each coupled to the second bearing, the upper drive tape being elastically deformable
and at least partially in contact with the first bearing and the second bearing, the lower drive tape being elastically deformable
and at least partially in contact with the first bearing and the second bearing;

a first linear actuator and a second linear actuator;
an inboard frame operably associated with the first linear actuator, the inboard frame being coupled to the upper drive tape;
an outboard frame operably associated with the second linear actuator, the outboard frame being coupled to the lower drive
tape; and

an input lever coupled to the upper drive tape and the lower drive tape;
wherein a reciprocal translation of the inboard frame and the outboard frame results in a movement of the input lever.

US Pat. No. 9,061,760

INDEPENDENT BLADE CONTROL SYSTEM WITH ROTARY BLADE ACTUATOR

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train and comprising a rotor blade; and
a rotary actuator coupled to the at least one rotor blade, the rotary actuator comprising:
a housing comprising a first chamber and a second chamber, wherein the first chamber features a first fluid opening and a
second fluid opening and the second chamber features a third fluid opening and a fourth fluid opening;

a first fluid source in fluid communication with the first and third fluid openings and configured to provide a first fluid
to the first chamber and the second chamber at a first pressure;

a second fluid source in fluid communication with the second fluid opening and configured to provide a second fluid to the
first chamber at a second pressure;

a third fluid source in fluid communication with the fourth fluid opening and configured to provide a third fluid to the second
chamber at a third pressure different than the second pressure;

a vane disposed within the housing, the vane comprising a first vane surface disposed within the first chamber between the
first fluid opening and the second fluid opening and a second vane surface disposed within the second chamber between the
third fluid opening and the fourth fluid opening; and

a shaft disposed at least partially within the housing and coupled to the vane, wherein the shaft is coupled to the rotor
blade such that the shaft transfers movement of the vane to the rotor blade.

US Pat. No. 9,476,312

SWASHPLATELESS ACTIVE BLADE PITCH CONTROL WITH A MECHANICAL DELTA-3 RESTRAINT HAVING AN INSTANTANEOUS BLADE PITCH-FLAP COUPLING RESPONSE

BELL HELICOPTER TEXTRON I...

1. An apparatus comprising:
a hub configured to couple to a mast;
a grip configured to couple to the hub and a rotor blade;
a pitch actuator coupled to the grip and configured to change a pitch of the rotor blade relative to the mast; and
a delta-3 restraint coupled to the pitch actuator, wherein the delta-3 restraint is fixed relative to the mast, the delta-3
restraint configured to change the blade pitch in response to flapping of the blade.

US Pat. No. 9,316,573

NON-METALLIC DEBRIS MONITORING SYSTEM

Bell Helicopter Textron I...

1. A system to detect particles in a fluid stream, comprising:
a separator configured to separate particles from bubbles passing through the fluid stream, the separator having:
a plurality of coils that form a first channel and a second channel;
a sensor configured to detect the particles; and
a monitoring chamber in fluid communication with both the first channel and the second channel;
wherein the sensor is positioned such that a field of vision extends through the monitoring chamber.

US Pat. No. 9,162,752

FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD

Bell Helicopter Textron I...

1. A method to control hovering flight of a rotary aircraft, the rotary aircraft having a longitudinal controller and a lateral
controller, the method comprising:
defining a first flight envelope having a first groundspeed threshold;
defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the
first envelope;

engaging an automatic hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope;
engaging an automatic position hold with a control law position hold architecture as the aircraft enters the second flight
envelope; and

interchanging the automatic hover hold and the automatic position hold as the rotary aircraft moves between the first flight
envelope and the second flight envelope;

wherein at least one of the engaging the automatic hover hold and the engaging an automatic position hold is performed in
response to at least one of the longitudinal controller and the lateral controller being in a detent position.

US Pat. No. 9,249,856

LIQUID INERTIA VIBRATION MOUNT

Bell Helicopter Textron I...

1. A vibration isolator, comprising:
an upper housing defining an upper fluid chamber;
a lower housing defining a lower fluid chamber;
a piston resiliently coupled to the upper housing with an upper elastomer member, the piston being resiliently coupled to
the lower housing with a lower elastomer member;

a tuning passage associated with the piston; and
a tuning fluid disposed within the upper fluid chamber, the lower fluid chamber, and the tuning passage, the tuning fluid
comprising a polytungstate;

wherein a density of the tuning fluid is selectively tailored in response to a tolerance variation in a size of the tuning
passage.

US Pat. No. 9,193,454

SYSTEM AND METHOD FOR PROVIDING FOR COLLECTIVE CONTROL IN AN AIRCRAFT

Bell Helicopter Textron I...

1. A trunnion, comprising:
a first portion operable to couple directly to a drive tube of an aircraft, wherein the drive tube is operable to rotate around
a first axis, the drive tube comprising:

a top end;
a bottom end opposed to the top end;
a cylindrical body having a side surface interposed between the top end and the bottom end; and
a second portion operable to couple to a swash plate of the aircraft, wherein the swash plate is operable to cause a pitch
of at least one of a plurality of aircraft blades to change;

wherein the first portion is operable to couple directly to the side surface of the cylindrical body of the drive tube without
mounting to the top end or the bottom end of the drive tube;

wherein the trunnion is operable to simultaneously change the pitch of the plurality of aircraft blades by sliding along the
first axis of the drive tube of the aircraft;

wherein the swashplate is operable to slide along the first axis of the drive tube with the trunnion.

US Pat. No. 9,399,511

ROTORCRAFT FLY-BY-WIRE CONTROL LAWS

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train and comprising a plurality of rotor blades;
a flight control system operable to change at least one operating condition of the rotor system;
a pilot control assembly configured to receive commands from a pilot, wherein the flight control system is a fly-by-wire flight
control system in electrical communication with the pilot control assembly; and

a flight control computer is in electrical communication between the flight control system and the pilot control assembly,
the flight control computer is configured to:

receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first
flight characteristic would result in an expected change to a second flight characteristic;

instruct, in response to the received pilot command, the flight control system to change a first operating condition of the
flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight
characteristic; and

instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second
operating condition of the flight control system to at least partially offset the expected change to the second flight characteristic
such that the flight control system at least partially decouples aircraft motions that are inherently coupled.

US Pat. No. 9,309,917

BIMETALLIC SHAFT FOR GEARBOX SYSTEMS TO LIMIT WEAR AND CORROSION

Bell Helicopter Textron I...

1. An apparatus comprising:
a housing;
a shaft protruding through an opening in the housing, the shaft comprising:
a first shaft member comprising a first material and having a first shaft axis, a first distal end having a first diameter,
and a first proximate end, wherein the first shaft member is disposed within the housing;

a second shaft member comprising a second material different from the first material, and having a second shaft axis, a second
proximate end having a second diameter, and a second distal end, wherein the second shaft member protrudes out of the housing;
and

a joint that permanently affixes the first distal end of the first shaft member to the second proximate end of the second
shaft member such that the first shaft axis is aligned with the second shaft axis, wherein the first distal end substantially
abuts the second proximate end, and wherein the first diameter is substantially identical to the second diameter; and

a seal sealing against an outer diameter of the second shaft member at a location at which the second shaft member protrudes
out of the housing.

US Pat. No. 9,180,964

AUTOROTATIVE ENHANCEMENT SYSTEM

Bell Helicopter Textron I...

1. An aircraft comprising:
a transmission having a driveshaft configured to couple to an engine;
a mast configured to couple to a plurality of rotor blades; and
an autorotative assist unit coupled to the transmission, the autorotative assist unit comprising:
a motor-generator or a hydraulic pump-motor; and
an energy storage unit coupled to the motor-generator or the hydraulic pump-motor,
wherein, during normal operation of the aircraft, the motor-generator or the hydraulic pump-motor is configured to convert
energy from the transmission into electrical energy or hydraulic energy, respectively, and the energy storage unit is configured
to receive and store the electrical energy or the hydraulic energy, respectively, and

wherein, upon loss of engine power, the energy storage unit is configured to provide the stored energy to the motor-generator
or the hydraulic pump-motor, and the motor-generator or the hydraulic pump-motor is configured to be powered by the energy
received from the energy storage unit to drive the rotor blades through the transmission to provide supplemental autorotative
assistance.

US Pat. No. 9,149,999

METHOD OF REPAIRING, SPLICING, JOINING, MACHINING, AND STABILIZING HONEYCOMB CORE USING POURABLE STRUCTURAL FOAM AND A STRUCTURE INCORPORATING THE SAME

Bell Helicopter Textron I...

1. A core stiffened structure comprising:
a skin having an airfoil shaped profile so as to have a leading edge portion, an upper portion, a lower portion, and a trailing
edge portion, the skin having outer surface and an inner surface thereby forming a skin thickness therebetween;

an inner support having an upper member, a lower member, a forward member, and an aft member which collectively form a hollow
void therebetween;

an upper core member having a plurality of columnar cell members that collectively have an upper surface network and a lower
surface network, whereby the upper surface network of the upper core member is bonded to the inner surface of the upper portion
of the skin and whereby the lower surface network of the upper core member is bonded to the upper member of the inner support;

a lower core member having a plurality of columnar cell members that collectively have an upper surface network and a lower
surface network, whereby the upper surface network of the lower core member is bonded to the lower member of the inner support
and whereby the lower surface network of the lower core member is bonded to the inner surface of the lower portion of the
skin;

a forward foam member bonded to a forward surface of the plurality of columnar cell members of the upper core member, a forward
surface of the plurality of columnar cell members of the lower core member, and the forward member of the inner support; and

an aft foam member bonded to an aft surface of the plurality of columnar cell members of the upper core member, an aft surface
of the plurality of columnar cell members of the lower core member, and the aft member of the inner support;

wherein the forward foam member joins by contact the upper core member and the lower core member.

US Pat. No. 9,254,915

ROTOR SYSTEM WITH TORQUE-SPLITTER ASSEMBLY

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft in mechanical communication with the power
source;

a rotor blade; and
a rotor head coupling the rotor blade to the power source, the rotor head comprising:
a yoke disposed about the drive shaft and coupled to the rotor blade;
a torque-splitter assembly comprising:
a spline assembly configured to receive the drive shaft through a first opening, the spline assembly having a first plurality
of outer splines oriented in a first direction and a second plurality of outer splines oriented in a second direction different
from the first direction;

a first trunion disposed about the first plurality of outer splines; and
a second trunion disposed about the second plurality of outer splines; and
a joint assembly coupling the first and second trunions to the yoke.

US Pat. No. 9,180,966

ACTUATION SYSTEM FOR AN ACTIVE ELEMENT IN A ROTOR BLADE

Bell Helicopter Textron I...

1. A flap mechanism configured for translating a moveable airfoil surface on a rotor blade, the flap mechanism comprising:
an input lever that is rotatable about a rotational axis, the input lever being coupled to an upper drive tape and a lower
drive tape, the upper drive tape and the lower drive tape each being elastically deformable and configured to alternately
pull the input lever so that the input lever reciprocally rotates about the rotational axis; and

a clevis fitting fixed to the moveable airfoil surface, the clevis fitting also being slidingly coupled to the input lever
such that the clevis fitting allows a translation of the moveable airfoil surface in a spanwise direction relative to the
input lever, such that a rotational input from the input lever causes the moveable airfoil surface to rotate about the rotational
axis.

US Pat. No. 9,145,277

SYSTEM AND METHOD OF MANUFACTURING COMPOSITE CORE

Bell Helicopter Textron I...

1. A method of wrapping a mandrel with a composite material, the method comprising:
securing the mandrel and a first coupling with a winding jig such that the first coupling is located adjacent to a first end
of the mandrel while sharing a central axis with the mandrel, the mandrel and the first coupling each having a same hexagonal
shape and hexagonal circumference, wherein the mandrel has a hollow interior extending along a length of the mandrel to provide
a fluid passage for heating of the mandrel during a curing process;

orienting the composite material at a wrap angle to the mandrel and the first coupling and
depositing the composite material around the hexagonal circumference of the mandrel and the first coupling starting from the
first coupling, such that the composite material completely covers the hexagonal circumference of the first end of the mandrel.

US Pat. No. 9,452,843

INFLATING ROTORCRAFT EXTERNAL AIRBAGS IN STAGES

Bell Helicopter Textron I...

1. An aircraft airbag inflation system comprising:
a first airbag, a second airbag, and a third airbag each mounted on an external surface of an aircraft, each of the first
airbag, the second airbag, and the third airbag configured to inflate in one of a plurality of stages prior to the aircraft
crashing, each stage associated with a respective pressure, the plurality of stages comprising a first stage associated with
a first pressure, a second stage associated with a second pressure greater than the first pressure, and a third stage associated
with a third pressure greater than the second pressure;

a plurality of sensors disposed on-board the aircraft and configured to sense a plurality of aircraft velocities and an aircraft
attitude; and

a controller disposed on-board the aircraft and configured to perform operations comprising:
receiving a plurality of signals from the plurality of sensors, the plurality of signals representing the plurality of aircraft
velocities and the aircraft attitude sensed by the plurality of sensors,

determining a crash event for the aircraft based on the received plurality of signals, the crash event comprising an aircraft
sink rate, an aircraft attitude at crash time, and an aircraft distance from an impact surface, and

determining a stage at which the airbags are to be inflated based on the crash event, comprising determining, based on the
determined crash event, that the first airbag is to be inflated to the first stage, the second airbag is to be inflated to
the second stage, and the third airbag is to be inflated to the third stage.

US Pat. No. 9,193,450

SYSTEM AND METHOD FOR AUTOMATION OF ROTORCRAFT ENTRY INTO AUTOROTATION AND MAINTENANCE OF STABILIZED AUTOROTATION

Bell Helicopter Textron I...

1. A method of automating an autorotation in an aircraft, the method comprising:
recognizing a failure of an engine;
analyzing a flight condition of the aircraft;
actuating a swashplate mechanism with a direct command from a flight control computer to an actuator coupled to the swashplate
mechanism so as to change a pitch of a plurality of main rotor blades to a predetermined collective pitch value, the predetermined
collective pitch value being chosen by the flight control computer referring to a look-up table containing desired collective
pitch values for a variety of aircraft flight conditions; and

temporarily pausing the step of actuating the swashplate for a period of time after a pilot has made an overriding command.

US Pat. No. 9,211,618

METHOD OF SECURING COMPOSITE CORE DURING A MANUFACTURING PROCESS

Bell Helicopter Textron I...

1. A method of carving a contour surface on a composite core, the method comprising:
positioning a first edge of the composite core against a first tooled member;
locating a first magnet within an outer cell member along the first edge of the composite core so that the first edge of the
composite core is magnetically drawn to the first tooled member;

locating a second magnet along a second edge of the composite core such that the second edge of the composite core is magnetically
drawn to a second tooled member; and

carving a first contour of a surface network of the composite core while the composite core is releasably secured to the first
tooled member and the second tooled member with the first magnet and the second magnet, such that the first contour is carved
while the composite core is in a tooled position that is indicative of a final desired contour in a composite structure.

US Pat. No. 9,169,010

OFFSET STACKED YOKE HUB FOR TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A rotor hub of a tiltrotor aircraft, comprising:
a first configuration of two or more yokes arranged in a first plane about a mast of the tiltrotor aircraft and having substantially
equal angular spacing therebetween;

a second configuration of an equal number of yokes as the first configuration, the equal number of yokes being arranged in
a second plane about the mast of the tiltrotor aircraft and having substantially equal angular spacing therebetween;

wherein the second plane is substantially parallel to and axially offset from the first plane; and
wherein a portion of each yoke in the first configuration overlaps with a portion of each azimuthally adjacent yoke in the
second configuration; and

a plurality of mounting plates disposed about the rotor hub, wherein each of the plurality of mounting plates includes a plurality
of mounting holes,

wherein the number of mounting holes disposed in each of the plurality of mounting plates equals a total quantity of both
the configuration yokes and the second configuration yokes.

US Pat. No. 9,162,760

RADIAL FLUID DEVICE WITH MULTI-HARMONIC OUTPUT

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train, the rotor system comprising a rotor blade;
an actuator coupled to and operable to move the rotor blade; and
a radial fluid device in fluid communication with the actuator, the radial fluid device comprising:
a cylinder block comprising a first plurality of radially extending cylinders and a second plurality of radially extending
cylinders, wherein the cylinder block is mounted for rotation;

a first plurality of pistons each slidably received within a different one of the first plurality of radially extending cylinders;
a second plurality of pistons each slidably received within a different one of the second plurality of radially extending
cylinders;

a first cam disposed about the first plurality of radially extending cylinders; and
a second cam disposed about the second plurality of radially extending cylinders, wherein the second cam has at least one
more lobe than the first cam.

US Pat. No. 9,096,325

FLY-BY-WIRE ENGINE POWER CONTROL SYSTEM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a main rotor system coupled to the power train, the main rotor system comprising at least one main rotor blade;
a pilot input device disposed within the body and comprising:
an engine power throttle adjustable among a neutral position, an increase position, and a decrease position, the pilot input
device configured to transmit a first signal in response to a pilot selection of the increase position and transmit a second
signal in response to a pilot selection of the decrease position;

a shaft coupling the engine power throttle to the body of the rotorcraft; and
a transmission wire disposed within the shaft and configured to electrically communicate signals from the engine power throttle
to an engine control unit; and

the engine control unit in electrical communication with the engine power throttle and operable to:
instruct the engine to increase power output in response to receipt of the first signal via the transmission wire; and
instruct the engine to decrease power output in response to receipt of the second signal via the transmission wire.

US Pat. No. 9,389,071

ESTIMATING THICKNESS OF A MATERIAL LAYER ON AN AIRCRAFT

Bell Helicopter Textron I...

1. A wireless system for estimating a thickness of a material layer adjacent a surface of an aircraft component, comprising:
a plurality of tag devices located between a portion of the surface of the aircraft component and the material layer adjacent
to and touching the surface of the aircraft component, the plurality of tag devices capable of wireless communication, the
material layer having a thickness that decreases over time in response to the aircraft component being used;

a transceiver configured to wirelessly communicate with the plurality of tag devices, wherein each signal strength of wireless
signals received from the plurality of tag devices and by the transceiver varies with the thickness of the material layer;
and wherein each wireless signal from a respective tag device received by the transceiver comprises tag identification information
of the respective tag device; and

one or more processors of the transceiver configured to receive the wireless signals from the plurality of tag devices, measure
a signal strength of each wireless signal from the respective tag device, triangulate a location of the transceiver relative
to the plurality of tag devices based on the signal strengths of the wireless signals and the tag identification information
received from the plurality of tag devices, and calculate the thickness of the material layer based on the signal strengths
of the wireless signals and the tag identification information, wherein the location of the transceiver is compensated for
when determining the thickness of the material layer.

US Pat. No. 9,228,571

VARIABLE RADIAL FLUID DEVICE WITH DIFFERENTIAL PISTON CONTROL

Bell Helicopter Textron I...

1. A radial fluid device comprising:
a cylinder block comprising a first plurality of radially extending cylinders and a second plurality of radially extending
cylinders forming a plurality of cylinder pairs, each cylinder pair comprising one cylinder of the first plurality and one
cylinder of the second plurality in fluid communication with the one cylinder of the first plurality, the plurality of cylinder
pairs comprising a first cylinder pair comprising a first cylinder associated with the first plurality and a second cylinder
associated with the second plurality and in fluid communication with the first cylinder;

a first plurality of cylindrical pistons each slidably received within a different one of the first plurality of radially
extending cylinders, the first plurality of cylindrical pistons comprising a first cylindrical piston slidably received within
the first cylinder, wherein each cylindrical piston includes:

a radially extending aperture; and
a shoe configured to slide along a surface of a first cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, the trailing edge
being the rearmost edge of the shoe when the shoe experiences movement, wherein the rounded forward and trailing edges form
two separate contact surfaces with the first cam and are separated by an elongated portion of the shoe, the first cam being
disposed about the first plurality of radially extending cylinders;

a second plurality of cylindrical pistons each slidably received within a different one of the second plurality of radially
extending cylinders, the second plurality of cylindrical pistons comprising a second cylindrical piston slidably received
within the second cylinder, wherein the second cylindrical piston is configurable to begin its stroke at a different time
relative to first cylindrical piston within the first cylinder pair, wherein each cylindrical piston comprises:

a radially extending aperture; and
a shoe configured to slide along a surface of a second cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, wherein the rounded
forward and trailing edges form two separate contact surfaces with the second cam and are separated by an elongated portion
of the shoe, the trailing edge being the rearmost edge of the shoe when the shoe experiences movement, the second cam being
disposed about the second plurality of radially extending cylinders; and

a passageway comprising:
a first opening in fluid communication with the first cylinder of the first cylinder pair;
a second opening in fluid communication with the second cylinder of the first cylinder pair; and
a third opening alternating between being in fluid communication with a first fluid port and a second fluid port, wherein
one of the first and second fluid ports is an inlet and the other of the first and second fluid ports is an exhaust.

US Pat. No. 9,206,944

LUBRICATION SYSTEM WITH PASSIVE DRAIN VALVE

Bell Helicopter Textron I...

1. A lubrication system, comprising:
a collection area for collecting lubricating media;
a pumping system for transporting the lubricating media from a withdrawal location of the collection area to a distribution
location of the collection area;

wherein the lubricating media collects in the collection area to a static level when the pumping system is off and to a dynamic
level when the pumping system is on;

a drain valve located between the static level and the dynamic level, the drain valve operable to open to drain a portion
of the lubricating media in response to the lubricating media reaching a predefined threshold temperature and level, wherein
the drain valve will fail open in the event of failure;

a spring arranged to provide an altering spring rate to unseal a valve seat opening; and
a material that changes phase or volume at a predetermined threshold temperature, the material provided in at least one of:
inside the spring, the spring surrounding a central portion of a piston;
between a plunger at a first end of the material and washers at a second end of the material opposite the first end of the
material, wherein the spring is provided to act against the cause a valve plug and the piston to move toward the first end
of the material; and

between the plunger and an end of an inner chamber, the plunger positioned between the inner chamber and the spring, wherein
the spring exerts a first force acting against a wall at a first end of the spring and exerts a second force acting directly
against the plunger at a second end of the spring opposite the first end of the spring.

US Pat. No. 9,162,276

SYSTEM AND METHOD OF MANUFACTURING A STRUCTURE

Bell Helicopter Textron I...

1. A method of manufacturing an article, the method comprising:
machining a single metal sheet to remove metal material from the metal sheet, the metal sheet originally being a flat sheet
having a first surface and second surface with a thickness therebetween, the machining of the metal creates a scaled feature
and a frame portion, the scaled feature being a thickness step change on the first surface, the scaled feature including a
periphery and a thickness profile with a greater thickness than a relatively thin section surrounding the scaled feature,
the frame portion being approximately uniform thickness around an edge portion of the metal sheet and surrounding the relatively
thin section and the scaled feature;

creating a plurality of tooling holes in the frame portion;
brake forming the metal sheet, subsequent to the step of machining the metal sheet, so as to fold the metal sheet around a
brake die to establish an outer radial portion on the second surface of the metal sheet; and

stretch forming the metal sheet, subsequent to the step of brake forming the metal sheet, so as to distort the scaled feature
by stretching the metal sheet by pulling the frame portion away from the outer radial portion.

US Pat. No. 10,266,252

WING EXTENSION WINGLETS FOR TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A pylon assembly for a tiltrotor aircraft comprising:a fixed pylon having an outboard end and an inboard portion;
a rotor assembly rotatably coupled to the inboard portion of the fixed pylon, the rotor assembly operable to rotate between a generally vertical orientation, in a VTOL flight mode, and a generally horizontal orientation, in a forward flight mode, and having an intermediate orientation therebetween, in a conversion flight mode, the rotor assembly including a proprotor operable to produce a slipstream;
a wing extension outboard of the rotor assembly, the wing extension having a forward edge and an outboard end; and
a winglet coupled to the outboard end of the wing extension, the winglet having a forward edge;
wherein the wing extension and the winglet form an angle of less than or equal to 90 degrees such that the winglet is substantially noncontributing to the forward-facing profile of the wing extension in the conversion flight mode, thereby reducing drag of the tiltrotor aircraft during forward motion in the conversion flight mode;
wherein the wing extension is rotatably coupled to the outboard end of the fixed pylon such that the rotor assembly and the wing extension are separated by the fixed pylon;
wherein the winglet is dihedral; and
wherein the wing extension and the winglet are operable to rotate in synchrony with the rotor assembly such that the forward edges of the wing extension and the winglet remain in the slipstream of the proprotor.

US Pat. No. 9,442,076

INFRARED RADIOMETRIC IMAGING INSPECTION OF STEEL PARTS

Bell Helicopter Textron I...

1. A method comprising:
heating a ground steel part that has been chemical-etched; and
detecting defects caused by grinding and watermarks caused by chemical etching by imaging the steel part with an infrared
camera to capture infrared radiation from regions of the steel part that include defects and watermarks, wherein imaging the
steel part comprises:

imaging regions of the steel part at long-wavelengths of infrared radiation to detect defects on the regions of the steel
part; and

generating a first image wherein the defects are visible in the image and the watermarks are not visible in the image.

US Pat. No. 9,856,029

TILTROTOR AIRCRAFT HAVING TIP RIB MOUNTED PYLON ASSEMBLIES

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having
an airframe including a fuselage and a wing, the propulsion system comprising:
an engine supported by the airframe proximate an outboard end of the wing;
a fixed gearbox operably coupled to the engine and having an output gear;
inboard and outboard tip ribs extending above the wing, the inboard tip rib defining an inboard slot, the outboard tip rib
defining an outboard slot;

inboard and outboard bearing cartridges respectively including inboard and outboard bearing assemblies, the inboard bearing
cartridge received within the inboard slot and coupled to the inboard tip rib, the outboard bearing cartridge received within
the outboard slot and coupled to the outboard tip rib;

a pylon assembly rotatably coupled between the inboard and outboard bearing assemblies, the pylon assembly including a spindle
gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the
mast, the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter
mode and the airplane mode; and

a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox,
the common shaft rotatable about the conversion axis.

US Pat. No. 9,849,640

PROCESSES FOR REPAIRING COMPLEX LAMINATED COMPOSITES

Bell Helicopter Textron I...

1. A method for repairing a laminated composite, the method comprising:
mapping dimensions and arrangement of a plurality of plies forming the laminated composite;
defining a repair region by identifying at least one of the plurality of plies that is damaged;
scoring the one or more damaged plies before peeling occurs, wherein fibers within the one or more damaged plies are taken
hold of to begin peeling and removing the one or more damaged plies, wherein the scoring is performed in such a way that the
one or more damaged plies are not completely cut through;

peeling and removing the one or more damaged plies from the repair region,
wherein each of the one or more damaged plies is separately peeled and removed; and
adding at least one replacement ply to the repair region,
wherein the number of replacement plies added is at least equal to the number of damaged plies that are separately peeled
and removed so as to preserve ply drops within the laminated composite, and

wherein the number of replacement plies match ply for ply the damaged plies that have been separately peeled and removed.

US Pat. No. 9,809,318

TILTROTOR AIRCRAFT HAVING SPHERICAL BEARING MOUNTED PYLON ASSEMBLIES

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having
an airframe including a fuselage and a wing, the propulsion system comprising:
an engine supported by the airframe proximate an outboard end of the wing;
a fixed gearbox operably coupled to the engine and having an output gear;
inboard and outboard pedestals supported by the airframe and positioned above the wing;
a pylon assembly rotatably coupled between the inboard and outboard pedestals, the pylon assembly including a spindle gearbox
having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast,
the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter
mode and the airplane mode; and

a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox,
the common shaft rotatable about the conversion axis;

wherein, each of the inboard and outboard pedestals further comprises a spherical bearing providing a self-aligning coupling
between the pylon assembly and the inboard and outboard pedestals, thereby reducing alignment sensitivity between the inboard
and outboard pedestals.

US Pat. No. 10,232,932

HIGH STIFFNESS HUB ASSEMBLY FOR PROPROTOR SYSTEMS

Bell Helicopter Textron I...

1. A high stiffness hub assembly for a proprotor system operable to rotate with a mast of a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode, the hub assembly comprising:a yoke having four blade arms each adapted to hold a proprotor blade, the yoke having a rotational plane and an upper surface; and
a constant velocity joint assembly providing a torque path from the mast to the yoke, the torque path including a trunnion assembly, four drive links and four pillow blocks, the trunnion assembly coupled to the mast and having four outwardly extending trunnions, each of the drive links having a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks and each pillow block independently mounted between the upper surface of the yoke and a hub plate with two connection members extending through the yoke and the pillow block;
wherein, the yoke has a gimballing degree of freedom relative to the mast.

US Pat. No. 9,303,638

VARIABLE RADIAL FLUID DEVICES IN SERIES

Bell Helicopter Textron I...

1. A fluid flow system comprising:
a first radial fluid device comprising:
a first cylinder block comprising a first plurality of radially extending cylinders, a second plurality of radially extending
cylinders, and a shaft opening;

a first plurality of cylindrical pistons each slidably received within a different one of the first plurality of radially
extending cylinders, wherein each cylindrical piston includes:

a radially extending aperture; and
a shoe configured to slide along a surface of a first cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, the trailing edge
being the rearmost edge of the shoe when the shoe experiences movement, the first cam being disposed about the first plurality
of radially extending cylinders;

a second plurality of cylindrical pistons each slidably received within a different one of the second plurality of radially
extending cylinders, wherein each cylindrical piston comprises:

a radially extending aperture; and
a shoe configured to slide along a surface of a second cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, the trailing edge
being the rearmost edge of the shoe when the shoe experiences movement, the second cam being disposed about the second plurality
of radially extending cylinders, the second cam movable relative to the first cam;

an input shaft coupled to the first cylinder block at the shaft opening, the input shaft operable to transmit rotational energy
to the first cylinder block of the first radial fluid device; and

a cam rotation device operable to rotate the first cam of the first radial fluid device in a first direction and the second
cam of the first radial fluid device in a second direction opposite the first direction, the cam rotation device of the first
radial fluid device comprising:

a first worm gear in contact with the first cam of the first radial fluid device;
a first reverse rotation gear coupled to the first worm gear;
a second worm gear in contact with the second cam of the first radial fluid device; and
a second reverse rotation gear coupled to the second worm gear and in contact with the first reverse rotation gear;
a second radial fluid device comprising:
a second cylinder block comprising a third plurality of radially extending cylinders, a fourth plurality of radially extending
cylinders, and a shaft opening;

a first plurality of cylindrical pistons each slidably received within a different one of the third plurality of radially
extending cylinders, wherein each cylindrical piston includes:

a radially extending aperture; and
a shoe configured to slide along a surface of a third cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, the trailing edge
being the rearmost edge of the shoe when the shoe experiences movement, the third cam being disposed about the first plurality
of radially extending cylinders;

a second plurality of cylindrical pistons each slidably received within a different one of the fourth plurality of radially
extending cylinders, wherein each cylindrical piston comprises:

a radially extending aperture; and
a shoe configured to slide along a surface of a fourth cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block the shoe having a rounded forward edge and a rounded trailing
edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, the trailing edge being
the rearmost edge of the shoe when the shoe experiences movement, the fourth cam being disposed about the second plurality
of radially extending cylinders, the fourth cam movable relative to the third cam; and

a coupling device in mechanical communication with the shaft opening of the second radial fluid device and the first cylinder
block of the first radial fluid device opposite the shaft opening of the first radial fluid device, the coupling device operable
to transmit rotational energy from the first cylinder block of the first radial fluid device to the second cylinder block
of the second radial fluid device.

US Pat. No. 9,074,638

MULTILINK CONSTANT VELOCITY JOINT

Bell Helicopter Textron I...

1. An apparatus comprising:
a rotor hub system comprising:
a floating plate;
a plurality of drive link trunnions each comprising a pivoting arm and a trunnion body and positioned radially about the floating
plate, wherein each drive link trunnion is coupled to the floating plate via a respective pivoting arm, and each drive link
trunnion is rotatably coupled to a housing disposed about the floating plate via a respective trunnion shaft disposed within
the drive link trunnion, each drive link trunnion configured to rotate about the respective trunnion shaft to move the floating
plate; and

wherein the housing is configured to couple to a mast.

US Pat. No. 9,067,672

PILOT CONTROL SYSTEM WITH PENDENT GRIP

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train and comprising a plurality of rotor blades;
a control assembly, comprising:
a post having a top, a bottom, and a body joining the top to the bottom, the body having an opening therethrough located above
the bottom and directly below the top;

at least one linkage disposed at least in part within the body;
a grip; and
a shaft having a first end coupled to the at least one linkage proximate to the body below the top and a second end opposite
the first end coupled to the grip, the shaft passing through the opening in the body and positioning at least part of the
grip directly over the top of the post without passing through the top; and

a rotorcraft control system operable to communicate commands to the rotor system based on movements of the at least one linkage.

US Pat. No. 9,841,077

ROTATING SHAFT DAMPING WITH ELECTRO-RHEOLOGICAL FLUID

BELL HELICOPTER TEXTRON I...

1. A method of damping vibrations in a rotorcraft rotating shaft, the method comprising:
surrounding at least a portion of a circumferential surface area of a portion of a rotorcraft rotating shaft with a plurality
of hollow members, each hollow member including an electro-rheological fluid having a viscosity that changes based on an electric
field applied to the electro-rheological fluid;

controlling a vibration of the rotorcraft rotating shaft by changing the viscosity of the electro-rheological fluid in response
to the electric field applied to the electro-rheological fluid; and

controlling the vibration of the rotorcraft rotating shaft by controlling a stiffness of an electromagnetic bearing positioned
between the rotorcraft rotating shaft and the plurality of follow members.

US Pat. No. 9,475,577

RETENTION SYSTEMS FOR ROTORCRAFT PEDAL ASSEMBLIES

BELL HELICOPTER TEXTRON I...

1. A rotorcraft pedal retention system comprising:
an insertion member inserted through a side of a pedal assembly of a rotorcraft, the insertion member including a spring compressible
against the side of the pedal assembly in response to the insertion member being inserted through the side, wherein an end
of the insertion member on the opposing side of the pedal assembly includes an insertion member tab having a non-circular
cross-section;

an axial retention member to receive and retain the insertion member on an opposing side of the pedal assembly, wherein the
axial retention member defines a passage to receive the insertion member tab and defines a pocket to retain the insertion
member tab when the insertion member is rotated on an axis of the insertion member; and

a transverse retention member inserted through a passage formed in the axial retention member.

US Pat. No. 9,841,333

METHOD AND SYSTEM FOR MEASURING TORQUE IN A TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising:
an engine disposed at a fixed location relative to a wing member;
a fixed gearbox;
a spindle gearbox that is rotatable about a conversion axis;
a rotor mast rotatably coupled to the spindle gearbox;
a quill shaft providing torque transfer between the fixed gearbox and the spindle gearbox; and
a torque measuring system associated with the quill shaft comprising:
a computer system configured to calculate the torque value through the quill shaft;
wherein the computer system is further configured to calculate the torque through the rotor mast.

US Pat. No. 9,523,278

ACTUATION SYSTEM FOR AN ACTIVE BLADE ELEMENT OF A ROTOR BLADE

BELL HELICOPTER TEXTRON I...

17. A system to actuate an active blade element attached to a rotor blade, the system comprising
an actuator system attached to a rotor blade and adapted to provide a linear motion in a direction that is spanwise to the
rotor blade; and

a linear transmission system comprising:
an inner elongated tubular member attached to the actuator system and adapted to traverse linearly in the direction that is
spanwise to the rotor blade in response to receiving the linear motion provided by the actuator system; and

an outer elongated tubular member positioned concentrically with the inner elongated tubular member and attached to an active
blade element of the rotor blade, the outer elongated tubular member adapted to at least partially rotate about an axis that
is in the direction that is spanwise to the rotor blade in response to the inner elongated tubular member traversing linearly,
wherein the outer elongated tubular member includes a plurality of helical grooves formed on an outer surface of the outer
elongated tubular member.

US Pat. No. 9,365,294

HELICOPTER TRANSMISSION MOUNT SYSTEM

Bell Helicopter Textron I...

1. A mount system for supporting a transmission in an aircraft, the mount system comprising:
a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis;
a second link coupled between the structure of the aircraft and the transmission, the second link having second axis;
a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis;
a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis;
wherein the first link and the second link are oriented such that the first axis and the second axis intersect at a forward
focal point;

wherein the third link and the fourth link are oriented such that the third axis and the fourth axis intersect at an aft focal
point;

wherein the forward focal point has a different waterline location compared to the aft focal point;
wherein the first link and the second link are coupled to the transmission at different locations;
wherein the third link and the fourth link are coupled to the transmission at different locations; and
wherein the forward focal point and the aft focal point are located within an interior portion of the transmission so that
a virtual roll axis extending between the forward focal point and the aft focal point passes through a portion of the transmission.

US Pat. No. 9,120,246

PRESSURE TUNABLE EXPANDABLE MANDREL FOR MANUFACTURING A COMPOSITE STRUCTURE

Bell Helicopter Textron I...

1. A method of making a composite core, the method comprising:
providing a plurality of mandrels, each mandrel comprising:
a body portion with an outer surface, the outer surface defining an ultimate shape of a tube member of the composite core;
and

a hollow portion that defines an internal surface of the body portion, the hollow portion having a star shaped geometry that
is collapsible in multiple pressure stages, the star shaped geometry having a plurality of flat walled leg portions that each
terminate at a point, the plurality of flat walled leg portions extending from an interior portion;

placing a composite material around each mandrel;
placing the plurality of mandrels in a tool, the tool being configured to constrain the plurality of mandrels as the mandrels
experience a thermal expansion;

heating the mandrels so that the mandrels thermally expand, thereby applying a pressure to the composite material during a
cure cycle, the step of heating the mandrels including increasing a temperature of the mandrels for a duration, the increase
in temperature during the duration causing a first pressure plateau as the flat walled leg portions of the hollow portion
collapse and second pressure plateau as a diameter of the interior portion collapses; and

cooling and separating the mandrels from the composite core.

US Pat. No. 9,840,325

DUAL SERIES PITCH LINK BEARING

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub coupled to the drive shaft;
a rotor blade coupled to the hub;
a swashplate positioned about the drive shaft;
a pitch link coupled between the swashplate and the hub corresponding to the rotor blade;
a bearing coupled between either the pitch link and the swashplate or the pitch link and the hub, the bearing comprising:
an outer housing having a first opening therethrough;
an intermediate housing adjacent the outer housing inside the first opening and having a second opening therethrough;
an inner housing adjacent the intermediate housing inside the second opening and having a third opening therethrough, the
inner housing comprising a first inner surface and a second inner surface defining the third opening, the second inner surface
oriented at a reflex angle relative to the first inner surface such that an interior diameter of the third opening is smaller
than an exterior diameter of the third opening;

a first bearing surface in contact with the intermediate housing and the inner housing and separating the intermediate housing
from the inner housing;

a first member adjacent the first inner surface inside the third opening having a fourth opening therethrough;
a second bearing surface in contact with the first inner surface and the first member and separating the first inner surface
from the first member;

a second member adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with
the fourth opening; and

a third bearing surface in contact with the second inner surface and the second member and separating the second inner surface
from the second member.

US Pat. No. 9,352,831

VARIABLE LOWER LIMIT COLLECTIVE GOVERNOR TO IMPROVE RECOVERY

Bell Helicopter Textron I...

1. A control system for an aircraft, comprising:
a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade;
the governor having a threshold limit relating to the maximum pitch angle of the rotor blade; and

a limiter configured to selectively remove the threshold limit, so as to permit a pilot full command of the collective above
the threshold limit;

wherein command signals from the governor and command signals from the limiter are summed to generate a total symmetric collective
pitch command for controlling the pitch of the rotor blade.

US Pat. No. 9,845,381

NANOLEVEL DISPERSION OF NANOPARTICLES IN HYDROPHOBIC MATERIALS

BELL HELICOPTER TEXTRON I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device; and
an aerospace material comprising a hydrophobic destination material and a dispersion of hydrophilic nanoparticles, the aerospace
material being applied to the body, and the aerospace material comprising a nanoparticle mixture obtained from the process
comprising:

providing a plurality of the nanoparticles suspended in a carrier;
adding a solvent to the plurality of nanoparticles suspended in a carrier;
removing at least some of the carrier to yield the plurality of nanoparticles suspended in the solvent;
mixing the nanoparticles suspended in the solvent with the destination material; and
removing at least some of the solvent from the mixture of nanoparticles suspended in the solvent and the destination material.

US Pat. No. 9,809,303

ROTOR POSITION DETERMINATION SYSTEM WITH MAGNETO-RESISTIVE SENSORS

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub coupled to the drive shaft;
a rotor blade;
a grip coupling the rotor blade to the hub; and
a position determination system disposed between the blade and the body, the position determination system comprising:
at least one magnet; and
a plurality of magneto-resistive sensors proximate to the at least one magnet;
wherein the at least one magnet is movable relative to the plurality of magneto-resistive sensors as a function of movement
of the grip relative to the hub.

US Pat. No. 9,592,919

ADAPTER FOR AIRCRAFT FLUID TRANSMISSION LINES

BELL HELICOPTER TEXTRON I...

1. An aircraft fuel line assembly clamp member, the clamp member comprising:
a c-shaped outer shell sized to be positioned within an outer tube of an aircraft fuel line assembly and including a first
edge and a second edge defining a first gap;

a plurality of spokes arranged on an inner surface of the outer shell, the plurality of spokes protruding from the inner surface
towards a center of the outer shell to define a shape to receive an inner tube of the aircraft fuel line assembly, the plurality
of spokes spaced apart on the inner surface, wherein a space between spaced apart edges of the outer shell is less than an
outer diameter of the inner tube of the aircraft fuel line assembly;

a c-shaped inner shell attached to ends of the plurality of spokes near the center of the outer shell and including a first
edge connected to one of the plurality of spokes and a second edge connected to another of the plurality of spokes, wherein
the first edge of the c-shaped outer shell, the first edge of the c-shaped inner shell, and the one of the plurality of spokes
defines a first space, and the second edge of the c-shaped outer shell, the second edge of the c-shaped inner shell, and the
another of the plurality of spokes defines a second space; and

wherein an axial width of the inner shell is substantially equal to or greater than an axial width of each spoke of the plurality
of spokes, and an axial width of the outer shell is greater than the axial width of each spoke of the plurality of spokes.

US Pat. No. 9,399,984

VARIABLE RADIAL FLUID DEVICE WITH COUNTERACTING CAMS

Bell Helicopter Textron I...

1. A radial fluid device comprising:
a cylinder block comprising a first plurality of radially extending cylinders and a second plurality of radially extending
cylinders, wherein the cylinder block is mounted for rotation;

a first plurality of cylindrical pistons each slidably received within a different one of the first plurality of radially
extending cylinders, wherein each cylindrical piston includes:

a radially extending aperture; and
a shoe configured to slide along a surface of a first cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, wherein the rounded
forward and trailing edges form two separate contact surfaces with the first cam and are separated by an elongated portion
of the shoe, the trailing edge being the rearmost edge of the shoe when the shoe experiences movement, the first cam being
disposed about the first plurality of radially extending cylinders;

a second plurality of cylindrical pistons each slidably received within a different one of the second plurality of radially
extending cylinders, wherein each cylindrical piston includes:

a radially extending aperture; and
a shoe configured to slide along a surface of a second cam that has two or more lobes configured such that the shoe completes
two or more sinusoidal strokes per revolution of the cylinder block, the shoe having a rounded forward edge and a rounded
trailing edge, the forward edge being the forward most edge of the shoe when the shoe experiences movement, wherein the rounded
forward and trailing edges form two separate contact surfaces with the second cam and are separated by an elongated portion
of the shoe, the trailing edge being the rearmost edge of the shoe when the shoe experiences movement, the second cam being
disposed about the second plurality of radially extending cylinders;

a passageway comprising:
a first opening in fluid communication with at least one of the first plurality of radially extending cylinders;
a second opening in fluid communication with at least one of the second plurality of radially extending cylinders; and
a third opening alternating between being in fluid communication with a first fluid port and a second fluid port, wherein
one of the first and second fluid ports is an inlet and the other of the first and second fluid ports is an exhaust; and

a cam rotation device coupled to the first cam and the second cam, the cam rotation device operable to rotate the first cam
in a first direction and the second cam in a second direction.

US Pat. No. 9,364,930

METHOD OF MACHINING A THIN-WALLED STRUCTURE

Bell Helicopter Textron I...

1. A method of manipulating a thin-walled structure, comprising:
providing a thin-walled structure in a first unconstrained configuration;
constraining the thin-walled structure to a first constrained configuration in which a first feature of the thin-walled structure
is spatially located relative to a second feature of the thin-walled structure in a predetermined manner, wherein an open
volume of the thin-walled structure is constrained to maintain a predetermined open volume shape; and

machining the thin-walled structure to a second constrained configuration in which the first feature of the thin-walled structure
remains spatially located relative to the second feature of the thin-walled structure in the predetermined manner; and

wherein constraining the thin-walled structure to the first constrained configuration comprises providing a constrainer into
the open volume of the thin-walled structure, the constrainer comprising at least partially solidified cetyl alcohol; and

wherein the constrainer further comprises at least one of a magnetic material and a ferrous material, and the constraining
comprises selectively applying a magnetic force to the constrainer.

US Pat. No. 9,051,046

VERTICAL SUPPORT SYSTEM

Bell Helicopter Textron I...

1. A vertical support system for an aircraft, comprising:
a first articulated leg assembly configured to carry a first load, the first articulated leg assembly comprising a first upper
leg and a first lower leg configured to carry the first load and rotatably connected to the first upper leg and a first wheel
assembly, the first articulated leg assembly being selectively movable between a first refracted configuration and a first
loaded configuration using a first actuator connected to the first articulated leg assembly; and

a second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated
leg assembly, the second articulated leg assembly comprising a second upper leg and a second lower leg configured to carry
the second load and rotatably connected to the second upper leg and a second wheel assembly, the second articulated leg assembly
being selectively movable between a second refracted configuration and a second loaded configuration using a second actuator
connected to the second articulated leg assembly;

wherein a lateral width ratio is equal to a value of less than about 0.6, the lateral width ratio being defined as a ratio
of (1) a minimum lateral width between the lateral extents of a first wheel assembly and a second wheel assembly when the
first articulated leg assembly is in the first retracted configuration and the second articulated leg assembly is in the second
refracted configuration to (2) a maximum lateral width between the lateral extents of the first wheel assembly and the second
wheel assembly when the first articulated leg assembly is in the first loaded configuration and the second articulated leg
assembly is in the second loaded configuration;

wherein, with the first articulated leg assembly in the first retracted configuration and the second articulated leg assembly
in the second refracted configuration, a first vertical footprint of the first articulated leg assembly and first actuator
overlaps a second vertical footprint of the second articulated leg assembly and second actuator; and

wherein the first upper leg is rotatable about a first primary axis of rotation, the second upper leg is rotatable about a
second primary axis of rotation, the first lower leg is rotatable about a first secondary axis of rotation, and the second
lower leg is rotatable about a second secondary axis of rotation, wherein the first articulated leg assembly is symmetric
to the second articulated leg assembly about a vertical axis through an origin of the vertical support system as the first
articulated leg assembly moves between the first retracted configuration and the first loaded configuration and the second
articulated leg assembly moves between the second retracted configuration and the second loaded configuration.

US Pat. No. 9,840,043

MANUFACTURE OF THERMOPLASTIC CORE

BELL HELICOPTER TEXTRON I...

1. A method of manufacturing a honeycomb core for a structural aircraft component, the method comprising:
positioning a first thermoplastic columnar cell adjacent a second thermoplastic columnar cell;
modifying a thermoplastic property of the first thermoplastic columnar cell, wherein the modified thermoplastic property permits
joining a circumferential surface of the first thermoplastic columnar cell to a circumferential surface of the second thermoplastic
columnar cell; and

joining the circumferential surface of the first thermoplastic columnar cell having the modified thermoplastic property to
the circumferential surface of the second thermoplastic columnar cell resulting in the honeycomb core for the structural aircraft
component.

US Pat. No. 9,683,616

MAGNETORHEOLOGICAL ROTORCRAFT ACTUATOR

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device; and
a first controlled-slippage actuator in mechanical communication between the pilot input device and the rotor system, the
first controlled-slippage actuator comprising:

a first driving member configured to receive mechanical energy from a power source;
a first driven member;
a first magnetorheological (MR) fluid disposed between the first driving member and the first driven member and configured
to transmit a variable amount of mechanical energy from the first driving member to the first driven member;

a first output member coupled between the first driven member and the rotor system; and
a first magnetic circuit configured to deliver a first magnetic field towards the first MR fluid, the first magnetic circuit
configured to vary the strength of the first magnetic field in response to inputs received from the pilot input device.

US Pat. No. 9,352,829

AIRCRAFT WITH PROTECTIVE NANOCOATING

Bell Helicopter Textron I...

1. An aircraft component, comprising:
an exterior surface configured to flex in response to applied forces; and
a protective nanocoating carried by the exterior surface;
wherein the protective nanocoating protects the aircraft component from oil, ultraviolet radiation, and ozone.

US Pat. No. 9,981,734

CROSS-WING DRIVESHAFT CHANNEL

Bell Helicopter Textron I...

1. An aircraft wing having a wing surface comprising:a fuel tank located in the wing,
a channel defining a cavity in the fuel tank, the channel comprising at least two channel ends terminating at the wing surface,
a driveshaft located in the cavity; and
an access panel located on the wing surface and being movable between an open position wherein access to the cavity is permitted, and a closed position wherein the cavity is at least partially covered by the access panel to inhibit access to the cavity.

US Pat. No. 9,783,290

JAM-TOLERANT ROTARY CONTROL MOTOR FOR HYDRAULIC ACTUATOR VALVE

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub coupled to the drive shaft;
a rotor blade coupled to the hub;
a hydraulic actuator in mechanical communication with the rotor blade and operable to change a position of the rotor blade;
an actuator control valve system operable to regulate a flow of fluid to the hydraulic actuator, the actuator control valve
system comprising a servo valve and a spool extending through the servo valve; and

a control motor in mechanical communication with the actuator control valve system, the control motor comprising:
a first permanent magnet operable to generate a first magnetic flux path;
a coil operable to selectively add magnetic flux to and subtract magnetic flux from the magnetic flux flowing in the first
magnetic flux path, wherein one of the first permanent magnet and the coil is a movable component and the other one of the
first permanent magnet and the coil is a static component, the movable component operable to rotate relative to the static
component in response to variations in flux flowing in the first magnetic flux path;

a shaft coupled to the movable component such that the shaft is operable to rotate in response to variations in flux flowing
in the first magnetic flux path;

a first non-magnetic material disposed between at least one of the movable components and at least one of the static components
and operable to prevent physical contact between at least one of the movable components and at least one of the static components,
wherein the first non-magnetic material is at least partially movable relative to both the movable component and the static
component;

and
A joint coupled between the shaft and the spool and operable to convert rotations of the shaft into axial movements of the
spool.

US Pat. No. 9,725,179

ELECTRICAL GENERATOR FOR ROTATING STRUCTURE

UNIVERSITE DU QUEBEC A CH...

1. An electrical generator assembly comprising:
a central rotatable shaft having first and second winding assemblies mounted thereto for rotation therewith, the central shaft
being a hollow helicopter mast;

a first rotatable permanent magnet assembly adjacent the first winding assembly and in use cooperating therewith to induce
a current in the first winding assembly;

a second rotatable permanent magnet assembly adjacent the second winding assembly and in use cooperating therewith to induce
a current in the second winding assembly; and

a drive system drivingly interconnecting the central shaft and the first permanent magnet assembly and interconnecting the
central shaft and the second permanent magnet assembly, the drive system defining a relative rotational speed between the
first permanent magnet assembly and the first winding assembly which is greater than an absolute rotational speed of the first
winding assembly, the drive system defining a relative rotational speed between the second permanent magnet assembly and the
second winding assembly which is greater than an absolute rotational speed of the second winding assembly;

wherein the drive system is a belt drive including:
a plurality of belts,
first and second mast pulleys connected to the central shaft to rotate therewith,
a first magnet assembly pulley connected to the first permanent magnet assembly to rotate therewith,
a second magnet assembly pulley connected with the second permanent magnet assembly and additional pulleys drivingly engaged
to one another, and

first, second, third and fourth support shafts each receiving a large pulley interconnected with a small pulley smaller than
the large pulley;

wherein the belts drivingly interconnect:
each mast pulley to the small pulley of a respective one of the first and third opposed support shafts, the mast pulley being
larger than the small pulley,

each large pulley of the first and third opposed support shafts to the small pulley of a respective one of the second and
fourth opposed shafts, and

each large pulley of the second and fourth support shaft to a respective one of the magnet assembly pulleys, the magnet assembly
pulleys being smaller than the large pulleys.

US Pat. No. 9,656,746

MAGNETORHEOLOGICAL HAPTIC TRIM ACTUATOR

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device; and
an actuator in mechanical communication with the pilot input device, the actuator comprising:
a first driving member configured to receive mechanical energy from a first power source;
a driven member;
a first magnetorheological (MR) fluid disposed between the first driving member and the driven member and configured to transmit
a variable amount of mechanical energy from the first driving member to the driven member;

an output member coupled between the driven member and the pilot input device; and
a first magnetic circuit configured to deliver a magnetic field towards the first MR fluid, the first magnetic circuit configured
to control movement of the pilot input device by varying the strength of the magnetic field delivered towards the first MR
fluid.

US Pat. No. 9,638,048

SYSTEMS AND METHODS OF CONSTRUCTING COMPOSITE ASSEMBLIES

BELL HELICOPTER TEXTRON I...

1. A method of constructing a cured composite assembly, comprising:
positioning a composite assembly within a bonding tool, wherein the composite assembly comprises:
an upper skin assembly comprising an integrally formed upper spar key, the upper skin assembly extending between a leading
edge and a trailing edge of the composite assembly;

a lower skin assembly comprising an integrally formed lower spar key, the lower skin assembly extending between the leading
edge and the trailing edge of the composite assembly; and

an uncured composite spar disposed between the upper skin assembly and the lower skin assembly;
reducing the size of a cavity formed between the outer surface of the spar and an inner concave surface of an abrasion strip
assembly; and

performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the upper skin
assembly and the lower skin assembly to the cured composite spar.

US Pat. No. 9,561,863

AIRCRAFT PROGNOSTICS HEALTH SYSTEM

Bell Helicopter Textron I...

1. A method of assessing reliability of a rotorcraft component, comprising:
identifying, by a processor, aboard a rotorcraft, a first probability of failure of the rotorcraft component installed on
the rotorcraft, the first probability of failure representing a probability of failure of the rotorcraft component prior to
application of at least one load;

receiving, by the processor, from one or more sensors installed on the rotorcraft, one or more measurements representative
of the at least one load applied against the rotorcraft component;

determining, by the processor, aboard the rotorcraft, a second probability of failure of the rotorcraft component based on
the first probability of failure and the received one or more measurements representative of the at least one load applied
against the rotorcraft component, the second probability of failure representing a probability of failure of the rotorcraft
component after application of the at least one load;

determining, by the processor, an equivalent life by assessing a cumulative damage of a change of a probability of failure
and then converting the change of the probability of failure back into a time domain;

subtracting, by the processor, a calculated used-life damage index from a baseline model to identify a variance and then credit
the variance towards a remaining useful life of the rotorcraft component so as to extend the remaining useful life of the
rotorcraft component; and

adjusting, by the processor, at least one of an operation and a maintenance of the rotorcraft based on the remaining useful
life.

US Pat. No. 9,550,347

METHOD OF CONFIGURING COMPOSITE CORE IN A CORE STIFFENED STRUCTURE AND A STRUCTURE INCORPORATING THE SAME

Bell Helicopter Textron I...

1. A method of manufacturing a core stiffened structure, the core stiffened structure having a first face sheet, a second
face sheet, and a plurality of wafers of composite core, the method comprising:
orienting the plurality of wafers in a non-uniform pattern onto the first face sheet, the non-uniform pattern producing non-uniform
spacing between adjacent wafers, each wafer having a plurality of hexagonal cell members, each hexagonal cell member having
a cell wall that terminates at a first surface network and a second surface network, the plurality of hexagonal cell members
assembled together such that a perimetrical shape of the wafer is hexagonal with the plurality of hexagonal cell members being
oriented with adiacent cell walls in a pattern that results in the perimetrical shape of the wafer being hexagonal in that
outerwardly exposed cell walls of the plurality of cell members create the perimetrical shape;

assembling a second face sheet onto the plurality of wafers; and
curing an adhesive to create a bond between the plurality of wafers, the first face sheet, and the second face sheet.

US Pat. No. 9,499,262

COMPOSITE FLEXURE FOR TILTROTOR ROTOR SYSTEM

Bell Helicopter Textron I...

1. A tiltrotor aircraft, comprising:
a body;
a wing member;
a power train coupled to the body and comprising a power source and a drive shaft in mechanical communication with the power
source; and

a rotor system coupled to the wing member and in mechanical communication with the drive shaft, at least part of the rotor
system being tiltable between a helicopter mode position and an airplane mode position, the rotor system comprising:

a gimbaled yoke in mechanical communication with the drive shaft;
a rotor blade having a single, uninterrupted blade body extending from a root end to a tip end and having a hollow cavity
therein, the hollow cavity having an open end and a closed end opposite the open end, the rotor blade comprising the root
end and an attachment location disposed within the hollow cavity and located outboard of the root end, the rotor blade being
twisted such that an angular difference exists between the chord of the rotor blade at the root end and the chord of the rotor
blade at the attachment location; and

a composite flexure comprising a composite member disposed completely within the hollow cavity of the rotor blade, the composite
flexure coupled to the gimbaled yoke at a first end and coupled to the rotor blade at a second end, wherein a first attachment
plane associated with the first end is angled relative to a second attachment plane associated with the second end such that
the composite member is twisted at a composite-flexure twist angle between the first end and the second end when the composite
flexure is not subject to torsional loads, the composite-flexure twist angle between the first end and the second end corresponding
to the angular difference between the chord of the rotor blade at the root end and the chord of the rotor blade at the attachment
location.

US Pat. No. 9,382,001

TORQUE TRANSFER SYSTEM FOR A ROTORCRAFT

Bell Helicopter Textron I...

1. A torque transfer system for a rotorcraft, the system comprising:
a first rotational joint connected to a rotorcraft rotary shaft, the first rotational joint to receive a portion of a torque
generated by rotation of the rotorcraft rotary shaft and to transfer the portion of the torque to a rotorcraft rotating component;
and

a second rotational joint separate from and transferring torque using a different mechanism than the first rotational joint,
wherein the second rotational joint is connected to the rotorcraft rotary shaft, the second rotational joint to receive a
remainder of the torque generated by the rotation of the rotorcraft rotary shaft and to transfer the remainder of the torque
to the rotorcraft rotating component.

US Pat. No. 9,174,731

FIXED ENGINE AND ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising:
an engine disposed at a fixed location relative to a wing member, the wing member having a first rib, a second rib, a first
spar, second spar; and an upper wing skin;

a proprotor mechanically coupled to the engine, the proprotor comprising:
a plurality of rotor blades;
a rotor mast having a rotor mast axis of rotation;
a spindle gearbox coupled to the rotor mast, the spindle gearbox being rotatable about a conversion axis, the conversion axis
and the rotor mast axis of rotation intersecting at an intersection point, the intersection point being centrally located
in a central portion, the central portion being a central region aft of the first spar, forward of the second spar, outboard
of the first rib, and inboard of the second rib, and above an airfoil surface profile of the upper wing skin;

wherein the first rib, the second rib, the first spar, and the second spar are coupled together to form a torque box.

US Pat. No. 10,086,936

STORAGE MODELS FOR TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode, the aircraft comprising:a fuselage;
a wing rotatably mounted to the fuselage and having first and second outboard ends, the wing reversibly rotatable between a flight orientation, substantially perpendicular to the fuselage, in the flight modes, and a stowed orientation, substantially parallel to the fuselage, in the storage mode;
first and second pylon assemblies respectively positioned proximate the first and second outboard ends of the wing;
first and second mast assemblies respectively rotatable relative to the first and second pylon assemblies, the first and second mast assemblies reversibly rotatable between a substantially vertical orientation, in the VTOL flight mode, and a substantially horizontal orientation, in the forward flight mode and the storage mode; and
first and second proprotor assemblies respectively rotatable relative to the first and second mast assemblies, the first and second proprotor assemblies each including first, second and third rotor blades and each having a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode, wherein the first rotor blade of the first proprotor assembly is folded beamwise below the wing substantially conforming with the first pylon assembly, the second and third rotor blades of the first proprotor assembly are folded beamwise above the wing substantially conforming with the first pylon assembly, the first and second rotor blades of the second proprotor assembly are folded beamwise to be substantially parallel with the third rotor blade of the second proprotor assembly and the rotor blades of the second proprotor assembly have a descending orientation relative to the wing.

US Pat. No. 9,849,656

METHOD OF REPAIRING A CORE STIFFENED STRUCTURE

Bell Helicopter Textron I...

1. A method of repairing a rotor blade, the method comprising:
removing a damaged portion of the rotor blade to provide a first core member within a cavity of the rotor blade;
installing an uncured composite shelf onto the first core member in the cavity;
bonding the uncured composite shelf onto the first core member with an adhesive;
concurrently curing the uncured composite shelf and the adhesive to form a cured composite shelf bonded to the first core
member;

bonding a second core member having a plurality of cells to the cured composite shelf;
depositing a foam mixture into a cell of the second core member;
allowing the foam mixture to expand and fill the plurality of cells in the second core member so as to form an expanded foam;
trimming the expanded foam; and
securing a skin patch over the second core member;
wherein the cured composite shelf provides a shear transfer medium between the first core member and the second core member.

US Pat. No. 9,731,819

SYSTEM AND METHOD FOR LINKAGE LENGTH ADJUSTMENT

BELL HELICOPTER TEXTRON I...

1. A rotor system, comprising:
a rotor;
an axis of rotation about which the rotor may be rotated;
a linkage system having an overall effective length, comprising:
a first adjustable length portion comprising a threaded component having a lengthwise axis in which the overall effective
length is measured;

a second adjustable length portion connected to the first adjustable length portion, the second adjustable length portion
comprising an eccentric bushing carried by a pitch horn connected to the rotor, the eccentric bushing having a bushing central
axis that is substantially orthogonal to the lengthwise axis, wherein the second adjustable length portion adjusts the overall
effective length of the linkage system by rotating the eccentric bushing about the bushing central axis;

wherein the second adjustable length portion is configured to provide a relatively finer adjustment of the overall effective
length of the linkage system as compared to the first adjustable length portion; and

wherein the rotor is configured to rotate about the axis in response to changing the overall effective length of the linkage
system.

US Pat. No. 9,751,624

INDIVIDUAL BLADE CONTROL UTILIZING PNEUMATIC MUSCLES

BELL HELICOPTER TEXTRON I...

1. A rotorcraft blade control system comprising:
a mechanical linkage to connect to a rotorcraft blade comprising a feather axis;
a pneumatic muscle having a first end connected to the mechanical linkage and a second end to connect to a rotorcraft member
such that the pneumatic muscle and the rotorcraft member are external to the rotorcraft blade and the pneumatic muscle is
not parallel to the feather axis; and

a movement member having a third end connected to the mechanical linkage and a fourth end to connect to the rotorcraft member
such that the movement member is external to the rotorcraft blade, the movement member is not parallel to the feather axis,
the feather axis extends between the movement member and the pneumatic muscle, and the pneumatic muscle and the movement member
are operable to move the mechanical linkage to control movement of the rotorcraft blade on the feather axis.

US Pat. No. 9,617,010

AIRCRAFT PROGNOSTICS HEALTH SYSTEM

Bell Helicopter Textron I...

1. A method of assessing use of an aircraft component installed on an aircraft, comprising:
receiving, by a processor, from one or more sensors installed on the aircraft, one or more measurements representative of
at least one load applied against the aircraft component;

selecting, by the processor, at least one usage model from a plurality of usage models, each usage model of the plurality
of usage models relating aircraft loads with received sensor data;

determining, by the processor, at least one load value based on the selected at least one usage model and the received one
or more measurements;

calculating, by the processor, based on the determined at least one load value, an amount of change in probability of failure
caused by application of the at least one load against the aircraft component;

determining, by the processor, an equivalent life by assessing a cumulative damage of a change of a probability of failure
and then converting the change of the probability of failure back into a time domain;

subtracting, by the processor, a calculated used-life damage index from a baseline model to identify a variance and then credit
the variance towards a remaining useful life of the rotorcraft component so as to extend the remaining useful life of the
rotorcraft component; and

adjusting, by the processor, at least one of an operation and a maintenance of the rotorcraft based on the remaining useful
life.

US Pat. No. 9,604,713

DOOR MIGRATION PREVENTION SYSTEM

Bell Helicopter Textron I...

1. An aircraft, comprising:
a body comprising a door opening and a door frame at least partially surrounding the door opening;
a power train coupled to the body and comprising a power source; and
a door system coupled to the body, the door system comprising:
a door coupled to the body proximate to the door opening;
a door-sliding system configured to allow the door to slide from an open position to a closed position in a first direction
parallel to a first axis;

a door attachment device coupled to the door; and
a receiver coupled to the body proximate to the door frame and comprising a receiving surface configured to at least partially
receive the door attachment device as the door attachment device moves along the first axis and maintains physical contact
with an elongated portion of the receiving surface, the receiving surface oriented relative to the door frame such that the
door attachment device moves the door closer to the door frame as the door attachment device moves along a path at least partially
defined by the receiving surface, the receiving surfacing having a non-planar portion curved relative to the first axis such
that the receiving surface responds to movement of the door attachment device in a second direction parallel to a second axis,
the second axis perpendicular to the first axis, by repositioning the door attachment device along the path in a third direction
perpendicular to the plane formed by the first axis and the second axis.

US Pat. No. 9,597,826

METHOD OF REPAIRING, SPLICING, JOINING, MACHINING, AND STABILIZING HONEYCOMB CORE USING POURABLE STRUCTURAL FOAM AND A STRUCTURE INCORPORATING THE SAME

Bell Helicopter Textron I...

1. A method of curing a composite structure, the method comprising:
providing a core member having a central portion and a perimeter portion, wherein the perimeter portion extends around the
entire perimeter of the core member and the central portion is surrounded by the perimeter portion;

machining a bevel portion into the perimeter portion of the core member, wherein the bevel portion extends around the entire
perimeter of the core member, the bevel portion has an acute angle, and the bevel portion extends from a top surface of the
core member to a bottom surface of the core member;

after the machining step, expanding a foam mixture into the entire bevel portion of the core member until the foam mixture
becomes an expanded foam;

laying a composite skin onto a surface of the core member having the bevel portion, such that the composite skin conforms
to the bevel angle of the bevel portion; and

curing the composite skin with heat and pressure,
wherein the central portion of the core member does not contain any foam after the curing step.

US Pat. No. 9,594,058

IMPLEMENTING STEEP DELTA WAVE TECHNIQUE TO INSPECT JOINTS

BELL HELICOPTER TEXTRON I...

1. A method of inspecting a joint that connects two parts, the method comprising:
directing an ultrasonic beam from an ultrasonic beam transmitter at a joint that connects two parts, the ultrasonic beam forming
an angle between at least 14 degrees and at most 21 degrees with a joint axis of the joint, wherein the ultrasonic beam passes
through a joint thickness of the joint; and

determining a quality of the joint based, in part, on a difference between a strength of the ultrasonic beam directed at the
joint and a strength of a portion of the ultrasonic beam that passed through the joint thickness.

US Pat. No. 9,541,142

MAGNETORHEOLOGICAL FLIGHT CONTROL CLUTCH SYSTEM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device;
a first flight control system comprising a first power source and a first clutch configured to receive mechanical energy from
the first power source, the first flight control system configured to receive an input from the pilot input device and transmit
a mechanical output to the rotor system based on the received input;

a second flight control system comprising a second power source and a second clutch configured to receive mechanical energy
from the second power source, the second flight control system configured to receive an input from the pilot input device
and transmit a mechanical output to the rotor system based on the received input;

a shared clutch system comprising:
a shared shaft configured to receive mechanical energy from a shared power source;
a first shared clutch corresponding to the first clutch and configured to receive mechanical energy from the shared shaft;
and

a second shared clutch corresponding to the second clutch and configured to receive mechanical energy from the shared shaft;
a first linkage providing mechanical communication between an output of the first clutch, an output of the first shared clutch,
and a first output device in mechanical communication with the rotor system; and

a second linkage providing mechanical communication between an output of the second clutch, an output of the second shared
clutch, and a second output device in mechanical communication with the rotor system.

US Pat. No. 9,514,628

ELECTRICAL LOAD MONITORING SYSTEM

BELL HELICOPTER TEXTRON I...

1. A composite electrical load monitoring system comprising: one or more computer systems; and a non-transitory computer-readable
medium storing instructions executable by the one or more computer systems to perform operations comprising: determining,
at a first time instant during a duration, a first margin between a first reading of a first electrical parameter and a first
electrical parameter limit for a first power source; determining, at the first time instant during the duration, a second
margin between a second reading of a second electrical parameter and a second electrical parameter limit for a second power
source; determining, after the first time instant, that the first margin is less than the second margin in response to determining
the first margin and the second margin; and displaying, in a display device and within the duration, an identifier for the
first power source in response to determining that the first margin is less than the second margin.

US Pat. No. 9,505,489

FLEXING CLEVIS ARRANGEMENT BOLTED JOINT ATTACHMENT FOR FLEXIBLE ROTOR HUB WITH HIGH OFFSET AND HIGH FLAPPING

BELL HELICOPTER TEXTRON I...

1. A flexible joint assembly for providing flexure to a rotor blade, the flexible joint assembly comprising:
an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint through the rotor blade
yoke and the upper and lower hub plates, the bolted joint located radially outward of a mast; and

an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate,
wherein the upper flexure assembly comprises an upper shoe disposed between the rotor blade yoke and the upper hub plate,
and wherein the lower flexure assembly comprises a lower shoe disposed between the rotor blade yoke and the lower hub plate,
wherein the upper shoe and the lower shoe are configured to abut the rotor blade yoke to promote flapping of the rotor blade
yoke about a flapping hinge located radially outward of the bolted joint; and

wherein at least one of the upper hub plate or the lower hub plate comprises a yoke-facing inward surface comprising a recess
located longitudinally between the bolted joint and the flapping hinge relative to a longitudinal length of the rotor blade
yoke, the recess defining a gap between the inward surface of the upper hub plate or lower hub plate and the upper shoe or
lower shoe, wherein the recess does not contact any of the rotor blade yoke, the upper flexure assembly, and the lower flexure
assembly, the recess configured to separate forces at the upper shoe and lower shoe from forces at the bolted joint and reduce
shear forces acting on the bolted joint from flapping of the rotor blade yoke.

US Pat. No. 9,394,063

METHODS UTILIZING COLD SPRAY TECHNIQUES FOR REPAIRING AND PROTECTING ROTARY COMPONENTS OF AVIATION PROPULSION SYSTEMS

Bell Helicopter Textron I...

1. A method, comprising:
identifying a non-compliant surface of a component, the component comprising temperature sensitive material and at least one
of electronic equipment, optical equipment, or fluid sensing devices, wherein the non-compliant surface is not within an allowable
tolerance;

cold spraying a powder comprising a metal onto the non-compliant surface, wherein the cold spraying comprises restricting
heat to the non-compliant surface and avoiding one or more undamaged portions of the component by masking off one or more
portions of the non-compliant surface from the undamaged portions of the component with a thermally insulating masking material,
wherein the cold spraying does not damage the electronic equipment, the optical equipment, or the fluid sensing devices;

localizing heat generated by the cold spraying away from the temperature sensitive material; and
forming a coating comprising the metal over the non-compliant surface, wherein an outer surface of the coating is within an
allowable tolerance.

US Pat. No. 9,347,487

ROTORCRAFT BEARING WITH ROTATION SLIP JOINT

Bell Helicopter Textron I...

1. A rotorcraft bearing system comprising:
a bearing housing attached to an elastomeric bearing on a longitudinal axis, an end surface of the elastomeric bearing attached
to an end surface of the bearing housing;

a sliding contact bearing having an end surface; and
an intermediate sliding contact bearing material on the end surface of the sliding contact bearing, wherein, under no load
on the longitudinal axis, the intermediate sliding contact bearing material is untouched by the bearing housing, and wherein,
under load on the longitudinal axis, the intermediate sliding contact bearing material is configured to touch an opposing
end surface of the bearing housing to form a rotational slip joint.

US Pat. No. 9,051,836

PILOT CONTROL SYSTEM WITH COMPACT GIMBAL MECHANISM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a rotor system coupled to the power train and comprising a plurality of rotor blades;
a control assembly, comprising:
a post having a top, a bottom, and a body joining the top to the bottom;
a first gimbal coupled to inside the body, the first gimbal rotatable about a first axis of rotation, the first gimbal comprising
a first linkage attachment point offset from the first axis of rotation;

a first linkage coupled to the first gimbal at the first linkage attachment point;
a second gimbal rotatably coupled to the first gimbal, the second gimbal rotatable relative to the first gimbal about a second
axis of rotation, the second gimbal comprising a second linkage attachment point offset from the second axis of rotation;

a second linkage coupled to the second gimbal at the second linkage attachment point;
a grip; and
a shaft having a first end coupled to the second gimbal and a second end coupled to the grip; and
a rotorcraft control system operable to communicate commands to the rotor system based on movements of the first linkage and
the second linkage.

US Pat. No. 9,501,820

AUTOMATED NITAL ETCH INSPECTION SYSTEM

Bell Helicopter Textron I...

1. A quality control inspection system, comprising:
a first image capturing device configured to capture a first set of images of a part from a first angle relative to the part;
a second image capturing device configured to capture a second set of images of the part from a second angle relative to the
part, the second angle being different from the first angle; and

a computer operably associated with the first image capturing device and the second image capturing device, the computer being
configured to receive and analyze the first set of images and the second set of images and configured to identify a part flaw,
the computer having an image of a second part devoid of flaws;

wherein the first and second image capturing devices are repositionable relative to each other such that the first and second
angles vary as the first and second image capturing devices are repositioned;

wherein the part is pretreated with a nital etchant solution, a mixture of alcohol and nitric acid; and
wherein the computer is configured to compare the first and second sets of images of the part with the image of the second
part devoid of flaws to determine if the part has defects.

US Pat. No. 9,868,542

TILTROTOR AIRCRAFT HAVING PILLOW BLOCK MOUNTED PYLON ASSEMBLIES

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having
an airframe including a fuselage and a wing, the propulsion system comprising:
an engine supported by the airframe proximate an outboard end of the wing;
a fixed gearbox operably coupled to the engine and having an output gear;
inboard and outboard pedestals supported by the airframe and positioned above the wing;
a pylon assembly rotatably coupled between the inboard and outboard pedestals, the pylon assembly including a spindle gearbox
having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast,
the spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter
mode and the airplane mode; and

a common shaft configured to transfer torque from the output gear of the fixed gearbox to the input gear of the spindle gearbox,
the common shaft rotatable about the conversion axis;

wherein, each of the inboard and outboard pedestals further comprises a pillow block housing.

US Pat. No. 9,834,303

METHOD AND APPARATUS OF CONNECTING A FIXED DRIVE SYSTEM TO A ROTATING DRIVE SYSTEM FOR A TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A quill shaft configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle
gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft comprising:
a first splined portion configured for coupling to an output gear of the fixed gearbox;
a second splined portion configured for coupling to an input gear of the spindle gearbox;
wherein the spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor
aircraft can selectively operate in a helicopter mode and airplane mode; and

wherein the quill shaft is configured to selectively transfer torque to the rotatable spindle gearbox from a spiral bevel
gearbox associated with a first engine, wherein the quill shaft is configured to selectively transfer torque to the rotatable
spindle gearbox from an interconnect drive shaft associated with a second engine, and wherein an output of the spiral bevel
gearbox is not substantially coaxial with the quill shaft.

US Pat. No. 9,789,951

CUSTOMIZABLE PEDAL SYSTEM

BELL HELICOPTER TEXTRON I...

1. A pedal system comprising:
a support base;
a first lever that is pivotally mounted to the support base;
a second lever that is pivotally mounted to the support base;
a first pedal coupled to the first lever and configured to be engaged by a foot of a user to rotate the first lever;
a second pedal coupled to the second lever and configured to be engaged by a foot of the user to rotate the second lever;
a crank coupled to the first and the second lever, the first lever or the second lever, or both the first and the second levers,
being rotatable from a default rotational orientation, about an axis of rotation, of the first and the second lever to actuate
the crank, and

an adjustment assembly configured to adjust a position of the crank to modify the default rotational orientation of the first
and the second lever, the first and the second lever positioned at the same default orientation in absence of an external
force applied to the first and the second lever to move the first and the second lever,

wherein the default rotational orientation of the first and the second lever with respect to the support base is adjustable
without actuating the crank.

US Pat. No. 9,688,421

AIRCRAFT COMPONENT REGIME RECOGNITION

Bell Helicopter Textron I...

1. A system for assessing health of two or more components of an aircraft, the aircraft comprising a first component, a second
component, and one or more flight measurement sensors operable to provide a plurality of flight measurements, the system comprising:
a regime recognition system comprising:
a regime repository comprising a plurality of flight regime records, each flight regime record defining a flight regime; and
a regime engine configured to identify at least two flight regimes that the aircraft operated in at the same time, the regime
engine configured to identify the two flight regimes from the plurality of flight regimes based on a comparison of the plurality
of measurements to the plurality of flight regime records, the at least two flight regimes comprising a first flight regime
and a second flight regime; and a health assessment system comprising:

a component repository comprising a plurality of component records, each component record corresponding to a component of
the aircraft and comprising a prioritized list of flight regimes, the plurality of component records comprising a first component
record specific to the first component and a second component record specific to the second component; and

a component engine configured to:
assign one of the first flight regime and the second flight regime to the first component based on where the first flight
regime and the second regime are located within the prioritized list of flight regimes in the first component's component
record; and

assign one of the first flight regime and the second flight regime to the second component based on where the first flight
regime and the second regime are located within the prioritized list of flight regimes in the second component's component
record.

US Pat. No. 10,112,709

VIBRATION CONTROL WITH ACTIVE LAG DAMPER

Bell Helicopter Textron I...

17. A method to control vibratory forces exerted on an aircraft hub assembly via a plurality of rotor blades, comprising:attaching a damper to each of the plurality of rotor blades; and
controlling a dynamic spring rate of each of the dampers associated with the plurality of rotor blades by individual pump systems for each of the dampers;
wherein each damper is a closed loop control system that uses feedback sensors to inform a control computer of the damper properties and performance which is then used to determine an appropriate action of the pump system to adjust the dynamic spring rate of the damper to achieve optimum performance.

US Pat. No. 9,500,561

EMBEDDING FIBER OPTIC CABLES IN ROTORCRAFT COMPOSITES

BELL HELICOPTER TEXTRON I...

1. A method of positioning a fiber optic cable, the method comprising:
embedding a length of a fiber optic cable between layers of a composite rotorcraft material;
orienting a portion of the length of the fiber optic cable in a substantially S-shape between the layers;
extending an end of the portion of the length of the substantially S-shaped fiber optic cable to an edge of the composite
rotorcraft material, wherein the substantially S-shape is defined by a first concave portion and a second concave portion,
a first direction of orientation of the first concave portion is opposite a second direction of orientation of the second
concave portion, and the first direction of orientation of the first concave portion substantially tracks a circumference
of an ellipse having a maximum radius and a minimum radius; and

terminating the end of the portion of the length of the substantially S-shaped fiber optic cable at the edge of the composite
rotorcraft material.

US Pat. No. 9,994,308

HELICOPTER SKID LANDING GEAR

Bell Helicopter Textron I...

1. A helicopter skid landing gear comprising:two longitudinal skid tubes for contact with the ground;
a front cross tubes interconnecting the two skid tubes; and
a rear cross tube interconnecting the two skid tubes, at least one of the cross tubes including:
a monolithic metallic tube having a central portion extending transversely between two end portions with longitudinal central axes of the central portion and of the end portions being located in a same plane, with
at least part of the central portion having a cross-section defining first and second axes with the first axis, the second axis and the longitudinal axis of the central portion extending perpendicularly to each other and intersecting at a common point, one of the first and second axes extending along a minimum outer cross-sectional dimension of the central portion, the first axis extending at a first angle with respect to the plane, the second axis extending at a second angle with respect to the plane, the second angle smaller than the first angle; and
at least part of each end portion having a cross-section defining third and fourth axes with the third axis, the fourth axis and the longitudinal axis of the end portion extending perpendicularly to each other and intersecting at a common point, one of the third and fourth axes extending along a minimum outer cross-sectional dimension of the end portion, the third axis extending at a third angle with respect to the plane, the fourth axis extending at a fourth angle with respect to the plane, the fourth angle smaller than the third angle;
wherein the cross-section of the central portion has inner and outer heights defined along the second axis and the cross-section of the end portions each have inner and outer heights defined along the fourth axis, and the inner and outer heights of one of the central portion and the end portion are respectively greater than the inner and outer heights of the other of the central portion and the end portion
wherein the second angle is different from the fourth angle.

US Pat. No. 9,868,550

LONG AND SHORT RANGE STORAGE AND TRANSMISSION SYSTEM ON AIRCRAFT PARTS

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub;
a rotor blade coupled to the hub;
an aircraft part;
an aircraft part storage system comprising:
a first storage device comprising a radio frequency identification tag coupled to the aircraft part and operable to store
and transmit a first set of information identifying the aircraft part; and

a second storage device comprising a contact memory button coupled to the same aircraft part and operable to store and transmit
a second set of information about the aircraft part, the second storage device having a larger storage capacity than the first
storage device but a shorter transmission range than the first storage device;

a vibration sensor coupled to the rotorcraft proximate to the aircraft part and configured to measure and transmit vibration
load data to the second storage device, wherein the second set of information about the aircraft part comprises the vibration
load data; and

an aircraft part information system comprising:
a first data repository operable to receive the first set of information about the aircraft part from the first storage device;
a second data repository operable to receive the second set of information about the aircraft part from the second storage
device; and

a correlation engine operable to correlate information between the first data repository and the second data repository.

US Pat. No. 9,657,582

GIMBALED TAIL ROTOR HUB WITH SPHERICAL ELASTOMERIC CENTRIFUGAL FORCE BEARING FOR BLADE RETENTION AND PITCH CHANGE ARTICULATION

BELL HELICOPTER TEXTRON I...

1. A tail rotor assembly for a helicopter comprising a rotor hub and a rotor blade, the rotor hub comprising:
a gimbal assembly that transfers rotational movement of a mast to the rotor hub and comprising two opposing pairs of elastomeric
bearings that enable the rotor hub to flap relative to the mast;

a plate attached to the gimbal assembly;
a pitch horn/shear restraint comprising a rotatable connection to the plate; and
an elastomeric centrifugal force bearing attached to the hub plate and configured to withstand centrifugal force of a rotor
blade when the mast is rotated and that is configured to accommodate pitch changes of the rotor blade, wherein the rotor blade
is positioned between the rotatable connection of the pitch horn/shear restraint and the elastomeric centrifugal force bearing.

US Pat. No. 9,682,767

COLLECTIVE PITCH INTEGRATION WITH CONTROL POWER MANAGEMENT SYSTEM

Bell Helicopter Textron I...

1. A rotary aircraft, comprising:
a rotor blade;
a nacelle; and
a flight control system, having:
a first sensor associated with the nacelle, the first sensor being configured to detect an angle of the nacelle;
a second sensor associated with the rotary aircraft, the second sensor being configured to detect a first flight parameter
of the rotary aircraft;

a third sensor associated with the rotor blade, the third sensor being configured to detect a lateral flapping movement and
a longitudinal flapping movement of the rotor blade;

a collective pitch parameter; and
a subsystem associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the
subsystem having:

a first loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the
first loop being configured to determine a lower longitudinal cyclic limit created by the rotor blade during flight; and

a second loop associated with the first sensor, the second sensor, the third sensor, and the collective pitch parameter, the
second loop being configured to determine an upper longitudinal cyclic limit created by the rotor blade during flight.

US Pat. No. 9,505,490

COMPOSITE ROTOR SYSTEM USING TWO RACE TRACK STYLE CANTILEVERED YOKES

BELL HELICOPTER TEXTRON I...

1. A hub system comprising:
at least one race-track style yoke having an annular shape and comprising a mast section, an outboard section, and a flexure
section extending between the mast section and the outboard section, the at least one race-track style yoke comprising a first
race-track style yoke and a second race-track style yoke;

at least one shear bearing; and
at least one mast adapter comprising a plurality of mast adapter arms configured to attach to and support the at least one
race-track style yoke and directly attach to and support the at least one shear bearing, the plurality of mast adapter arms
comprising a first set of opposing arms extending from an intermediate member of the mast adapter and a second set of opposing
arms extending from the intermediate member, the intermediate member comprising a cylindrical body having a central mast aperture
configured to attach to a rotor mast, the first set of opposing arms attached to the intermediate member at a first end of
the intermediate member, and the second set of opposing arms attached to the intermediate member at a second end of the intermediate
member such that the first set of opposing arms is physically separate from the second set of opposing arms, the first set
of opposing arms connecting to the first race track style yoke, and the second set of opposing arms connecting to the second
race track style yoke;

wherein the flexure section is free from direct contact from the at least one mast adapter; and
wherein the at least one race-track style yoke has a flapping hinge that is non-coincident with a flapping hinge of the at
least one shear bearing.

US Pat. No. 9,464,958

DYNAMIC CENTER OF GRAVITY DETERMINATION

Bell Helicopter Textron I...

1. An on-board tiltrotor aircraft system for determining center of gravity of the tiltrotor aircraft, the system comprising:
one or more computers; and
a computer-readable medium storing instructions executable by the one or more computers to perform operations comprising:
storing a multi-dimensional matrix mapping a plurality of tiltrotor aircraft parameters to a plurality of three-dimensional
(3D) centers of gravity of the tiltrotor aircraft, each 3D center of gravity comprising a respective longitudinal center of
gravity, lateral center of gravity, and vertical center of gravity;

receiving a plurality of input signals from a corresponding plurality of on-board sensors, the plurality of input signals
representing characteristics of the tiltrotor aircraft;

determining one or more tiltrotor aircraft parameters from the plurality of input signals;
identifying, from the multi-dimensional matrix mapping, a longitudinal center of gravity, a lateral center of gravity, and
a vertical center of gravity that corresponds to the determined one or more tiltrotor aircraft parameters; and

providing the identified longitudinal center of gravity, the identified lateral center of gravity, and the identified vertical
center of gravity in response to receiving the plurality of input signals.

US Pat. No. 10,131,427

TILT-ROTOR OVER-TORQUE PROTECTION FROM ASYMMETRIC GUST

Bell Helicopter Textron I...

1. A system, comprising:a first mast torque transfer system;
a second mast torque transfer system coupled to the first mast torque transfer system; and
a torque limiting system, comprising:
a first sensor configured to determine a torque of the first mast torque transfer system;
a second sensor configured to determine a torque of the second mast torque transfer system; and
a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

US Pat. No. 9,994,300

STRAPPED WINDSHIELD ASSEMBLY FOR ROTORCRAFT

BELL HELICOPTER TEXTRON I...

1. A rotorcraft, comprising:an airframe;
a windshield;
a plurality of independent straps connected to the airframe and the windshield and extending between the airframe and the windshield configured to hold the windshield, each strap is separated from the other straps and operative to move independently with respect to the other straps and to flex with respect to the windshield and the airframe; and
wherein each strap is coupled to the windshield by a connector, the connector operative to allow movement of the windshield relative to the strap.

US Pat. No. 9,856,017

TORQUE BASED METHOD OF LIMITING VERTICAL AXIS AUGMENTATION

Bell Helicopter Textron I...

1. A system for limiting vertical axis augmentation in a rotorcraft, the system comprising:
a sensor configured to measure a torque during flight of the rotorcraft; and a computer having a control law, the control
law operable to generate a command to an actuator based upon a difference between a commanded vertical state and an actual
vertical state;

wherein the computer is configured for comparing the torque measured by the sensor to a predetermined lower torque limit,
such that when the torque is below the predetermined lower torque limit, the computer is configured to adjust the command
to prevent a decrease in torque below the lower torque limit, during flight of the rotorcraft;

wherein the computer is configured to adjust the command by reducing an authority of the command by a percentage of a total
command authority, the authority of the command being decreased in response to a decrease in the difference between the measured
torque and the lower torque limit;

wherein the reducing the authority of the command causes a change in the difference between the commanded vertical state and
the actual vertical state; and

when the measured torque were below a lower torque limit, the preventing a rotor overspeed of the rotorcraft is a higher priority
than maintaining the commanded vertical state.

US Pat. No. 9,796,479

SELF-REFERENCING SENSORS FOR AIRCRAFT MONITORING

BELL HELICOPTER TEXTRON I...

1. An aircraft monitoring system comprising:
a plurality of wireless aircraft sensors mounted on-board an aircraft, each wireless aircraft sensor configured to sense an
aircraft parameter;

a plurality of meta sensors mounted on-board the aircraft, each meta sensor associated with a respective wireless aircraft
sensor, each meta sensor configured to determine a location or orientation on the aircraft of the respective wireless aircraft
sensor with which each meta sensor is associated;

a data acquisition system mounted on-board the aircraft and connected to the plurality of wireless aircraft sensors and the
plurality of meta sensors, the data acquisition system comprising a computer-readable medium storing instructions executable
by one or more processors to perform operations comprising:

receiving the aircraft parameter(s) that each wireless aircraft sensor is configured to sense, a configuration information
for each wireless aircraft sensor, and the determined location or orientation on the aircraft of each wireless aircraft sensor
with which each meta sensor is associated,

identifying one or more aircraft monitoring operations that the aircraft monitoring system can perform using the received
configuration information and the received locations or orientations on the aircraft,

performing the identified aircraft monitoring operations based, in part, on the received aircraft parameters sensed by one
or more of the plurality of wireless aircraft sensors and on the received location or orientation of the one or more of the
plurality of wireless aircraft sensors determined by respective one or more of the meta sensors.

US Pat. No. 9,783,292

MAINTAINING DRIVE SYSTEM ALIGNMENT IN AIRCRAFT

Bell Helicopter Textron I...

1. A drive system for an aircraft having an airframe, the drive system comprising:
a first gearbox coupled to the airframe and having an input gear;
a second gearbox having an output gear;
a common shaft configured to transfer torque from the output gear of the second gearbox to the input gear of the first gearbox,
the common shaft rotatable about a longitudinal axis; and

a support assembly coupling the second gearbox to the airframe, the support assembly including a fixed joint proximate the
longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree
of freedom to the second gearbox relative to the longitudinal axis and a second directional reacting joint remote from the
longitudinal axis providing a second radial growth degree of freedom to the second gearbox relative to the longitudinal axis;

wherein, the first radial growth degree of freedom is not parallel with the second radial growth degree of freedom; and
wherein, the support assembly maintains the output gear of the second gearbox in substantial collinear alignment with the
input gear of the first gearbox.

US Pat. No. 9,739,326

ROTOR BRAKE WITH INTEGRATED IMPELLER

BELL HELICOPTER TEXTRON I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a main rotor system coupled to the power train, the main rotor system comprising at least one main rotor blade;
a rotor brake system coupled to the power train, the rotor brake system comprising at least one caliper, at least one brake
pad, a duct, and a rotor brake in mechanical communication with the drive shaft, the rotor brake comprising:

a first braking surface having an opening therethrough;
a second braking surface adjacent to the first braking surface; and
an impeller disposed between the first and second braking surfaces such that rotation of the impeller pulls fluid through
the opening of the first braking surface and expels the fluid out through a gap between the first and second braking surfaces;

wherein at least a portion of the rotor brake is disposed within the duct; and
wherein an end of the duct that is disposed nearest the first braking surface is offset from the first braking surface along
an axis of rotation of the impeller.

US Pat. No. 9,757,883

JOINING STRUCTURAL MEMBERS USING FOAM

BELL HELICOPTER TEXTRON I...

1. A method of forming an aircraft component, the method comprising:
bonding a first end of a honeycomb structure to a surface of an aircraft skin member, the honeycomb structure comprising a
plurality of connected cells;

spraying foam on a second end of the honeycomb structure, the second end opposite the first end;
curing the foam on the second end of the honeycomb structure;
wherein the aircraft skin member is a first aircraft skin member and the honeycomb structure is a first honeycomb structure,
and wherein the method further comprises:

bonding a first end of a second honeycomb structure to a surface of a second aircraft skin member, the second honeycomb structure
comprising a plurality of connected cells;

positioning an end of the first aircraft skin member adjacent an end of the second aircraft skin member to form a void in
which the foam on the first honeycomb structure is positioned adjacent the second honeycomb structure;

spraying foam in the void and on a second end of the second honeycomb structure and the foam on the first honeycomb structure,
the second end of the second honeycomb structure opposite the first end of the second honeycomb structure; and

curing the foam on the second end of the second honeycomb structure and the foam on the first honeycomb structure.

US Pat. No. 9,663,240

SELF-REFERENCING SENSORS FOR AIRCRAFT MONITORING

BELL HELICOPTER TEXTRON I...

1. An aircraft monitoring system comprising:
a plurality of wireless aircraft sensors mounted on-board an aircraft, each wireless aircraft sensor configured to sense an
aircraft parameter;

a plurality of meta sensors mounted on-board the aircraft, each meta sensor associated with a respective wireless aircraft
sensor, each meta sensor configured to determine a location or orientation on the aircraft of the respective wireless aircraft
sensor with which each meta sensor is associated;

a data acquisition system mounted on-board the aircraft and connected to the plurality of wireless aircraft sensors and the
plurality of meta sensors, the data acquisition system comprising a computer-readable medium storing instructions executable
by one or more processors to perform operations comprising:

receiving the aircraft parameter(s) that each wireless aircraft sensor is configured to sense, a configuration information
for each wireless aircraft sensor, and the determined location or orientation on the aircraft of each wireless aircraft sensor
with which each meta sensor is associated,

identifying one or more aircraft monitoring operations that the aircraft monitoring system can perform using the received
configuration information and the received locations or orientations on the aircraft,

performing the identified aircraft monitoring operations based, in part, on the received aircraft parameters sensed by one
or more of the plurality of wireless aircraft sensors and on the received location or orientation of the one or more of the
plurality of wireless aircraft sensors determined by respective one or more of the meta sensors.

US Pat. No. 9,534,644

MAGNETORHEOLOGICAL ROTORCRAFT ACTUATION SYSTEM

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device; and
an actuation system in mechanical communication between the pilot input device and the rotor system, the actuation system
comprising:

a plurality of threaded member portions comprising a first threaded member portion having a first thread and a second threaded
member portion having a second thread;

a plurality of roller nuts comprising a first roller nut configured to receive the first thread of the first threaded member
portion and a second roller nut configured to receive the second thread of the second threaded member portion;

a driving member configured to receive mechanical energy from a power source, the driving member coupled to either the plurality
of threaded member portions or the plurality of roller nuts;

a plurality of driven members comprising a first driven member and a second driven member, each of the plurality of driven
members being coupled to either a corresponding threaded member portion of the plurality of threaded member portions or a
corresponding roller nut of the plurality of roller nuts;

a magnetorheological (MR) fluid disposed between the plurality of driven members and at least one braking surface, the MR
fluid configured to generate a variable amount of friction between the plurality of driven members and the at least one braking
surface;

a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the
strength of the magnetic field in response to inputs received from the pilot input device; and

an output member coupled between the rotor system and either the plurality of threaded member portions or the plurality of
roller nuts and configured to translate linearly in response to the threaded member portions advancing or receding within
the roller nuts.

US Pat. No. 9,488,109

SERIES BATTERY START CONTROLLER

BELL HELICOPTER TEXTRON I...

1. An apparatus, comprising:
a series switching logic;
a relay control switch electrically coupled to the series switching logic; and
a series-parallel relay electrically coupled to the relay control switch, wherein the series-parallel relay is configured
to selectively configure a plurality of batteries between a series and parallel connection; and

wherein the series switching logic comprises a bipolar junction transistor, an emitter of the bipolar junction transistor
is electrically coupled to an engine start input, a base of the bipolar junction transistor is electrically coupled to an
external power input, and a collector of the bipolar junction transistor is electrically coupled to a first terminal of a
first resistor.

US Pat. No. 9,870,004

HIGH AUTHORITY STABILITY AND CONTROL AUGMENTATION SYSTEM

Bell Helicopter Textron I...

1. A rotary aircraft, comprising:
a fuselage;
a rotary system carried by the fuselage;
a control input having a first axis;
a first flight control computer carried by the fuselage, the first flight control computer having;
a first processor for commanding the first actuator; and
a second processor for commanding the first actuator;
a second flight control computer carried by the fuselage;
a first actuator commanded by the first flight control computer for manipulating the rotary system along the first axis;
a second actuator commanded by the second flight control computer for manipulating the rotary system along the first axis;
and

a third actuator for manipulating the rotary system along the first axis;
wherein the first actuator compares commands from the first processor of the first flight control computer to commands from
the second processor of the first flight control computer to find a failure in the first actuator; and

wherein an output of the first actuator is summed with an output of the second actuator and summed with the control input
for manipulating the rotary system with full authority in only the first axis by controlling the third actuator.

US Pat. No. 9,701,403

BROAD GOODS COMPOSITE YOKE FOR ROTOR SYSTEM

Bell Helicopter Textron I...

1. A tiltrotor aircraft, comprising:
a body;
a wing member;
a power train coupled to the body and comprising a power source and a drive shaft in mechanical communication with the power
source;

a plurality of rotor blades comprising a first rotor blade, a second rotor blade, and a third rotor blade; and
a rotor system coupled to the wing member and in mechanical communication with the drive shaft, at least part of the rotor
system being tiltable between a helicopter mode position and an airplane mode position, the rotor system comprising a yoke
coupled between the drive shaft and the plurality of rotor blades, wherein:

the yoke comprises a plurality of arms corresponding in number to the plurality of rotor blades, the plurality of arms comprising
a first arm oriented along a first axis and coupled to the first rotor blade, a second arm oriented along a second axis and
coupled to the second rotor blade, and a third arm oriented along a third axis and coupled to the third rotor blade; and

the plurality of arms, in combination, comprises:
a first plurality of fibrous plies, each fibrous ply of the first plurality of fibrous plies extending continuously throughout
all of the plurality of arms, each fibrous ply of the first plurality of fibrous plies comprising a plurality of fibers aligned
in a direction that is substantially parallel to the first axis;

a second plurality of fibrous plies, each fibrous ply of the second plurality of fibrous plies extending continuously throughout
all of the plurality of arms, each fibrous ply of the second plurality of fibrous plies comprising a plurality of fibers aligned
in a direction that is substantially parallel to the second axis; and

a third plurality of fibrous plies, each fibrous ply of the third plurality of fibrous plies extending continuously throughout
all of the plurality of arms, each fibrous ply of the third plurality of fibrous plies comprising a plurality of fibers aligned
in a direction that is substantially parallel to the third axis.

US Pat. No. 9,695,837

DIRECT DRIVE DEVICE FOR PASSIVELY MOVING FLUID

Bell Helicopter Textron I...

1. A device for moving a fluid within a gearbox, the device comprising:
a screw member coupled to a rotatable member within the gearbox;
a casing having an inlet that is submerged in a fluid reservoir, the casing is supported by an attachment to a floor of the
fluid reservoir;

wherein rotation of the rotatable member causes the screw member to rotate, thereby causing a fluid to be drawn into the inlet.

US Pat. No. 9,517,842

FILTERS FOR AIRCRAFT ENGINE INLETS

BELL HELICOPTER TEXTRON I...

1. An aircraft engine barrier filtration system comprising: an engine barrier filter layer positioned near an aircraft engine
intake, the filter layer to filter aircraft engine intake air; and a passive one-way check valve assembly positioned adjacent
to the engine barrier filter layer, the passive one-way check valve assembly to permit the engine intake air to flow into
the engine in a first flow direction through the filter layer during a first aircraft operation mode and to substantially
prevent air flow away from the engine in a second flow direction through the filter layer opposite the first flow direction
during a second aircraft operation mode that is different from the first aircraft operation mode; wherein the check valve
assembly comprises a system of reed valves; with: a first layer comprising a plurality of openings; and a second layer attached
to the first layer, the second layer comprising a plurality of reeds, each reed aligned with a corresponding opening of the
plurality of openings.

US Pat. No. 9,873,507

ROTORCRAFT ELASTOMERIC BEARING ASSEMBLY

Bell Helicopter Textron I...

1. A rotor system for a rotorcraft, the rotor system comprising:
a yoke;
a blade; and
a spindle associated with the yoke, wherein the center length of the spindle defines a center axis that passes through a center
of an elastomeric bearing assembly, wherein the elastomeric bearing assembly comprises:

a housing disposed around the center axis, the housing configured to rotate about the center axis, the housing coupled to
the blade;

an elastomeric shear bearing, wherein an interior portion of the shear bearing is coupled to the spindle, an exterior portion
of the shear bearing is coupled to the housing, an outer perimeter of the shear bearing comprises a race that has a first
radial aperture and the housing has a second radial aperture, the first and second radial aperture configured to allow a fastener
to be disposed within both the first and second radial aperture, and wherein the shear bearing is configured to counteract
a torsional force; and

an elastomeric centrifugal force bearing pressed against the housing, the centrifugal force bearing configured to counteract
a compression force.

US Pat. No. 9,868,522

ROTORCRAFT AUTOPILOT CONTROL

BELL HELICOPTER TEXTRON I...

1. A rotorcraft autopilot system, comprising:
a series actuator connecting a cockpit control component to a swashplate of a rotorcraft, the series actuator to modify a
control input from the cockpit control component to the swashplate through a downstream control component;

a differential friction system connected to the cockpit control component and the downstream control component, the differential
friction system comprising a variable friction device grounded to the rotorcraft proximate the downstream control component,
the variable friction device configured to increase or decrease a friction on the downstream control component; and

wherein the differential friction system is configured to selectively apply the friction on the downstream component to control
the series actuator to automatically adjust a position of the cockpit control component during rotorcraft flight based, in
part, on a flight mode of the rotorcraft.

US Pat. No. 9,701,406

CONVERTIBLE TILTROTOR AIRCRAFT

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a wing coupled to the body;
an engine;
a first proprotor coupled to the wing, the first proprotor comprising:
a plurality of blades;
a shaft defining a first axis in mechanical communication with the first proprotor, wherein the shaft is configured to selectively
rotate around the first axis;

a pusher propeller; and
a torque splitter comprising:
a sun gear;
a ring gear;
a planet carrier in mechanical communication with the shaft;
a plurality of planetary gears, each in mechanical communication with the planet carrier and the ring gear and the sun gear;
and

a clamp associated with the ring gear, the clamp being configured to selectively prevent rotation of the ring gear.

US Pat. No. 9,656,735

SKIN IMPACT SNUBBER

Bell Helicopter Textron I...

1. An aircraft comprising:
a structural assembly comprising a first rigid element and a second rigid element, the first and second rigid elements separated
from each other longitudinally by a void;

a skin disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect inward into
the void in response to an impact force received by the skin; and

a snubber disposed in the void and extending longitudinally between the first and second rigid elements and positioned such
that, when the skin deflects inwardly in response to the impact force, the skin contacts the snubber and the snubber reduces
further deflection of the skin into the void;

wherein prior to the impact force, the first rigid element is not between the second rigid element and the skin and the second
rigid element is not between the first rigid element and the skin.

US Pat. No. 9,683,652

METHOD FOR THE DELIVERY OF LUBRICANT TO A ROTORCRAFT GEARBOX

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a rotor blade;
a power train coupled to the body and operable to rotate the rotor blade, the power train comprising:
an engine;
a gearbox in mechanical communication with the engine; and
a driveshaft in mechanical communication with the gearbox;
a sensor operable to detect a rotorcraft parameter;
a main lubrication system configured to deliver lubricant to the gearbox, the main lubrication system comprising a main lubrication
reservoir and a main pressurizing device;

a secondary lubrication system configured to deliver lubricant to the gearbox, the secondary lubrication system comprising
a secondary lubrication reservoir and a secondary pressurizing device; and

a lubrication flow calculation unit operable to:
receive the rotorcraft parameter;
generate a flow rate based on the rotorcraft parameter, wherein the flow rate increases the amount of time that the rotorcraft
can operate when the gearbox experiences a reduction in lubricant pressure; and

transmit the flow rate to the secondary lubrication system;
wherein one of the primary and secondary lubrication systems delivers lubricant to the gearbox at the generated flow rate.

US Pat. No. 9,550,334

METHOD OF REPAIRING A CORE STIFFENED STRUCTURE

Bell Helicopter Textron I...

1. A method of repairing a core stiffened structure, the method comprising:
removing a damaged portion of the core stiffened structure to expose a non-damaged portion of an existing core member;
cutting a repair core member from a repair core material;
fitting the repair core member onto the existing core member such that the repair core member mates with the non-damaged portion
of the existing core member;

bonding the repair core member to the existing core member; and
placing a skin patch over the repair core member,
wherein the step of bonding the repair core member to the existing core member includes pouring a foam mixture into a plurality
of cells formed by the existing core member and the repair core member.

US Pat. No. 9,541,468

SYSTEM AND METHOD FOR IMPROVING A WORKPIECE

BELL HELICOPTER TEXTRON I...

1. A method of modifying a workpiece, comprising:
providing a workpiece;
determining a tensile load stress profile associated with a tensile load condition;
determining a compressive load stress profile associated with a compressive load condition;
determining a residual stress profile, wherein a sum of the tensile load stress and the residual stress is within a tensile
stress limit and a sum of the compressive load stress and the residual stress is within a compressive stress limit of the
workpiece; and

providing the workpiece with the residual stress profile.

US Pat. No. 9,879,722

LOW SHEAR MODULUS TRANSITION SHIM FOR ELASTOMERIC BEARING BONDING IN TORSIONAL APPLICATIONS

BELL HELICOPTER TEXTRON I...

1. A bearing assembly comprising:
a bearing comprising alternating rigid and elastomeric layers;
a shim fitted within the bearing, the shim comprising fiberglass;
a metal rotor blade spindle disposed within the shim; and
an adhesive layer that adheres the shim to the metal rotor blade spindle,
wherein the shim comprises a first material and the metal rotor blade spindle a second material,
wherein the first material has an elastic modulus value that is lower than an elastic modulus value of the second material,
and the shim is configured to absorb at least a portion of a torsional strain between the metal rotor blade spindle and the
bearing that reduces torsional strain on the adhesive layer.

US Pat. No. 9,828,088

SCISSORING FOLD ARRANGEMENT FOR DUAL PLANE FOUR BLADED ROTOR HUBS

Bell Helicopter Textron I...

1. A rotor blade system, comprising:
a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast;
a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly
being positioned at a space relative to the first hub assembly;

a torque splitter device engaged with both the first hub assembly and the second hub assembly; and
an actuator operably associated with the torque splitter;
wherein the actuator is configured to rotate the torque splitter;
wherein the torque splitter device is configured to allow movement of the of the first hub assembly relative to the second
hub assembly; and

wherein the torque splitter device comprises:
a base;
a first opening extending through the base and configured to receive a first shaft associated with the first hub assembly;
a second opening extending through the base and configured to receive a second shaft associated with the second hub assembly;
and

an extension member configured to engage with the first opening and the first shaft.

US Pat. No. 9,821,520

HYBRID COMPOSITE-METAL SHAFT

Bell Helicopter Textron I...

1. A method for making a composite-metal hybrid shaft for a rotorcraft, comprising:
providing a tubular metal member that includes an internal surface defining a space therein;
providing a curing tool;
preparing a composite member by placing a plurality of composite layers onto the curing tool, wherein the plurality of composite
layers consists of a carbon-reinforced epoxy material;

placing a sacrificial fiberglass layer on the composite member, the fiberglass layer being an outer layer with respect to
all layers of carbon-reinforced epoxy material;

curing the composite member with the outer fiberglass layer, creating a cured composite member;
expanding the metal member with heat, creating an expanded metal member;
placing the cured composite member completely into the space defined by the internal surface of the expanded metal member;
and

allowing the expanded metal member to cool;
wherein the cured composite member reinforces the composite-metal hybrid shaft.

US Pat. No. 9,777,788

ROTORCRAFT VIBRATION SUPPRESSION SYSTEM IN A FOUR CORNER PYLON MOUNT CONFIGURATION

Bell Helicopter Textron I...

1. A pylon mount structural assembly for an aircraft, comprising:
a first pylon structure extending between a first set of vibration isolators, the pylon structure being configured to suspend
a first portion of a vibrating body between the first set of vibration isolators; and

a second pylon structure extending between a second set of vibration isolators, the pylon structure being configured to suspend
a second portion of the vibrating body between the second set of vibration isolators;

wherein each pylon structure is formed to locate the vibration isolators away outboard from a point of coupling between the
vibrating body and each of the first and the second pylon structure;

wherein each vibration isolator includes a spherical bearing assembly having a spherical elastomeric member coupled to an
airframe of the aircraft;

wherein each of the spherical bearing assemblies are located on a centerline plane equal to a waterline of a driveshaft axis;
and

wherein a location of the spherical bearing assembly minimizes chucking in a coupling.

US Pat. No. 9,656,745

MAGNETORHEOLOGICAL ACTUATOR WITH TORSIONAL SPRING

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine;
a rotor system coupled to the power train, the rotor system comprising at least one rotor blade;
a pilot input device; and
an actuator in mechanical communication with the pilot input device, the actuator comprising:
a driving member configured to receive mechanical energy from a power source;
a driven member;
a magnetorheological (MR) fluid disposed between the driving member and the driven member and configured to transmit a variable
amount of mechanical energy from the driving member to the driven member such that the driven member moves in a first direction;

an output member coupled between the driven member and the pilot input device;
a spring in mechanical communication with the output member and configured to apply a force in a second direction opposite
of the first direction; and

a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to control
movement of the pilot input device by varying the strength of the magnetic field delivered towards the MR fluid.

US Pat. No. 9,650,128

AIRCRAFT LANDING GEAR

Bell Helicopter Textron I...

1. A landing gear for an aircraft, the landing gear comprising:
a wheel in mechanical communication with an axle forming a wheel assembly;
a strut coupled to the wheel assembly and configured to resist longitudinal compression along a first axis, the strut comprising:
a piston having an opening therein; and
a housing associated with the piston; and
a linear actuator comprising:
a one-piece elongated shaft at least partially disposed within the opening of the piston; and
a motor operable to reposition the strut by rotating the elongated shaft;
wherein the piston and the one-piece elongated shaft are substantially centered on the first axis.

US Pat. No. 10,183,745

TILTROTOR WITH INBOARD ENGINES

BELL HELICOPTER TEXTRON I...

1. An aircraft, comprising:a fuselage;
a wing coupled to the fuselage;
a first rotor system coupled to the wing, the first rotor system comprising:
a first proprotor system comprising a first pylon disposed proximate to a first wing tip of the wing, the first pylon being tiltable between a helicopter mode position and an airplane mode position;
a first engine in mechanical communication with the first proprotor system and coupled above the wing proximate to the first wing tip, outboard of the fuselage, and inboard of the first pylon;
a second rotor system coupled to the wing, the second rotor system comprising:
a second proprotor system comprising a second pylon disposed proximate to a second wing tip of the wing opposite the first wing tip, the second pylon being tiltable between a helicopter mode position and an airplane mode position; and
a second engine in mechanical communication with the second proprotor system and coupled above the wing proximate to the second wing tip, outboard of the fuselage, and inboard of the second pylon;
one or more interconnect drive shafts in mechanical communication with the first and second engines;
a first gearbox in mechanical communication with the first engine, the first proprotor system, and the one or more interconnect drive shafts; and
a second gearbox in mechanical communication with the second engine, the second proprotor system, and the one or more interconnect drive shafts;
an interconnect driveshaft gear configured to communicate mechanical energy between the first gearbox and the one or more interconnect driveshafts;
one or more accessory gears coplanar with and in mechanical communication with the interconnect driveshaft gear;
a proprotor gear located inboard of the first proprotor system, the proprotor gear being coplanar with and in mechanical communication with the interconnect driveshaft gear and the one or more accessory gears, the proprotor gear configured to communicate mechanical energy to the first proprotor system; and
an engine gear coplanar with and in mechanical communication with the interconnect driveshaft gear, the one or more accessory gears, and the proprotor gear, the engine gear configured to transmit mechanical energy from the first engine to the first proprotor system via the proprotor gear.

US Pat. No. 9,981,750

TILTROTOR AIRCRAFT HAVING SPHERICAL BEARING MOUNTED PYLON ASSEMBLIES

Bell Helicopter Textron I...

1. A propulsion system for a tiltrotor aircraft having a helicopter mode and an airplane mode, the tiltrotor aircraft having an airframe including a fuselage and a wing, the propulsion system comprising:an inboard pedestal supported by the airframe and positioned above the wing, the inboard pedestal including an inboard spherical bearing;
an outboard pedestal supported by the airframe and positioned above the wing, the outboard pedestal including an outboard spherical bearing; and
a pylon assembly coupled to the inboard and outboard spherical bearings such that the pylon assembly is rotatably positioned between the inboard and outboard pedestals, the pylon assembly including a spindle gearbox rotatable about a conversion axis to selectively operate the tiltrotor aircraft between the helicopter mode and the airplane mode;
wherein, the spherical bearings provide a self-aligning coupling between the pylon assembly and the inboard and outboard pedestals, thereby reducing alignment sensitivity between the inboard and outboard pedestals.

US Pat. No. 9,745,055

ACTIVE VIBRATION ISOLATION WITH DIRECT FLUID ACTUATION

BELL HELICOPTER TEXTRON I...

1. A method of isolating vibrations between vibrating bodies, the method comprising:
determining a pressure differential between a first fluid chamber and a second fluid chamber of a liquid inertia vibration
eliminator (LIVE) unit, the LIVE unit comprising the first fluid chamber, the second fluid chamber, and a port connecting
the first chamber and the second chamber, wherein the first chamber, second chamber, and the connecting port define a volume
occupied by a fluid, and the LIVE unit is tuned to a vibration isolation frequency between the vibrating bodies and has one
or more frequency response characteristics; and

selectively adjusting the vibration isolating frequency and the one or more frequency response characteristics of the LIVE
unit based on the pressure differential using a fluid regulator in fluid communication between the LIVE unit and a fluid source,
wherein the fluid regulator selectively injects fluid from the fluid source into one of the fluid chambers of the LIVE unit
and simultaneously withdraws and returns fluid from the other fluid chamber of the LIVE unit to the fluid source.

US Pat. No. 9,656,744

ADJUSTABLE BLADE-TO-HUB LEAD-LAG DAMPER ATTACHMENT

Bell Helicopter Textron I...

1. An aircraft, comprising:
a rotor blade; and
a rotor hub system, having:
a lead-lag damper having a rod end and being operably associated with the rotor blade;
a blade adapter, having:
a first arm and an opposing second arm;
a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and
an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and
the second arm.

US Pat. No. 9,891,196

ULTRASONIC INSPECTION OF COMPOSITE PARTS

BELL HELICOPTER TEXTRON I...

1. A method to inspect a plurality of composite components of an aircraft, the method comprising:
identifying the plurality of composite components of an aircraft in need of ultrasonic inspection;
traversing a plurality of ultrasonic probe arrays capable of being repositioned in different configurations on surfaces of
a first composite component of the aircraft, wherein the surfaces are either separate from or at angles to each other;

simultaneously passing a plurality of ultrasonic signals into the plurality of component surfaces of the composite component
by:

generating a plurality of ultrasonic signals; and
transmitting the plurality of ultrasonic signals through the composite components;
detecting, using the plurality of ultrasonic probe arrays, ultrasonic signals that are transmitted through and reflected from
the first composite component; and

determining the position of the plurality of repositionable ultrasonic probe arrays with an encoder to identify the location
of defects or features of the first composite components;

repositioning the ultrasonic probe arrays into a new configuration on the surface of the aircraft to match a second composite
component within the aircraft; and repeating the detection step to identify additional defects on the aircraft.

US Pat. No. 9,857,158

ESTIMATING THICKNESS OF A MATERIAL LAYER ON AN AIRCRAFT

BELL HELICOPTER TEXTRON I...

1. A wireless system for estimating a thickness of a material layer adjacent a surface of an aircraft component, comprising:
a plurality of tag devices located between a portion of the material layer and a portion of the surface, each tag device capable
of wireless communication, wherein the material layer comprises a thickness that decreases over time in response to the aircraft
component being used;

a transceiver configured to wirelessly communicate with the plurality of tag devices, wherein a signal strength of each of
wireless signals received from the corresponding tag device from the plurality of tag devices and by the transceiver varies
with the thickness of the material layer; and

one or more processors connected to the transceiver and configured to calculate the thickness of the material layer based
on the signal strengths and tag identification information of the wireless signals from the plurality of tag devices, the
one or more processors configured to triangulate a relative position between the transceiver and the plurality of tag devices
to compensate for the relative position when determining the thickness of the material layer.

US Pat. No. 9,765,641

SYSTEM AND METHOD FOR VIBRATION ISOLATION

Bell Helicopter Textron I...

3. A system, comprising:
a first housing comprising a first volume of fluid, the first housing operable to couple to a first element and to a second
element, the first housing comprising:

a first portion operable to couple to the second element;
a second portion operable to couple to the second element; and
a moveable portion operable to couple to the first portion and the second portion, the moveable portion further operable to
couple to the first element;

a second housing coupled to the first housing, the second housing comprising a second volume of fluid and a volume of gas,
the first volume of fluid being in fluid communication with the second volume of fluid;

a seal positioned within the second housing, the seal operable to separate the second volume of fluid from the volume of gas;
a spring system positioned within the second housing, the spring system operable to apply pressure to the first volume of
fluid and the second volume of fluid; and

a piston positioned within the second housing and between the seal and the spring system;
wherein the seal is in contact with the second volume of fluid and further positioned between the second volume of fluid and
the spring system;

wherein the first housing is operable to reduce an amount of movement transferred from the first element to the second element
by transferring a portion of the first volume of fluid from the second portion of the first housing to the first portion of
the first housing through the moveable portion, wherein the first volume of fluid is operable to be transferred from the second
portion of the first housing to the first portion of the first housing due to movement of the moveable portion.

US Pat. No. 9,630,724

SINGLE-GAUGE MONITORING OF MULTIPLE COMPONENTS

Bell Helicopter Textron I...

1. A rotorcraft, comprising:
a body;
a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;
a hub;
a rotor blade coupled to the hub;
a first sensor configured to measure a first performance aspect of a gearbox in mechanical or fluid communication with the
power source;

a second sensor configured to measure a second performance aspect of a gearbox in mechanical or fluid communication with the
power source, the first and second performance aspects both being either temperature aspects or pressure aspects;

a gauge disposed within a cockpit of the body and operable to display information to a pilot; and
a display prioritization system configured to:
receive a first measurement from the first sensor and a second measurement from the second sensor;
select a prioritization criterion based on at least the received first and second measurements;
select, without user input, one priority measurement for display from the received measurements based on the prioritization
criterion selected by the display prioritization system; and

instruct the gauge to display information representative of the one priority measurement selected by the display prioritization
system without user input such that the gauge displays only the information representative of the one priority measurement
and does not display information representative of any other received measurements.

US Pat. No. 9,889,927

VARIABLE HUB-TO-HUB PHASING ROTOR SYSTEM

Bell Helicopter Textron I...

1. An aircraft, comprising:
a first rotor assembly and a second rotor assembly;
a rotor phase angle control system having a phase adjustor operably associated with the first rotor assembly and the second
rotor assembly, wherein the phase adjustor is a clutch;

a first output shaft rotatably attached to both the clutch and the first rotor assembly; and
a second output shaft rotatably attached to both the clutch and the second rotor assembly;
wherein the clutch is configured to disengage and reengage with the first output shaft and the second output shaft so as to
offset the first rotor assembly relative to the second rotor assembly;

wherein the first rotor assembly rotates relative to the second rotor assembly; and
wherein the phase adjustor is configured to adjust the phase angle of the first rotor assembly relative to the second rotor
assembly during flight.

US Pat. No. 10,086,934

COMPOSITE ROTOR SYSTEM USING TWO RACE TRACK STYLE CANTILEVERED YOKES

BELL HELICOPTER TEXTRON I...

1. A hub system comprising:a stacked yoke comprising at least a first race-track style yoke and a second race-track style yoke each having an annular shape; and
a mast adapter configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation, and configured to attach to and support the stacked yoke, the mast adapter including an outer plate and an inner plate connected by a web, wherein the inner plate attaches to the stacked yoke and comprises an inboard section that is not connected to any other portion of the mast adapter such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.