US Pat. No. 9,505,492

MISSION ADAPTIVE ROTOR BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A rotor assembly for a rotary wing aircraft comprising:
a plurality of rotor blades operably connected to a rotor shaft; and
active adaptive devices disposed at one or more rotor blades of the plurality of rotor blades, the active adaptive devices
operably connected to an aircraft flight control system such that, when activated, the active adaptive devices change one
or more operational characteristics of the rotor assembly, the active adaptive devices including:

a spar air duct extending along one or more rotor blades of the plurality of rotor blades, the spar air duct having at least
one inlet disposed at a first edge of the rotor blade and at least one outlet disposed at a second opposing edge of the rotor
blade;

one or more valves to selectively turn on an airflow through the at least one outlet for a first mission and turn off an airflow
through the at least one outlet for a second mission; and,

a blade tip outlet disposed at a blade tip of the one or more rotor blades, the blade tip outlet in fluid communication with
the spar air duct;

wherein an airflow through the spar air duct is selectably urgable through the at least one outlet to increase lift of the
one or more rotor blades in the first mission, and selectably urgable through the blade tip outlet to reduce noise of the
rotor assembly in the second mission.

US Pat. No. 9,555,880

FLEXBEAM ROTOR

SIKORSKY AIRCRAFT CORPORA...

12. A rotor assembly for a helicopter comprising:
a rotor hub operably connectable to a shaft of a helicopter;
at least two flex beams extending through the rotor hub within the same plane, the at least two flex beams comprising a first
flex beam and a second flex beam, wherein an opening formed in the first flex beam defines a passage through which the second
flex beam extends through the first flex beam such that the first flex beam and the second flex beam cross at an axis of the
shaft;

one or more inner bearings disposed at the rotor hub to spherically support the at least two flex beams in the rotor hub,
the rotor hub being configured to provide a preload required for operation of the one or more inner bearings; and

a plurality of rotor blades, each rotor blade operably connected to one end of the at least two flex beams.

US Pat. No. 9,203,459

HARMONIC DATA TRANSFER IN ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft comprising:
a rotor assembly including:
a rotor sensor generating a rotor sensor time domain signal;
a rotor transform module converting the rotor sensor time domain signal to a rotor sensor frequency domain signal; and
a rotor transceiver for transmitting the rotor sensor frequency domain signal over a transfer medium;
an airframe assembly including:
an airframe transceiver receiving the rotor sensor frequency domain signal; and
an airframe transform module converting the rotor sensor frequency domain signal to the rotor sensor time domain signal.

US Pat. No. 9,284,029

HELICOPTER EXTERNAL LIFE RAFT POD

SIKORSKY AIRCRAFT CORPORA...

1. An emergency pod configured for use with a rotary wing aircraft, comprising:
a rigid, generally hollow shell including a movable portion configured to move between a closed position and an open position,
wherein the shell is configured as a floatation device when the movable portion is in the closed position and the open position;

an inflatable life raft arranged within an interior portion of the hollow shell, the life raft being coupled to an inflation
mechanism; and

a first activation device and a second activation device operably coupled to the inflation mechanism, the second activation
device being disposed within the shell and fastened to the movable portion of the shell, wherein the first activation device
and the second activation device are operable independently of one another and are configured to operate the inflation mechanism
to initiate inflation of the life raft when a force is applied to either the first activation device or the second activation
device.

US Pat. No. 9,284,050

AIRFOIL FOR ROTOR BLADE WITH REDUCED PITCHING MOMENT

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade for a rotary wing aircraft comprising:
a root region extending from a rotor head to about 15% to 20% of a blade radius;
a main region extending from a radial extent of the root region to about 80% to 95% of the blade radius; and
a tip region extending from a radial extent of the main region to a blade tip, at least a portion of one of the root region,
the main region and the tip region including an airfoil profile section defined by a scaled set of coordinates in which a
set of x/c coordinates defined as a ratio of an x coordinate to a blade chord length, and y/c coordinates defined as a ratio
of a y coordinate to the blade chord length, listed in Table I are scaled by a selected factor.

US Pat. No. 9,169,971

SEALED BEARING ASSEMBLY FAILURE DETECTION

Sikorsky Aircraft Corpora...

1. An anti-torque system for a rotary wing aircraft comprising:
an outer ring of a sealed bearing;
an inner ring of said sealed bearing
a bearing element between said outer ring and said inner ring; and
a multiple of ferrous metal segments bonded to said inner ring with a thermally-affected bonding agent, the thermally-affected
bonding agent operable to break down at a temperature threshold and detach at least one of the multiple of ferrous metal segments
from the inner ring, said inner ring defines a rod end engageable with a servo.

US Pat. No. 9,097,496

LIGHTWEIGHT PROJECTILE RESISTANT ARMOR SYSTEM WITH SURFACE ENHANCEMENT

SIKORSKY AIRCRAFT CORPORA...

1. A hard ballistic material comprising:
a monolithic ceramic layer;
a Diamond-Like Carbon (DLC) coating applied to a front face of said monolithic ceramic layer; and
a rear face Ceramic Matrix Composite (CMC) layer continuously bonded to a rear face of said monolithic ceramic layer, wherein
said rear face CMC layer includes one of (1) a ceramic matrix and (2) a glass matrix.

US Pat. No. 9,243,675

ROTOR BRAKE

SIKORSKY AIRCRAFT CORPORA...

1. A brake disc of a rotor brake comprising:
a generally cylindrical body having a first planar surface, a second, opposite planar surface, and a central opening extending
there through;

a plurality of first connection members extending generally outwardly from the first planar surface, the first connection
members being generally equidistantly spaced about a diameter of the first planar surface; and

a plurality of second connection members extending generally outwardly from the second planar surface, the second connection
members being generally equidistantly spaced about a diameter of the second planar surface;

wherein at least one of the plurality of first connection members and second connection members are substantially similar
in size and/or shape.

US Pat. No. 9,470,793

OPTICAL TRACKING OF ROTOR BLADE MOTION

SIKORSKY AIRCRAFT CORPORA...

1. An optical blade tracking system for a rotary wing aircraft, the system comprising:
a light source generating at least one polarized light beam, the light source coupled to a rotor blade of the rotary wing
aircraft, wherein movement of the rotor blade is imparted to the light source;

a two-dimensional position detector generating signals indicative of a position of the light beam along a first axis and a
position of the light beam along a second axis, the first axis and the second axis being in the same plane, the two-dimensional
position detector generating an intensity signal indicative of an angular position of the light beam about a third axis, the
third axis perpendicular to the plane;

a processor receiving the signals, the processor determining at least one of lead-lag, flap and pitch of the rotor blade in
response to the signals; and

a polarizer filter positioned between the light source and the two dimensional position detector, the polarizer filter modulating
intensity of the light beam onto the two-dimensional position detector.

US Pat. No. 9,352,841

VIRTUAL ICE ACCRETION METER DISPLAY

Sikorsky Aircraft Corpora...

1. A flight display for an aircraft, comprising:
a virtual ice accretion meter display having a liquid water content portion and an ice thickness portion, wherein the ice
thickness portion is configured to display a virtual ice thickness value, wherein the virtual ice thickness value is calculated
as a function of a liquid water content (LWC), an airspeed through an icing cloud, and a time of passage through the icing
cloud.

US Pat. No. 9,193,455

FLY BY WIRE SERVOS WITH INTERNAL LOOP CLOSURE

SIKORSKY AIRCRAFT CORPORA...

1. A servo assembly comprising:
a hydraulic primary servo;
a plurality of electro-mechanical actuators coupled to the primary servo and configured to drive the primary servo;
at least one device configured to perform loop closure; and
a summation bar coupled to a plurality of output arms associated with the plurality of electro-mechanical actuators and configured
to perform a mechanical averaging of differences in outputs of the electro-mechanical actuators.

US Pat. No. 9,068,999

AIRSPEED ESTIMATION USING ROTOR VIBRATIONS

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
determining, by a computing device comprising a processor, at least one parameter associated with a rotorcraft;
obtaining, by the computing device, a profile of a vibration associated with operation of the rotorcraft based on the at least
one parameter;

determining, by the computing device, an amplitude of the vibration using the profile; and
determining, by the computing device, an airspeed of the rotorcraft based on the amplitude.

US Pat. No. 9,068,818

DRIVE MECHANISMS FOR VARIABLE DIAMETER ROTOR SYSTEMS

SIKORSKY AIRCRAFT CORPORA...

1. A rotor hub assembly comprising:
a rotor hub for supporting a telescoping rotor blade having an outboard section; and
a drive mechanism associated with the telescoping rotor blade, the drive mechanism including:
a motor;
a spool driven by the motor; and
a strap wound on the spool, the strap coupled to the outboard section of the telescoping rotor blade;
wherein the motor is operated as a pump when the outboard section of the telescoping rotor blade is extended away from the
rotor hub.

US Pat. No. 9,316,630

ANTI-CLOG AND NON-METALLIC DEBRIS DETECTOR FOR LUBRICATION SYSTEM INLET

SIKORSKY AIRCRAFT CORPORA...

1. A contaminant detection system for use in a fluid distribution system, the contaminant detection system comprising:
a first detector assembly including an inlet housing and detector screen through which fluid in the fluid distribution system
passes and a first sensor to detect a first type of contaminant caught in the detector screen; and

a second detector assembly including a second sensor which activates when one of the inlet housing and the detector screen
is clogged to detect whether the fluid contains a second type of contaminant that is distinct from the first type of contaminant
when the first sensor does not detect the first type of contaminant.

US Pat. No. 9,284,996

SELECTIVE ELECTRICAL CONTROL OF ELECTROMECHANICAL CLUTCH ASSEMBLY

SIKORSKY AIRCRAFT CORPORA...

1. A clutch assembly of a vehicle, comprising:
a shaft configured to rotate around a rotation axis inside the shaft;
a connection arm connected to the shaft, to a pilot-controlled mechanism, and to a mechanical servo that controls a movement
of the vehicle; and

a first electromechanical actuator configured to be selectively mechanically engaged with the shaft via a first electromechanical
clutch and a second electromechanical actuator configured to be selectively mechanically engaged with the shaft via a second
electromechanical clutch, such that the first and second electromechanical actuators are disconnected from controlling a movement
of the shaft and the connection arm when the first and second electromechanical clutches are disengaged, and one of the first
and second electromechanical actuators is configured to control movement of the shaft and the connection arm when one of the
first and second electromechanical clutches is engaged, the first electromechanical actuator and second electromechanical
actuator configured in a redundant configuration, such that each of the first electromechanical actuator and second electromechanical
actuator is configured to engage the shaft based on receiving a shaft-position control signal, the first electromechanical
clutch configured to be disengaged based on the second electromechanical clutch being engaged, the first electromechanical
clutch configured to be engaged based on a failure being detected in at least one of the second electromechanical actuator
and the second electromechanical clutch.

US Pat. No. 9,273,400

MULTILAYERED COATING FOR IMPROVED EROSION RESISTANCE

SIKORSKY AIRCRAFT CORPORA...

1. An erosion resistant coating for a substrate comprising:
an inner coating layer affixed to the substrate formed from a metal or high metal content material;
an outermost coating layer formed from a high hardness, high modulus of elasticity material, relative to the inner coating
layer, wherein the high hardness, high modulus of elasticity material includes a combination of a ceramic material and a metal
material; and

two or more intermediate coating layers disposed between the inner coating layer and the outer coating layer, each intermediate
coating layer formed from an applied mixture of the high hardness, high modulus of elasticity material and a metal material;

wherein the coating has an increasing modulus of elasticity and hardness from the inner coating layer to the outer coating
layer furthest from the substrate; and

wherein a percent by volume of the metal material in the a first intermediate coating layer closest to the substrate is greater
than a percent by volume of the metal material in a second intermediate coating layer farther from the substrate.

US Pat. No. 9,248,909

SWASHPLATELESS COAXIAL ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A main rotor system of an aircraft comprising:
a first rotor coupled to a transmission and configured to rotate about a first axis in a first direction;
a second rotor coupled to the transmission, the second rotor being configured to rotate about the first axis in a second direction,
wherein at least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of
a plurality of blades of the first rotor independently;

a standpipe fixedly attached to the aircraft, the standpipe being arranged such that the first rotor and the second rotor
rotate relative to the standpipe; and

at least one slip ring configured to transmit at least one of electrical power or a control signal to the at least one IBCS.

US Pat. No. 9,199,720

NON-ROTATING STATIONARY GROUND TUBE FOR A WIND FAIRING

SIKORSKY AIRCRAFT CORPORA...

1. A wind fairing system for use in a rotor assembly comprising:
an upper hub fairing configured for coupling to an upper hub of the rotor assembly;
a lower hub fairing configured for coupling to a lower hub of the rotor assembly; and
a wind fairing configured for coupling to a ground tube, the ground tube comprising:
a first portion including a first through aperture aligned along a longitudinal axis, the first portion having a tubular body
from an open first end to an opposed second end; and

a second portion including a second through aperture from an open third end to an open fourth end, the second through aperture
being aligned along the longitudinal axis, and the second portion being coupled to the first portion;

wherein the first portion and second portion of the ground tube are stationary in relation to both the upper hub and the lower
hub.

US Pat. No. 9,174,730

AUTOMATED ROTATING TAIL ROTOR CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
causing, by a computing device comprising a processor, a rotating tail rotor to operate in a tail rotor mode when an aircraft
is operating at a speed less than a rudder control power threshold;

receiving, by the computing device, a command that indicates a request to transition the aircraft;
determining, by the computing device, that a rudder of the aircraft has control power in an amount greater than a second threshold
based on receiving the command; and

causing, by the computing device, the rotating tail rotor to operate in a pusher propeller mode based on determining that
the rudder has control power in the amount greater than the second threshold.

US Pat. No. 9,162,419

COMPOSITE STAPLE

SIKORSKY AIRCRAFT CORPORA...

1. A laminate design, comprising:
a substrate formed to define through-holes;
an initially uncured pre-preg laminate disposable proximate to the substrate; and
an initially uncured pre-preg staple, the staple including a main member and legs extending from the main member and being
disposable with the legs extending through the through-holes to pierce the laminate, the staple being co-curable with the
laminate.

US Pat. No. 9,120,569

CLICKABLE CAMERA WINDOW

SIKORSKY AIRCRAFT CORPORA...

1. An apparatus comprising:
a touchscreen;
at least one processor; and
memory storing instructions that, when executed by the at least one processor, cause the apparatus to:
receive an input on the touchscreen including a command for re-location of an aircraft from a first location to a second location,
the input identifying the second location,

determine at least one of a distance, a direction, and a latitude and longitude for the aircraft to travel from the first
location to the second location, and

transmit the command and the at least one of a distance, a direction, and a latitude and longitude to the aircraft;
wherein the touchscreen is configured to display a map comprising an identification of the first location enclosed by a ring
and a scale that provides a distance associated with the ring, the ring representing a radius on the ground, the radius varying
with variations in altitude of the aircraft based on an angle of a field of view of a camera on the aircraft and the altitude
of the aircraft.

US Pat. No. 9,150,305

VIBRATION ABSORBING DEVICE FOR FLEXBEAMS

SIKORSKY AIRCRAFT CORPORA...

1. A vibration absorbing device for replacing a wear wrap of a flexbeam comprising:
a flexbeam of a rotor blade; and
a sleeve having a hollow interior within which a central portion of the flexbeam is received the sleeve including a plurality
of layers of vibration absorbing material and having a cut edge such that a portion of the sleeve is movable to provide access
to the hollow interior.

US Pat. No. 9,404,172

EROSION AND FATIGUE RESISTANT BLADE AND BLADE COATING

SIKORSKY AIRCRAFT CORPORA...

1. An airfoil blade comprising:
an airfoil blade component body comprising a polymer matrix composite and a metal sheath covering the polymer matrix composite;
a metallic erosion strip disposed on a leading edge of the airfoil blade component body and comprising opposite terminal strip
portions proximate to the leading edge at opposite sides of the airfoil blade component body; and

a cermet coating disposed on a leading edge surface of the strip, the cermet coating having a compressive residual stress
of about 90-110 ksi and comprising opposite terminal coating portions that are respectively associated with the opposite terminal
strip portions and respectively recessed toward the leading edge of the airfoil blade component from the opposite terminal
strip portions.

US Pat. No. 9,297,290

ROTARY WING AIRCRAFT HAVING COLLOCATED EXHAUST DUCT AND PROPELLER SHAFT

SIKORSKY AIRCRAFT CORPORA...

1. An exhaust system for reducing infrared emissions of a rotary wing aircraft, the exhaust system comprising:
an exhaust duct having a fore end connected with an aft turbine section of an engine of the rotary wing aircraft in a fluidly
sealed manner, the exhaust duct having an aft end having an exhaust opening to expel engine exhaust proximate to a tail fairing
of the rotary wing aircraft, the exhaust duct having a central axis extending from the fore end to the aft end; and

a drive shaft providing rotational force to an aft propeller of the rotary wing aircraft, at least a portion of the drive
shaft being coaxial with the central axis between the fore and aft ends.

US Pat. No. 9,243,407

STRUCTURE REPAIR WITH POLYMER MATRIX COMPOSITES

SIKORSKY AIRCRAFT CORPORA...

1. A method of forming a polymer matrix patch about a load-bearing, metallic structural component, comprising:
wrapping a plurality of layers around the surface of a flange-like member of the load-bearing, metallic structural component
in-situ, such that the patch extends parallel to an axis of the flange-like member and wraps equidistantly, over two opposing
sides of the load-bearing metallic structural component such that a first end and a second, opposite end of each the plurality
of layers is arranged within a same plane on opposing sides of the structural component, each layer having a plurality of
fibers arranged therein; and

curing the plurality of layers.

US Pat. No. 9,240,083

ROTOR SYSTEM HEALTH MONITORING USING SHAFT LOAD MEASUREMENTS AND VIRTUAL MONITORING OF LOADS

Sikorsky Aircraft Corpora...

1. A method of real-time rotor system condition detection comprising:
measuring a set of loads to obtain measured signals;
virtually monitoring the set of loads to obtain estimated signals, the virtual monitoring accomplished through use of an empirical
load model representing a real-time environment;

subtracting the estimated signals from the measured signals to obtain residuals;
comparing the residuals to a categorical model; and
identifying a categorical output representative of a rotor system condition within the categorical model.

US Pat. No. 9,234,460

ENGINE INLET

SIKORSKY AIRCRAFT CORPORA...

1. An inlet duct for an engine comprising:
two or more inlet duct legs directly coupled to one another and converging at a single duct outlet, the duct outlet directly
coupled to an engine inlet of a single engine; and

a flow relief pathway disposed at each inlet duct leg, the flow relief pathway being arranged upstream of the duct outlet
to condition an inlet airflow from the inlet duct legs at the engine inlet for substantially axial flow of the inlet airflow
into the engine inlet.

US Pat. No. 9,114,586

LATTICE GRID CAUL FOR HONEYCOMB COMPOSITE STRUCTURE

SIKORSKY AIRCRAFT CORPORA...

1. A caul system for a composite structure having one or more core elements comprising:
a lattice grid hard caul selectively locatable at a portion of the composite structure without core elements; anda soft caul selectively locatable at a portion of the composite structure having a core element;
wherein the lattice grid caul includes one or more contours to accommodate changes in thickness of the composite structure.

US Pat. No. 9,051,047

FLEXBEAM ROTOR ATTACHMENT TO ROTOR BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade assembly comprising;
a flex-beam member;
a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length;
a rotor blade surrounding the flex beam member extending from the torque tube to a blade tip; and
a connecting pin assembly to secure the rotor blade and the torque tube at the flex-beam member, the connecting pin assembly
including:

a first pin member having a first shaft extending at least partially into the rotor blade assembly through the rotor blade
from a first rotor blade side; and

a second pin member disposed at a second rotor blade side; wherein a clamping load between the first pin member and the second
pin member secures the rotor blade and torque tube to the flex-beam member.

US Pat. No. 9,452,830

CONSTANT VELOCITY DRIVE FOR TILT ROTOR ASSEMBLY

SIKORSKY AIRCRAFT CORPORA...

1. A constant velocity drive comprising;
a drive ring having a drive ring axis of rotation;
a driven ring disposed around the drive ring and which is driven by the drive ring to rotate about a driven ring axis of rotation;
a plurality of drive links extending from the drive ring to the driven ring to transfer torque applied at the drive ring to
the driven ring, each of the drive links comprising an extended portion with an outer surface; and

a plurality of elastomeric bearings, each elastomeric bearing disposed in contact with and between the driven ring and the
outer surface of the extended portion of one of the plurality of drive links to transfer torque from one of the plurality
of drive links to the driven ring, each elastomeric bearing including both spherical bearing elements and planar bearing elements
to allow for tilt of the driven ring axis of rotation with respect to the drive ring axis of rotation while ensuring a constant
rotational velocity of the driven ring with respect to the rotational velocity of the drive ring wherein a center to center
distance between the spherical bearing elements of the elastomeric bearings varies as the driven ring and drive ring rotate
about their respective axes of rotation.

US Pat. No. 9,090,348

PORTABLE CONTROL SYSTEM FOR ROTARY-WING AIRCRAFT LOAD MANAGEMENT

SIKORSKY AIRCRAFT CORPORA...

1. A control system for portable control of a rotary-wing aircraft, the control system comprising:
a portable, hand-held, control device executing a control application, the control device operating in a loaded mode when
a load is attached to the rotary-wing aircraft and an unloaded mode when no load is attached to the rotary-wing aircraft,
the control device presenting command icons in response to being in loaded mode and unloaded mode;

a vehicle management system in the rotary-wing aircraft;
a sensor package on the rotary-wing aircraft; and
a communication system providing communications between the control device and the rotary-wing aircraft, vehicle management
system and sensor package;

wherein the control device communicates commands to the vehicle management system to implement loading and unloading of the
rotary-wing aircraft;

wherein the control device executes a receive aircraft mode, hover mode, en-route mode and ground mode, wherein in the receive
aircraft mode, the control device presents a list of aircraft within range of the control device and available for control
by the control device, wherein in the hover mode, the control device presents icons to control the rotary-wing aircraft in
a hover flight, wherein in the en route mode, the control device commands the rotary-wing aircraft to follow a preloaded flight
plan and wherein in the ground mode, the control device commands the rotary-wing aircraft to land.

US Pat. No. 9,429,025

EROSION RESISTANT HELICOPTER BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade comprising:
a main portion having a main portion leading edge shield;
a main portion impact-resistant layer formed on a nose of the leading edge shield;
a main portion erosion-resistant layer formed on a top and bottom of the main portion with forward-most edges terminating
rearward of a forward section of the main portion impact-resistant layer;

a main portion foil formed on the top and the bottom of the main portion with forward-most edges terminating rearward of a
forward section of the main portion erosion-resistant layer;

a tip cap having a tip cap leading edge shield acting as a tip cap erosion-resistant layer;
a tip cap impact-resistant layer formed on a surface of the tip cap leading edge shield; and
a tip cap foil formed on the top and the bottom of the tip cap with forward-most edges terminating rearward of a forward section
of the tip cap erosion-resistant layer.

US Pat. No. 9,284,048

GLOBAL AIRFRAME HEALTH CHARACTERIZATION

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
determining, by a controller comprising a processor, that an aircraft is on a landing surface based on a weight-on wheels
sensor reading;

setting, by the controller, an initial vibration frequency to be applied to an airframe of the aircraft;
commanding, by the controller, one or more force generators to apply a vibratory load to the airframe at the initial vibration
frequency based on determining that the aircraft is on the landing surface and the aircraft is in a pre-flight or diagnostic
mode, wherein the one or more force generators are components of an active vibration control system configured to attenuate
vibration of the aircraft while the aircraft is in a flight or normal operation mode and to characterize a global stiffness
of the airframe while the aircraft is in the pre-flight or diagnostic mode and positioned on the landing surface;

determining, by the controller, a vibration response of the airframe at the initial vibration frequency using a plurality
of sensors;

sweeping, by the controller, through a range of vibration frequencies to be applied to the airframe;
commanding, by the controller, the one or more force generators to apply a plurality of vibratory loads to the airframe over
the range of vibration frequencies;

determining, by the controller, a range of vibration responses of the airframe over the range of vibration frequencies using
the plurality of sensors;

determining, by the controller, the global stiffness of the airframe based on the vibration response and the range of vibration
responses;

comparing the global stiffness of the airframe to a threshold value; and
determining a level of damage to the airframe based on a difference between the global stiffness and the threshold value;
and

reporting, by the controller, results of determining the global stiffness of the airframe.

US Pat. No. 9,278,760

TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft comprising:
an airframe;
a rotor assembly including:
a first rotor rotatable about a rotor axis in a first direction; and
a second rotor coaxial with the first rotor and rotatable about the rotor axis in a second direction opposite the first direction;
and

a drive system including:
an engine outputting a first torque;
a gearbox assembly to reduce the first torque to a second torque and transfer the second torque to the rotor assembly, the
gearbox assembly including:

an input shaft to input the first torque into the gearbox assembly;
an input bevel shaft operably connected to the input shaft to transfer the first torque therethrough; and
two gear sets operably connected to the input bevel shaft, each gear set including:
a first intermediate shaft including:
 a first intermediate idler meshed with a transfer gear of the input bevel shaft; and
 a first output pinion to transfer a second torque acting in the first direction to the first rotor; and
a second intermediate shaft including:
 a first intermediate gear meshed with the first intermediate idler; and
 a second output pinion to transfer the second torque acting in the second direction to the second rotor.

US Pat. No. 9,172,272

ELECTRICAL POWER DISTRIBUTION SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A distributed electrical power system, comprising:
a first AC generator configured for supplying an AC electrical voltage;
a second AC generator configured for supplying the AC electrical voltage;
an AC power distribution network connected to the first AC generator and the second AC generator for receiving the AC electrical
voltage, the AC power distribution network including one of a two and four-wire AC power distribution circuit;

at least one power distribution module remotely located for receiving the AC electrical voltage from the power distribution
network;

a system controller connected to a data bus for controlling operation of the at least one power distribution module; and
at least one contactor electrically connected between the at least one power distribution module and each of the first AC
generator and the second AC generator for selectively switching supply of the AC electrical voltage to the at least one power
distribution module from one of the first AC generator and the second AC generator upon failure of either one of the first
AC generator and the second AC generator.

US Pat. No. 9,108,727

BLADE FOLD SYSTEM MONITORING

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade fold system for an aircraft comprising:
one or more actuators operably connected to one or more blade components of a plurality of rotor blades of the aircraft;
one or more sensors disposed at the plurality of rotor blades configured to sense operation of the one or more blade components;
and

a fold control system which is configured to monitor output from the one or more sensors and capable of stopping operation
of the blade fold system, via communication with the one or more actuators, if the one or more blade components are not operating
within predetermined limits, the fold control system monitoring progress and rate of the folding of a first blade of the plurality
of rotor blades and comparing it to a progress and rate of the folding of a second, adjacent blade of the plurality of rotor
blades.

US Pat. No. 9,050,691

SLEEVE AND ROD SUPPORT FOR FUEL BLADDER

SIKORSKY AIRCRAFT CORPORA...

1. A flexible fuel bladder structure for an aircraft comprising:
one or more sleeves affixed to and extending along a top exterior surface of the fuel bladder, each sleeve extending continuously
from a first lateral side to a second lateral side of the fuel bladder; and

one or more rods extending through the one or more sleeves along the top exterior surface to at least partially suspend the
fuel bladder in the aircraft, the one or more rods extending continuously through the one or more sleeves from the first lateral
side to the second lateral side of the fuel bladder.

US Pat. No. 9,470,303

SELF SCAVENGING GEAR SHIELD

SIKORSKY AIRCRAFT CORPORA...

1. A gearbox assembly comprising:
a gearbox housing;
a gear disposed in the housing and rotatable about a central axis; and
one or more gear shields fixed in the housing and at least partially surrounding the gear and defining a cavity between the
gear and the one or more gear shields,

the one or more gear shields comprising a lip over which lubricant spills into the cavity and an exterior wall that extends
radially inwardly toward the lip,

the one or more gear shields being configured relative to the gear such that a pumping action is created by the gear rotation
relative to the gear shield to direct gearbox lubricant circumferentially around the cavity and toward an out of the cavity.

US Pat. No. 9,102,400

METHODS AND SYSTEMS FOR PROVIDING CONSTANT-FEEL, MULTI-AXIS TACTILE CUES

SIKORSKY AIRCRAFT CORPORA...

8. A system for adjusting tactile cues comprising:
a controller having an axis and a cross-axis;
an axis tactile cue generated in response to the position of the controller along the axis;
a position scaling unit scaling a cross-axis controller position to generate a scaled cross-axis controller position;
a force scaling unit scaling a cross-axis controller force to generate a scaled cross-axis controller force;
a combiner combining the scaled cross-axis controller position and the scaled cross-axis controller force to generate an adjustment
factor; and

an adjuster adjusting the axis tactile cue in response to the adjustment factor to generate an adjusted axis tactile cue to
be applied along the axis of the controller;

wherein the axis tactile cue has a depth and a width, and the adjusted axis tactile cue has one of an adjusted depth and an
adjusted width;

wherein the axis and cross-axis are perpendicular;
wherein the controller is coupled to a servo, the servo coupled to a linkage to control a rotor of a rotary wing aircraft;
wherein the controller is coupled to the servo in a fly-by-wire system with no direct mechanical connection between the controller
and the servo and with no direct mechanical connection between the controller and the linkage.

US Pat. No. 9,441,495

ROTARY WING AIRCRAFT PITCH BEAM ATTACHMENT WITH ANTI-ROTATION PLATE DESIGN

SIKORSKY AIRCRAFT CORPORA...

1. A retaining assembly for a tail rotor system, comprising:
a washer including a plurality of splines, the washer being configured to couple to a pitch change shaft;
a retaining nut including a self-locking feature and a flange arranged at a first end, the retaining nut being configured
to threadably couple to the pitch change shaft such that the flange is in contact with the washer, wherein the flange includes
a plurality of first holes configured to at least partially align between the splines of the washer; and

a lock plate including a body and a plurality of tabs extending generally perpendicularly from the body and extending exteriorly
past an outer periphery of the flange and an outer periphery of the washer, the lock plate being slidably positioned about
the pitch change shaft adjacent the flange, wherein the lock plate is operably coupled to the retaining nut and the washer
to limit rotational movement thereof about the pitch change shaft.

US Pat. No. 9,409,358

COMPOSITE STRUCTURE CORE CRUSH PREVENTION

SIKORSKY AIRCRAFT CORPORA...

1. A composite structure comprising:
a core assembly including:
a core component having a plurality of core cells; and
a layer of rigidized filler material disposed at a first face of the core component at least partially filling selected cells
of the core component to a fill depth, the filler material being arrayed in one or more contiguous filled strips extending
across two or more cells of the core component and configured to prevent movement and/or crushing of the core component under
a pressure applied in a direction substantially perpendicular to a thickness of the core component;

a first laminate; and
a layer of adhesive to secure the first laminate to the core assembly.

US Pat. No. 9,234,743

TIP CLEARANCE MEASUREMENT

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:
an airframe;
first and second main rotors rotatably supported on the airframe to rotate about a rotational axis in opposite directions;
first and second emitters disposed on an emitter blade of the second main rotor, each of the first and second emitters being
configured to emit an emission toward a detector blade of the first main rotor;

a detector disposed on the detector blade of the first main rotor, the detector being configured to detect the emissions of
the first and second emitters; and

a flight computer which determines a clearance between the first and second main rotors in accordance with detections of the
emissions by the detector.

US Pat. No. 9,212,679

HIGH SHEAR CAPABILITY INTERFACE

SIKORSKY AIRCRAFT CORPORA...

1. A connection between a first component and a second component comprising:
a first hole formed in a portion of the first component;
a second hole formed in a portion of the second component, the second hole being aligned with the first hole;
a pin including a through hole having a pin hole diameter, the pin extending through a portion of the first hole and into
a first portion of the second hole, the pin being configured to absorb a shear load applied to the connection;

a bolt extending through the second hole and the pin, the bolt having an outer diameter smaller than the pin hole diameter
such that a clearance fit is formed between the bolt and the pin, the bolt being configured to absorb an axial load applied
to the connection; and

a nut connected to a free end of the bolt to limit movement of the bolt relative to the first component and the second component.

US Pat. No. 9,156,540

HARD LANDING DETECTION AND ORIENTATION CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
obtaining, by a device, data associated with an aircraft;
processing, by the device, the data;
determining, by the device, that the aircraft is likely to impact the ground with a probability greater than a threshold within
a second threshold amount of time based on the processed data;

causing, by the device, a change in an attitude of the aircraft relative to the ground based on the determination to adjust
an impact angle of the aircraft relative to the ground; and

causing, by the device, a lateral velocity associated with the aircraft relative to the ground to be reduced to an amount
less than a third threshold based on the determination.

US Pat. No. 9,586,692

ENGINE INLET CONFIGURATION

SIKORSKY AIRCRAFT CORPORA...

1. An engine inlet assembly comprising:
an inlet duct including a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet
duct leg extending toward a common inlet duct outlet disposed at an engine inlet;

the first inlet duct leg and the second inlet duct leg fixedly secured to an airframe of an aircraft at an air inlet; and
the inlet duct outlet having a floating interface with the engine inlet, wherein the inlet duct extends through an opening
in a firewall such that a free end of the common inlet duct outlet is located within an engine compartment of the aircraft
at a position upstream of the engine inlet.

US Pat. No. 9,430,725

UNIQUE IDENTIFIER INSERT FOR PERISHABLE OR CONSUMABLE TOOLING

SIKORSKY AIRCRAFT CORPORA...

1. A device for tracking a consumable or perishable tool, comprising:
a connector configured to couple to a body of the consumable or perishable tool such that the connector remains in constant
contact with the consumable or perishable tool for a life of the tool, the connector including a first piece and a second
piece complementary to the first piece, the first piece and the second piece being configured to couple about the body to
restrict movement of the body relative to the connector, the connector including an exposed unique identifier configured to
provide identification information about the tool when accessed by an asset management software.

US Pat. No. 9,355,571

MODULES AND METHODS FOR BIASING POWER TO A MULTI-ENGINE POWER PLANT SUITABLE FOR ONE ENGINE INOPERATIVE FLIGHT PROCEDURE TRAINING

Sikorsky Aircraft Corpora...

1. A method for conducting flight procedures training in a rotary-wing aircraft with a multi-engine powerplant comprising:
continuously determining an instantaneous available power margin of the multi-engine powerplant system in real time;
continuously determining a variable bias relative to the instantaneous available power margin;
limiting a torque of each engine of the multi-engine powerplant system relative to the variable bias to simulate a reduced
power available for a flight condition; and

displaying symbology indicative of the simulated reduced power available flight condition.

US Pat. No. 9,321,238

NON-CERAMIC STRUCTURAL PANEL WITH BALLISTIC PROTECTION

Sikorsky Aircraft Corpora...

1. An armor panel comprising:
a pressure-consolidated, high molecular weight polyethylene fiber composite material layer;
a first skin on a first side of said high molecular weight polyethylene fiber composite material layer;
a second skin on a second side of said high molecular weight polyethylene fiber composite material layer; and
a multiple of pins which penetrate said first skin, said high molecular weight polyethylene fiber composite material layer
and said second skin, said polyethylene fiber composite material layer stabilizing said multiple of pins from buckling, wherein
said multiple of pins form a truss structure with said first skin and said second skin.

US Pat. No. 9,308,992

HELICOPTER BLADE RETENTION COMPOSITE YOKE

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft yoke comprising:
an arcuate medial portion; and
a pair of arms, each extending from the medial portion and terminating in a distal end, the distal ends being substantially
aligned such that an adjacent component is received within an opening formed between the distal ends of the pair of arms,
each arm being made from plies of glass fibers and graphite fibers having varying configurations such that no two consecutive
plies are identical in material and orientation, wherein at least a portion of the glass plies in the yoke have a ±4° fiber
orientation;

wherein a number of graphite plies increases along each arm from adjacent the medial portion to the distal end and wherein
the distal end of each arm is formed from a plurality of graphite plies and a plurality of glass plies arranged in an alternating
configuration.

US Pat. No. 9,190,071

NOISE SUPPRESSION DEVICE, SYSTEM, AND METHOD

SIKORSKY AIRCRAFT CORPORA...

1. A noise-suppression assembly of a mechanical drive system having a rotational frequency, the mechanical drive system including
a rotor of a helicopter, the assembly comprising:
an audio filter unit configured to receive a first audio signal and a timing signal of the mechanical drive system, the audio
filter unit configured to generate a noise-cancellation signal based on a frequency of the timing signal, said frequency based
on the rotational frequency of the rotor, to suppress a noise generated by the mechanical drive system and to apply the noise-cancellation
signal to the first audio signal to produce a filtered first audio signal, the frequency based on a signal obtained from at
least one sensor located on the rotor, wherein the sensor is a proximity sensor configured to detect the position of the rotor
relative to a fixed position.

US Pat. No. 9,132,911

DAMAGE ADAPTIVE CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A method for providing adaptive control to a fly-by-wire rotary wing aircraft, the method comprising:
measuring, via at least one first sensor, at least one of a damage and a compromise associated with a component of the fly-by-wire
rotary wing aircraft;

measuring, via at least one second sensor, a state of the fly-by-wire rotary wing aircraft, the at least one second sensor
comprising a fly-by-wire sensor;

determining, from the measuring of the at least one first sensor at least one of a region and a location of the at least one
of a damage and a compromise and a level of the at least one of a damage and a compromise; and

adapting an operational envelope for the fly-by-wire rotary wing aircraft based on the measured state of the fly-by-wire rotary
wing aircraft measured via the at least one second sensor and the determined at least one of a region and a location of the
at least one of a damage and a compromise and the level of the at least one of a damage and a compromise,

wherein adapting the operational envelope for the fly-by-wire rotary wing aircraft comprises adjusting one or more operational
thresholds via a fly-by-wire control configuration of the fly-by-wire rotary wing aircraft to prohibit a state of operation
of the fly-by-wire rotary wing aircraft that exceeds a safe or reliable operation threshold.

US Pat. No. 9,429,952

ROTORCRAFT CONTROL LAWS FOR SEA-BASED OPERATIONS

SIKORSKY AIRCRAFT CORPORA...

1. A method of controlling a rotorcraft for sea-based operations, comprising:
receiving, with a processor, sensed information indicative of an operation of the rotorcraft;
receiving, with the processor, operator commands, ship models and system constraints including relative velocity limits between
the ship and the rotorcraft, accuracy of a landing position on the ship, landing gear structural integrity, sink rate of the
rotorcraft, and impact velocity of the rotorcraft on the ship;

determining, with a model predictive control (MPC) prediction module that employs a model based feedforward control utilizing
a prediction algorithm, a solution to an optimization function that avoids violating the system constraints, the solution
being representative of control command signals for augmenting a flight response of the rotorcraft to a ship;

determining, with the processor, a solution to continuously update the system constraints that optimize a cost function utilizing
MPC theory; and

commanding the displacement of servos and linkages for controlling said rotorcraft.

US Pat. No. 9,278,755

MODULAR INTEGRATED DEVICE FOR ROTOR BLADE CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade assembly comprising:
a rotor blade;
a first interface piece disposed at a pocket extending through an outer surface of the rotor blade, the first interface piece
defining a first spanwise extent of the pocket;

a second interface piece secured to the rotor blade to define a second spanwise end of the pocket; and
a housing located at the rotor blade disposed entirely within the corresponding pocket, the housing secured to the first interface
piece and the second interface piece via one or more interlocking elements of the housing.

US Pat. No. 9,217,376

MULTI-MODE ADAPTIVE FAIL-FIXED SYSTEM FOR FADEC CONTROLLED GAS TURBINE ENGINES

Sikorsky Aircraft Corpora...

1. A gas turbine engine control system comprising:
an automatic control operable to control a gas turbine engine; and
a module configured to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure
of said automatic control, said multiple of pre-determined modes each different than said automatic control operative to control
said gas turbine engine,

wherein said multiple of pre-determined modes includes a low fuel flow power mode, a moderate fuel flow power mode and a high
fuel flow power mode,

wherein said automatic control includes a Full Authority Digital Engine Control (FADEC), and said module is remote from said
FADEC.

US Pat. No. 9,192,985

REMOVABLE PASSAGE MANDREL

SIKORSKY AIRCRAFT CORPORA...

16. A method for forming a passage in a cast component comprising:
arranging a composite core into an interior of a mold, wherein the composite core includes a core element arranged within
a structural element, and a shell element formed integrally with the structural element; disposing a material between the
core element and the structural element;

pouring material of the component into the mold;
curing the material to form the component;
applying a force to a first exposed portion of the composite core such that the core element separates from the composite
core; and
applying a force to a second exposed portion of the composite core such that the structural element deforms inside the component
so as to break the shell element.

US Pat. No. 9,435,261

REDUNDANT COOLING FOR FLUID COOLED SYSTEMS

SIKORSKY AIRCRAFT CORPORA...

1. A fluid cooled system comprising:
a first heat generating component;
a first heat exchanger disposed at a first airflow pathway, the first airflow pathway comprising a first duct having a first
duct outlet and configured to direct a first flow of air across the first heat exchanger;

a second heat exchanger disposed at a second airflow pathway, the second airflow pathway comprising a second duct having a
second duct outlet and configured to direct a second flow of air across the second heat exchanger, a first working fluid flowed
sequentially from the first heat generating component, through the first heat exchanger and through the second heat exchanger
and returned to the first heat generating component;

a second heat generating component;
a third heat exchanger disposed at the first airflow pathway, the first airflow pathway configured to direct the first flow
of air across the third heat exchanger, wherein the first heat exchanger and the third heat exchanger are each disposed upstream
of the first duct outlet; and

a fourth heat exchanger disposed at the second airflow pathway, the second airflow pathway configured to direct the second
flow of air across the fourth heat exchanger, a second working fluid flowed sequentially from the second heat generating component,
through the third heat exchanger and through the fourth heat exchanger and returned to the second heat generating component,
wherein the second heat exchanger and the fourth heat exchanger are each disposed upstream of the second duct outlet.

US Pat. No. 9,359,073

AIRCRAFT TAIL ROTOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft tail rotor system, comprising:
a tail rotor shaft;
a pitch change servo rod;
a bearing assembly including a first bearing arranged in series relative to and spaced from a second bearing, the first bearing
including a first raceway, a second raceway, and a plurality of bearing arranged therebetween, the first raceway being rotatable
with and movable within the tail rotor shaft in accordance with translational movement of the pitch change servo rod, the
second bearing including an third raceway, a fourth raceway and a plurality of bearings arranged therebetween;

a connection non-rotatably coupling the third raceway of the second bearing and the first raceway of the first bearing; and
a lock coupled to the second bearing, the lock selectively preventing rotation of the third raceway relative to the fourth
raceway, the lock being configured to directly and independently respond to a seizing of the first bearing at the second bearing
from a transmission of rotation of the first bearing to the second bearing and to selectively use the second bearing to prevent
transmission of rotational energy from the tail rotor shaft to the pitch change servo rod in an event of the seizing of the
first bearing.

US Pat. No. 9,327,838

ON-BLADE DEICE HEATER MAT

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade assembly comprising;
a rotor blade; and
a heater mat secured to the rotor blade, the heater mat including:
a plurality of electrically conductive heater wires extending in a path along a span of the rotor blade;
a plurality of yarn thread knitted to the plurality of heater wires, each of the yarn threads looping around at least one
of the plurality of heater wires; and

a warp thread disposed between two adjacent heater wires of the plurality of heater wires and knitted to adjacent pairs of
the yarn threads without looping around the plurality of heater wires, each warp thread knitted to at least a first yarn thread
wrapped around a first adjacent heater wire of the two adjacent heater wires and a second yarn thread wrapped around a second
adjacent heater wire of the two adjacent heater wires to maintain spacing between the two adjacent heater wires;

wherein an electrical current flowed through the plurality of heater wires inhibits ice accumulation on the rotor blade assembly.

US Pat. No. 9,317,041

ROTOR MOMENT FEEDBACK FOR STABILITY AUGMENTATION

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
obtaining at least one measurement of blade bending from a blade mounted sensor associated with at least one blade of at least
one rotor of an aircraft;

processing, by a device comprising a processor, the at least one measurement to obtain moment data;
obtaining data from an inertial measurement unit (IMU), wherein the data obtained from the IMU pertains to at least one of
a pitch of the aircraft and an angular rate; and

processing, by the device, the moment data and the data from the IMU to generate a command configured to stabilize the aircraft,
wherein the command is based on a reference input, and wherein the reference input is based on at least one input provided
by a pilot of the aircraft.

US Pat. No. 9,090,343

ROTOR BLADE COMPONENT COOLING

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade for a rotary wing aircraft comprising:
a component bay disposed substantially enclosed in the rotor blade;
one or more electric actuators disposed in the component bay and operably connected to a control surface of the rotor blade
to drive motion of the control surface;

an airflow inlet disposed at the component bay; and
an airflow outlet disposed at the component bay radially outboard of the airflow inlet, the airflow inlet and airflow outlet
configured to urge a continuous airflow through the component bay via centrifugal forces of rotation of the rotor blade, the
continuous airflow configured to cool the one or more electric actuators at the component bay.

US Pat. No. 9,248,907

ENGINE STARTING SYSTEM FOR ROTORCRAFT IN FLIGHT

SIKORSKY AIRCRAFT CORPORA...

1. A rotorcraft engine starting system comprising:
a starting system controller in communication with a flight control computer;
a first electric engine starter-generator for starting a first engine and a second electric engine starter-generator for starting
a second engine;

an electrical power distributor; and
a plurality of power sources coupled to the electrical power distributor, the plurality of power sources including a power
shaft generator mechanically coupled to an output shaft of the first engine and a main gearbox-mounted generator;

the starting system controller selecting at least one of the power shaft generator and the main gearbox-mounted generator
and instructing the electric power distributor to use the at least one of the power shaft generator and the main gearbox-mounted
generator to power the second electric engine starter-generator;

wherein when the rotorcraft is in flight and the first engine is running, the starting system controller selects the power
shaft generator to power the second electric engine starter-generator;

wherein when the rotorcraft is in flight and the first engine is not running, the starting system controller selects the main
gearbox-mounted generator to power the second electric engine starter-generator.

US Pat. No. 9,233,753

HELICOPTER ROTOR LOAD REDUCTION AND TIP CLEARANCE CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A method of controlling an aircraft comprising an upper rotor including blades and a coaxial lower rotor including blades,
the upper rotor and lower rotor being hingeless, rigid rotors, the method comprising:
receiving, by a computing device comprising a processor, at least one input associated with the aircraft;
generating, by the computing device, flight control signals based on the received at least one input;
detecting, by sensors incorporated into the blades of at least one of the upper or lower rotor, bending moments;
converting said bending moments into raw bending signals;
extracting, by the computing device, harmonic loads from the raw bending signals;
generate, by the computing device, servo control signals based on the harmonic loads and flight control signals; and
controlling, by the computing device, servos connected to the blades to adjust the blades according to the servo control signals
to reduce bending of the blades to improve blade tip clearance between blades on the upper rotor and blades on the lower rotor.

US Pat. No. 9,132,914

LOW DRAG HIGH RESTORING MOMENT AIRFOILS

SIKORSKY AIRCRAFT CORPORA...

1. A rotor hub fairing system for use in a counter-rotating, coaxial rotor system comprising:
an upper hub fairing defined about an axis;
a lower hub fairing defined about the axis; and
an airfoil shaped shaft fairing disposed between the upper hub fairing and the lower hub fairing, wherein the airfoil shaped
shaft fairing has a thickness to chord ratio in the range of about 20% and about 45% and wherein the airfoil shaped shaft
fairing has a negative moment coefficient configured to decrease as an angle of attack of the airfoil shaped shaft fairing
increases.

US Pat. No. 9,102,399

LIFE IMPROVING FLIGHT CONTROL SYSTEM

Sikorsky Aircraft Corpora...

1. A flight control system comprising:
a command model modified in response to a Life Improving Control (LIC) algorithm;
an inverse aircraft model in communication with said command model to generate a flight control system command to command
an aircraft state; and

a feedback path from said command model and said aircraft state, said feedback path in communication with said flight control
system command, said feedback path modified in response to said Life Improving Control (LIC) algorithm, wherein said Life
Improving Control (LIC) algorithm is configured to modify the command model to reduce fatigue loads applied to an aircraft
component in response to an aircraft maneuver.

US Pat. No. 9,505,491

HELICOPTER COMPOSITE BLADE SPAR AND METHOD

SIKORSKY AIRCRAFT CORPORA...

1. A composite spar for a helicopter blade comprising:
first and second upper layers of unidirectional laminate material extending from an upper airfoil portion of the spar and
terminating at a backwall portion of the spar between the upper airfoil portion and a lower airfoil portion;

first and second lower layers of unidirectional laminate material extending from the lower airfoil portion of the spar and
terminating at the backwall portion, the first upper layer of unidirectional laminate material overlapping the first lower
layer of unidirectional laminate material at the backwall portion;

a first ply of bi-directional laminate extending from the upper airfoil portion of the spar and terminating at the backwall
portion, the first ply of bi-directional laminate disposed between the first and second upper layers of unidirectional laminate
material; and

a second ply of bi-directional laminate material extending from the lower airfoil portion of the spar and terminating at the
backwall portion, the second ply of bi-directional laminate material disposed between the first and second lower layers of
unidirectional laminate material;

wherein the first ply of bi-directional laminate and the second ply of bi-directional laminate overlap at the backwall portion
between the first upper layer of unidirectional laminate and the second lower layer of unidirectional laminate defining at
least one crackstopper layer configured to prevent propagation of defects in the spar, and wherein a length of overlap of
the first ply of bi-directional laminate and the second ply of bi-directional laminate is different than a length of overlap
of the first upper layer of unidirectional laminate material and the first lower layer of unidirectional laminate material.

US Pat. No. 9,508,139

APPARATUS AND METHOD TO AUTOMATICALLY DISTINGUISH BETWEEN CONTAMINATION AND DEGRADATION OF AN ARTICLE

SIKORSKY AIRCRAFT CORPORA...

1. An inspection apparatus comprising:
an imaging unit producing image signals;
a processing unit for receiving the image signal;
the imaging unit producing a stack of images of an article at different focal lengths in response to the processing unit;
the processing unit generating a depth map from the stack of images;
the processing unit analyzing the depth map to derive a depth profile of an object of interest;
the processing unit determining a surface mean for the article from the stack of images; and
the processing unit characterizing the article as degraded or contaminated in response to comparison of the depth profile
and the surface mean, wherein:

if the depth profile is below the surface mean, the article is characterized as degraded, and
if the depth profile is above the surface mean, the article is characterized as contaminated depending on secondary factors.

US Pat. No. 9,317,042

PITCH FEEDBACK CONTROL SPLITTING FOR HELICOPTERS WITH REDUNDANT ACTUATORS

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
generating, by a processing device, a feedback command for an aircraft based on a difference between a reference input and
an actual output response of the aircraft;

analyzing, by the processing device, the feedback command to allocate control to a plurality of control surfaces over a plurality
of separate frequency bands;

applying an equivalence filter to the control that converts control of a first of the plurality of control surfaces into an
equivalent amount of control in a second of the plurality of control surfaces to enable allocation over dynamically equivalent
control surfaces; and

applying an inversion of the equivalence filter to re-allocate control in an opposite or second direction.

US Pat. No. 9,266,608

COMPENSATING FOR LEAD-LAG IN ROTOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A control system for a rotor assembly comprising:
a plurality of sensors configured to detect a lead-lag rate of each rotor blade of a plurality of rotor blades rotatable around
a shaft; and

a flight control computer configured to generate lead-lag compensation signals based on the detected lead rate and lag rate
of each rotor blade to control each rotor blade;

wherein the flight control computer is configured to convert the detected lead-lag rate of each rotor blade into a composite
longitudinal lead-lag rate signal and a composite lateral lead-lag rate signal by performing an individual blade coordinate
to multi-blade coordinate conversion;

wherein the flight control computer is configured to generate a filtered longitudinal lead-lag rate signal and a filtered
lateral lead-lag rate signal by passing the composite longitudinal lead-lag rate signal and the composite lateral lead-lag
rate signal through a regressive lag mode band-pass filter and a progressive lag mode variable band-pass filter, and

the flight control computer is configured to generate the lead-lag compensation signals based on the filtered longitudinal
lead-lag rate signal and the filtered lateral lead-lag rate signal.

US Pat. No. 9,506,945

ROTORCRAFT FLIGHT PARAMETER ESTIMATION

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:
an airframe including first and second rotor apparatuses at upper and tail portions of the aircraft, respectively, to provide
for control and navigational drive;

a stabilizer component disposed at the tail portion in a position displaced from downwash of the first and second rotor apparatuses
at airspeed ranges; and

a control system configured to apply a dither actuation signal to the stabilizer component at the airspeed ranges by which
an aircraft response to a stabilizer component input is measurable for airspeed estimation purposes.

US Pat. No. 9,250,629

TERRAIN ADAPTIVE FLIGHT CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A helicopter, comprising:
an air frame formed to accommodate a pilot;
flight control elements disposed on the airframe to generate lift and thrust in accordance with servo commands derived from
control commands issued by the pilot and a current control mode associated with a conversion of data reflective of the control
commands into the servo commands;

a sensor disposed on the airframe to sense helicopter proximity to terrain and obstacles; and
a flight computer configured to change the current control mode based on sensed helicopter proximity to the terrain and the
obstacles.

US Pat. No. 9,211,950

MULTI-ELEMENT ROTOR BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A main rotor assembly for a rotary wing aircraft comprising:
a blade assembly secured to a rotor hub including:
a rotor blade;
a slat positioned to define a slat gap between the rotor blade and the slat;
one or more struts extending from the rotor blade to the slat to position the slat and to control motion of the slat;
a slat pitch bearing to operably connect the strut to the rotor blade, defining an axis about which the slat locally rotates
relative to the rotor blade; and

a journal bearing connecting the slat to the strut allowing relative motion in a radial direction between the slat and the
rotor blade to prevent transmission of edgewise bending loads into the strut; and

a rotor cuff to connect the blade assembly to the rotor hub, the rotor blade secured to the rotor cuff at a main element retention,
the slat secured to the rotor cuff at a separate secondary element retention.

US Pat. No. 9,482,647

GEAR FAULT DETECTION

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
generating an estimated impact energy signal corresponding to each of a plurality of teeth of a gear over a revolution of
a shaft associated with the gear tooth;

obtaining an impact energy signal associated with each of the plurality of teeth;
comparing the estimated impact energy signal with the obtained impact energy signal;
generating, by a computing device comprising a processor, a profile of the impact energy signal; and
declaring a fault associated with at least one tooth of the plurality of teeth, the fault being based on said comparing indicating
a deviation between the estimated impact energy signal and the obtained impact energy signal in an amount greater than a threshold.

US Pat. No. 9,481,457

VERTICAL TAKE-OFF AND LANDING AIRCRAFT WITH VARIABLE WING GEOMETRY

SIKORSKY AIRCRAFT CORPORA...

1. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage extending along a longitudinal axis that has a nose cone section at a first longitudinal end of the fuselage, a
tail section opposite from the nose cone section at a second longitudinal end of the fuselage;

wings extending from opposite sides of the fuselage to define a support plane; and
engine nacelles disposed along the wings,
each of the wings comprising ground support elements and a variable geometry such that a portion of the ground support elements
are pivotable about a pivot axis that is parallel to the longitudinal axis:

alignable with the support plane and disposed aft of the wings during in-flight conditions with the longitudinal axis oriented
substantially horizontally, and

displaceable from the support plane and disposed below the wings during grounded conditions with the longitudinal axis oriented
substantially vertically.

US Pat. No. 9,428,268

FLEXBEAM HINGE FOR HELICOPTER BLADE ACTIVE TRAILING EDGE FLAP

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade system, comprising:
a rotor blade body having a span extending between first and second ends and a chord extending between first and second edges,
the body being rotatable about an axis proximate to the first end to define the second edge as a trailing edge;
a flap disposed along the trailing edge and being configured to pitch about a pitching axis defined along the span;
a flexbeam coupled at a first end thereof to the body and at a second end thereof to the flap, the flexbeam being configured
to retain the flap under first, second and third loadings and being flexible to rotate the flap about the pitching axis; and

a torque tube surrounding the flexbeam.

US Pat. No. 9,427,940

IMPACT RESISTANT COMPOSITE PANEL AND METHOD OF FORMING A COMPOSITE PANEL

SIKORSKY AIRCRAFT CORPORA...

1. A composite panel, comprising:
a support layer including a first plurality of prepreg plies wrapped around at least one mandrel;
a mid-plane impact layer including a second plurality of prepreg plies, the mid-plane impact layer adjacent to the support
layer;

a upper skin layer including a third plurality of prepreg plies, the upper skin layer adjacent to the mid-place impact layer;
and

a lower skin layer including a fourth plurality of prepreg plies, the lower skin layer adjacent to the support layer;
wherein each of the first, second, third, and fourth plurality of prepreg plies are co-cured to form the composite panel,
and the first plurality, the second plurality, and the third plurality of prepreg plies are arranged symmetrically from a
radially innermost prepreg ply of the support layer to a radially outermost prepreg ply of the upper skin layer.

US Pat. No. 9,315,268

PAYLOAD TOUCHDOWN DETECTION

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
obtaining data associated with at least one aircraft flight parameter when an aircraft is being operated in flight;
processing the data to determine that the at least one aircraft flight parameter indicates a change in value in an amount
greater than a threshold; and

decoupling a load from the aircraft based on determining that the at least one aircraft flight parameter indicates the change
in value in the amount greater than the threshold.

US Pat. No. 9,382,016

AIRCRAFT LANDING MONITOR

SIKORSKY AIRCRAFT CORPORA...

1. A method of monitoring landing of an aircraft, the method comprising:
determining whether the aircraft is in a landing phase to maneuver the aircraft to a landing zone;
setting, by a landing profile monitor, a landing instability indicator based on determining that the aircraft is in the landing
phase, wherein the landing profile monitor compares aircraft sensor data indicative of a current state of the aircraft to
a landing profile of the aircraft and sets the landing instability indicator based on the landing profile;

setting, by a pattern matcher, the landing instability indicator based on determining that the aircraft is in the landing
phase, wherein the pattern matcher identifies a pattern associated with the landing zone in perception sensor data indicative
of current conditions at the landing zone for the aircraft, monitors the pattern for a change indicative of landing zone instability
and sets the landing instability indicator based on detecting the change indicative of landing zone instability; and

triggering landing abort logic to abort landing of the aircraft based on the landing instability indicator being set.

US Pat. No. 9,360,869

VEHICLE HEADING ERROR COMPENSATION

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling an aircraft, comprising:
obtaining at least one of ground-referenced longitudinal movement data of the aircraft and ground-referenced lateral movement
data of the aircraft;

obtaining a ground-referenced heading of the aircraft;
calculating a heading error based on a difference between the ground-referenced heading and a target heading;
generating a lateral movement error value based on at least one of the ground-referenced longitudinal movement data and ground-referenced
lateral movement data, and based on the heading error; and

generating a longitudinal movement error value based on at least one of the ground-referenced longitudinal movement data and
ground-referenced lateral movement data, and based on the heading error, wherein the longitudinal movement error value is
a ground-referenced longitudinal speed error value, and

the ground-referenced longitudinal speed error value is generated according to the equation:
uerr=utgt?u cos(?err)?v sin(?err)

wherein uerr is the longitudinal ground speed error value, utgt is a longitudinal ground speed target value, u is a detected ground-referenced longitudinal speed value, v is a detected ground-referenced
lateral speed value and ?err is a value of the heading error.

US Pat. No. 9,235,217

AUTOMATIC DUAL ROTOR SPEED CONTROL FOR HELICOPTERS

Sikorsky Aircraft Corpora...

1. A flight control system for a rotary-wing aircraft having at least one rotor, comprising:
an automatic rotor speed control configured to transition the at least one rotor between a high speed, normal operational
mode and a low speed, low noise operational mode in response to a plurality of received information without pilot action,
said automatic rotor speed control configured to transition the at least one rotor from the low speed, low noise operational
mode to the high speed, normal operational mode if any one of said plurality of received information comprises at least one
of a plurality of inhibits.

US Pat. No. 9,169,011

ROTOR WITH BLADES INCLUDING OUTER BLADE SHELL AND INNER STRUCTURAL MEMBER

SIKORSKY AIRCRAFT CORPORA...

1. A rotor for use in an aircraft comprising:
an inner hub; and
a plurality of blades arranged around the inner hub, each of the plurality of blades comprising:
an inner structural member;
a structural outer blade shell surrounding the inner structural member;
a centering block located at a base of the inner structural member proximal to the inner hub, wherein the centering block
is located between a first lateral portion of the inner structural member and a second lateral portion of the inner structural
member, wherein the centering block is further connected to the outer blade shell, wherein the centering block is connected
to the outer blade shell by at least two bearings having a common axis of rotation, the base of the inner structural member
fastened directly to the inner hub, and

wherein the centering block allows the inboard portion of the structural outer blade shell to rotate about a single axis approximately
corresponding to the inner structural member, an inboard portion of the outer blade shell rotatable about the single axis
relative to both the centering block and the inboard portion of the base of the inner structural member proximal to the inner
hub;

wherein the first lateral portion of the inner structural member and the second lateral portion of the inner structural member
extend from the base of the inner structural member and beyond the centering block in a direction towards an outboard end
of the outer blade shell.

US Pat. No. 9,618,378

OIL LEVEL INDICATOR FOR ROTARY WING AIRCRAFT TRANSMISSION

SIKORSKY AIRCRAFT CORPORA...

1. A fluid level sensor for determining an amount of a first fluid in a system, the fluid level sensor having a pivot point,
the sensor comprising:
a first substantially transparent sight glass distinct from and mounted outside the system, the first substantially transparent
sight glass being fluidly coupled to the first fluid in the system such that a level of first fluid in the first sight glass
is indicative of the amount of the first fluid in the system; and

a second substantially transparent sight glass having an independent closed loop containing a second fluid, the second sight
glass being positioned outside the system such that a plane extending through the first sight glass and the second sight glass
includes the pivot point, wherein a comparison of the level of first fluid in the first sight glass and a level of second
fluid in the second sight glass indicates if the amount of first fluid in the system requires adjustment independent of an
orientation of the system and if the level of first fluid and the level of second fluid are substantially identical, no adjustment
of the amount of first fluid in the system is needed.

US Pat. No. 10,071,493

TRIGGERING SYSTEMS FOR CARTRIDGE ACTIVATED DEVICES

SIKORSKY AIRCRAFT CORPORA...

1. A hoist system, comprising:a cable;
a cable cutter including primary and secondary cartridges coupled to the cable;
a triggering system operatively associated with the cutter, including:
a primary actuation circuit operatively coupled to the primary cartridge;
a secondary actuation circuit operatively coupled to the secondary cartridge; and
a serializing switch with actuate and test switch positions operably arranged between the primary actuation circuit and the second actuation circuit, wherein the serializing switch connects the first and second actuation circuits in parallel with one another in the actuate position, wherein the serializing switch connects the first and second actuation circuits in series with one another in the test position.

US Pat. No. 9,802,694

COAXIAL ROTOR LOW-SPEED MIXING

SIKORSKY AIRCRAFT CORPORA...

1. A method for estimating rotor mixing commands for an aircraft, comprising:
receiving signals indicative of reference commands from one or more controllers;
receiving signals from one or more sensors indicative of airspeed and sideslip angle for the aircraft, the sideslip angle
being indicative of a direction of flight for the aircraft;

calculating a sine and cosine of the sideslip angle;
determining gains for roll and pitch as a function of the airspeed, the determining includes referencing a look-up table that
indexes the gain with the airspeed; and

determining the one or more rotor mixing commands from the determined gain, the one or more rotor mixing commands being applied
synchronously to the rotors in the aircraft.

US Pat. No. 9,798,007

OBSTACLE DATA MODEL CONSTRUCTION SYSTEM WITH RANGE SENSOR SHADOWS AND USE IN MOTION PLANNING

SIKORSKY AIRCRAFT CORPORA...

1. A method of operating an obstacle data model construction system, comprising:
with a vehicle moving through a vehicle obstacle space from a first to a second position, scanning the vehicle obstacle space
at the first and second positions;

generating first and second boundary data sets from results of the scanning at the first and second positions, respectively;
deriving first and second shrouded regions from the first and second boundary data sets, respectively;
identifying a high confidence occupancy region from intersecting portions of the first and second shrouded regions; and
limiting additional scanning in the high confidence occupancy region.

US Pat. No. 9,539,769

COMPOSITE STRUCTURE AND CORE POSITIONING PLY

SIKORSKY AIRCRAFT CORPORA...

1. A method of forming a composite structure comprising:
positioning a first laminate in a molding tool;
co-curing at least one locking ply to a honeycomb core element;
positioning the honeycomb core element and the at least one locking ply co-cured to the honeycomb core element in the molding
tool;

positioning a second laminate over the core element, wherein the at least one locking ply extends outwardly from said honeycomb
core element such that a portion of the at least one locking ply is positioned directly between the first laminate and the
second laminate; and

applying pressure to the second laminate thereby retaining the at least one locking ply between the first laminate and the
second laminate and preventing movement of the core element.

US Pat. No. 9,501,062

ROTOR MOMENT FEEDBACK FOR STABILITY AUGMENTATION

SIKORSKY AIRCRAFT CORPORA...

1. A rotorcraft comprising:
at least one rotor including a plurality of rotor blades; and
a flight control computer configured to:
obtain a blade bending measurement from a sensor mounted to one of the plurality of rotor blades;
process, the rotor blade bending measurement to obtain moment data for the rotorcraft;
obtain data from an inertial measurement unit (IMU) operatively connected to the flight control computer, wherein the data
obtained from the IMU pertains to at least one of a pitch of the rotorcraft and an angular rate of the rotorcraft; and

process, the moment data and the data from the IMU to generate a command configured to stabilize the rotorcraft, wherein the
command is based on a reference input, and wherein the reference input is based on at least one input provided by a pilot
of the rotorcraft aircraft.

US Pat. No. 9,315,265

ADJUSTABLE SCISSOR CONTROL LINK

SIKORSKY AIRCRAFT CORPORA...

1. A control link disposed to transfer rotor shaft rotation from a walking beam rotatable with the rotor shaft to a rotating
swashplate, the control link comprising:
a structure including:
a first sidewall and a second sidewall terminating at respective first ends as mating elements which are securable to the
walking beam such that the walking beam is rotatable about an axis defined through the mating elements and such that a moment
reaction in opposition to structure rotation about the walking beam is generated, the first sidewall and the second side wall
being convergent toward one another at respective second ends and connecting to each other at their second ends to define
a through-hole,

rib members connected to each of the first sidewall and second sidewall between the first ends and second ends; and
a rod coupled to the rotating swashplate and configured to be coupled to a second end of the structure and to the rib members
at variable distances relative to the rotating swashplate.

US Pat. No. 9,177,481

SEMANTICS BASED SAFE LANDING AREA DETECTION FOR AN UNMANNED VEHICLE

SIKORSKY AIRCRAFT CORPORA...

1. A method for determining a suitable landing area for an aircraft, comprising:
receiving signals indicative of terrain information for a terrain via a three-dimension (3D) perception system;
receiving signals indicative of image information for the terrain via a camera perception system, the image information separate
from the terrain information;

evaluating, with the processor, the terrain information and generating information indicative of a landing zone candidate
region;

co-registering in a coordinate system, with the processor, the landing zone candidate region and the image information;
segmenting, with the processor, an image region from the image information corresponding to the landing zone candidate region
to generate segmented regions;

classifying, with the processor, the segmented regions into semantic classes;
determining, with the processor, contextual information from a contextual model and using the contextual information to detect
an error in at least one semantic classes; and

ranking and prioritizing the semantic classes.

US Pat. No. 9,660,435

MULTI-DIRECTIONAL ELECTRICAL POWER PROTECTION SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A multidirectional electrical power protection system, comprising:
first and second power supplies configured for supplying power to a main bus circuit;
first and second load buses electrically connected to each of the first and second power supplies via respective connections
with the main bus circuit and configured for energizing at least first and second devices;

first and second smart contactors connected in series to the main bus circuit between the respective connections of the first
and second load buses with the main bus circuit and the first and second power supplies,

each of the first and second smart contactors being configured for sensing a first current flowing in a first direction through
the main bus circuit and for sensing a second current flowing in a second direction through the main bus circuit and respectively
including first and second logic controls each in communication with a sensor for delivering an output signal for opening
the corresponding one of the first and second smart contactors in response to the sensing of an overcurrent flowing in either
of the first or the second directions via the sensor;

first and second power supply contactors electrically connected to the first and second power supplies in series with the
connection of the first and second load buses with the main bus circuit and the first and second smart contactors, respectively,
and

an nth load bus with an absence of power supply or smart contactors electrically connected to each of the first and second
power supplies via a connection with the main bus circuit between the first and second smart contactors.

US Pat. No. 9,597,743

MACHINE FOR MACHINING GEAR TEETH AND GEAR TEETH MACHINING METHOD

SIKORSKY AIRCRAFT CORPORA...

1. A machine for machining a workpiece having a first central longitudinal axis, the machine comprising:
a grinding spindle having a body, a wheel supporting an abrasive and an insulator electrically isolating the wheel from the
body, the wheel being operable to remove material from the workpiece, the grinding spindle having a second central longitudinal
axis about which the grinding spindle rotates and being disposed with the first and second central longitudinal axes intersecting
one another so as to create a continuous gear tooth on the workpiece; and

an electrochemical grinding (ECG) element electrically connected to the wheel and the workpiece, the ECG element being configured
to execute ECG processing on the grinding spindle and the workpiece to soften the workpiece as the gear tooth is being created
by the grinding spindle.

US Pat. No. 9,499,264

UNMANNED VEHICLE OPERATING MODES

SIKORSKY AIRCRAFT CORPORA...

1. A vehicle, comprising:
a frame;
drive elements configured to drive movements of the frame; and
a computer, including at least a processor, configured to receive mission planning commands comprising at least one of mission
details, on-board system details or waypoint setting and manual commands comprising local maneuvering commands and to control
operations of the drive elements to operate in a safe mode in which the mission planning commands are accepted but the manual
commands are refused, a manual mode in which the mission planning commands are refused but the manual commands are accepted
and an enroute mode,

wherein the safe mode comprises a stationary mode characterized in that the frame is stationary relative to ground,
wherein the manual mode comprises a movable mode characterized in that the frame is movable relative to the ground, and
wherein the computer is further configured to only allow mode transitions directly between the safe and manual modes and directly
between the safe and enroute modes.

US Pat. No. 9,448,558

DAMAGE ADAPTIVE CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft system comprising:
at least one first fly-by-wire sensor configured to measure a state of a rotary wing aircraft;
at least one second sensor configured to measure at least one of a damage and a compromise associated with a structural component
of the rotary wing aircraft; and

a control computer configured to receive data from the at least one first fly-by-wire sensor and the at least one second sensor,
the control computer further configured to analyze the data to determine (i) the structural component that is at least one
of damaged and compromised, (ii) a location of the structural component, and (iii) a level of operability of the structural
component that is at least one of damaged and compromised,

wherein the control computer is configured to provide information relating to the determined structural component, location,
and level of operability to an Input/Output (I/O) device; and

wherein the control computer is configured to adapt an operational envelope of the rotary wing aircraft based on the measured
state of the rotary wing aircraft and the determined structural component, location, and level of operability.

US Pat. No. 9,428,267

IN-FLIGHT MECHANICALLY ASSISTED TURBINE ENGINE STARTING SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. An engine starting system for a rotary wing aircraft, comprising:
a controller that receives a signal indicative of a start command for an engine;
a transmission input module that is mechanically coupled to a transmission system and an accessory gearbox, the transmission
input including a freewheel device; and

a starter motor that is mechanically coupled to a compressor drive shaft of the engine, wherein the controller is configured
to couple the freewheel device to the compressor drive shaft and transmit motive power from a second engine to the compressor
drive shaft.

US Pat. No. 9,415,866

LOW DRAG ROTOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A rotor assembly comprising:
a rotor hub rotatable about a central axis including a plurality of rotor hub arms integrally formed with and extending radially
outwardly from the rotor hub, the plurality of rotor hub arms including:

a plurality of rotor hub upper arms; and
a plurality of rotor hub lower arms, the rotor hub lower arms offset from the rotor hub upper arms along the central axis
and defining an arm opening therebetween;

blade yokes, each blade yoke comprising:
yoke arms located at opposing lateral sides of a corresponding one of the rotor hub arms to which the rotor hub arm is operably
connected, each of the yoke arms includes a cantilevered end; and

a bearing outer race secured to the cantilevered end of corresponding one of the yoke arms through a mechanical fastener and
extending through the arm opening, the blade yoke in a noncontact arrangement with the rotor hub, wherein the mechanical fastener
extends along an axis substantially parallel to the central axis;

blade retention bearings, each blade retention bearing being a single-element bearing disposed at a corresponding one of the
rotor hub arms and which is supportive of a corresponding one of the blade yokes and including:

a bearing inner race extending between and secured to one of the rotor hub upper arms and the corresponding rotor hub lower
arm radially outboard of the bearing outer race; and

a bearing element disposed between the bearing outer race and the bearing inner race;
rotor blades, each rotor blade being secured to a corresponding one of the blade yokes;
wherein an entirety of each blade retention bearing is located radially inboard of an outer diameter of their respective rotor
hub arms.

US Pat. No. 9,308,985

DECELERATION TO HOVER MODULATION

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling a deceleration profile of an aircraft, comprising:
determining the deceleration profile to obtain a hover condition at a commanded location; and
adjusting the deceleration profile in a continuous manner by manual input from a pilot, wherein adjusting comprises:
receiving, with a processor, a signal indicative of a deceleration command;
receiving with the processor, signals indicative of a sensed velocity and a commanded heading rate;
determining, with the processor, a commanded velocity in response to the receiving of the deceleration command and the commanded
heading rate;

determining, with the processor, an estimated deceleration command as a function of the commanded velocity; and
determining, with the processor, an actual deceleration command in response to the determining of the estimated deceleration
command.

US Pat. No. 9,145,926

FRICTION CLUTCH FOR SHAFT DRIVEN ACCESSORIES

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft comprising:
an airframe;
a main rotor system configured to rotate about a first axis;
a propulsion system for driving the main rotor system about the first axis, the propulsion system including a device for limiting
a transfer of torque between a first rotatable component and a second rotatable component, the device for limiting a transfer
of torque having:

a first portion connected to the first component, the first portion having a flange extending radially outward therefrom;
and

a second portion coupled to the second component, the second portion including a cartridge assembly arranged concentrically
with at least part of the first portion such that the first portion is arranged between the second portion and the first axis,
the second portion having a first end arranged adjacent a first side of the flange and a first washer arranged adjacent a
second, opposite side of the flange, a second end of the cartridge assembly having at least one hole including a biasing mechanism
arranged therein, the biasing mechanism being configured to bias the first end of the cartridge assembly and the first washer
into contact with the flange to transmit torque between the first component and the second component when a torque applied
to the first component is below a predetermined threshold.

US Pat. No. 9,120,567

HIGH SPEED COMPOUND ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft comprising:
an airframe;
an extending tail extending from the airframe;
a main rotor assembly operably connected to the airframe including:
a plurality of rotor blades operably connected to a rotor shaft; and
a spar air duct extending along one or more rotor blades of the plurality of rotor blades, the spar air duct having at least
one inlet and at least one outlet, the at least one inlet disposed at a trailing edge of the rotor blade such that airflow
is urged into the spar duct through the at least one inlet via rotation of the rotor blade about the rotor shaft, the spar
air duct operably connected to an aircraft flight control system, the spar air duct including a valve located within the rotor
blade to regulate airflow through the spar air duct such that, when the valve is activated, the airflow through the spar air
duct changes one or more operational characteristics of the rotor assembly; and

a tail rotor operably connected to the extending tail, the tail rotor rotatable about a tail rotor axis, the tail rotor axis
movable from laterally-extending to rearward-extending.

US Pat. No. 9,708,979

ENGINE INLET DUCT INSTALLATION

SIKORSKY AIRCRAFT CORPORA...

1. An inlet duct assembly comprising an inlet duct having a bifurcated configuration along a longitudinal axis thereof and
comprising:
a first inlet duct leg comprising a pair of first flanges extending along opposing longitudinal edges thereof, each first
flange including:

a first mounting flange; and
a plurality of fasteners extending from the first mounting flange, each fastener having a fastener head disposed at a preselected
distance from the mounting flange;

a second inlet duct leg comprising a pair of second flanges extending along opposing longitudinal edges thereof, each second
flange including:

a second mounting flange configured to abut a respective one of the first mounting flanges and comprising a plurality of fastener
openings receiving the fasteners therethrough; and

a mounting strip moveably located on the second mounting flange having:
a plurality of strip openings, a respective one of the fasteners extending therethrough each strip opening; and
a tightening ramp corresponding to each strip opening having an increasing height in one direction;
the first and second inlet duct legs configured to extend along lateral sides of an engine axis and around a mount shaft located
at the engine axis:

wherein movement between the mounting strips and the fastener heads in an axial direction of the mounting strips increases
a tension on the fasteners and thus secures the first mounting flanges to the second mounting flanges.

US Pat. No. 9,645,571

RELIABILITY MAINTAINING SERIAL NUMBER CREDIT PROCESS

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
receiving, by a computing device comprising a processor, an anticipated usage input, a load input and a strength input associated
with one of an aircraft and an aircraft component;

calculating, by the computing device, a baseline reliability value based at least in part on the anticipated usage input,
the load input and the strength input of the one of an aircraft and an aircraft component;

receiving, by the computing device, usage data associated with use of the one of an aircraft and an aircraft component;
generating, by the computing device, an updated reliability value based on at least some of the inputs used to calculate the
baseline reliability value and the usage data;

comparing measured data for a regime of use with data based on at least one user input;
determining a category of uncertainty in the usage data based on the comparison;
fitting a distribution to the usage data based on the category;
determining, by the computing device, a lifetime for the one of an aircraft and an aircraft component based on the updated
reliability value; and

updating a usage monitor and reliability factor (UMRF) of the one of the aircraft and the aircraft component based on the
determined lifetime; and

retiring the one of the aircraft and the aircraft component after the UMRF indicates a retirement time.

US Pat. No. 9,481,456

RELATIVE ACCELERATION BLADE POSITION MEASUREMENT

SIKORSKY AIRCRAFT CORPORA...

16. An aircraft comprising:
an airframe;
a hub extending from the airframe and including hub arms, the hub being rotatable about an axis;
blades respectively extending from each of the hub arms, the blade being configured to generate lift according to the rotation
of the hub;

hub arm sensors respectively disposed at each of the hub arms to measure motion associated with the hub;
blade sensors respectively disposed as multiple blade sensors at roots of each of the blades to measure motion associated
with each of the blades; and

a control computer configured to:
obtain data from the hub sensors and the blade sensors;
process the data to isolate blade dynamics from aircraft maneuvering dynamics using relative blade-hub acceleration based
on the data obtained from the hub arm sensors and the multiple blade sensors for each of the blades;

obtain at least one parameter associated with the blade dynamics for each of the blades based on the processing; and
control each of the blades using the obtained one parameter.

US Pat. No. 9,725,166

COUNTER-ROTATING ROTOR SYSTEM WITH STATIC MAST

SIKORSKY AIRCRAFT CORPORA...

1. A coaxial, dual rotor system comprising:
a first rotor assembly disposed at a rotor axis;
a first rotor quill shaft operably connected to the first rotor assembly at the rotor axis to drive rotation of the first
rotor assembly about the rotor axis;

a non-rotating static mast extending along the rotor axis inside of the first rotor quill shaft;
a second rotor assembly disposed at the rotor axis;
a second rotor quill shaft operably connected to the second rotor assembly to drive rotation of the second rotor assembly
about the rotor axis, the second rotor quill shaft coaxial with the first rotor quill shaft and disposed inside of the static
mast, wherein the second rotor assembly is mounted concentrically with the second rotor quill shaft and the non-rotating static
mast, the non-rotating static mast extending from the first rotor assembly to the second rotor assembly; and

a rotor bearing disposed between the second rotor assembly and the static mast to transfer loads from the second rotor assembly
to the static mast.

US Pat. No. 9,758,242

LIFT OFFSET MANAGEMENT AND CONTROL SYSTEMS FOR COAXIAL ROTORCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A lift offset management system, comprising:
first and second rotors disposed to oppositely rotate about a same rotational axis;
sensors disposed to generate hub moment, tip clearance and lift offset data of the first and second rotors;
an input unit configured to generate a target lift offset reference command based on flight data, the hub moment data and
the tip clearance data; and

a feedback system configured to generate a correction command based on the lift offset data and comprising:
a summation unit at which the target lift offset reference and correction commands are combined into an actual lift offset
command; and

a servo control unit disposed to control blade pitching of the first and second rotors based on the actual lift offset command.

US Pat. No. 9,686,653

PREDICTIVE DIRECTIONAL ANTENNA TARGETING

SIKORSKY AIRCRAFT CORPORA...

1. A method of predictive targeting of a directional antenna, the method comprising:
receiving a plurality of state information at a directional antenna control system from a mobile communication node, the state
information comprising a position and a trajectory of the mobile communication node;

logging the state information, by the directional antenna control system, as a last known position and a last known trajectory
of the mobile communication node;

determining an estimated future position of the mobile communication node based on the last known position, the last known
trajectory, and a time period;

based on a loss of communication between the directional antenna and the mobile communication node, positioning the directional
antenna by the directional antenna control system to establish a line-of-sight between the directional antenna and the estimated
future position of the mobile communication node.

US Pat. No. 9,639,088

AUTONOMOUS LONG-RANGE LANDING USING SENSOR DATA

SIKORSKY AIRCRAFT CORPORA...

1. A method of autonomous landing of an aircraft in a landing area, the method comprising:
receiving, with a processor, sensor signals related to the landing area via a sensor device, wherein the sensor device is
operable to maintain a relative orientation and size of the landing area;

obtaining, with the processor, a template of the landing area in response to the receiving of the sensor signals;
matching, with the processor, one or more features of the template with one or more features acquired from the sensor signals
related to the landing area; and

controlling, with the processor, each of the sensor device and an aircraft control system independently based on said matching.

US Pat. No. 9,598,168

METHOD OF ASSEMBLING AND BALANCING ROTOR BLADES

SIKORSKY AIRCRAFT CORPORA...

1. A method of assembling a rotor blade assembly comprising:
determining a first spanwise moment of a first component of the rotor blade assembly;
comparing the first spanwise moment to a target first spanwise moment;
adjusting the first spanwise moment of the first component based on a result of the comparison to provide a balanced first
component;

determining a second spanwise moment of a second component of the rotor blade assembly;
comparing the second spanwise moment to a target second spanwise moment;
adjusting the second spanwise moment of the second component based on a result of the comparison to provide a balanced second
component;

assembling the balanced first and second components to provide the rotor blade assembly meeting a target spanwise moment of
the rotor blade assembly, wherein:

the first component comprises one of a leading edge assembly, a trailing edge pocket assembly, and a spar assembly; and
the second component comprises another one of the leading edge assembly, the trailing edge pocket assembly, and the spar assembly.

US Pat. No. 9,482,595

ROTOR STATE SENSOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A rotor state sensor system for use with a rotor including a hub, a hub arm and a blade coupled to the hub by the hub arm,
the sensor system comprising:
a plurality of sensors disposed on a radially outer portion of the hub arm to define a first plane, which emit emissions and
receive reflected emissions, and which generate a signal according to the received reflected emissions;

a plurality of reflector plates disposed at varying positions about a pitch axis of the blade on a radially inward portion
of the blade and which define a second plane at locations where the emissions from the sensors are incident on the reflector
plates and from which the reflected emissions are reflected towards the sensors

the sensors being configured to detect the locations from the reflected emissions and to generate the signal to be indicative
of the locations; and

a computing device which receives the signal from the sensors, determines relative orientations of the first and second planes
according to the received signal and determines a condition of the rotor based on the determined relative orientations.

US Pat. No. 9,452,829

YAW CONTROL OF CO-AXIAL ROTOR

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling rotor blades of a co-axial counter-rotating rotor assembly of an aircraft including a first rotor
co-axial with a second rotor, comprising:
identifying a first zone of rotor rotation angles of the co-axial counter-rotating rotor assembly, the first zone defining
a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the
rotor rotation angles other than the first zone of rotation angles being defined as a second zone;

receiving a yaw command to adjust a yaw moment of the aircraft; and
applying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to
rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command.

US Pat. No. 9,944,400

ADAPTIVE ENGINE ACCELERATION FOR ACCESSORY LOADS

SIKORSKY AIRCRAFT CORPORA...

1. A method of adaptive engine acceleration for accessory loads, the method comprising:receiving an accessory load indicator corresponding to an accessory load of an engine;
comparing the accessory load indicator to an adjustment threshold;
adjusting an acceleration schedule of the engine by increasing the acceleration schedule when the accessory load indicator is below the adjustment threshold;
decreasing the acceleration schedule when the accessory load indicator is above the adjustment threshold; and
selecting an acceleration value for the aircraft from the adjusted acceleration schedule based on an acceleration demand.

US Pat. No. 9,863,468

ROD END WEAR PREVENTION

SIKORSKY AIRCRAFT CORPORA...

1. A rod and bracket assembly comprising:
a bracket;
a rod connected to the bracket via a fastener extending through a bracket hole; and
a bushing assembly disposed at the bracket hole including:
a bushing having a bushing flange; and
a wear pad disposed between the bushing flange and an inner face of the bracket, and retained thereat by the bushing flange,
to prevent wear of the bracket and/or the rod.

US Pat. No. 9,758,247

COMBINED LAUNCH AND MISSION VEHICLES

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:
a mission vehicle configured to follow vertical take-off and landing (VTOL) operations and to execute forward flight, hover/loiter
and landing operations; and

a launch vehicle configured to drive the mission vehicle through at least vertical take-off (VTO) operations, the launch vehicle
including:

a fuselage including an engine nacelle along the fuselage, and
alighting elements coupled to the fuselage proximate to the engine nacelle and configured to support the launch vehicle in
a vertical orientation during ground operations,

the launch vehicle and the mission vehicle are umbilically coupled, in the vertical orientation prior to VTO operation and
during the VTO operations; and the launch vehicle is releasable from the mission vehicle thereafter,

wherein the launch vehicle at least partially drives rotations of rotors of the mission vehicle during at least the VTO operations.

US Pat. No. 9,752,878

UNMANNED AERIAL VEHICLE CONTROL HANDOVER PLANNING

SIKORSKY AIRCRAFT CORPORA...

1. A method of control handover planning for an unmanned aerial vehicle (UAV), the method comprising:
determining, by a planning system, a current location of a mobile control system and a current location of the UAV;
identifying a target location;
determining a control handover zone based on a communication range constraint between the mobile control system and the UAV,
the control handover zone located between the current location of the mobile control system, the current location of the UAV,
and the target location; and

creating a mobile control system path plan based on a location of the control handover zone and a UAV path plan based on the
location of the control handover zone, wherein each of the mobile control system path plan and the UAV path plan includes
a control handover waypoint in the control handover zone, the control handover waypoint defining a planned location to place
the mobile control system in control of the UAV, wherein the mobile control system and the UAV are expected to reach their
respective control handover waypoints at the same time.

US Pat. No. 9,682,771

CONTROLLING ROTOR BLADES OF A SWASHPLATELESS ROTOR

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling rotor blades of a rotor assembly, comprising:
determining an azimuthal position of a rotor assembly;
identifying a lateral command value, a longitudinal command value and a collective command value of a rotor assembly control
system;

calculating a sine value and a cosine value of the azimuthal position;
generating a separate blade control signal for each separate blade of the rotor assembly to control a position of each blade
independent of each other blade based on combining the sine value and cosine value of the azimuthal position with the lateral
command value, the longitudinal command value and the collective command value, wherein the sine value of the azimuthal position
is combined with the lateral command, and the cosine value of the azimuthal position is combined with the longitudinal command,
and wherein each blade control signal is generated to be different from each other blade control signal; and

adjusting the position of one or more blades in response to the separate blade control signals generated.

US Pat. No. 9,623,964

COUNTER-ROTATING ROTOR SYSTEM WITH STATIONARY STANDPIPE

SIKORSKY AIRCRAFT CORPORA...

1. A coaxial, dual rotor system connected to a gearbox, the system comprising:
a first rotor assembly disposed at a rotor axis and which imparts a first axial load and a first moment;
a first rotor shaft operably connected to the first rotor assembly at the rotor axis to drive rotation of the first rotor
assembly about the rotor axis;

a first bearing assembly connecting the gearbox to the first rotor shaft and which transfers the first axial load from the
first rotor shaft to the gearbox;

a second rotor assembly disposed at the rotor axis and which imparts a second axial load and a second moment;
a second rotor shaft operably connected to the second rotor assembly at the rotor axis to drive rotation of the second rotor
assembly about the rotor axis, the second rotor shaft coaxial with and radially offset from the first rotor shaft;

a second bearing assembly connecting the gearbox to the second rotor shaft and which transfers the second axial load from
the second rotor shaft to the gearbox;

a nonrotating standpipe disposed at the rotor axis radially between the first rotor shaft and the second rotor shaft;
an intershaft bearing assembly disposed at the standpipe and which transfers the first and second moments from the first rotor
assembly and the second rotor assembly to the standpipe using the first and second bearing assemblies; and

an aerodynamic fairing secured to the standpipe between the first rotor assembly and the second rotor assembly via a plurality
of fasteners extending from the standpipe.

US Pat. No. 9,606,535

SPATIAL RECOGNITION IN AN AUTONOMOUS VEHICLE GROUP

SIKORSKY AIRCRAFT CORPORA...

1. An autonomous vehicle comprising:
a sensor interface coupled to a gyroscope system;
a wireless communication interface;
a processor; and
memory having instructions stored thereon that, when executed by the processor, cause the autonomous vehicle to:
establish a plurality of wireless communication links with two or more vehicles in a group comprising the autonomous vehicle
and the two or more vehicles;

monitor a signal strength of each of the wireless communication links to determine an observed signal strength of each of
the wireless communication links;

determine a desired position of the autonomous vehicle based on an expected signal strength of each of the wireless communication
links;

receive control commands from a commander node through the plurality of wireless communication links; and
initiate a position adjustment of the autonomous vehicle based on the control commands and a difference between the expected
signal strength and the observed signal strength in combination with data from the gyroscope system.

US Pat. No. 9,567,105

AIRCRAFT WITH INTEGRATED SINGLE SENSOR

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:
a single sensor; and
wings extending outwardly in opposite directions from a fuselage, each wing comprising a main section, an engine section supported
on the main section and tail surfaces extending transversely relative to the main section, and

the single sensor being mountable to one of the tail surfaces with a field of view (FOV) representable as a spherical wedge
having a dihedral angle exceeding 180°;

wherein the single sensor comprises:
a pylon coupled to a distal end of the one of the tail surfaces and disposed to extend to the outer diameter of a rotor disk;
an aerodynamic fairing disposed along the pylon; and
a sensor element coupled to a distal end of the pylon.

US Pat. No. 10,054,957

HAPTIC FEEDBACK FOR REALTIME TRAJECTORY CONSTRAINTS

SIKORSKY AIRCRAFT CORPORA...

1. A system for receiving feedback in a flight plan of a vehicle, comprising:a haptic-enabled device comprising a crew seat with an inceptor mounted thereto; and
a processor with memory having instructions stored thereon that, when executed by the processor, cause the system to:
receive signals indicative of the flight plan for the vehicle;
receive deviation signals indicative of a proposed deviation in a trajectory for the flight plan; and
transmit signals to the haptic-enabled device representing trajectory constraints in the proposed deviation in response to the receiving of the deviation signals, wherein the trajectory constraints include soft constraints including at least one of fuel efficiency and time for a mission.

US Pat. No. 10,053,207

DE-ROTATION SYSTEM FOR A SHAFT FAIRING

SIKORSKY AIRCRAFT CORPORA...

1. A fairing system for a rotary wing aircraft comprising:a shaft fairing mounted for rotation about a first axis of rotation;
a de-rotation system contained within the shaft fairing, the de-rotation system including a toroidal continuously variable transmission (CVT) configured to control the rotation of the shaft fairing about the first axis of rotation; and
a position control system including at least one position sensor configured to monitor a position of the shaft fairing relative to the first axis of rotation and a controller operably coupled to the at least one position sensor and to the de-rotation system, the controller being configured to adjust a gear ratio of the toroidal CVT in response to a sensed position of the shaft fairing.

US Pat. No. 9,944,388

ROTORCRAFT STATE CONTROL

Sikorsky Aircraft Corpora...

1. An aircraft comprisinga rotor system including blades to provide thrust for the aircraft at a rotor efficiency level;
a power system which powers the rotor system at a power output level; and
a controller which selectively changes rotor efficiency of the rotor system to change a rotor system state of the aircraft without changing the power output level, wherein the controller issues command output to the rotor system to carry out the intended state change by adjusting drag and/or efficiency at a substantially constant thrust on one or more rotor blades of the rotorcraft.

US Pat. No. 9,908,615

ROTOR BLOWN WING AIRCRAFT INCLUDING A ROTOR BLOWN WING HAVING AT LEAST ONE SELECTIVELY CONTROLLABLE CONTROL SURFACE AND A METHOD OF CONTROLLING A ROTOR BLOWN WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blown wing (RBW) aircraft comprising:
an airframe;
at least one rotor blown wing (RBW) including a first selectively controllable control surface arranged on one side of the
at least one rotor blown wing and a second selectively controllable control surface arranged on a second, opposing side of
the at least one rotor blown wing directly opposite of the first selectively controllable surface;

at least one rotor configured to generate and direct an airflow over the at least one RBW; and
a control system operatively connected to the first and second selectively controllable control surfaces, the control system
selectively controlling the first and second selectively controllable control surfaces to change the airflow over the at least
one RBW to facilitate a vertical landing.

US Pat. No. 9,874,878

SYSTEM AND METHOD FOR ADAPTIVE MULTI-SCALE PERCEPTION

SIKORSKY AIRCRAFT CORPORA...

1. A method of adaptive multi-scale perception of a target for an aircraft, comprising:
receiving, with a processor, sensor signals indicative of aircraft information with respect to the target;
selecting, with the processor, one or more sensor devices in response to the receiving of the aircraft information;
receiving, with the processor, sensor information from the one or more sensor devices indicative of the target;
dynamically selecting, with the processor, sensor processing parameters for the one or more sensor devices based on at least
one of aircraft altitude and distance to one of a location and a target; and

analyzing, with the processor, the sensor information from the selected sensor devices and using the selected sensor processing
parameters.

US Pat. No. 9,802,698

ROTOR HUB FOR ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotor hub configured to support and rotate a plurality of rotor blades about an axis of rotation which rotates in a horizontal
plane, the rotor hub comprising:
a cylindrical body having a central shaft hole including the axis of rotation, the hole having a radius extending from the
axis in a radial direction;

a plurality of radial spokes, each radial spoke extending from the cylindrical body in a spoke direction; and
a plurality of arcuate segments, the arcuate segments extending between a distal end of adjacent spokes to define a plurality
of hub apertures,

wherein the spoke direction extends at an angle to the radial direction in both the horizontal plane and a vertical plane
perpendicular to the horizontal plane such that a line defined by the spoke direction does not intersect the axis of rotation;
and the spoke direction extends at an angle in the horizontal plane in a direction opposite to a direction of rotation of
the rotor hub about the axis of rotation.

US Pat. No. 9,759,809

LIDAR-BASED SHIPBOARD TRACKING AND STATE ESTIMATION FOR AUTONOMOUS LANDING

SIKORSKY AIRCRAFT CORPORA...

1. A method for state estimation of a surface of a platform at sea, comprising:
receiving, with a processor, sensor signals indicative of LIDAR data for the platform;
applying, with the processor, a Bayesian filter to the LIDAR data for a plurality of hypotheses;
determining, with the processor, vertical planes representing azimuth and elevation angles for the LIDAR data;
applying, with the processor, a robust linear estimation algorithm to the vertical planes;
determining, with the processor, candidate points in response to the applying of the robust linear estimation algorithm; and
landing an aircraft on the surface of the platform that is estimated by the candidate points.

US Pat. No. 9,719,800

SCREEN SYMBOLOGY

SIKORSKY AIRCRAFT CORPORA...

1. A method for enhancing situational awareness in a rotary wing aircraft, comprising:
receiving, with a processor, signals indicative of environmental information for the aircraft during a hover;
determining, with the processor, signals indicative of a heading, course, and speed for the aircraft relative to a tactical
plot in response to the receiving of the environmental information;

displaying, with the processor, the tactical plot and a composite symbology for heading, course, and speed on tactical display
on the tactical plot, wherein the composite symbology for course provides both a direction of travel relative to the heading
of the rotary wing aircraft and the speed of the rotary wing aircraft in the direction of travel; and

determining a course and location of other vehicles in relation to the aircraft.

US Pat. No. 9,718,541

SWASHPLATE APPARATUS

SIKORSKY AIRCRAFT CORPORA...

1. A swashplate apparatus for use with a rod end, comprising:
a first swashplate including outer and inner bodies and an intermediate portion defining a major groove between the outer
and inner bodies;

a second swashplate disposable in the major groove to be rotatable relative to the first swashplate, the second swashplate
including an interior facing surface radially separated from the inner body to define a minor groove and defining a recess
in which the rod end is disposable;

a connector disposable in the recess to pivotably couple the rod end to the second swashplate; and
a plate element disposable in the minor groove and affixable to the interior facing surface of the second swashplate and the
connector.

US Pat. No. 9,656,760

VARIABLE GEOMETRY HELICOPTER ENGINE INLET

SIKORSKY AIRCRAFT CORPORA...

1. A dual variable area engine inlet of a helicopter, comprising:
a fuselage section;
a horizontally oriented top wall section disposed to oppositely face the fuselage section at a distance;
a main rotor pylon section extending between the fuselage section and the horizontally oriented top wall section;
vertically oriented side wall sections respectively extending between the fuselage section and opposite ends of the horizontally
oriented top wall section and being respectively disposed to face opposite sides of the main rotor pylon section at a distance,

the fuselage section, a leading side of the horizontally oriented top wall section, the main rotor pylon section and a leading
side of the vertically oriented side wall sections defining capture areas with forward-most portions thereof being forward
facing openings through which airflow is drawn; and

movable portions respectively disposed as components of the horizontally oriented top wall section within the capture areas
to occupy and move between first and second positions respectively associated with non-constricted and constricted conditions
of the capture areas and each being independently movable to reduce or increase respective heights of the capture areas.

US Pat. No. 9,528,375

NON-UNIFORM BLADE DISTRIBUTION FOR ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A translational thrust system for a rotary wing aircraft comprising:
a propeller system having at least a first pair of propeller blades and a second pair of propeller blades extending radially
outward from a rotatable propeller hub, wherein each pair of propeller blades includes a first propeller blade and a second
propeller blade arranged diametrically opposite one another about a circumference of the propeller hub, and the first pair
of propeller blades and the second pair of propeller blades are arranged such that an angle between a first propeller blade
of the first pair of propeller blades and a first propeller blade of the second pair of propeller blades is less than if the
first and second pairs of propeller blades were uniformly distributed around the circumference of the propeller hub, wherein
the first pair of propeller blades and the second pair of propeller blades are configured to rotate to an indexed position
when the rotary wing aircraft is grounded, and a distance between a rotational axis of the propeller hub and a surface on
which the rotary wing aircraft is supported when the rotary wing aircraft is grounded is less than a length of one of the
propeller blades.

US Pat. No. 9,511,855

POWER AND DATA TRANSFER TO HUB SENSORS

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
providing, by a coil embedded in a structure of a rotor hub composed of a paramagnetic material, power to at least one sensor;
and

receiving, by the coil, data from the at least one sensor.

US Pat. No. 9,452,831

INTEGRATION OF ROTARY ELECTRICAL ACTUATOR FOR SWASHPLATELESS INDIVIDUAL BLADE CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. An individual blade control system (IBCS) for a rotor system having a rotor hub comprising:
a plurality of blade cuffs mounted to the rotor hub, each blade cuff being configured to receive a rotor blade and rotate
about a blade axis;

a plurality of electrical actuators mounted to the rotor hub diametrically opposite one another and adjacent at least one
of the plurality of blade cuffs, each electrical actuator being configured to rotate about an actuator axis, the plurality
of blade axes and the plurality of actuator axes being arranged in a plane; wherein each electrical actuator is coupled to
an adjacent blade cuff such that rotation of one of the plurality of electrical actuator causes a proportional rotation of
only the blade cuff coupled to that electrical actuator.

US Pat. No. 9,272,785

WING MOUNT ADJUSTMENT

SIKORSKY AIRCRAFT CORPORA...

1. A mounting apparatus, comprising:
a fixed mounting structure that is fixed relative to a wing of a vehicle, the fixed mounting structure including a first fixed
fitting and a second fixed fitting, wherein the first fixed fitting includes a plurality of first flanges;

a rotatable mounting structure having a swivel fitting configured to engage the first fixed fitting and to swivel with respect
to the first fixed fitting about an axis of rotation oriented generally perpendicular to the fixed mounting structure, the
swivel fitting includes a plurality of second flanges, at least one of the plurality of second flanges being configured to
rest on at least one of the plurality of first flanges when the swivel fitting is engaged with the first fixed fitting, the
rotatable mounting structure also having a slide fitting configured to slide with respect to the second fixed fitting based
on the swivel fitting being engaged with the first fixed fitting;

an adjustment assembly arranged at an interface between the second fixed fitting and the slide fitting, the adjustment assembly
being configured to adjust an angular position of the slide fitting relative to the swivel fitting.

US Pat. No. 9,169,027

ELECTRIFIED ROTORCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling a propulsion system for a rotary wing aircraft, comprising:
receiving by a flight control computer a signal indicative of a power demand on an engine, the engine coupled to a generator,
the generator providing electric power to a main rotor electric motor to drive a main rotor;

determining by the flight control computer if a battery is available to supply electrical power to the main rotor electric
motor in response to the power demand;

upon determining that the battery is not available to supply the electrical power performing:
communicating with a vehicle health and usage monitoring system to determine if there are any system components or conditions
that interfere with providing electrical energy to the main rotor electric motor;

detecting a status of system components;
increasing power from the engine to drive the generator; and
distributing electrical power from the generator to the main rotor electric motor:
upon determining that the battery is available to supply the electrical power performing:
communicating with the vehicle health and usage monitoring system to determine if there are any system components or conditions
that interfere with providing electrical energy to the main rotor electric motor;

detecting the status of system components;
instructing a power processing unit to manage electrical energy;
upon the power processing unit determining that the battery has sufficient stored energy, distributing power from the generator
and the battery to the main rotor electric motor;

upon the power processing unit determining that the battery lacks sufficient stored energy, distributing power from the generator
to the main rotor electric motor while recharging the battery.

US Pat. No. 10,048,180

COATING BOND TEST METHOD AND METHOD OF MAKING A SPECIMEN FOR TESTING BOND STRENGTH OF A COATING

SIKORSKY AIRCRAFT CORPORA...

1. A coating bond test method, comprising:attaching with an adhesive a pull-off bar to a coating on a planar surface of a substrate for which a normal bond strength between the coating and the substrate is sought;
reducing a first area defined by an interface between the substrate and the coating to a value less than a second area defined by an interface between the adhesive and the coating;
urging the pull-off bar away from the substrate in a direction normal to the planar surface until failure occurs; and
recording a load at which failure occurred.
US Pat. No. 9,994,947

METHOD FOR PRODUCING DEFECT-FREE THREADS FOR LARGE DIAMETER BETA SOLUTION TREATED AND OVERAGED TITANIUM-ALLOY BOLTS

SIKORSKY AIRCRAFT CORPORA...

1. A method for producing an alpha-beta titanium alloy article, comprising:providing a work piece of an alpha-beta titanium alloy having a beta transus;
subjecting the work piece to a beta solution heat treatment process in a furnace with a vacuum at a temperature above the beta transus;
quenching the work piece in the furnace using pressurized inert gas following the subjecting of the work piece in the beta solution heat treatment process;
subjecting the work piece to an overage heat treatment process in the furnace with a vacuum to overage the work piece following the quenching of the work piece;
cooling the work piece in a pressurized inert gas following the subjecting of the overage heat treatment process;
wherein the work piece is processed during each of the beta solution heat treatment process, pressurized inert gas quenching, overage heat treatment process, and pressurized inert gas cooling without removal from the furnace; and
manufacturing threads into the work piece using a pre-machined wave formed thread pattern prior to thread rolling.

US Pat. No. 9,849,996

ENGINE ELECTRICAL LOAD SHED CONTROL

SIKORSKY AIRCRAFT CORPORA...

1. A method of engine electrical load shed control, the method comprising:
monitoring an engine torque;
receiving an accessory load indicator corresponding to an accessory load powered by an engine;
detecting a request for acceleration of the engine;
comparing the engine torque to a low engine power threshold; and
depowering one or more electrical buses providing power to the accessory load to reduce a rotor droop associated with the
acceleration of the engine based on detecting the request for acceleration of the engine when the engine torque is less than
the low engine power threshold and the accessory load indicator exceeds a shedding threshold.

US Pat. No. 9,828,089

ROTOR DRIVE SYSTEMS FOR ROTORCRAFT

Sikorsky Aircraft Corpora...

1. A rotor drive system, comprising:
a stationary mast defining a rotation axis;
an electric motor with a stator portion fixed to the mast and a rotor portion rotatable relative to the stator portion about
the rotation axis;

a clutch connected to the rotor portion of the electric motor; and
a rotor assembly rotatable about the rotation axis and operably connected to the clutch, wherein the clutch is coaxially arranged
between the electric motor and the rotor assembly about the rotation axis to disengage the electric motor from the rotor assembly
when rotational speed of the rotor assembly about the rotation axis exceeds rotational speed of the rotor portion of the electric
motor.

US Pat. No. 9,103,633

LIGHTWEIGHT PROJECTILE RESISTANT ARMOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A hard ballistic material comprising:
a monolithic ceramic layer; and
a rear face Ceramic Matrix Composite (CMC) layer continuously bonded to a rear face of said monolithic ceramic layer, wherein
said rear face CMC layer includes one of (1) a ceramic matrix and (2) a glass matrix.

US Pat. No. 10,161,441

SELF-LUBRICATED BEARINGS

SIKORSKY AIRCRAFT CORPORA...

1. A plain bearing comprising:an outer member;
an inner member rotatably engaged in at least two axes of rotation to the outer member, the inner member having a first coefficient of thermal expansion (CTE) and the outer member having a second coefficient of thermal expansion (CTE), the first coefficient of thermal expansion being substantially less than the second coefficient of thermal expansion; and
a coating formed about an exterior surface of the inner member.

US Pat. No. 9,776,385

EXTERNAL TO BAGGING MECHANICAL CLAMP

SIKORSKY AIRCRAFT CORPORA...

1. A tool for forming a panel including a core area, at which plies sandwich a core, and a trim area surrounding the core,
at which the plies are bonded together, the tool comprising:
a body having an uppermost surface, the panel being formable on the uppermost surface at the core area and the uppermost surface
defining a single plane above which the plies are disposed for bonding at the trim area where the core and trim areas are
both defined along the single plane, the body further including a step-down surface feature laterally offset from the single
plane;

a lock arranged at the step-down surface, the lock being operable to secure the plies;
an assembly including a vacuum bag to apply bonding pressure to the plies at least at the core and trim areas above the single
plane, wherein the vacuum bag at least partially covers the lock; and

a clamping device external to the assembly to apply at a tangentially localized spot at the trim area a spot load clamping
force directly to the vacuum bag so that the vacuum bag in turn applies a corresponding spot load clamping force directly
to the plies,

a width of the tangentially localized spot in a circumferential dimension, which is defined around the core, extending only
as a straight line from a first end of a partial arc-segment of the circumferential dimension to a second end of the partial
arc-segment.

US Pat. No. 9,745,056

MAIN ROTOR BLADE WITH COMPOSITE INTEGRAL SKIN AND CUFF

SIKORSKY AIRCRAFT CORPORA...

1. A main rotor blade assembly comprising:
a spar having a main section;
a main core positioned adjacent a trailing side of the main section of the spar;
a tip assembly including a main tip core and a tip end pocket core, the tip assembly being positioned adjacent an outboard
end of the main core and the spar such that the main tip core is substantially aligned with a longitudinal axis of the main
core and the tip end pocket core is substantially aligned with a longitudinal axis of the spar, wherein at least a portion
of both the main tip core and the tip end pocket core comprises a high density core; and

an upper composite skin and a lower composite skin, wherein both the upper composite skin and the lower composite skin extend
over the spar, the main core, the main tip core, and the tip end pocket core, and at least a portion of the upper composite
skin and the lower composite skin has a thickness sufficient to be load bearing.

US Pat. No. 9,765,875

LUBRICATION SYSTEMS FOR GEARBOX ASSEMBLIES

Sikorsky Aircraft Corpora...

1. A gearbox assembly, comprising:
a housing with an interior and a sump which holds lubricant;
a transmission element disposed within the interior and above the sump which receives and is lubricated by the lubricant;
and

a lubricant impoundment disposed between the transmission element and the sump,
wherein the lubricant impoundment is connected in series between the transmission element and the sump in a primary lubricant
flow path through which the lubricant held in the sump reaches the transmission element, and

wherein the lubricant impoundment maintains a supply of lubricant having passed through the transmission element for a secondary
lubricant flow path other than the primary lubricant flow path and disposed within the gearbox housing through which the lubricant
held in the lubricant impoundment reaches the transmission element.

US Pat. No. 9,727,059

INDEPENDENT SPEED AND ATTITUDE CONTROL FOR A ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A flight control system for independent speed and attitude control of a rotary wing aircraft comprising a main rotor system
and a translational thrust system, the flight control system comprising:
a flight control computer configured to interface with the main rotor system and the translational thrust system, the flight
control computer comprising processing circuitry configured to execute control logic comprising:

a pitch attitude reference generator configured to generate a pitch attitude reference and provide the pitch attitude reference
to a main rotor controller in response to a first pilot input to command the main rotor system;

a longitudinal reference generator configured to produce a longitudinal reference as a longitudinal position or longitudinal
velocity based on a second pilot input;

an attitude-to-propulsor crossfeed configured to convert the pitch attitude reference into a propulsor trim adjustment; and
a propeller pitch controller configured to combine the longitudinal reference and the propulsor trim adjustment into a propeller
command, and provide the propeller command to the translational thrust system.

US Pat. No. 9,718,547

SYSTEM AND METHOD FOR DETERMINING A LENGTH OF AN EXTERNAL LOAD SLING

SIKORSKY AIRCRAFT CORPORA...

1. A method for determining length of load sling assembly in an aircraft, comprising:
receiving, with a processor, information via one or more sensors regarding a load length during a delivery and descent state,
the load length comprising length of a load sling assembly and a load height;

controlling, with the processor, a minimum altitude of operation of the aircraft that ensures that the load does not touch
a ground or obstacles during one or more of a flight plan, during decent, or during delivery;

determining, with the processor, when a load has touched the ground during load release in response to the receiving of the
load length information; and

releasing, with the processor, the load from the load sling assembly when the processor determines that the load has touched
the ground.

US Pat. No. 9,620,022

AIRCRAFT MOTION PLANNING METHOD

SIKORSKY AIRCRAFT CORPORA...

1. A method of route planning for a vehicle proceeding from a current location to a destination in a planning space, the method
comprising:
generating, through a processor, a destination-rooted tree from global information that provides cost-to-go routing to the
destination from multiple locations in the planning space, wherein the global information includes course information including
topographic and global weather information at various altitudes;

generating, through the processor, a vehicle-rooted tree using local information from the current location out to a sensing
horizon generated by vehicle based sensors;

determining, through the processor, a local destination at the sensing horizon, the local destination corresponding to minimal
cost-to-go routing obtained from the destination-rooted tree; and

continually reducing the cost-to-go routing of the destination-rooted tree based on the local destination.

US Pat. No. 9,600,556

METHOD FOR THREE DIMENSIONAL PERCEPTION PROCESSING AND CLASSIFICATION

SIKORSKY AIRCRAFT CORPORA...

1. An apparatus for providing automatic control of a vehicle, the apparatus comprising:
at least one processor; and
memory storing instructions that, when executed by the at least one processor, cause the apparatus to:
organize items of raw data received from at least one sensor of the vehicle as a first data structure,
organize classified data objects as a second data structure,
link at least one item of the first data structure to at least one object of the second data structure, and
receive a search request and return generated search results comprising both raw data from the first data structure and classified
data objects from the second data structure that are relevant to the search request,

wherein the first data structure comprises a super node configured to provide a link as a relational database link to at least
one of the classified data objects in the second data structure,

wherein the linking of the super node to the at least one of the classified data objects provides for the automatic control
of the vehicle.

US Pat. No. 9,599,210

DAMAGE MITIGATION FOR GEARBOX

SIKORSKY AIRCRAFT CORPORA...

1. A method of rebuilding a damaged portion of a surface of a gearbox housing, the surface configured to engage with and support
a load of a portion of an aircraft, the method comprising:
forming an area in the surface by removing all material exhibiting at least one of localized damage, corrosion and pitting;
preparing the area;
creating a structural deposit in the area, the structural deposit being integrally formed with the gearbox housing, and the
structural deposit configured to share the load applied to the gearbox housing by the portion of the aircraft; and

removing excess material from the structural deposit.

US Pat. No. 9,580,187

ROTOR INDEX SENSOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. An integral rotor position sensing system for use in detecting a position of a rotor of an aircraft, the aircraft comprising:
an airframe;
a primary gearbox disposed within and rotationally fixed relative to a main section of the airframe;
a secondary gearbox disposed within one of a pylon section and a tail section of the airframe; and
a driveshaft, which extends through the outer housing and is coupled to the secondary gearbox to thereby drive rotation of
the rotor relative to the airframe via the secondary gearbox, the driveshaft including an inner shaft and an outer shaft,

the integral rotor position sensing system being displaced from the pylon and tail sections of the airframe and comprising:
a sensor integrally affixed to an outer housing of the primary gearbox and which is rotationally fixed with the primary gearbox
relative to the airframe, and

a sensed element sensed by the sensor and which is directly attached to the outer shaft of the driveshaft,
wherein rotational characteristics of the driveshaft are sensed according to signals received from the sensor.

US Pat. No. 9,567,871

IMPELLER RETENTION APPARATUS

SIKORSKY AIRCRAFT CORPORA...

1. An impeller retention apparatus, comprising:
a bearing element;
a rotatable gear shaft, which is rotatably supported within an outer body by the bearing element;
an impeller disposed about and coupled to the rotatable gear shaft to rotate with the rotatable gear shaft;
a preload spacer disposed along the rotatable gear shaft between the impeller and the bearing element, the preload spacer
comprising a forward preload spacer end to abut an aft end of the bearing element, an aft preload spacer end to abut a forward
face of the impeller and an elastic element which biases the impeller away from the bearing element in an axial direction
along the rotatable gear shaft; and

a flexible coupling coupled to the rotatable gear shaft such that the outer body and the flexible coupling cooperatively define
an annulus from which the impeller receives an airflow.

US Pat. No. 9,511,537

BONDING TOOL, SYSTEM TO APPLY PRESSURE DURING A BONDING PROCESS AND METHOD TO APPLY PRESSURE DURING A BONDING PROCESS

SIKORSKY AIRCRAFT CORPORA...

1. A bonding tool to facilitate bonding of a liner to a surface of a workpiece, the bonding tool comprising:
first and second bladders, which are each formed to define a fully enclosed interior and which are each inflatable from an
initial size to an expanded size; and

a frame formed to define first and second recesses in which the first and second bladders are respectively disposed, the first
and second recesses being oriented such that, when inflated from the initial size to the expanded size, the first and second
bladders apply a predefined pressure to the liner such that the liner is pressed against the surface of the workpiece,

wherein the bonding tool further comprises a third recess and a third bladder and the frame comprises:
a support member;
a first flange coupled to a distal end of the support member, the first flange being formed to define the first recess in
which the first bladder is disposed to expand in a first predominant direction; and

a second flange coupled to a central portion of the support member to define the second recess between the first and second
flanges in which the second bladder is disposed to expand in a second predominant direction transverse to the first predominant
direction,

the second flange being formed to define the third recess in which the third bladder is disposed to expand in the first predominant
direction.

US Pat. No. 9,327,842

METHOD AND SYSTEM FOR DETECTING FORCES ON AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A method for sensing a takeoff of an aircraft comprising:
receiving a rate of change in vertical motion of the aircraft;
determining whether the rate of change in the vertical motion of the aircraft exceeds a first threshold;
integrating the rate of change in the vertical motion of the aircraft and outputting a virtual altitude signal, responsive
to receiving an indication that a portion of the aircraft is contacting a surface;

delaying the virtual altitude signal through a discrete low pass filter and outputting a delayed virtual altitude signal;
subtracting the delayed virtual altitude signal from the virtual altitude signal to output an altitude perturbation signal;
determining whether the altitude perturbation signal exceeds a second threshold value; and
outputting an indication that the portion of the aircraft is not contacting the surface responsive to determining that the
rate of change in the vertical motion of the aircraft exceeds the first threshold and determining that the altitude perturbation
signal exceeds the second threshold value.

US Pat. No. 9,139,290

AIRCRAFT WEIGHT IDENTIFICATION USING FILTERED TRIM ESTIMATION

SIKORSKY AIRCRAFT CORPORA...

1. A method comprising:
receiving, by a computing device comprising a processor, at least one control input associated with an aircraft;
obtaining, by the computing device, a predicted response to the at least one control input by filtering on a trim position,
wherein the predicted response is based on a model of the aircraft;

obtaining, by the computing device, an actual response of the aircraft to the at least one control input;
comparing, by the computing device, the predicted response and the actual response by subtracting the predicted response from
the actual response;

updating, by the computing device, the model using a correction factor determined in response to the subtracting the predicted
response from the actual response; and

determining, by the computing device, at least one attribute based on the comparison.

US Pat. No. 10,112,697

AIRCRAFT WITH THRUST VECTORING TAIL

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:an airframe having an upper section and a tail section;
a main rotor assembly operably disposed at the upper section and including a main rotor that is rotatable about a rotational axis defined through the airframe;
one or more tail rotor assemblies operably disposed on the tail section and respectively including one or more articulated propellers with thrust vectoring capability that are each independently rotatable about a respective variable rotational axis; and
not more than one controllable wing extending outwardly from a side of the aircraft.

US Pat. No. 9,951,825

MULTI-PLATE CLUTCH

SIKORSKY AIRCRAFT CORPORA...

1. A multi-plate clutch apparatus, comprising:an outer housing having an external surface, a gear being defined by the external surface;
an inner housing arranged within the outer housing;
a multi-plate clutch arranged within the inner housing, the multi-plate clutch being disposed to occupy clutch and non-clutch positions at which rotation of an input shaft is and is not transmitted to an output shaft, respectively;
a drive element disposed about the multi-plate clutch and configured to generate rotational energy, the drive element having a gear element meshingly engaged with the gear defined by the external surface of the housing; and
a linear actuator disposed to convert the rotational energy of the drive element to linear movement by which the multi-plate clutch is controllable to occupy one of the clutch and non-clutch positions.

US Pat. No. 9,803,958

WEAPONS STORES PROCESSOR PANEL FOR AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft weapons control system comprising:
a weapons stores processor panel for receiving input signals from a weapons input;
a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons;
a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight
management system providing control signals to the weapons interface, the flight management system separate from the weapons
stores processor panel; and

a control panel on the weapons stores processor panel, the control panel including a master arm switch for selecting a master
arm position, a safe position and an off position;

wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons,
the weapons interface requiring an enable signal from the weapons stores processor panel to fire a weapon;

wherein when the master arm switch is in the master arm position, the weapons stores processor panel provides power to a weapons
interface controller and the weapons stores processor panel enables generation of the fire signals;

wherein when the master arm switch is in the safe position, the weapons stores processor panel provides power to a weapons
interface controller and the weapons stores processor panel prevents generation of the fire signals;

wherein when the master arm switch is in the off position, the weapons stores processor panel disables power to a weapons
interface controller and the weapons stores processor panel prevents generation of the fire signals.

US Pat. No. 9,778,655

UNMANNED VEHICLE OPERATING MODES

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:
an airframe;
drive elements configured to drive movements of the airframe; and
a computer, including at least one processor, configured to receive flight planning and manual commands and to control operations
of the drive elements to operate in:

first and second safe modes in which the flight planning commands are accepted but the manual commands are refused,
first and second manual modes in which the flight planning commands are refused but the manual commands are accepted, and
an enroute mode and first and second special modes in which the manual commands are refused,
the computer being further configured to only allow mode transitions directly between the first safe mode and the first manual
mode, directly between the second safe mode and the second manual mode, directly between the first safe mode and the second
safe mode and directly between the second safe mode and the enroute mode.

US Pat. No. 9,637,242

TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft, comprising:
an airframe;
a rotor assembly including a first rotor rotatable about a rotor axis in a first direction and a second rotor coaxial with
the first rotor and rotatable about the rotor axis in a second direction opposite the first direction; and

a drive system including plural engines outputting torque and a gearbox assembly to reduce torque produced from one or more
of the engines to a reduced torque and to transfer the reduced torque to the rotor assembly, the gearbox assembly comprising:

an input shaft to input the torque into the gearbox assembly;
an input bevel shaft operably connected to the input shaft to transfer the torque therethrough; and
two gear sets operably connected to the input bevel shaft, each gear set including first and second intermediate shafts,
the first intermediate shaft having a first intermediate idler meshed with a transfer gear of the input bevel shaft and a
first output pinion to transfer the reduced torque to the first rotor, and

the second intermediate shaft having a first intermediate gear meshed with the first intermediate idler and a second output
pinion to transfer the reduced torque to the second rotor.

US Pat. No. 9,638,588

MULTIFUNCTIONAL LOAD AND DAMAGE SENSOR

SIKORSKY AIRCRAFT CORPORA...

13. An apparatus comprising:
at least one processor; and
memory having instructions stored thereon that, when executed by the at least one processor, cause the apparatus to:
obtain at least one prior sample of data with a piezoelectric sensor associated with a structure, the at least one prior sample
being a baseline data point corresponding to no damage to the structure;

obtain at least one sample of load and load path data from the piezoelectric sensor associated with the structure;
compare the at least one sample of data to at least one prior sample of data obtained from the piezoelectric sensor including
determining a change in load magnitude and a change in load path direction between the at least one sample and the at least
one prior sample; and

provide a status of a health of the structure based on the comparison based on load detection and damage detection with the
same piezoelectric sensor.

US Pat. No. 9,617,011

PROBABILISTIC SAFE LANDING AREA DETERMINATION

SIKORSKY AIRCRAFT CORPORA...

1. A method of performing a probabilistic safe landing area determination for an aircraft, the method comprising:
receiving sensor data indicative of current conditions at potential landing areas for the aircraft;
performing feature extraction on the sensor data;
performing geospatial partitioning of the sensor data to subdivide processing of the sensor data into a plurality of cells;
collecting sensor data for the cells over a period of time; and
computing slope and variance feature values of the cells based on the sensor data that are collected over the period of time;
updating, by a processing subsystem of the aircraft, a probabilistic safe landing area map based on comparing extracted features
of the sensor data with a probabilistic safe landing area model, the probabilistic safe landing area model defining probabilities
that terrain features are suitable for safe landing of the aircraft; and

generating a list of ranked landing areas based on the probabilistic safe landing area map.

US Pat. No. 9,452,824

FLY BY WIRE SERVOS WITH INTERNAL LOOP CLOSURE

SIKORSKY AIRCRAFT CORPORA...

1. A servo assembly comprising:
a hydraulic primary servo;
an actuator coupled to the primary servo and configured to drive the primary servo; and
at least one sensor configured to determine a difference between a desired ram position and an actual ram position driving
a spool to perform a loop closure;

wherein the actuator comprises a plurality of electro-mechanical actuators coupled to the primary servo and configured to
drive the primary servo.

US Pat. No. 10,073,455

VEHICLE HEADING ERROR COMPENSATION

SIKORSKY AIRCRAFT CORPORA...

1. A method for controlling an aircraft, comprising:obtaining at least one of longitudinal ground speed and a lateral ground speed of the aircraft;
obtaining a ground-referenced heading of the aircraft;
calculating a heading error based on a difference between the ground-referenced heading and a target heading;
generating a lateral movement error value defining a ground-referenced lateral speed error value based on the heading error, the longitudinal ground speed and the lateral ground speed and the equation: verr=vtgt?v cos(?err?)+u sin(?err), wherein verr is the ground-referenced lateral speed error value, vtgt is a lateral ground speed target value, v is a detected or derived lateral ground speed value, u is a detected longitudinal ground speed value and ?err is a value of the heading error;
generating a lateral movement command signal based on the lateral movement error value to control a ground-referenced lateral speed of the aircraft; and
adjusting a control surface of the aircraft based on the lateral movement command signal.

US Pat. No. 10,053,212

TRANSMISSION FOR COAXIAL MULTI-ROTOR SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A coaxial, dual rotor system comprising:a first rotor assembly disposed at a rotor axis and rotatable thereabout;
a second rotor assembly disposed at the rotor axis radially inboard of the first rotor assembly and rotatable thereabout;
a rotationally fixed static mast disposed radially between the first rotor assembly and the second rotor assembly; and
a transmission including:
a rotor input shaft including a first sun gear and a second sun gear;
a star gear arrangement operably connected to the first sun gear and the static mast to drive rotation of the first rotor assembly about the rotor axis; and
a planetary gear arrangement operably connected to the second sun gear and the static mast to drive rotation of the second rotor assembly about the rotor axis.

US Pat. No. 9,964,960

HOVER ATTITUDE TRIM FOR VEHICLE

SIKORSKY AIRCRAFT CORPORA...

1. A vertical take-off and landing (VTOL) aircraft, comprising:a fuselage, wings extending outwardly from the fuselage to define a wing plane and a prop-rotor operably disposed to generate thrust;
a flight computer; and
controllable surfaces disposed on at least one of the fuselage, the wings and the prop-rotor, the controllable surfaces including cyclically controllable prop-rotor blades, and at least one of spoilers, flaps and ailerons, the controllable surfaces being controllable by the flight computer to position the wing plane in accordance with a predominant local wind direction, the flight computer positioning the cyclically controllable prop-rotor blades to turn the wing plane toward an alignment condition and positioning at least one of the spoilers, flaps and ailerons to decrease a differential value between a target pitch attitude and an actual pitch attitude of the wing plane.

US Pat. No. 9,944,061

PLASMA DETECTION TRACERS FOR PROCESS MONITORING

SIKORSKY AIRCRAFT CORPORA...

1. A method of bonding a member to a substrate, comprising:applying a dye agent to a tracer fiber, wherein the dye agent changes color when exposed to a selected level of plasma radiation;
weaving the tracer fiber into a surface of the member;
exposing the surface to the plasma radiation;
inspecting the tracer fiber for a change in a color of the dye agent; and
bonding the surface to the substrate after the dye agent changes color.

US Pat. No. 9,790,598

REMOVABLE MASK FOR COATING A SUBSTRATE

SIKORSKY AIRCRAFT CORPORA...

1. A method for selectively coating a substrate, comprising:
magnetically coupling a removable mask to at least one surface of the substrate;
forming a coating of a coating material on the at least one surface of the substrate with the magnetically coupled removable
mask using a first bath containing copper plating materials to form a copper plating on the at least one surface of the substrate
and a second bath containing conversion treatment coating materials to form a conductive conversion coat on the copper plating;
and

selectively decoupling the removable mask from the at least one coated surface to reveal a portion of the surface without
the coating.

US Pat. No. 9,771,152

FLEXBEAM TO ROTOR BLADE INTERFACE

SIKORSKY AIRCRAFT CORPORA...

1. A spar for a rotor blade assembly comprising:
a generally hollow, tubular body;
a flexbeam assembly disposed within the body, the flexbeam assembly including a first arm and a second arm separated from
one another at an inboard end and connected at an outboard end;

a spacer extending from at least one surface of the body along a length of the body; and
a hole extending through both the body and the spacer, wherein the hole is configured to align with a through hole in the
flexbeam assembly and the spacer is configured to contact a surface of the flexbeam assembly to create a match fit between
the body and the flexbeam assembly.

US Pat. No. 9,759,252

HIGH SPEED COMPOSITE DRIVE SHAFT

SIKORSKY AIRCRAFT CORPORA...

1. A shaft assembly having a shaft axis and comprising:
one or more axially-arranged plies arranged along the shaft axis including:
a plurality of bundles arranged adjacent to each other in each of the one or more axially-arranged plies, the plurality of
bundles extending in an axial direction of the shaft axis and in parallel with the shaft axis, each bundle of the plurality
of bundles including:

a plurality of carbon fiber strands arranged at least substantially parallel to each other and in the axial direction of the
shaft axis, the plurality of carbon fiber strands formed of an ultra-high modulus carbon fiber material having a tensile modulus
of at least 70 Mpsi; and

one or more wrap strands of glass fiber wrapped around the plurality of carbon fiber strands of each bundle of the plurality
of bundles; and

a volume of resin injected into the one or more axially-arranged plies;
wherein the one or more axially-arranged plies are arranged in a tubular shape about the shaft axis,
further comprising one or more end fittings secured to one or more axial ends of the shaft assembly, the end fitting being
connectible to a drive train.

US Pat. No. 9,688,395

BOUNDARY LAYER INGESTING BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A propeller including a hub and at least one boundary layer ingesting (BLI) blade having a span, the at least one BLI blade
comprising:
a root section having an inboard end connected to the hub and an outboard end, the inboard end of the root section having
a chordal length and a maximum thickness location defined at approximately 25% of the chordal length;

a tip section disposable at a distance from the hub and having a twist; and
a body extending in a spanwise dimension from the outboard end of the root section to the tip section,
the body having a local twist from the root section to about a 70% span location, which is greater than the twist of the tip
section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.

US Pat. No. 9,616,487

RIVETING TOOL

SIKORSKY AIRCRAFT CORPORA...

1. A riveting tool configured to install a plurality of fasteners simultaneously comprising:
a body having a generally central cavity, wherein a strike surface, configured for application of a force thereto by a hammering
tool, is arranged at a first end of the body, and a plurality of contactors extend generally outwardly from a second, opposite
end of the body, each contactor includes an engagement surface configured to contact a surface of an adjacent fastener when
the force is applied to the strike surface, the strike surface being substantially parallel to the engagement surface;

a biasing mechanism arranged within the cavity adjacent an upper cavity surface; and
a dowel positioned within the cavity adjacent to the biasing mechanism, the dowel is positionable within a nut of an adjacent
nut plate and translates within the cavity, wherein when the force is applied to the strike surface, the biasing mechanism
compresses such that each of the biasing mechanism, the dowel, and the nut are received within the cavity.

US Pat. No. 9,580,183

ACTUATION MECHANISM FOR A CONVERTIBLE GAS TURBINE PROPULSION SYSTEM

Sikorsky Aircraft Corpora...

1. A method of powering a rotary-wing aircraft, comprising:
selectively coupling and uncoupling a first power turbine which drives a rotor system and a second power turbine which drives
a secondary propulsion system to change a power distribution between the rotor system and the secondary propulsion system,
wherein exhaust gas from the first power turbine is free to move to the second power turbine when the first and second power
turbines are both coupled and uncoupled, wherein work is extracted from the second power turbine to drive the secondary propulsion
system when coupled to the first power turbine and negligible work is extracted from the second power turbine to drive the
secondary propulsion system when uncoupled from the first power turbine.

US Pat. No. 9,475,576

FLEXBEAM ROTOR ATTACHMENT TO ROTOR BLADE

SIKORSKY AIRCRAFT CORPORA...

1. A rotor blade assembly comprising;
a flex-beam member;
a torque tube surrounding the flex-beam member and extending partially along a rotor blade assembly length;
a rotor blade surrounding the flex beam member extending from the torque tube to a blade tip; and
a connecting assembly to secure the rotor blade and the torque tube at the flex-beam member, the connecting assembly including:
a first connecting member extending at least partially into the rotor blade assembly through the rotor blade from a first
rotor blade side; and

a second connecting member disposed at a second rotor blade side;
wherein a clamping load between the first connecting member and the second connecting member secures the rotor blade and torque
tube to the flex-beam member.

US Pat. No. 9,046,148

ACTIVE FORCE GENERATION SYSTEM FOR MINIMIZING VIBRATION IN A ROTATING SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. A vibration isolation system for reducing vibrations in a rotating system rotatable about an axis of rotation, comprising:
a multiple of masses coaxially disposed about an axis of rotation of a rotating system, each of said multiple of masses radially
offset from said axis of rotation;

a drive system to independently spin each of said multiple of masses about said axis of rotation at an angular velocity; and
a control system in communication with said drive system to control the angular velocity of each of said multiple of masses
to reduce vibrations generated by the rotating system.

US Pat. No. 10,094,514

SELF-CLOSING DRAIN PLUGS WITH REDUNDANT SEALING

SIKORSKY AIRCRAFT CORPORA...

1. A drain plug assembly, comprising:a valve body having a central bore extending between an inlet and an axially opposite outlet, the bore having a seat arranged between the inlet and the outlet of the valve body;
a removable closure having a seated position and an unseated position, the closure being spaced apart from the seat in the unseated position, the closure abutting the seat in the seated position to form an outer seal fluidly isolating the outlet from the inlet;
a poppet arranged in the bore on a side of the seat opposite the outlet and movable between an open position and a closed position, the poppet being spaced apart from the seat in the open position, the poppet abutting the seat in the closed position to form an inner seal fluidly isolating the outlet from the inlet; and
a resilient member arranged between the inlet and the poppet, wherein the resilient member is configured to bias the poppet towards the poppet closed position to fluidly separate inlet from the outlet when the closure is in the seated and unseated positions.

US Pat. No. 9,969,488

AUTOMATIC PROPELLER TORQUE PROTECTION SYSTEM

SIKORSKY AIRCRAFT CORPORA...

1. An aircraft, comprising:one or more main rotors;
one or more propellers comprising blades that are rotatable about a rotational axis, a pitch of each of the blades being controllable;
a flight control computer disposed to control the pitch of each of the blades to reduce propeller blade pitch angles to a pre-defined safe pitch level in an event of an engine failure; and
an override actuator, which, when activated, overrides a reduction of the propeller blade pitch angles by the flight control computer before reaching the pre-defined safe level.

US Pat. No. 9,908,614

CREW SEAT INTEGRAL INCEPTOR SYSTEM FOR AIRCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A system for controlling a trajectory of a vehicle, comprising:
a crew seat with a seat arm;
an inceptor mounted to a portion of the seat arm, the inceptor including a spherical body having vertical, horizontal and
three rotational degrees of freedom for selecting a trajectory of the vehicle, the spherical body including a plurality of
controls for inputting the selected trajectory to the vehicle;

a processor with memory having instructions stored thereon that, when executed by the processor, cause the system to:
select a trajectory for the vehicle in response to a motion of the inceptor along at least one of the horizontal, vertical
and rotational degrees of freedom; and

transmit to the vehicle signals for controlling the trajectory of the vehicle in response to the selecting the trajectory.

US Pat. No. 9,884,680

ELASTOMERIC BEARING SYSTEM MOTION LIMITER

Sikorsky Aircraft Corpora...

1. A tail rotor blade assembly comprising:
a flexbeam;
a torque tube defined at least partially around said flexbeam;
a retainer mounted to said flexbeam;
an elastomeric bearing having an inner race and an outer race defined along an axis, said inner race mounted to said retainer,
wherein said elastomeric bearing includes an outer damper portion adjacent said outer race, an inner snubber portion adjacent
said inner race, and a rigid transition layer between said outer damper portion and said inner snubber portion;

a backing plate mountable to said outer race, said torque tube between said backing plate and said outer race;
wherein said backing plate includes a redundant pivot generally opposite a motion limiter;
wherein said motion limiter is outboard of said redundant pivot; and
wherein a surface of said rigid transition layer contacts a wall of said motion limiter in a retainer disbond condition.

US Pat. No. 9,731,832

TORQUE CONVERTER FOR ROTORCRAFT

SIKORSKY AIRCRAFT CORPORA...

1. A rotary wing aircraft comprising:
an airframe;
a drive system including: a piston engine;
a gearbox operably connected to the engine; and
a torque converter operably connected to the engine via an input shaft and operably connected to the gearbox via an output
shaft, the torque converter including:

an impeller operably connected to the input shaft and rotatable therewith;
a turbine operably connected to the output shaft and rotatable therewith;
a fluid flow system to direct a flow of motive fluid through the impeller and through the turbine to drive rotation of the
output shaft relative to the input shaft, the fluid flow system including a fluid pump and a fluid reservoir for the motive
fluid, the fluid reservoir dedicated to the torque converter and not the gearbox, the fluid flow system independent of the
gearbox and the motive fluid isolated by the fluid flow system for use by the torque converter, the motive fluid urged from
the fluid reservoir by the fluid pump;

wherein the fluid flow system including the fluid reservoir and the motive fluid is isolated from the gearbox, and not integrated
with the gearbox;

a lockup mechanism engagable to urge rotation of the output shaft at an output shaft rotational speed identical to an input
shaft rotational speed; and

a switching module to control an actuation system to urge engagement of the lockup mechanism, the fluid pump operably connected
to the switching module to flow the motive fluid to the switching module, and a hydraulic line connecting the switching module
to the impeller;

wherein the actuation system utilized is the fluid flow system operably connected via the switching module to provide fluid
communication to the lockup mechanism by hydraulic lines to selectively control operation thereof, and the switching module
receives operational commands from a flight control system; and

a rotor assembly operably connected to the drive system.

US Pat. No. 10,112,729

VIBRATION ABSORBING DEVICE FOR FLEXBEAMS

SIKORSKY AIRCRAFT CORPORA...

1. A method of forming a replacement vibration absorbing device comprising:applying a layer of release material to a tool head;
wrapping a plurality of layers of vibration absorbing material over the release material;
applying a border material adjacent the vibration absorbing material;
applying uniform compression to the tool head;
curing the tool head; and
cutting the vibration absorbing material along an edge for removal from the tool head.