US Pat. No. 9,168,996

AIRCRAFT PRESSURIZED CABIN DOOR MADE OF FIBER COMPOSITE

Airbus Helicopters Deutsc...

1. An aircraft pressurized cabin door defining a height direction, a width direction, and a depth direction, the aircraft
pressurized cabin door comprising:
an integral door structure unit made of a fiber composite and including an outer skin and a door framework disposed on an
inner side of the outer skin, the framework including a plurality of edge supports and a plurality of longitudinal supports
that extend in the width direction between the edge supports, such that a plurality of door framework interstices, each delimited
by the inner side of the outer skin, by an edge support and a longitudinal support, are configured in a manner open toward
an inner side of the door;

wherein the door structure unit has at least one outer cover ply and a plurality of inner plies, each inner ply comprising
a bottom, two lateral edge limbs generally transverse to the bottom, and two lateral longitudinal limbs generally transverse
to the bottom and generally transverse to the lateral edge limbs, each inner ply extending continuously in a pan-shaped form,
each lateral edge limb cooperating with an adjacent lateral edge limb to form a strut of one of the plurality of edge supports,
each lateral longitudinal limb cooperating with an adjacent lateral longitudinal limb to form a strut of one of the plurality
of longitudinal supports, wherein each continuous inner ply forms, at an end of the lateral edge limbs and lateral longitudinal
limbs opposed to the bottom, a free-end flange facing away from the outer skin and generally transverse to the struts of the
edge supports and the struts of the longitudinal supports; and

wherein the outer skin is formed by the outer cover ply and the bottoms of the plurality of inner plies.

US Pat. No. 9,058,750

FLIGHT SIMULATOR VIBRATION SYSTEM

Airbus Helicopters Deutsc...

1. A flight simulator vibration system for an aircraft, the system defining three coordinate axes, the system comprising:
a crew seat with a first predefined momentum weight driven by a first electric motor, a second predefined momentum weight
driven by a second electric motor, and a third predefined momentum weight driven by a third electric motor, each respective
electric motor being disposed within a respective motor casing removably retained by a respective flexible stripe,

a flight control stick with a fourth momentum weight driven by a fourth electric motor,
a panel vibration system with a fifth momentum weight driven by a fifth electric motor, and
at least one electronic control circuit configured to individually control the electric motors to provide vibrations about
all three coordinate axes, wherein when the respective flexible stripes are removed the respective motors may be rotated for
tuning and the respective momentum weights may be adjusted or replaced for tuning.

US Pat. No. 9,056,428

MANUFACTURING METHOD FOR HOLLOW COMPONENTS MADE OF FIBER COMPOSITE MATERIALS IN TUBULAR DESIGN, TUBULAR FILM AND MANUFACTURING METHOD FOR A TUBULAR FILM

Airbus Helicopters Deutsc...

1. A manufacturing method for manufacturing a hollow component for an aerospace element, the aerospace element having a variable
cross section and corners and being manufactured by conforming a plastic material preform, the method using a tubular film
and a mould having inner surfaces with corresponding variable cross sections and corners, the method having the following
steps:
a) feeding a plastic material preform in the area of the inner surfaces of the mould, the plastic material preform having
a first fiber layer and a second fiber layer;

b) conforming the plastic material preform to mechanically conform to the inner surfaces of the mould;
c) feeding a tubular film into the mould so that the plastic material preform is positioned between an outer surface of the
tubular film and the mould, the tubular film being unwound from a roll, expanded by pressure and/or a vacuum, and then contoured
by a guide tool before it is fed into the mould in step c) such that its contour in a sectional plane perpendicular to its
longitudinal extension is furnished with an outer contour with a plurality of recesses alternating with a plurality of protuberances
distributed about its circumference and extending in the direction of its longitudinal extension, the tubular film being fed
from an endless roll;

d) expanding the contoured tubular film using pressure and/or a vacuum when the inner surfaces of the mould are joined together,
the expanding of the contoured tubular film being performed without the contoured tubular film having to move along the plastic
material preform, the protuberances contacting the plastic material preform prior to the recesses; and

e) applying a pressure above atmospheric pressure in the contoured tubular film and heating the mould so that the plastic
material preform is adapted to fuse the fiber layers and conform the fiber layers to an inner contour of the mould and an
outer contour of the expanded tubular film.

US Pat. No. 9,359,071

AERODYNAMIC BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER

Airbus Helicopters Deutsc...

1. An aerodynamic blade attachment for a bearingless rotor of a helicopter, comprising:
an airfoil blade having a tip end and a root end forming opposite ends thereof and having a pitch axis from the tip end to
the root end;

a flexbeam;
a control cuff enclosing and extending along at least a predominant portion of the flexbeam; and
a separable junction arrangement between the flexbeam, the control cuff and the root end of the airfoil blade, the junction
arrangement being mechanical between the flexbeam, the control cuff and the root end of the airfoil blade with a removable
main bolt and a removable supporting bolt respectively removable connecting the root end of the airfoil blade and the control
cuff with the flexbeam, the junction arrangement comprising fairing means encompassing the main bolt and the supporting bolt
and the flexbeam, wherein the fairing means are formed with a first circular segment and a second circular segment at a free
end of the control cuff, the root end of the blade having corresponding first and second circular segments, a first center
of the first circular segment being aligned with a central axis of the main bolt, a second center of the second circular segment
being offset from the first center and between the central axis of the main bolt and a central axis of the supporting bolt,
a radius of the second circular segment being greater than a radius of the first circular segment.

US Pat. No. 9,174,728

ELECTRICAL POWERED TAIL ROTOR OF A HELICOPTER

Airbus Helicopters Deutsc...

1. An electrical powered tail rotor assembly of a helicopter comprising:
a tail rotor having multiple blades;
a housing around the tail rotor;
two coaxial permanent magnet synchronous motors that are each provided with a stator and a rotatable component that is coaxial
with respect to the stator, each stator including multiple poles, the synchronous motors being integrated as a torus around
an opening of the housing encompassing the tail rotor;

supply means for supplying electric energy to the synchronous motors; and
blade pitch control means provided at the torus, the blade pitch control means including a gear that is mounted between the
rotatable components of the synchronous motors and that links the blades of the tail rotor to each of the rotatable components.

US Pat. No. 9,216,540

ULTRASONIC WELDING DEVICE AND METHOD OF OPERATING SAID DEVICE

Airbus Helicopters Deutsc...

1. An ultrasonic welding device comprising:
an adapter frame, an ultrasonic horn and a converter, said ultrasonic horn being driven by the adapter frame mounted converter
for ultrasonic welding of workpieces to at least one fixed workpiece on a tooling, said workpieces being particularly preforms,

wherein said at least one fixed workpiece is a fiber reinforced plastics (FRP) component, wherein said ultrasonic horn is
movable towards the workpieces, the ultrasonic horn being centrally inside the adapter frame, and wherein the ultrasonic welding
device further comprises a pick member;

wherein the pick member comprises:
a press pad mounted resiliently to said adapter frame,
passive clamping means located on the press pad for improved adherence of the workpieces when the press pad exerts a pressure
on the workpieces, and

grippers located on the press pad and suitable for the workpieces so that the workpieces are movable to a weld position at
the fixed workpiece by means of control means controlling the coordinates of the ultrasonic welding device relative to the
workpieces and activation means for controlled activation of the pick member and the ultrasonic horn.

US Pat. No. 9,321,526

COMPOUND HELICOPTER

AIRBUS HELICOPTERS DEUTSC...

1. A compound helicopter comprising:
a fuselage with an upper side, a lower side opposed to the upper side, a left hand side, a right hand side, and a transverse
axis extending from the left hand side to the right hand side;

at least one engine disposed on the upper side of the fuselage;
a main rotor mounted to the upper side of the fuselage at the transverse axis, the main rotor being driven by the at least
one engine;

a first fixed wing mounted on the left hand side and a second fixed wing mounted on the right hand side of the fuselage; and
a respective longitudinally oriented propulsion device mounted to each of the fixed wings at a respective tip of each of the
fixed wings, the fixed wings encompassing encompassing each a respective drive shaft from the at least one engine, wherein:

each fixed wing comprises a lower main wing and an upper secondary;
wing, and the upper secondary wing is anhedral;
the upper secondary wing and the lower main wing of each fixed wing are connected to each other within an interconnection
region;

each respective propulsion device is arranged at the respective interconnection region of the respective fixed wing aft of
the transverse axis, the propulsion devices including propellers in pusher configuration, the propellers being arranged aft
of respective trailing edges of the respective fixed wings; and

and the upper secondary wings house the respective drive shafts from the at least one engine.

US Pat. No. 9,453,516

BLADE ROTARY ASSEMBLY WITH AERODYNAMIC OUTER TOROID SPOILER FOR A SHROUDED PROPULSION ROTARY ASSEMBLY

Airbus Helicopters Deutsc...

1. A propulsion rotor assembly for a vehicle, the propulsion rotor assembly being motorized or mechanically driven through
a motion source; the propulsion rotor assembly having at least: a driven rotor system to be rotated longitudinally around
a rotary axis parallel to a length dimension of the propulsion rotor assembly and a stator hollow structure housing the driven
rotor system; the stator hollow structure having a central hub and a hollow duct defining an inside vessel surface; the inside
vessel surface being extending along the longitudinal rotary axis between two longitudinally opposed transverse distal openings;
the driven rotor system being functionally mounted in the inside vessel surface, pivotal on the central hub and having a plurality
of rotor blades; the rotor blades being motorized/mechanically driven by the motion source, so that the rotor blades are rotated
around the rotary axis, when a controlled airflow is required; the rotor blades have an inner shank radially opposed to an
outer tip, with the inner shank being mounted on the central hub, while the rotor blades are locally separated from neighboring
blades by an angular air spacing; characterized in that the propulsion rotor assembly includes:
an inside vessel arrangement fixedly secured in the stator hollow structure in at least one of the transverse distal openings,
the inside vessel arrangement having an enlarged static circumference housing opened towards the outside of the stator hollow
structure; and

an aerodynamic outer toroid spoiler in a shape of a profiled airfoil type; the aerodynamic outer toroid spoiler being shaped
with an outer external surface complementary to the static circumference housing, but smaller than the static circumference
housing; the aerodynamic outer toroid spoiler being pivotally linked and radially secured to each outer tip of the rotor blades,
so that the outer toroid spoiler is: longitudinally upright with a distal opening of the circumference enlarged housing(s),
radially remote from the circumference enlarged housing(s) with the outer external surface facing a corresponding static circumference
housing and distanced from the corresponding static circumference housing by a torus air gap; so that an outer laminar flux
is admitted simultaneously with/in parallel to an inlet inner stream and guided through the torus air gap between the circumference
enlarged housing and the aerodynamic outer toroid spoiler towards the transverse distal opening longitudinally opposed to
the circumference enlarged housing, and the inlet main stream and outer laminar flux are converged to merge together in a
single outlet control airflow.

US Pat. No. 9,475,578

ROTARY WING AIRCRAFT WITH A TAIL SHROUD

Airbus Helicopters Deutsc...


where for all the points Pi (i=1 . . . 5) the following constraints must be fulfilled:
x1 z1?z2?z3; and
z5?z4?z3.

US Pat. No. 9,152,165

COUNTERBALANCED CONTROL STICK SYSTEM

Airbus Helicopters Deutsc...

1. A counterbalanced control stick system for a vehicle, particularly a counterbalanced control stick system for an air vehicle,
comprising:
a shaft with a shaft axis rotationally mounted in a casing;
a joystick with a transversal axis, said joystick being pivotally mounted relative to said rotational shaft axis for angular
movements of said joystick relative to said shaft axis, said joystick being provided with a handgrip section on a first side
of said shaft and an opposed section on a second side opposed to said first side relative to said shaft, said opposed section
of said joystick being linked by resilient means to adjustable fixing points, characterized in that a movable plate is provided,
said movable plate being offset from the joystick and movable relative to said casing and in that the adjustable fixing points
are controlled by means of said movable plate;

at least one angle sensor is provided at the shaft and/or the joystick respectively for detection of any angular moves of
the shaft relative to the casing and/or of the joystick relative to the shaft; and

electronics are provided to which signals generated by the at least one angle sensor are supplied and where the signals are
digitized and differing detected values are harmonized,

wherein a supplemental rotational spring and/or a bent leaf spring is/are associated to the shaft, and wherein a gear pattern
is provided on respective parts of the rotational shaft interacting with the supplemental rotational spring and/or the bent
leaf spring.

US Pat. No. 9,409,643

HELICOPTER WITH CROSS-FLOW FAN

AIRBUS HELICOPTERS DEUTSC...

1. A helicopter comprising:
a fuselage having a roll axis extending longitudinally, and at least one driving unit disposed in the fuselage;
at least one main rotor mounted to the fuselage and drivable by the at least one driving unit to rotate about a yaw axis perpendicular
to the roll axis;

a cross-flow fan housing mounted to the fuselage extending essentially in the direction of the roll axis with an offset relative
to the yaw axis; and

an air inlet for incoming air and an air outlet for outgoing air are provided along at least a part of a circumference of
the fan housing, the air inlet and the air outlet being formed by angularly offset and separate gaps between an inside segment
and an outside segment essentially extending in the direction of the roll axis; and at least one rotatable compressor provided
with a plurality of airfoil blades oriented radially about a fan axis inside the fan housing, the at least one rotatable compressor
being drivable by the at least one driving unit;

wherein operation of the at least one rotatable compressor within the fan housing is configured to produce:
lift oriented from the air inlet in a lift direction opposite to a flow direction of the incoming air due to ingestion of
the incoming air into the at least one rotatable compressor, and

lateral thrust oriented from the air outlet in a lateral thrust direction opposite to a flow direction of the outgoing air
for anti-torque,

wherein the cross-flow fan housing is split into a front section, an aft section and a mid-section, the front section being
closest to the yaw axis, the aft section being distal to the yaw axis and the mid-section being between the front section
and the aft section, the front section, the aft section and the mid-section being separately and independently from each other
pivotable about the fan axis.

US Pat. No. 9,214,088

OBSTACLE INFORMATION SYSTEM OF A HELICOPTER

Airbus Helicopters Deutsc...

1. An obstacle information system for a helicopter with a warning information processor and a display unit of any obstacle
within a predetermined minimum distance d4 with regard to the helicopter, the warning information processor being fed with information related to detected distance
d5 and direction of the at least one obstacle with regard to the helicopter detected by an obstacle sensor system to compute
and prepare the information for presentation on the display unit, the display unit comprising at least an indication area
with two sub-areas, a central circular surface and a concentric ring-shaped area around the circular surface, the circular
surface being used exclusively for alerts, the ring-shaped area being used for both warnings as well as alerts and the repartition
in the indication area of the circular surface and ring-shaped area being dependent on the detected distance d5 of the at least one obstacle with regard to the helicopter, characterized in that coloring is provided at least at a section
of the ring-shaped area with an inner radius rw, rw being the result of a projection gw of the at least one obstacle from a section d3 of a distance scale onto a section d3* of an indication scale, the projection providing a smaller inner radius rw of the colored ring-shaped surface the closer the obstacle is to an alerting distance d1+d2, with d1 being the radius of a concentric inner ring shaped alert zone za, d1+d2 being an inner warning radius and d1+d2+d3=d4 being an outer warning radius of an outer ring shaped warning zone zw.

US Pat. No. 9,527,577

ROTORCRAFT WITH A FUSELAGE AND AT LEAST ONE MAIN ROTOR

Airbus Helicopters Deutsc...

1. A rotorcraft with a fuselage comprising a nose and with at least one main rotor suitable for rotating around a rotor mast
axis, the rotorcraft assuming varying pitch attitudes in operation, and the fuselage being equipped with at least one passive
wing-type aerodynamic device that is adapted for generating independently of the varying pitch attitudes a lift force acting
on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft
against the passive wing-type aerodynamic device wherein the passive wing-type aerodynamic device comprises at least one wing
element that is rotatable relative to the fuselage around an associated rotation axis, the at least one wing element being
adapted to self-adjust its rotational orientation relative to the fuselage by rotating in reaction to the air flow, wherein
the at least one wing element is positioned longitudinally closer to the nose of the fuselage than the rotor mast axis, and
wherein at least one wing element comprises a combined neutral point designating a location, where a derivative of an aerodynamic
pitching moment generated in operation of the rotorcraft is zero with respect to changes in an angle of attack encompassed
between the air flow, that is directed in operation of the rotorcraft against the at least one wing element, and a chord line
of the at least one wing element, wherein the associated rotation axis is arranged relative to the air flow at a position
located upstream of the combined neutral point, if the aerodynamic pitching moment tends to increase the angle of attack.

US Pat. No. 9,254,921

AIR INLET COMBINING A FILTER AND A BYPASS DEVICE FOR USE WITH A TURBINE ENGINE

Airbus Helicopters Deutsc...

1. An air inlet for an engine of an aircraft, the inlet comprising:
a duct for feeding outside air to said engine;
at least one filter and
at least one bypass device allowing said outside air to pass therethrough when said filter is obstructed;
the air inlet being characterized in that said duct, said filter and said bypass device are fastened to a common support,
said support being situated at one end of said duct and being fastenable to the aircraft so that the filter and the bypass
device can be assembled on the support away from the aircraft.

US Pat. No. 9,080,024

HEAT CONTROL SYSTEM FOR CONSOLIDATION ROLLER

Airbus Helicopters Deutsc...

1. A heat control system for a consolidation roller for producing fiber reinforced polymers made of consolidated layers from
a band of at least one resin pre-impregnated flat tape or tow of composite materials formed by a heating system adapted to
emit heat radiation directed towards the band on an application surface, the system comprising the consolidation roller and
a spindle, the consolidation roller being rotatable on the spindle and comprising a surface made of an elastic deformable,
flexible material,
wherein at least one additional roller with thermal control means is provided and the at least one additional roller is pressed
from outside against the surface of the consolidation roller, the at least one additional roller having a contact surface
defined by a contact region between the at least one additional roller and the surface of the consolidation roller, the contact
surface having a generally oval shape.

US Pat. No. 9,511,872

POWER PLANT, AN APPLICATION OF SUCH A POWER PLANT AND A METHOD OF OPERATING SUCH A POWER PLANT

Airbus Helicopters Deutsc...

1. A mobile power plant having an engine together with a main gear box and a free wheel assembly suitable for driving a rotary
wing by means of the main gear box and further having an electric motor-generator, wherein supplemental to the main gear box
there is provided an accessory gear box, an additional freewheel assembly and a pump, the electric motor-generator being on
a first side mechanically connected in series via the additional freewheel assembly and the accessory gear box to the main
gear box in order to be capable of being driven by the main gear box and the electric motor-generator being mechanically connected
on a second side to the pump.

US Pat. No. 9,469,399

SEPARABLE BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER

Airbus Helicopters Deutsc...

1. A separable blade attachment for a bearingless rotor of a helicopter, comprising:
an airfoil blade with a tip end and a root end forming opposite ends thereof;
a flexbeam with an attachment end, the flexbeam being flexible;
a torsion stiff and lead lag stiff control cuff enclosing at least a predominant portion of the flexbeam;
a separable junction arrangement between the attachment end of the flexbeam, the control cuff and the root end of the airfoil
blade, wherein the junction arrangement is mechanical between the attachment end of the flexbeam, the control cuff, and the
root end of the airfoil blade, with removable fasteners respectively removably connecting the root end of the airfoil blade
and the control cuff with the attachment end of the flexbeam, the removable fasteners comprising at least one bolt and wherein
a stiffened link is provided between respective trailing edges of the control cuff and the airfoil blade, the stiffened link
being mounted to the respective trailing edges of the control cuff and the airfoil blade by the removable fasteners and the
stiffened link being push-pull stiff with regard to loads aligned with the trailing edge.

US Pat. No. 9,304,199

OBSTACLE AND TERRAIN WARNING RADAR SYSTEM FOR A ROTORCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. An obstacle and terrain warning radar system for a rotorcraft, the system having a plurality of radar units, said rotorcraft
having at least one main rotor with an axis of rotation, at least two blades, and a rotor head, each radar unit transmitting
a radar beam with a beam width in azimuth ? of at least 5° and a beam width in elevation ? of at least 5°, the elevation direction
being along said axis of rotation of said main rotor, and a zone scanned in azimuth by said radar beam being in a plane perpendicular
to said axis of rotation, the radar system comprising at least two assemblies positioned and fixed mounted in a regular manner
around said axis of rotation directly on said rotor head between said blades, each assembly having at least one radar unit,
each radar unit transmitting a centrifugal radar beam, said radar system scanning the surroundings around said rotorcraft
electronically in elevation with an angular coverage of at least +/?15° and automatically in azimuth with an angular coverage
of 360° during the rotation of the said main rotor.

US Pat. No. 9,267,558

SHAFT MOUNTED ROTOR BRAKE

Airbus Helicopters Deutsc...

1. A rotor brake device for a helicopter having a main rotor, a gear box for rotatably driving a rotatable shaft of the main
rotor, the gear box having a gear box housing with oil inside, the rotor brake device comprising:
at least one braking force absorption element mounted to said rotatable shaft;
a stationary brake actuator mounted to said gear box housing,
a braking force transmission element, said stationary brake actuator actuating said braking force transmission element that
is functionally coupled to the at least one braking force absorption element, so as to exert a braking effect; and

at least one rotor brake deactivation device, wherein the at least one braking force absorption element comprises stationary
lamellas and rotary lamellas interacting with the stationary lamellas, said rotary lamellas and stationary lamellas being
arranged inside of the gear box housing with oil inside, wherein the rotor brake deactivation device is dependent on a pressure
p of oil inside the gear box housing, the pressure being controlled by the rotor speed of the main rotor

wherein the brake deactivation device has a control piston in a control casing forming a control piston chamber, the control
piston chamber connected to an oil supply line providing oil pressure; and

wherein the control casing of the brake deactivation device forms an oil pressure line having a non-return valve and a non-return
spring, wherein the oil pressure line is controlled by a position of the control piston and the non-return valve.

US Pat. No. 9,266,607

COMPOUND HELICOPTER WITH TAIL BOOMS

Airbus Helicopters Deutsc...

1. A compound helicopter with a pair of tail booms comprising:
a fuselage with a cabin inside, a fuselage rear end and a fuselage front end;
a longitudinal roll axis extending through the fuselage rear end and the fuselage front end, the roll axis and a pitch axis
transversal to the roll axis defining an essentially horizontal plane (X, Y);

the pair of tail booms being longitudinal structures arranged respectively symmetric to opposed sides of the fuselage in the
essentially horizontal plane (X, Y) and the tail booms being interconnected with each other a respective boom rear end of
each respective tail boom by means of an essentially horizontal tail plane;

at least one power plant with a plurality of drive lines;
a main rotor mounted onto the fuselage and driven by the power plant,
at least one pair of fixed main wings attached to the opposed sides of the fuselage, and
at least two propulsive devices, the at least two propulsive devices providing thrust and/or anti-torque;
wherein a first respective propulsive device of the at least two propulsive devices is disposed on a port side relative to
the longitudinal roll axis and a second respective propulsion device of the at least two propulsive devices is disposed on
a starboard side relative to the longitudinal roll axis, the first respective propulsion device and the second respective
propulsion device being disposed in the essentially horizontal plane (X, Y),

the at least two propulsive devices are pusher propellers mounted at trailing ends of the tail booms behind the fuselage and
the at least two propulsive devices are driven by the power plant via the drive lines,
wherein the power plant comprises two engines, one of the engines with associated drive lines being arranged in each of the
tail booms.

US Pat. No. 9,114,875

LEAD LAG DAMPER FOR HELICOPTER ROTOR UNIT

Airbus Helicopters Deutsc...

1. A lead lag damper for a rotor unit of a rotary wing aircraft, the rotor unit having a rotor and a hub, the damper comprising:
a first side configured to couple to the hub with a central axis of the first side being generally coaxial with a central
axis of the hub;

a second side spaced from the first side and being opposed to the first side;
linking means at the second side to link the second side to a plurality of blades of the rotor; and
an essentially cylindrical damper body extending between the first side and the second side and comprising an elastomer material,
the lead lag damper being a spring/damping system which is axially preloaded, so that the lead lag damper acts in a homogenous
manner in inplane eigenmodes of the rotor.

US Pat. No. 9,527,574

AIRCRAFT WITH INTEGRATED JETTISON MECHANISM

AIRBUS HELICOPTERS DEUTSC...

1. An aircraft with jettison mechanism, comprising:
an airframe;
at least one door with connection means comprising at least one of a guide arm and a hinge to movably mount the door to the
airframe;

at least one door lock mechanism mounted to the door at an interface of the door with the airframe to releasably lock the
door to the airframe; and

actuation means comprising at least one handle mounted to the door for actuation of the door lock mechanism;
at least one emergency button integrated in and moveable relative to the handle, the emergency button in communication with
the connection means to jettison the door from the aircraft upon actuation by severing all connections of the door to the
airframe;

wherein the handle has a hollow casing, a pin and a spring disposed inside the hollow casing; the pin being mounted to slide
relative to the handle upon actuation of the emergency button against the spring; and the emergency button being for activation
of the pin for completely separating at least one of the guide arm and the hinges of the connection means from the airframe
for jettisoning of the door.

US Pat. No. 9,481,454

LINKING DAMPER SYSTEM FOR A ROTORCRAFT LANDING GEAR

Airbus Helicopters Deutsc...

18. A rotorcraft having a linking system for attaching a cross tube to a skid of a landing gear of the rotorcraft, the linking
system comprising a hinge element, cross tube attaching means suitable for connecting the hinge element to the cross tube
and skid attaching means suitable for connecting the hinge element to the skid, the hinge element in turn comprising:
a cross tube-sided part attached to the cross tube attaching means and a skid-sided part attached to the skid attaching means,
the cross tube-sided part and the skid-sided part being linked by at least one bearing element suitable for allowing a relative
rotation between the cross tube-sided part and the skid-sided part;

a torsion bar spring communicating with the cross tube-sided part and the skid-sided part; and
at least one rotary damper element suitable for dissipating a ground resonance excitation energy when the rotation of the
cross tube-sided part with respect to the skid-sided part occurs,

the skid attaching means comprising first lateral attaching means and second lateral attaching means;
the skid-sided part comprising a first lateral part extending longitudinally along a longitudinal axis, with the first lateral
part being secured to the first lateral attaching means, and a second lateral part extending longitudinally along the longitudinal
axis, with the second lateral part being secured to the second lateral attaching means;

the cross tube-sided part extending longitudinally along the longitudinal axis, with the cross tube-sided part being secured
to the cross tube attaching means, the cross tube-sided part being located longitudinally between the first lateral part and
the second lateral part.

US Pat. No. 9,381,995

ADVANCED PITCH STABILIZER

Airbus Helicopters Deutsc...

1. A rotorcraft comprising a vertical mid-plane, a fuselage, a tailboom, a fin and a pitch stabilizer, wherein the pitch stabilizer
has box configuration suitable for providing stability to the rotorcraft;
the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly
on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises:

one anhedral upper pitch stabilizing means extending transversally in span from an upper inner airfoil to an upper outer airfoil;
and extending longitudinally in chord from an upper leading edge to an upper trailing edge; a chord variation in span being,
between an upper longest airfoil and the upper outer airfoil, a tapered variation, with the chord decreasing from the upper
longest airfoil to the upper outer airfoil,

one dihedral lower pitch stabilizing means extending transversally in span from a lower inner airfoil to a lower outer airfoil,
and extending longitudinally in chord from a lower leading edge to a lower trailing edge; a chord variation in span being,
between a lower longest airfoil and the lower outer airfoil, a tapered variation with the chord decreasing from the lower
longest airfoil to the lower outer airfoil,

one wing tip element extending in elevation between a corresponding upper outer airfoil and a corresponding lower outer airfoil,
wherein, for each pitch stabilizing assembly:
the upper pitch stabilizing means are forwardly offset in a longitudinal direction from the lower pitch stabilizing means
by a longitudinal distance of between 0.5 and 3 times a mean chord of the upper pitch stabilizing means,

the upper pitch stabilizing means are upwardly offset in an elevation direction from the lower pitch stabilizing means by
a vertical distance of between 0.5 and 3 times the mean chord of the upper pitch stabilizing means,

the distance between the vertical mid-plane and a point of the pitch stabilizer furthest from the vertical mid-plane is comprised
between 0.5 times and once a width of the fuselage,

wherein each upper pitch stabilizing means comprise:
an upper inner structural frame,
an upper surface rigidly joined to the upper inner structural frame and located around said upper inner structural frame,
and upper connecting means in turn comprising:
an upper bracket in each upper pitch stabilizing means, rigidly mounted on the upper inner structural frame, and,
a rotational shaft, rigidly attached to the upper bracket and suitable for rotating around a top mount rigidly connected to
the tailboom,

and in that each lower pitch stabilizing means comprise:
a lower inner structural frame,
a lower surface rigidly joined to the lower inner structural frame and located around said upper inner structural frame,
and lower connecting means in turn comprising:
a lower bracket in each lower pitch stabilizing means, rigidly mounted on the lower inner structural frame, each lower bracket
comprising a screw, and,

a lower mount comprising, at each side of the vertical mid-plane, at least two inserts, so that the screw of each lower bracket
can alternatively be inserted in one of the at least two inserts of the corresponding side of the vertical mid-plane, thus
allowing the rotation of the pitch stabilizer around the rotational shaft.

US Pat. No. 9,517,831

ROTARY WING AIRCRAFT AIRFRAME

Airbus Helicopters Deutsc...

1. An airframe for a rotary wing aircraft, the rotary wing aircraft having a longitudinal axis and comprising:
a subfloor structure for supporting cabin floor panels, the subfloor structure having a bottom shell, ribs, main frames and
floor panels, the ribs and main frames extending essentially in planes perpendicular to the longitudinal axis on one side
of the bottom shell and the floor panels being in an essentially horizontal plane essentially parallel to the longitudinal
axis on the same side of the bottom shell as the ribs and main frames and mounted on flat top edges of the ribs and of main
frames; the flat top edges being opposite in position to the bottom shell, the bottom shell having an essentially flat shell
portion including longitudinally oriented sides and two curved lateral shell portions extending integrally from said flat
shell portion along the longitudinally oriented sides and being curved towards respective lateral borders of said ribs and
main frames;

longitudinal support beams along at least a longitudinal section of the subfloor structure along the longitudinal axis, the
longitudinal support beams provided with attachments for the floor panels, the longitudinal support beams being attached to
at least one of the ribs and the main frames and featuring along at least ? of their longitudinal extension a height 2 to
20 times smaller than a corresponding adjacent distance between the floor panel and the bottom shell; and

at least a pair of membrane elements of bulgy shape; each membrane element laterally protruding to the outside of the longitudinal
support beams one each side of the subfloor structure; each membrane element being provided with an upper longitudinal hem
attached to said longitudinal support beams and a lower longitudinal hem attached to the bottom shell; the membrane elements
being attached to the longitudinal support beams for purely two-dimensional loading of the membrane elements.

US Pat. No. 9,213,096

PROXIMITY WARNING SYSTEM FOR HELICOPTERS

Airbus Helicopters Deutsc...

1. A proximity warning system for a helicopter for detection of obstacles and warning against rotor strike by the obstacles,
the helicopter comprising a roof top structure, a main rotor and a main rotor head, the main rotor head having a non-rotating
standpipe on top of the main rotor head, the proximity warning system comprising:
a standard torus-shaped housing mountable to a non-rotating standpipe or fixable on a roof top structure below a main rotor
head, the standard torus-shaped housing being openable and having a joint and associated closure; and

at least two radar units arranged to transmit microwaves and to receive reflections of the microwaves from obstacles, the
at least two radar units being integrated into the standard torus- shaped housing for horizontally scanning an entire environment
of 360° around the helicopter, a respective unit of the at least two radar units operating in at least one fundamental frequency
in a range between 70 GHz and 80 GHz.

US Pat. No. 9,114,588

SKIN-STIFFENER TRANSITION ASSEMBLY, METHOD OF MANUFACTURE AND APPLICATION OF SAID SKIN-STIFFENER TRANSITION ASSEMBLY

Airbus Helicopters Deutsc...

1. A skin-stiffener transition assembly with a skin and two fiber-reinforced fabric preforms for a flange and a composite
gusset filler integrated between said skin and said two fiber-reinforced fabric preforms, said composite gusset filler being
preformed to an essentially polygonal cross section, characterized in that the skin comprises two separate skin layers and
the flange comprises a flange layer, each of said skin layers and said flange layer being provided with cut outs along one
side, at least one of said cut outs being bent relative to at least one adjacent cut out, and said skin layers and the flange
layer being attached to the composite gusset filler with at least one of their cut-outs to one side of the essentially polygonal
cross section of the composite gusset filler and with at least one of their adjacent cut-outs to another side of the essentially
polygonal cross section of the composite gusset filler.

US Pat. No. 9,470,248

FLEXIBLE RESPONSE SECURED MECHANICAL BALANCING FOR MULTIPLE CONTROL ACTUATORS WITH A COMMON OUTPUT

Airbus Helicopters Deutsc...

1. A mechanical balancing device for a fluid-pressure actuating system; the actuating system including first fluid-pressure
connecting means to a first fluid-pressure network and second first fluid-pressure connecting means to a second fluid-pressure
network, the first fluid-pressure network being independent from the second fluid-pressure network and both networks being
connected to the mechanical balancing device; the actuating system having at least a first actuator and a second actuator,
the first fluid-pressure connecting means are for linking and feeding the first actuator with fluid-pressure from the first
fluid-pressure network, while the second fluid-pressure connecting means are for linking and feeding the second actuator with
fluid-pressure from the second fluid-pressure network; the first actuator and the second actuator being mechanically linked
to cooperate for displacing at least a first common output member and a second common output member between two extreme control
positions; the first and second actuators includes respectively a first and second movable piston each severing an extraction
fluid-pressure chamber and a refraction fluid-pressure chamber,
wherein for the fluid-pressure balancing device to provide flexible/continuous force fight compensation for respective first
and second actuators, the fluid-pressure balancing device includes, for each of first/second-extension/retraction chambers
of the first and second actuators, one dedicated fluid-pressure commanded balance valve; a first balance valve being commanded
to balance fluid-pressure from the first fluid-pressure network to a given extension fluid-pressure chamber of the first actuator,
is rigidly coupled by a corresponding coupling rod to a cooperating second balancing valve balancing fluid-pressure from the
second fluid-pressure network to a given extension fluid-pressure chamber of the second actuator; while a third balancing
valve commanded to balance fluid-pressure from the first fluid-pressure network to a given retraction fluid-pressure chamber
of the first actuator, is rigidly coupled by another corresponding coupling rod to a cooperating fourth balancing valve balancing
fluid-pressure from the first fluid-pressure network to a given retraction fluid-pressure chamber of the second actuator;
each fluid-pressure commanded balance valve being arranged to allow relief of differential pressure, directly into a dedicated
return pressure relief line of an associated first fluid-pressure network or an associated second fluid-pressure network;
a locking assembly cooperating with the mechanical balancing device and includes, for each of a pair of first/second balance
valves and third/fourth first balance valves, a fluid-pressure controlled locking device, each locking device having first
and second retainer pins adapted to engage with the corresponding coupling rods thus inhibiting the corresponding pair of
first/second balance valves and third/fourth first balance valves, in case of loss of fluid-pressure in one of the first fluid-pressure
network or the associated second fluid-pressure network.

US Pat. No. 9,415,868

ROTOR BLADE WITH CONTROL FLAP

Airbus Helicopters Deutsc...

1. A rotor blade with an exterior shell extending in a span and chord wise direction and at least one control flap extending
in essentially span wise direction to said exterior shell, particularly a rotor blade with an exterior shell extending in
a span and chord wise direction and at least one control flap extending in essentially span wise direction to said exterior
shell for a main rotor of a helicopter, said at least one control flap projecting in an essentially chord wise direction beyond
said exterior shell, said rotor blade comprising:
at least one blade chamber inside said exterior shell and at least one passage from said at least one blade chamber to said
at least one control flap;

load transmission means in said at least one blade chamber, said load transmission means comprising at least one piling type
housing respectively with one actuator, one flap drive and a longitudinal girder, said at least one piling type housing supporting
centrally said one actuator distal to said longitudinal girder, said flap drive being oriented essentially in said chord direction
and being in driving connection with said actuator and said at least one control flap, said longitudinal girder being fixed
to said exterior shell and extending longitudinally in said essentially span wise direction,

at least one pivot bearing mounted to said longitudinal girder to support said at least one control flap;
at least one bearing at said at least one control flap for connection of said at least one control flap to said at least one
flap drive; and

withholding means for each actuator with orientation essentially in said span wise direction, said withholding means being
respectively fixed at one end to said exterior shell and at another end to each actuator,

wherein said at least one piling type housing comprises at least one upper strap and at least one lower strap oriented essentially
in said chord direction in between said longitudinal girder on one side and the support for said at least one actuator on
another side, each of said upper and lower straps being aligned in chord direction relative to said at least one pivot bearing
and said at least one actuator, and said upper and lower straps being stiff in chord direction and flexible in span wise direction.

US Pat. No. 9,194,285

HYBRID DRIVE AND ENERGY SYSTEM FOR AIRCRAFT

EADS Deutschland GmbH, (...

1. A hybrid drive system for a helicopter, the system comprising:
a first energy generating module comprising an internal combustion engine and a generator configured to be powered by the
internal combustion engine to generate electrical energy;

at least one electric motor for powering a main rotor of the helicopter;
connecting means configured to supply the electrical energy from the generator to the at least one electric motor,
a second electric motor for powering a tail rotor of the helicopter;
a storage unit electrically coupled to the first energy generating module and configured for supplying at least one of the
first electric motor and the second electric motor; and

a tail rotor pivotally supported at a top and a bottom of the tail rotor to be rotatable around a vertical axis of the helicopter
to such an extent that a lateral thrust component of the tail rotor is configured to offset a yawing moment caused by the
main rotor.

US Pat. No. 9,067,350

CONTROLLED CIRCUMFERENTIAL IMPREGNATION DEVICE

Airbus Helicopters Deutsc...

1. A molding device by impregnation of at least one reinforcing layer constituting of a piece to be molded or at least one
reinforcing layer covering a piece, with a resin in liquid form, the device comprising a mold extending around the reinforcing
layer by defining a resin circulation space, an end piece for supplying resin into the circulation space, an end piece for
evacuating surplus resin as well as means for generating a flow of resin in the circulation space, wherein the mold comprises,
a flexible conduit, and means for mechanically deforming the flexible conduit, to shape the circulation space according to
the impregnation parameters, the means for mechanically deforming the flexible conduit being at least in part integrated or
embedded in the material constituting the flexible conduit and comprising at least one displaceable rigid rod, integrated
in the material constituting the flexible conduit, each end of the rigid rod being articulated on a separate mobile arm, the
position of the mobile arms determining the position of the rigid rod and consequently the conformation of the flexible conduit.

US Pat. No. 9,499,276

HELICOPTER WITH ENGINE AIR INTAKES

Airbus Helicopters Deutsc...

1. A helicopter comprising:
a fuselage having an essentially vertical midplane separating a first lateral side and a second lateral side,
at least two engines substantially inside the fuselage,
an air intake for each of the at least two engines,
at least two separate lateral air inlet ports for the at least two engines in the fuselage, the lateral air inlet ports being
arranged on sides opposed to each other relative to an essentially vertical midplane of the fuselage and oriented with their
respective cross section substantially parallel to a forward flight direction of the helicopter, a first air duct fluidly
coupling one of the lateral air inlet ports with one of the engines on the first lateral side, a second air duct fluidly coupling
another of the lateral air inlet ports with another of the engines on the second lateral side, and

at least one frontal air inlet port with a forward portion being provided separate from the lateral air inlet ports, the at
least one frontal air inlet port being located on a gear cowling of the fuselage and being oriented with a cross section of
the frontal air inlet port being substantially perpendicular to a forward flight direction, a third air duct fluidly coupling
the frontal air inlet port with one of the engines on the first lateral side, a fourth air duct fluidly coupling the frontal
air inlet port with another of the engines on the second lateral side,

whereby a straight path for airflow through the at least one frontal air inlet port aligned with the longitudinal airflow
is provided through the third air duct and the fourth air duct to each air intake of the engines, respectively, and two further
separate paths through the separate lateral air inlet ports are provided through the first air duct and the second air duct
to each air intake of the engines, respectively, wherein the first, second, third and fourth air ducts provide separate and
independent airflow pathways to the respective air intakes of the engines such that airflow within each air duct remains separate
from airflow within the other air ducts.

US Pat. No. 9,283,696

MOLDING DEVICE

Airbus Helicopters Deutsc...

1. A molding device for curing of composite components comprising:
a molding die;
heat application means;
sheathing means for sealing the composite components and the molding die off about at least one vacuum chamber; and
vacuum means applying a vacuum to the composite components in/on the molding die via the vacuum chamber, wherein
the heat application means comprise at least one heat pipe integrated into the molding die for heat exchange to the molding
die for thermal conduction to the composite components.

US Pat. No. 9,484,843

ELECTRIC CIRCUIT WITH POWER AMPLIFIER FOR PIEZOELECTRIC ACTUATORS

Airbus Helicopters Deutsc...

1. An electric circuit with one power amplifier for at least two piezoelectric actuators, the at least two piezoelectric actuators:
being in antagonist arrangement connected mechanically in series and being connected electrically with each other through
a first junction point between two first terminals of the piezoelectric actuators;

being operated by the one power amplifier commanded by an input signal of a control circuit for time-variant energizing of
the at least two piezoelectric actuators in push-pull fashion, the power amplifier having a first terminal which is grounded
and a second terminal connected to the first junction point between such first terminals of the piezoelectric actuators;

the electrical circuit further comprising a one-directional diode whose anode is connected to the first junction point and
therefore to the second terminal of the power amplifier and to the first terminals of the at least two piezoelectric actuators;

wherein:
the cathode of the diode is connected to a second junction point to which a first terminal of a first buffer capacitor and
a first terminal of a first static resistor, the first buffer capacitor and the first static resistor being connected in parallel
to each other, are also connected;

the second terminal of the first buffer capacitor and the second terminal of the first static resistor are connected to a
third junction point to which a first terminal of a second buffer capacitor and a first terminal of a second static resistor,
the second buffer capacitor and the second static resistor being connected in parallel to each other, are also connected;

the second terminal of the second buffer capacitor and the second terminal of the second static resistor are grounded;
the third junction point is also connected to a first terminal of an at least one protection resistor, whose second terminal
is connected to the second terminal of a first one of the at least two piezoelectric actuators, with the second terminal of
a second one of the at least two piezoelectric actuators being grounded.

US Pat. No. 9,116,029

OPTICAL LIQUID LEVEL SENSOR HAVING A PLURALITY OF OPTICAL FIBERS

Airbus Helicopters Deutsc...

1. An optical level sensor for detection of a current liquid level inside a tank, the sensor being mounted to the tank, the
sensor comprising: a light source, a light detector with a processing unit, and optical fibers, the optical fibers comprising
each at least one input side, assigned to the light source and reaching from the light source into the tank, and at least
one output side, assigned to the processing unit via the light detector and reaching from inside the container or tank to
the light detector, wherein the optical level sensor also includes:
mounting means for mounting the sensor to a ceiling of the tank; and
a sensor tube attached to the tank and having a housing sealed by sealing means to the tank above the liquid level and a bottom
surface below the liquid level;

the sensor tube being provided with support and guidance elements extending with at least three radially distributed positions
inside the tank and which collect support and guide optical fibers to different heights of the tank, with each optical fiber
having a number of input sides and a number of turns forming sensor heads between two input sides, for a different level;
each optical fiber being guided in its half-length through a corresponding support and guidance element, with the corresponding
support and guidance element bending the fiber in turns forming the sensor heads of a small radius r around at least one corresponding
guideway of the corresponding support and guidance element.

US Pat. No. 9,139,281

AIR VEHICLE WITH A SLIP PROTECTING AND GAS SEALING COMPOSITE FLOOR

Airbus Helicopters Deutsc...

1. An air vehicle having a fuselage and a slip-protecting and gas-sealing composite floor inside the fuselage, the slip-protecting
and gas-sealing composite floor comprising:
at least one elastomer layer, the elastomer layer being cured by thermal treatment and having a top surface and a bottom surface,
the top surface being profiled with shaped protrusions for slip protection, the shaped protrusions being inserted or milled
during the thermal treatment of the elastomer layer, the bottom surface being provided with a cross-linking agent,

at least one upper sandwich layer having a further component and partially thermosetting resin, the upper sandwich layer being
covered by the profiled elastomer layer,

at least one lower sandwich layer having a further component and partially thermosetting resin,
a honeycomb layer sandwiched between the at least one upper sandwich layer and the at least one lower sandwich layer, and
a bottom layer to provide sealing protection of the composite floor.

US Pat. No. 9,592,899

ROTARY WING AIRCRAFT WITH A MULTIPLE BEAM TAIL

AIRBUS HELICOPTERS DEUTSC...

1. A rotary wing aircraft with a longitudinal axis in x-direction comprising at least:
a fuselage forwardly oriented relative to the longitudinal axis with a port side and a starboard side as lateral sides,
a main rotor arranged above the fuselage,
a tail rotor mounted on a tail, the tail being attached to a rearward oriented part of the fuselage, the tail having a rear
end supporting the tail rotor, and

at least one engine for driving at least one of the rotors, the engine being mounted on the fuselage; wherein:
the tail is provided with two beam boom elements extending to the rear end of the fuselage, one of the two beam boom elements
extending to the port side and the other beam boom element extending to the starboard side, a front root end of each of the
two beam boom elements being respectively attached to the corresponding port or starboard side of the fuselage by a front
attachment, the beam boom elements being canted with respect to the longitudinal axis and interconnected to each other at
the rear end of the tail; and

at least one of the front attachments is releasable and at least the other of the front attachments is pivotable, so that
the tail is pivotable about a z-direction, around at least one of the front attachment.

US Pat. No. 9,061,758

NOISE AND PERFORMANCE IMPROVED ROTOR BLADE FOR A HELICOPTER

Airbus Helicopters Deutsc...

1. A noise reduced and performance improved rotor blade for a helicopter, comprising three aerodynamic sections along a blade
span between a leading edge and a trailing edge, with an inner rectangular or tapered section, a blade root for connecting
the blade to a rotor hub rotating about a rotor axis of the helicopter, a middle section adjacent to the inner section and
opposed to the blade root, the leading edge of the middle section being forward swept over a distance along the blade span
and the trailing edge of the middle section being forward swept over a distance along a corresponding span of the blade, and
an outer section between the middle section and a blade tip, the outer section being back swept along a further part of the
span of the blade, the inner section extending from radii R0 to R1, R0 being in a range from R0=0.29·R?14%·R to R0=0.29·R+4%·R and R1 being in a range from R1=0.8·R+10%·R to R1=0.8·R?14%·R, the middle section extending from the R1 to R2 with R2 being in a range from R2=0.875·R+10%·R to R2=0.875·R?10%·R, the outer section extending to the blade tip with a distance R from the rotor axis, the middle section and
outer section having a twist decreasing in a multi-linear or non-linear progression along the span of the rotor blade, wherein
R2 corresponds to a most forward-swept portion of the blade and the trailing edge throughout the outer section is linear.

US Pat. No. 9,266,303

GRID TYPE FIBER COMPOSITE STRUCTURE AND METHOD OF MANUFACTURING SUCH GRID TYPE STRUCTURE

Airbus Helicopters Deutsc...

1. A grid type fiber composite structure with longitudinal stiffening elements oriented in at least two directions, comprising:
a grid of polygon cell modules, each polygon cell module comprising:
two parallel polygon surfaces connected by peripheral surfaces perpendicular to the two polygon surfaces; and
at least three substantially u-shaped ribs, each rib having a transverse web section positioned along one of the peripheral
surfaces and two flat cap sections integral with the transverse web section and each positioned along one of the respective
polygon surfaces, at least one of the two flat cap sections extending only partially along one of the respective polygon surfaces;

wherein a foam core is provided inside of and its peripheral edges are fully encased by the at least three substantially u-shaped
ribs for support of the transverse web sections and the flat cap sections, the foam core being delimited by the two parallel
polygon surfaces and the peripheral surfaces and the foam core being in contact with the transverse web sections and the flat
cap sections of each rib; and

wherein each of the cell modules is preassembled from the foam core and the ribs are made of fiber composite layer;
layers of intersecting strips; and
a skin sheet;
wherein the polygon cell modules are joined together along respective transverse web sections of equal length such that there
is substantially no longitudinal or transversal offset between the adjoining transverse web sections of two cell modules;

wherein the layers of intersecting strips are provided outside the flat cap sections on at least one of the polygon surfaces,
the layers of intersecting strips being aligned with the ribs in one direction of the longitudinal stiffening elements, at
least one of the flat cap sections being allocated between the at least one layer of intersecting strips and the foam core;

wherein the skin sheet is directly attached to the layers of intersecting strips and/or to the flat cap sections and/or to
a base of the foam core; and

wherein the longitudinal stiffening elements are provided by the polygon cell modules in cooperation with the layers of intersecting
strips along the ribs.

US Pat. No. 9,266,304

GRID TYPE ELEMENT OF OPEN POLYGONAL CELLS

Airbus Helicopters Deutsc...

1. A grid type fiber composite structure comprising:
a plurality of open polygon cells arranged in a planar layout and each comprising at least three cell segments, the at least
three cell segments comprising:

a multipartite core being made of foam and comprising at least three core segments, each of the core segments having a substantially
rectangular cross section, an inner planar surface corresponding to a first side of the rectangular cross section, and an
outer planar surface corresponding to a second side of the rectangular cross section that is opposite the first side,

wherein each of the core segments extends principally along a respective inherent longitudinal axis, and
wherein the inner and outer planar surfaces of a core segment are positioned transverse to the inherent longitudinal axis
and perpendicular to the planar layout;

a fiber composite layer sheathing entirely the inner planar surface of each of the multipartite cores; and
a fiber composite layer sheathing entirely the outer planar surface of each of the multipartite cores,
wherein each of the at least three cell segments is pivotably interconnected with at least another one of the at least three
cell segments to form one of the open polygon cells, the cell segments being oriented in at least two different directions,
and the open polygon cells are joined together along respective outer planar surfaces to form a grid;

an essentially planar skin sheet attached to one side of the grid; and
a layer of intersecting strips positioned on the opposite side of the grid from the planar skin sheet, wherein strips in the
layer of intersecting strips cover the cell segments of the open polygon cells along each of the at least two different directions.

US Pat. No. 9,302,446

SKIN-STIFFENED COMPOSITE PANEL

AIRBUS HELICOPTERS DEUTSC...

1. A skin-stiffened composite panel extending essentially along a common plane, said panel comprising:
at least two essentially longitudinal stiffeners arranged distant to each other in said plane, said at least two essentially
longitudinal stiffeners having each at least one base flange;

a skin of a planar outer continuous composite layer and an inner continuous composite layer, the at least two essentially
longitudinal stiffeners being each bonded unilaterally by means of said at least one base flange to one side of the inner
continuous composite layer of the skin, wherein the at least two essentially longitudinal stiffeners have a height a perpendicular
to the skin;

at least two sandwich assemblies in said common plane along each one of the at least two essentially longitudinal stiffeners,
said at least two sandwich assemblies comprising each the planar outer and the inner continuous composite layers and a foam
module, with the foam modules on the same side of the planar outer continuous composite layer as the essentially longitudinal
stiffeners between the inner continuous composite layer and the planar outer continuous layer and the foam modules each having
a height b less than 3.5 mm, perpendicular to the planar outer continuous composite layer, the foam module having a grid-type
structure with openings and flat ribs along first and second angled directions in said plane, the width c of the flat ribs
being at least 5 times larger than the height b of the foam modules, the inner continuous composite layer and the planar outer
continuous layer being connected to each other within the openings of the foam module and along at least two interstices between
the at least two sandwich assemblies for the at least two essentially longitudinal stiffeners.

US Pat. No. 9,242,713

AERODYNAMIC, BLUNT AFT BODY

Airbus Helicopters Deutsc...

1. An aerodynamic blunt aft body of a helicopter fuselage with a longitudinal middle plane, the helicopter fuselage comprising
left hand and right hand side fuselage surfaces essentially parallel to the longitudinal middle plane,
an aft surface between the left hand and right hand fuselage surfaces with an essentially normal alignment of the aft surface
to the longitudinal middle plane, and

at least two stakes provided along the aft surface and/or the respective left hand and right hand side fuselage surfaces as
an essentially mirrored image of each other with respect to the longitudinal middle plane, wherein each respective strake
is defined by:

an upper plane normal to the longitudinal middle plane and passing through a junction between the aft surface and a tail boom,
a lower plane normal to the longitudinal middle plane and being placed at 10% of the helicopter width above the lowest horizontal
station of the fuselage,

a first intersection line defined by a respective first set of points between the upper plane and the lower plane, wherein
at the respective first set of points, local tangents to the respective surface lying in a horizontal plane are inclined at
an angle of 15° relative to the central plane; and

a second intersection line defined by a respective second set of points between the upper plane and the lower plane, wherein
at the respective second set of points, local tangents to the respective surface lying in a horizontal plane are inclined
at an angle of 60° relative to the central plane;

each respective strake being defined within a respective bounding box with a height of 13% (+/?7%) offset relative to the
fuselage width

with a two or three dimensional spline towards the aft surface inside the first and second intersection lines.

US Pat. No. 9,586,670

WINDSHIELD MOUNTING ASSEMBLY

Airbus Helicopters Deutsc...

1. A windshield mounting assembly, comprising:
a windshield that is adapted to be arranged on an associated vehicle frame, the windshield comprising at least one peripheral
edge that is provided with at least one lateral recess notched into the at least one edge;

at least one mounting frame that is attached to the windshield for mounting of the windshield to the associated vehicle frame,
the at least one mounting frame comprising at least one fastener receiving opening that is aligned with the at least one lateral
recess to receive an associated frame fastener for fastening the mounting frame to the associated vehicle frame; and

a bonding interface that is arranged at least partially between the at least one edge of the windshield and the at least one
mounting frame, the bonding interface directly bonding the at least one edge of the windshield to the at least one mounting
frame.

US Pat. No. 9,623,950

FUSELAGE AIRFRAME

AIRBUS HELICOPTERS DEUTSC...

1. A fuselage airframe of a helicopter comprising a subfloor compartment for a fuel tank, encompassed by a concave cover shell,
standard frames and a floor panel covering the subfloor compartment above the concave cover shell, wherein at least one differential
frame is mounted to the concave cover shell, the at least one differential frame being perpendicular and symmetric with regard
to a longitudinal axis and having an upper section above the floor panel and a lower section below the floor panel and respectively
lateral frame root regions merging the upper and lower sections, the at least one differential frame partitioning the subfloor
compartment between the standard frames, wherein the lower section of the at least one differential frame has a web with variable-heights
with respect to the cover shell between a minimum height at the longitudinal axis and a maximum height at the lateral frame
root regions, and wherein at least one transversal beam is provided, bridging the entire web portion of the lower section
with the variable-height of the at least one differential frame and being hingedly attached at its both lateral ends to the
lower section of the at least one differential frame by means of at least one bolt.

US Pat. No. 9,598,028

RACEWAY FOR FASTENING, GUIDING AND/OR PROTECTING ELECTRIC CABLE MEANS

Airbus Helicopters Deutsc...

1. A raceway of at least two channel modules for fastening, guiding and/or protecting an electric cable along or on top of
at least one structural part, particularly along or on top of at least one structural part of an aircraft, the channel modules
comprising:
essentially longitudinal channel sections each with a base wall integral with essentially parallel side walls, the base wall
and the side walls providing an open end at both ends of each of the at least two essentially longitudinal channel sections,
the at least two essentially longitudinal channel sections being movable telescopically into one another at the open ends
by means of complementary male and female elements and each of the essentially longitudinal channel sections is provided with
at least one fixation hole wherein:

the male element projects from a central part of an open end of one essentially longitudinal channel section and the female
element is spared from another central part of the open end of an opposed essentially longitudinal channel section;

the essentially longitudinal channel sections are made of thermoplastic material; and
the at least one fixation hole is inside each one of the channel sections through the base wall of each essentially longitudinal
channel section,

characterized in that pairwise slots are provided inside the channel sections respectively next to each of the side walls
through the base wall to a clearance in the base wall, the pairwise slots and the clearance forming an opening passage for
a cable tying ring.

US Pat. No. 9,718,542

BLADE ATTACHMENT FOR A BEARINGLESS ROTOR OF A HELICOPTER

AIRBUS HELICOPTERS DEUTSC...

1. A blade attachment for a bearingless rotor of a helicopter, comprising:
an airfoil blade having a tip end and a root end forming opposite ends thereof and having a pitch axis from the tip end to
the root end;

a flexbeam including a flexbeam body and a fork-shaped flexbeam head at an end of the flexbeam body, the flexbeam body being
flexible;

a control cuff enclosing and extending along at least a predominant portion of the flexbeam;
a separable junction arrangement between the flexbeam head, the control cuff and the root end of the airfoil blade, wherein
the junction arrangement is mechanical between the flexbeam head, the control cuff and the root end of the airfoil blade with
removable fasteners respectively removably connecting the root end of the airfoil blade and the control cuff with the flexbeam
head, the removable fasteners comprising a main bolt and a supporting bolt both arranged lying perpendicular to the lead-lag
pivoting plane of the airfoil blade and being asymmetric with regard to the pitch axis of the airfoil blade;

the airfoil blade having a leading edge and a rear edge, and the control cuff having a C-shaped profile in a plane perpendicular
to the pitch axis of the airfoil blade, the C-shaped profile enclosing the airfoil blade, the C-shaped profile having a closed
portion at the leading edge of the airfoil blade and a pair of rear portions towards the rear edge of the airfoil blade, the
main bolt and the supporting bolt of the removable fasteners passing through the pair of rear portions of the control cuff.

US Pat. No. 9,725,180

SHORT TERM, AUTONOMOUS, ELECTRICAL POWER SUPPLY SYSTEM

AIRBUS HELICOPTERS DEUTSC...

1. An emergency short term, autonomous, electrical power supply system, the system comprising:
an emergency actuator with an electrical motor;
an electrical generator for driving the electrical motor of the emergency actuator;
a turbine in driving engagement with the electrical generator;
a gas generator of combustible, fluidic energy and/or gas generating chemicals;
a fluid line from the gas generator to the turbine;
an emergency control unit; and
an igniter arranged inside the gas generator and controlled by the emergency control unit;
wherein the emergency actuator is linked to a door via a support arm.

US Pat. No. 9,751,623

FLEXBEAM UNIT FOR A HINGELESS OR A HINGE AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam
elements that define a predetermined number of torsion elements and a ring-shaped connection zone for attachment to a rotor
hub associated with a rotor shaft of the multi-blade rotor, each flexbeam element passing the ring-shaped connection zone
in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of the predetermined
number of torsion elements, wherein each flexbeam element overlaps at least one in a circumferential direction of the ring-shaped
connection zone immediately following flexbeam element and is overlapped by at least one in the circumferential direction
of the ring-shaped connection zone immediately preceding flexbeam element, wherein each flexbeam element comprises at least
one lath-shaped beam member, and wherein the at least one lath-shaped beam member of each flexbeam element comprises at least
one lateral projection projecting into the ring-shaped connection zone and defining at least one attachment point for attachment
of the flexbeam element to the rotor hub.

US Pat. No. 9,637,089

WINDSHIELD WIPER SYSTEM

AIRBUS HELICOPTERS DEUTSC...

1. A windshield wiper system for rotary wing aircrafts with a windshield having a curved surface and an oscillating gear drive
with a central park position, the system comprising:
two wiper arms and wiper blades with lips, the wiper blades being mounted by means of the wiper arms to the oscillating gear
drive for oscillation across the windshield about an oscillatory axis,

the windshield and the wiper blade lips have a frictional coefficient (?) therebetween,
the wiper blades being mounted to the at least one wiper arm distal to oscillatory axis and defining in the central park position
a longitudinal axis along the curved surface of the windshield, and the at least one wiper arm in the central park position
being aligned with the longitudinal axis; wherein

the two wiper blades each with a wiper blade fit bolt, bearing bushes, a prolongation fitting and a rocker are provided, the
two wiper blades being mounted rotatable about a wiper blade rotation axis, perpendicular to the oscillatory axis and the
longitudinal axis, the wiper blade rotation axis, being defined by a center line through the wiper blade fit bolts mounted
opposed to each other on the two wiper blades being essentially parallel with a distance (a) to each other, the rocker rotatable
attaching each of the two wiper blades by means of a respective one of the wiper blade fit bolts, and the prolongation fitting
rotatable attaching the rocker to the wiper arms, a rocker fit bolt defining a rocker rotation axis in a plane defined by
the oscillatory axis and the longitudinal axis with an inclination angle ? to the outer surface of the windshield in the central
park position providing a distance (b) direct under the wiper blades rotation axis between the windshield and the rocker rotation
axis perpendicular to the windshield in the central park position fulfilling


US Pat. No. 9,868,419

WINDSHIELD WIPER SYSTEM

AIRBUS HELICOPTERS DEUTSC...

3. A windshield wiper system for a vehicle having a windshield with an outer curved surface, the windshield wiper system comprising:
a pair of wiper arms connected at a first end to an oscillating gear drive for oscillation across the windshield about an
oscillatory axis of the gear drive, wherein longitudinal axes of the wiper arms are generally perpendicular to the oscillatory
axis of the gear drive:

a prolongation fitting mounted to the pair of wiper arms at a distal end opposite the gear drive, the prolongation fitting
mounted to rotate about a prolongation rotation axes oriented at an inclining angle that is inclined between 45° and 135°
relative to the longitudinal wiper arm axes; and

a flexible wiper blade rotatably mounted to the prolongation fitting with a wiper blade holder, wherein the wiper blade is
rotatable about a wiper blade rotation axis being substantially tangential to the outer curved surface of the windshield and
generally perpendicular to the oscillatory axis and perpendicular to the longitudinal wiper arm axes,

wherein the wiper blade defines a longitudinal extension for contacting the outer curved surface of the windshield, and when
the gear drive is in a park position, the longitudinal wiper arm axis is aligned with the longitudinal extension of the wiper
blade and is positioned along a central region of the windshield,

wherein as the wiper arms oscillate away from the park position, rotation of the prolongation fitting about the prolongation
rotation axis and rotation of the wiper blade about the wiper blade rotation axis allow the longitudinal extension of the
wiper blade to maintain contact with the outer curved surface of the windshield.

US Pat. No. 9,623,963

PARTLY CRUCIFORM FLEXBEAM AND METHOD OF MANUFACTURING SUCH A FLEXBEAM

AIRBUS HELICOPTERS DEUTSC...

1. A partly cruciform flexbeam of a bearingless main rotor system of a helicopter with a hub drive and an airfoil blade, said
partly cruciform flexbeam comprising:
a flexbeam head with a flat bearing laminate at one end, the flexbeam head being adapted for releasable connection to the
airfoil blade;

a root end, the root end being opposed to the flexbeam head, the root end being adapted for releasable connection to the hub
drive, and

a flexbeam body between the flexbeam head and the root end, the flexbeam body being torsion soft with a substantially cruciform
cross section, the substantially cruciform cross section of the flexbeam body comprising bars and fillets, the bars being
integral with and essentially perpendicular to the fillets and the bars being in line with the flexbeam head, the flexbeam
body being assembled along the respective bars and fillets to the substantially cruciform cross section with separations at
least along the fillets, wherein

the fillets and the bars include a plurality of rovings, the plurality of rovings extending from at least beyond the separations
along the fillets of the flexbeam body and along the flexbeam head, and

at least two L-shaped integral tissue layers extending from in between of the flexbeam body up to an entire width of the flexbeam
head with the rovings in between at the flexbeam head, wherein the at least two L-shaped integral tissue layers are alternating
with the rovings of the flexbeam head and/or with supplemental rovings.

US Pat. No. 9,731,831

AIRCRAFT WITH AN AIR INTAKE FOR AN AIR BREATHING PROPULSION ENGINE

AIRBUS HELICOPTERS DEUTSC...

1. An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum
fuselage width (AW) determined in the region of the at least one air breathing propulsion engine and comprising at least one
front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion
engine at least partly,
the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal
axis of the at least one air breathing propulsion engine by a predetermined cowling offset (W) to define a dynamic air intake
through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation,

the dynamic air intake defining an at least partly funnel-shaped air duct towards an engine integrated air inlet and being
provided with at least one air-permeable engine protection member that is adapted to clean the intake air stream upstream
of the engine integrated air inlet in an associated protection mode,

the at least one air-permeable engine protection member being arranged transverse to the at least one front fuselage cowling
with a predetermined protection inclination angle (?),

wherein the dynamic air intake comprises an outer intake cover that extends from the at least one rear fuselage cowling in
a direction opposed to the engine integrated air inlet, the outer intake cover defining an outer scoop of the at least partly
funnel-shaped air duct, and

wherein the outer intake cover defines a cover front edge and that the at least one air-permeable engine protection member
defines a protection leading edge and a protection trailing edge, the protection leading edge being arranged, in the associated
protection mode, upstream of the cover front edge at the at least one front fuselage cowling and the protection trailing edge
being arranged, in the associated protection mode, downstream of the cover front edge at the at least one rear fuselage cowling.

US Pat. No. 9,688,381

SUBFLOOR STRUCTURE WITH AN INTEGRAL HULL FOR A ROTARY WING AIRCRAFT

Airbus Helicopters Deutsc...

1. A subfloor structure for a rotary wing aircraft having an airframe extended along an anteroposterior plane, including and
delimiting the subfloor structure,
the subfloor structure comprising:
an integral subfloor bowl hull made of a U-shaped one-piece having material and structural continuity and jointlessly defining
at least a bottom central portion, two lateral transition regions and two upward web portions, and two upper external extensions;
the upward web portions integrally extending from the bottom central portion to form two longerons for the subfloor structure
extending at least locally along a longitudinal axis, the bottom central portion being delimited transversally by the two
upward web portions, the two upward web portions being integrated to the integral subfloor bowl hull together with the two
lateral transitional regions; the lateral transition regions being opposed one to the other relatively to the anteroposterior
plane, each transition region being continuously merged with the bottom central portion and one of the two upward web portions;

at least a pair of crossbeams defined by inner and outer ribs and at least locally extending along a transverse direction
orthogonal to the anteroposterior plane;

at least a pair of outer side shells extending outward aside the bottom central portion and being attached to the integral
subfloor bowl hull in the vicinity of the lateral transition regions; and

floor panels defining a floor surface at least locally perpendicular to an elevation direction of the anteroposterior plane;
wherein the integral subfloor bowl hull and the at least a pair of outer side shells provide an outer bottom shell for the
subfloor structure;

wherein the two upward web portions and the at least a pair of crossbeams provide a construction framework for the subfloor
structure;

wherein the two upper external extensions each laterally extend from the upward web portions as a planar surface parallel
to the floor surface, each of the upward web portions having a transitional location rigidly attached to the corresponding
upper external extension, each transitional location being located proximal a top end portion of the corresponding upward
web portion; and

wherein the planar surface of each of the two upper external extensions extends outwardly and continuously from a respective
upward web portion to a respective outer side shell for direct connection therewith, the planar surface of each of the two
upper external extensions extending longitudinally across at least the pair of crossbeams.

US Pat. No. 9,758,245

ROTOR DRIVE SYSTEM

AIRBUS HELICOPTERS DEUTSC...

1. A rotor drive system of a tail rotor of a helicopter, the rotor drive system comprising:
a stator and a rotor, the rotor being mounted to the stator with a rotatable central carrier and rotor blades radially attached
to the rotatable central carrier, the rotor blades defining one rotation plane with a radial central axis of each of the rotor
blades and each of the rotor blades being pivotable about their respective radial central axis for variation of blade pitch,

drive means for the rotor, and
pitch control means for the pivotable rotor blades wherein along at least one blade radius at least one permanent magnet is
fixed on each rotor blade and a plurality of electromagnets on the stator is provided coaxially on at least one stator radius
to allow inductive interaction between the plurality of electromagnets and the at least one permanent magnet on each rotor
blade, the at least one permanent magnet offset from the radial central axis of each rotor blade in a direction perpendicular
to the rotation plane for individual pitch control of each of the rotor blades by individual control of electric supply to
each of the electromagnets.

US Pat. No. 10,066,430

SLIDING CLOSING ELEMENT, IN PARTICULAR A SLIDING DOOR OR A SLIDING WINDOW, FOR A SLIDING CLOSING ELEMENT ARRANGEMENT OF A VEHICLE, IN PARTICULAR OF AN AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A sliding closing arrangement comprising:at least one rail adapted for slidably supporting a closing element;
a fail safe sliding arm assembly comprising:
a bogie support arm;
a bogie assembly having at least one guide roller for rolling along
a safety arm defined by a connector beam having a mounting plate and a safety retainer extending perpendicularly from the connector beam, the mounting plate rigidly and removably attaching to the closing element with fasteners,
a rail reception gap defined between the bogie assembly and the safety retainer, the rail reception gap receiving the at least one rail;
wherein the safety arm retains the fail safe sliding arm assembly on the at least one rail in case of a failure of the bogie support arm.

US Pat. No. 9,745,065

DEVICE FOR PROTECTING AN INDIVIDUAL SITTING ON A SEAT, A SEAT, AND A VEHICLE

AIRBUS HELICOPTERS, (FR)...

1. A protection device for protecting an individual held on a seat with the help of a harness that has a left shoulder strap
and a right shoulder strap, the protection device comprising:
a set of inflatable protection members including a neck airbag and left inflatable lateral means and right inflatable lateral
means, the left inflatable lateral means having a left lower airbag and a left upper airbag, the right inflatable lateral
means having a right lower airbag and a right upper airbag, each upper airbag overlying a lower airbag in an elevation direction;

a C-shaped inflatable lower pocket provided with a lower base forming the neck airbag and two lower lateral branches respectively
forming the left lower airbag and the right lower airbag for positioning on a chest of the individual, the lower base including
an orifice for admitting an inflation fluid; and

a C-shaped inflatable upper pocket provided with an upper base forming a head airbag and two upper lateral branches extending
longitudinally and forming respectively the left upper airbag and the right upper airbag, each upper lateral branch having
at least one longitudinal internal wall so as to provide at least two tubes in each upper airbag, the upper pocket being in
fluid flow communication with the lower pocket, the upper pocket being secured at least in part to the lower pocket, so that
each upper airbag of an inflatable lateral means is secured at least in part to the lower airbag of the inflatable lateral
means;

wherein the lower pocket has a lower wall and the upper pocket has an upper wall, the lower wall being secured in part to
the upper wall by two joint areas per inflatable lateral means, the protection device further comprising a left path and a
right path being provided respectively between the left lower airbag and the left upper airbag and between the right lower
airbag and the right upper airbag in order to enable the shoulder straps to pass, the left path being defined between the
two joint areas of the left inflatable lateral means and the right path being defined between the two joint areas of the right
inflatable lateral means.

US Pat. No. 9,845,154

EXTERNAL LOAD MASS ROPE OF A ROTORCRAFT

Airbus Helicopters Deutsc...

1. An external load mass rope for attachment to a cargo hook device of a rotorcraft that comprises at least one first cargo
hook and at least one second cargo hook, the external load mass rope comprising at least one first rope leg and at least one
second rope leg, wherein the at least one first rope leg is configured for attachment to the at least one first cargo hook
and the at least one second rope leg is configured for attachment to the at least one second cargo hook, wherein at least
one third rope leg is connected to the at least one first rope leg and the at least one second rope leg such that the at least
one first, second and third rope legs define a Y-rope, the at least one third rope leg comprising an external load mass interface
for attachment to an external load mass that is to be carried by the rotorcraft in operation, wherein the first rope leg comprises
a first length adjustment unit in-line with the first rope leg and that is adapted to shorten or lengthen the first rope leg
in flight operation of the rotorcraft on the basis of associated operating parameters, and wherein the second rope leg comprises
a second length adjustment unit in-line with the second rope leg and that is adapted to shorten or lengthen the second rope
leg in flight operation of the rotorcraft on the basis of the associated operating parameters, the first and second length
adjustment units defining a length adjustment device;
wherein the external load mass is deflected in forward flight direction or backward flight direction of the rotorcraft in
operation by an associated external load mass deflection angle; and

wherein the cargo hook device is configured as a double cargo hook arrangement defining a forward cargo hook attachment point
and an aft cargo hook attachment point, the first rope leg of the external load mass rope being a forward leg configured for
attachment to the forward cargo hook attachment point using the at least one first cargo hook and with the first length adjustment
unit being adapted to shorten or lengthen the forward rope leg in flight operation, the second rope leg of the external load
mass rope being an aft leg configured for attachment to the aft cargo hook attachment point using the at least one second
cargo hook and with the second length adjustment unit being adapted to shorten or lengthen the aft rope leg in flight operation.

US Pat. No. 9,714,579

CONNECTION JOINT FOR ATTACHING AN AIRFOIL BLADE TO A HELICOPTER'S BEARINGLESS MAIN ROTOR

AIRBUS HELICOPTERS DEUTSC...

1. An airfoil blade comprising:
a root end;
a tip end; and
a body extending between the root end and the tip end with a pitch axis extending from the root end to the tip end, wherein
the root end defines a chordwise axis extending perpendicular to the pitch axis and includes a first fastener hole and a second
fastener hole aligned along the chordwise axis, the first and second fastener holes extending through the root end of the
airfoil blade from a top surface of the root end of the airfoil blade to a bottom surface of the root end of the airfoil blade,
the first and second fastener holes being configured to receive first and second fasteners, respectively, to couple the root
end to a control cuff and a flexbeam head, the first fastener hole having a first diameter and being spaced a first distance
from the pitch axis, the second fastener hole having a second diameter and being spaced a second distance from the pitch axis,
the first distance being different from the second distance, the first diameter being larger than the second diameter, wherein
the first fastener hole is between the leading edge and second fastener hole.

US Pat. No. 9,862,475

DRAINAGE END CAP DEVICE FOR DRAINING FLUID FROM A HOLLOW SPACE IN A VEHICLE

Airbus Helicopters Deutsc...

1. A drainage end cap device for an aircraft configured to drain fluid from a hollow space in the aircraft, the device comprising:
a mounting unit having a carrier defining an opening, the carrier defining a first mounting face configured to durably mount
on an outer surface of an outer shell of the aircraft with the opening arranged congruent with a drainage opening of the aircraft,
the carrier defining a second mounting face opposite to the first mounting face, the second mounting face defining a mounting
plane, the mounting unit having a retainer extending peripherally around and away from the second mounting face and forming
a guide groove between the retainer and the second mounting face; and

a drainage cap removably mounted to the mounting unit, the drainage cap having a housing defining a fluid inlet intersecting
a cap mounting face and a fluid outlet intersecting a rear face, the fluid inlet and fluid outlet interconnected by a drainage
channel, the cap mounting face configured to mate with the second mounting face of the mounting unit, the cap mounting face
surrounded by a peripheral collar sized for receival by the guide groove of the mounting unit, wherein the fluid inlet intersects
the cap mounting face, and wherein the housing is aerodynamically shaped over a longitudinal extension of the housing from
the fluid inlet in a direction of the fluid outlet and the rear face;

wherein the drainage channel is zigzagged over the longitudinal extension of the housing such that the drainage channel has
four wall segments extending substantially perpendicular to the mounting plane of the mounting unit and defining an L-shaped
channel section configured such that fluid within the hollow space drains via the drainage channel to outside the aircraft
and such that spray water ingressing into the drainage cap via the fluid outlet from outside the aircraft strikes at least
one of the four wall segments and is prevented from traversing the drainage channel and reaching the hollow space of the aircraft.

US Pat. No. 9,873,512

AIRCRAFT FRAMEWORK STRUCTURE WITH INTEGRAL VENTILATION AIR DUCT

Airbus Helicopters Deutsc...

18. A rotary wing aircraft comprising:
a cockpit framework structure provided by a plurality of frame beams integrally formed as a unitary, load-bearing, complex
curved geometrical structure comprising fiber reinforced polymers in one composite piece, wherein at least one of the plurality
of frame beams is hollow such that an inner wall surface defines an integrated air duct, the integrated air duct having an
inlet configured to receive ventilation air from a helicopter ventilation system, the duct extending from the inlet to a first
outlet with a first static nozzle, a second outlet with a second static nozzle, and a third outlet with an adjustable nozzle
and an associated internal scoop, wherein a condense water outlet is defined by the at least one of the plurality of frame
beams and intersects the duct to provide a drain, and wherein an outlet cover is associated with the condense water outlet
and positioned within the duct;

a main window supported by the cockpit framework structure;
a secondary window supported by the cockpit framework structure;
a door frame connected to and supported by the cockpit framework structure; and
a subfloor supported by the cockpit framework, the subfloor having at least one longitudinal frame integrated air duct connecting
an air-generating ventilation system to the integrated air duct of the cockpit framework and providing ventilation air thereto;

wherein the first outlet is positioned adjacent to the main window such that the first static nozzle is configured to direct
ventilation air towards the main window;

wherein the second outlet is positioned adjacent to the secondary window such that the second static nozzle is configured
to direct ventilation air towards the secondary window; and

wherein the third outlet is positioned adjacent to a presumed pilot location such that the adjustable nozzle is configured
to direct ventilation air towards the presumed pilot location.

US Pat. No. 10,035,590

SHROUDED ROTARY ASSEMBLY FROM SEGMENTED COMPOSITE FOR AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A manufacturing method for making a stator hollow structure for a shrouded propulsion rotary assembly for an aircraft, the stator hollow structure comprising:a central hub casing for a stator gearbox of the stator hollow structure, an external hollow duct surrounding the central hub casing and between the central hub casing and the external hollow duct, at least three profiled guide vanes, each profiled guide vane forming a fixed blade supporting the central hub casing; each profiled guide vane having a radial shank location and a radial tip location; each radial shank location being fixedly attached to the central hub casing and each radial tip location being fixedly attached to the external hollow duct;
wherein the manufacturing method comprises:
preparing at least three composite angular segments separately from components of composite material, so that each composite angular segment comprises: a core arched section of the central hub casing, a peripheral rim section of the external hollow duct and, between the core arched section and the peripheral rim section, a pair of angularly opposed sliced portions respectively for one profiled guide vane;
securing the at least three composite angular segments together once prepared to form a unitary piece encompassing an overall shape of the stator hollow structure; and
reinforcing at least one of the three composite angular segments with a honeycomb band incorporated in the core arched section and/or the peripheral rim section, for stabilization purposes of the stator hollow structure.

US Pat. No. 9,975,630

ROTOR SYSTEM OF A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A rotor system of a rotary wing aircraft comprising:a rotor mast with a longitudinal rotation axis, a rotor hub coaxially arranged at the rotor mast,
at least four, angularly generally even distributed rotor blades;
swash plate struts mounted to each of the rotor blades for pitch and subsequently flap control,
the rotor blades being respectively pairwise mounted lag-stiff and flap-stiff to each other with zero offset to the rotor hub for rotation about the rotation axis in a generally common rotor plane, and connected opposed to each other and generally symmetrical with regard to the rotor hub, wherein:
the rotor hub is provided with a circular hollow bearing having at least one further bearing inside the circular hollow bearing, respectively arranged in line with the rotation axis,
a first pair of the rotor blades is mounted by means of a first yoke on the circular hollow bearing and pivotable about a first flap axis generally perpendicular to the rotation axis, and
at least a second pair of the rotor blades is mounted by means of a second yoke that extends through the circular hollow bearing and is pivotable on the at least one further bearing about a second flap axis generally perpendicular to the first flap axis and the rotation axis, and independently of the first pair of rotor blades.

US Pat. No. 10,113,609

VIBRATION ISOLATING DEVICE FOR AN ELASTIC COUPLING OF TWO COMPONENTS

AIRBUS HELICOPTERS DEUTSC...

1. A vibration isolating device that is adapted for an elastic coupling of a first component to a second component and for vibration isolation in predetermined frequency ranges between the first and second components, the vibration isolating device comprising at least a first and a second elastically deformable plate that are attached to each other in at least two separate connecting points, the first elastically deformable plate comprising a first curvature located in a region between the at least two separate connecting points and the second elastically deformable plate comprising a second curvature located in a region between the at least two separate connecting points, wherein the first and second curvatures are arranged such that a gap is defined between the first and second elastically deformable plates in the regions between the at least two separate connecting points, and wherein the first and second curvatures are adapted to be reduced in operation if a tension force that moves the at least two separate connecting points away from each other is applied to the vibration isolating device, and wherein the first and second curvatures are adapted to be increased in operation if a compression force that moves the at least two separate connecting points towards each other is applied to the vibration isolating device; wherein at least one of the first and second elastically deformable plates comprises an associated vibration isolation mass and in that the at least one of the first and second elastically deformable plates comprises an associated lever that is mounted to the at least one of the first and second elastically deformable plates, in the region of at least one of the first and second curvatures, of the at least one of the first and second elastically deformable plates, at least one associated lever being provided with a vibration isolation mass.

US Pat. No. 9,925,942

ENERGY ABSORBING SYSTEM FOR ABSORBING ENERGY OF AN OBJECT IN A VEHICLE IN A CRASH SITUATION

AIRBUS HELICOPTERS DEUTSC...

1. An energy absorbing system that is adapted for absorbing energy of an object in a vehicle in a crash situation by decreasing acceleration and force acting on the object in the crash situation, the energy absorbing system comprising at least one plastically deformable energy absorber that is plastically deformable in the crash situation, the energy absorbing system being provided with a mass-dependent self-adjusting mechanism, the mass-dependent self-adjusting mechanism being adapted for adjusting, on the basis of an underlying mass of the object, a required compensation force that is to be provided by the energy absorbing system in the crash situation for plastically deforming the at least one plastically deformable energy absorber in order to decrease the acceleration and force acting on the object, wherein the mass-dependent self-adjusting mechanism comprises at least one first and one second roller that are spaced apart from each other by means of at least one spring pushing the first and second rollers in opposed directions, the first and second rollers being adapted for applying the required compensation force to the at least one plastically deformable energy absorber in the crash situation for plastically deforming the at least one plastically deformable energy absorber in the crash situation.

US Pat. No. 10,059,424

ARRANGEMENT FOR MOVING A DOOR IN SWINGING AND SLIDING MOTIONS

Airbus Helicopters Deutsc...

1. An arrangement for moving a door, the door being configured to close an opening of a structure, and the arrangement comprising:pivoting means attachable to the structure and to a first attachment point of the door, the pivoting means being suitable for allowing a rotation of the door around a plurality of axes of rotation of the pivoting means, the plurality of axes of rotation comprising a slide axis and at least one swing axis, wherein the pivoting means comprises a spherical bearing suitable for allowing a free rotation of the door around a center of rotation of the spherical bearing, the slide axis and the at least one swing axis passing through the center of rotation of the spherical bearing,
a guiding rail attachable to the structure,
guiding means attachable to a second attachment point of the door and comprising a slider for moving along the guiding rail, the guiding means being suitable for allowing the door to slide over the guiding rail while pivoting around the slide axis, and for allowing the door to swing about the at least one swing axis, the at least one swing axis passing through a swing point of the guiding means.

US Pat. No. 10,124,898

SEAT BENCH DEVICE WITH A SEAT BENCH COMPONENT AND AT LEAST ONE RESTRAINING UNIT

Airbus Helicopters Deutsc...

1. A seat bench device with a seat bench component and a plurality of restraining units, the seat bench component comprising a seating surface and a backrest, and wherein each restraining unit comprises a harness for restraining a seat bench occupant on the seat bench component, wherein at least two guide elements are provided, wherein each restraining unit is movably arranged on the at least two guide elements for being movable on the at least two guide elements along the backrest at least between a storage position and an associated operating position, in which the harness is operational for buckling up of a seat bench occupant.

US Pat. No. 10,065,733

FLEXBEAM UNIT FOR A BEARINGLESS OR A HINGE AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, said flexbeam unit comprising a plurality of flexbeam elements, each defining a load passing member that is attachable to a rotor hub associated with a rotor shaft of said multi-blade rotor, said plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of said multi-blade rotor, wherein at least one of the predetermined number of torsion elements comprises at least one first flexbeam element defining a first longitudinal direction and at least one second flexbeam element defining a second longitudinal direction, said first and second longitudinal directions being inclined to each other with a predetermined inclination angle, and wherein said at least one first and second flexbeam elements are interconnected by a beam connector in a direction transverse to said first longitudinal direction and/or said second longitudinal direction.

US Pat. No. 9,932,104

AIRCRAFT WITH A SUBFLOOR REGION THAT ACCOMMODATES AN AUXILIARY COMPARTMENT

AIRBUS HELICOPTERS DEUTSC...

1. A rotorcraft with a fuselage, the rotorcraft comprising:a floor structure that is arranged inside the fuselage defining a subfloor region between the floor structure and a fuselage underside of the fuselage;
an equipment bay with at least one auxiliary equipment arranged within the subfloor region, the at least one auxiliary equipment being at least partly stowable in the equipment bay in a stow mode; and
at least one auxiliary compartment being at least partly arranged in a region between the equipment bay and the floor structure such that the at least one auxiliary compartment separates the equipment bay from the floor structure;
wherein the at least one auxiliary equipment is forcibly moved in the equipment bay by a crash load from a stow position associated with the stow mode into at least one crash position in the equipment bay to reduce force on the auxiliary equipment.

US Pat. No. 10,023,313

ROPE SUSPENSION DEVICE WITH AT LEAST ONE ROPE SUSPENSION MODULE

AIRBUS HELICOPTERS DEUTSC...

1. A rope suspension device with at least one rope suspension module that is adapted for suspension of at least one rope from a rotorcraft, the rope suspension module comprising at least one lockable load beam that is rotatable around an axis of rotation between a locked state and an unlocked state and that is adapted for supporting in the locked state at least one rope that is to be suspended from the rope suspension module, the at least one lockable load beam being, upon unlocking in operation, rotatable from the locked state around the axis of rotation into the unlocked state by application of a load to the at least one lockable load beam by means of the at least one rope that is supported by the at least one lockable load beam, wherein:the at least one lockable load beam is provided with a hinge, the hinge being pivotally mounted to an associated support member;
at least one locking element is provided that is movable between at least a first and a second position, the at least one locking element being adapted for locking the at least one lockable load beam in the first position and for unlocking the at least one lockable load beam in the second position; and
the at least one locking element is translationally movable in a direction that is at least approximately parallel to a longitudinal extension of at least one lockable load beam in locked state.

US Pat. No. 10,137,976

AIRFOILS FOR ROTOR BLADES OF ROTARY WING AIRCRAFTS

AIRBUS HELICOPTERS DEUTSC...

wherein a maximum error of each one of the predetermined intrados coordinate value pairs x/c, yint/c and the predetermined extrados coordinate value pairs x/c, yext/c amounts to ±3%.

US Pat. No. 10,005,552

FLEXBEAM UNIT WITH AT LEAST ONE TWISTED FLEXBEAM ELEMENT

AIRBUS HELICOPTERS DEUTSC...

1. A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising:a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element having the form of a bar and comprising at least one stiff rotor hub connecting area adapted to be connected to an associated rotor hub of the multi-blade rotor and at least one stiff blade connecting area adapted to be connected to an associated rotor blade of the multi-blade rotor;
at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction by a predetermined twist angle that is comprised in a range between 90° and 270°, the at least one twisted area being at least partially arranged between the at least one stiff rotor hub connecting area and the at least one stiff blade connecting area;
a multiplicity of fiber reinforced polymer layers, at least one of the multiplicity of fiber reinforced polymer layers extending from the at least one stiff rotor hub connecting area through the at least one twisted area to the at least one stiff blade connecting area; and
a multiplicity of separation layers arranged in the at least one twisted area between the multiplicity of fiber reinforced polymer layers.

US Pat. No. 9,963,226

TAIL ASSEMBLY FOR A ROTORCRAFT, ROTORCRAFT AND METHOD OF MANUFACTURE OF A STRENGTHENED TAIL ASSEMBLY

Airbus Helicopters Deutsc...

1. A method of manufacturing a tail assembly for a rotorcraft; the tail assembly including a power transmission shaft covered by at least one non-load bearing fairing and a load bearing structure defining, from fore to aft, a tail boom and a tail fin; the load bearing structure having a fore end and a longitudinal median boom portion extending from the fore end towards the tail fin; the tail assembly comprising a power transmission shaft penetrating inside the tail fin by a passing through opening in the load bearing structure; the passing through opening positioned on a surface of the load bearing structure facing the fore end;wherein the method includes:
a transition stage of providing the load bearing structure of the tail assembly with at least one transition structure that is longitudinally arranged between the longitudinal median boom portion and the tail fin; the non-load bearing fairing being detachably secured to the longitudinal median boom portion for allowing access to the power transmission shaft and being flush with a longitudinal part of the transition structure; at least one transverse section of the transition structure having an upwards dimension that is higher than an elevation junction dimension of the longitudinal median boom portion at a junction between the longitudinal median boom portion and the transition structure;
a cut-out arrangement stage of providing the transition structure with at least one cut-out elevation step, the passing through opening being made in the cut-out elevation step, such that the power transmission shaft extends at least partly externally above the longitudinal median boom portion between the fore end and the cut-out elevation step, the power transmission shaft penetrating in the load bearing structure through the passing through opening;
an upper location stage of determining a longitudinal distance shift at which an upper end of the cut-out elevation step is longitudinally shifted forwards relative to a leading edge of the tail fin; and
a lower offset stage of defining a lower offset at which a lower end of the cut-out elevation step is longitudinally shifted forwards with respect to the upper end of the cut-out elevation step.

US Pat. No. 10,040,546

BAR OF COMPOSITE MATRIX MATERIAL

AIRBUS HELICOPTERS DEUTSC...

1. A bar of composite matrix material, the bar adapted to join a rotor blade of a rotor to a hingeless rotary hub assembly of a rotary wing aircraft, the bar having a longitudinal axis perpendicular to a cross section of the bar, the cross section having upper and lower surfaces, the longitudinal axis having essentially equal distances from the upper and lower surfaces, and the cross sections joining the rotor blade to the hingeless rotary hub assembly being located at regions that are flexible to allow the rotor blade to undergo movements in a flapping direction, in a lead-lag direction and in a pitch angle direction, the bar of composite matrix material comprising:a first group of fibers which extend parallel to the longitudinal axis, wherein the first group of fibers define the upper and lower surfaces of the cross section; and
a second group of fibers which extend at an angle to the longitudinal axis, the second group of fibers defining an uppermost layer and a lowermost layer of a torsion box extending along the longitudinal axis, the uppermost and lowermost layers being respectively offset of the longitudinal axis and of the upper and the lower surfaces, the uppermost and lowermost layers being laterally joint, wherein the cross section (i) between the uppermost and lowermost layers, (ii) between the uppermost layer and the upper surface, and (iii) between the lowermost layer and the lower surface is at least partially filled, in a direction of the longer sides of the cross section, with the first group of fibers extending essentially parallel to the longitudinal axis, and the first group of fibers between the uppermost and lowermost layers define a thickness in a first direction extending from the lowermost layer to the uppermost layer, and wherein the thickness increases along the cross section in a second direction orthogonal to the first direction.

US Pat. No. 10,029,784

FLEXBEAM UNIT FOR A BEARINGLESS OR A HINGE- AND BEARINGLESS MULTI-BLADE ROTOR OF A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising a plurality of inner layers of a first fiber reinforced material that are embedded between at least two outer layers of a second fiber reinforced material, the at least two outer layers being composed of main plies comprising unidirectional fibers and the plurality of inner layers defining a cross section profile center in the associated longitudinal direction of the at least one flexbeam element, the cross section profile center being at least substantially composed of interconnected bias plies comprising fibers that are oriented transversely relative to the unidirectional fibers, wherein at least one of the plurality of inner layers comprises at least two curved bias plies that are embedded between at least two substantially plane bias plies and connected with the plane bias plies, the curved bias plies defining associated cavities and having curved sections, wherein the curved bias plies comprise straight sections extending from the curved sections, and wherein the at least one of the plurality of the inner layers comprises at least four main plies that are arranged in the form of axial extensions of the straight sections of the curved bias plies between the plane bias plies.

US Pat. No. 10,005,538

AIRCRAFT WITH INWARDLY FOLDABLE REAR DOOR

Airbus Helicopters Deutsc...

1. An aircraft comprising:a rear door,
a landing gear,
a fuselage extending longitudinally between a nose and a rear part, and extending in elevation between a lower part and an upper part, the lower part being the part of the fuselage on which the landing gear is mounted and the rear part in turn comprising a rear opening, at least a portion of the rear opening configured to be closed by the rear door,
an auxiliary door pivotally connected to the fuselage and configured to open outwardly with respect to the fuselage, the auxiliary door configured to close at least another portion of the rear opening, wherein the
auxiliary door is configured to lock at (i) a first outward position (H) with respect to the fuselage in which the auxiliary door extends along the longitudinal direction of the aircraft, and (ii) a second outward position (V) with respect to the fuselage in which the auxiliary door extends along the elevation direction of the aircraft, and
an arrangement comprising:
a first link comprising:
a first main body,
a first door attaching means, and
a first fuselage attaching means,
wherein the first main body extends along a first length (L1) between the first door attaching means and the first fuselage attaching means, and the first link is pivotally attached to the rear door by means of the first door attaching means and is pivotally attached to the fuselage at a first end by means of the first fuselage attaching means, and
a second link comprising:
a second main body,
a second door attaching means, and
a second fuselage attaching means,
wherein the second main body extends along a second length (L2), greater than the first length (L1), between the second door attaching means and the second fuselage attaching means, and the second link is pivotally attached to the rear door by means of the second door attaching means and is pivotally attached to the fuselage at a first end by means of the second fuselage attaching means,
wherein the first and second fuselage attaching means are attached to the fuselage,
wherein the second fuselage attaching means is located longitudinally closer to the nose of the fuselage than the first fuselage attaching means,
such that when the first and the second links rotate around the first and the second fuselage attaching means, the rear door rotates around the first and the second door attaching means, so that the rear door can be inwardly displaced in the longitudinal direction and in the elevation direction between a first position (F) wherein the rear door closes the at least a portion of the rear opening and at least a second position (S) at the interior of the fuselage wherein the rear door extends along the longitudinal direction, and
wherein a longitudinal axis of the first link and a longitudinal axis of the second link intersect at a location within the fuselage and above the first ends of the first and second links with the rear door in the first position (F).

US Pat. No. 9,902,500

AIRCRAFT WITH AN ENGINE HAVING A BY-PASS AIR INLET OPENING AND A BLEED AIR OUTLET

Airbus Helicopters Deutsc...

1. An engine for an aircraft, comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, the
main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through the main air inlet
opening into the engine, the by-pass air inlet opening being provided with a by-pass door that is operable by an associated
operating element to enable a by-pass air stream through the by-pass air inlet opening into the engine, and the bleed air
outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, wherein the associated
operating element is connected to the bleed air outlet and controllable by the outgoing bleed air stream in operation, wherein
the associated operating element is configured to open the by-pass door in operation at least if a given clogging rate of
the inlet barrier filter exceeds a predetermined threshold.

US Pat. No. 9,950,787

CONTROL SYSTEM FOR CONTROLLING COLLECTIVE AND CYCLIC PITCH OF ROTOR BLADES OF A MULTI-BLADE ROTOR IN A ROTARY-WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft, wherein the multi-blade rotor comprises a rotor shaft that defines an associated rotor axis, the control system comprising a swash plate assembly with at least one non-rotating plate and at least one rotating plate that is mounted rotatably to the at least one non-rotating plate, the at least one rotating plate and the at least one non-rotating plate being mounted to a non-rotating sliding sleeve that is adapted to be mounted axially displaceable parallel to the associated rotor axis on the rotor shaft, wherein a spherical bearing is provided on the non-rotating sliding sleeve, the at least one rotating plate being rotatable around an associated sliding sleeve axis and being mounted with the at least one non-rotating plate to the spherical bearing such that the at least one rotating plate and the at least one non-rotating plate are tiltable in any direction around the associated sliding sleeve axis by means of the spherical bearing, characterized in that at least one non-rotating stop arm is provided for non-rotatably connecting the at least one non-rotating plate to the non-rotating sliding sleeve in order to inhibit relative rotational movement around the associated sliding sleeve axis between the at least one non-rotating plate and the non-rotating sliding sleeve, the at least one non-rotating stop arm being mounted to the at least one non-rotating plate and to the non-rotating sliding sleeve.

US Pat. No. 10,131,424

COMPOUND ROTORCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A compound rotorcraft with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein the compound rotorcraft comprises at least one propeller at least adapted for generating forward thrust in operation, the at least one propeller being mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region, each of the at least one propeller being mounted to an associated interconnection region; the compound rotorcraft being provided with a wheel-type main landing gear,wherein the lower wing comprises an inboard section defining a first quarter chord line and a first centroid axis and an outboard section defining a second quarter chord line and a second centroid axis, the inboard section being an integral part of the fuselage at the lower wing root joint area and to the outboard section at a sections interconnection region, the wheel-type main landing gear being mounted to the inboard section adjacent to the sections interconnection region and the outboard section being connected to the inboard section at the sections interconnection region and to the upper wing at the associated interconnection region, wherein the second centroid axis is inclined relative to the first centroid axis by a relative dihedral angle that is defined in a first coordinate plane, and wherein the second quarter chord line is inclined relative to the first quarter chord line by a relative sweep angle that is defined in a second coordinate plane;
wherein the upper wing is removably attached to the upper wing root joint area by means of a hinged root joint and that the outboard section is removably attached to the inboard section at the sections interconnection region by means of a hinged joint or a clamped joint.

US Pat. No. 10,065,378

PRODUCTION AND REPARATION OF NON-POROUS LAMINATES WITH ASSESSABLE LOW DEGREE OF FIBER CONTENT

AIRBUS HELICOPTERS DEUTSC...

1. A method of forming a fiber reinforced composite structure having a fiber volume fraction below 50 vol.-% using vacuum bag molding, the method comprising the steps of:placing an assembly of fiber laminates on a tool surface;
placing a vacuum bag comprising a resin inlet over the assembly of fiber laminates and sealing the vacuum bag against the tool surface, thus forming an airtight envelope;
creating a predetermined maximum difference of pressure between the inside and the outside of the airtight envelope;
during a first infusion time, creating a flow of resin in the vacuum bag by infusing resin into the assembly of fiber laminates through the resin inlet of the vacuum bag while keeping the maximum difference of pressure, until the assembly of fiber laminates is completely filled with resin, wherein the assembly of fiber laminates is formed with a fiber volume fraction of more than 50 vol.-%;
during a second infusion time, reducing the difference of pressure between the inside and the outside of the airtight envelope without interrupting the flow of resin, such difference of pressure reaching during the second infusion time a predetermined minimum value, inferior to the predetermined maximum difference of pressure, so that the assembly of fiber laminates expands and infusing resin into the assembly of fiber laminates continues thus forming a resin infused assembly of fiber laminates with a fiber volume fraction below 50 vol.-%;
closing the resin inlet;
curing the resin infused assembly of fiber laminates at the minimum value of the difference of pressure between the inside and the outside of the airtight envelope reached during the second infusion time, thus forming a fiber reinforced composite structure having a fiber volume fraction below 50 vol.-%.

US Pat. No. 10,107,669

LIQUID LEVEL SENSOR WITH INSULATING REGION OVER THE PROBE FOOT

AIRBUS HELICOPTERS DEUTSC...

1. A liquid level sensor for a fuel tank in an aircraft, the liquid level sensor comprising an inner capacitor tube, an outer capacitor tube and a probe foot suitable for placing the liquid level sensor on a bottom wall of the fuel tank, the inner and outer capacitor tubes respectively extending upwardly relative to the probe foot from an inner capacitor tube base and an outer capacitor tube base in such a way that a capacitor region arranged to hold a liquid is defined between the outer capacitor tube and the inner capacitor tube, the inner capacitor tube being located at an inside of the outer capacitor tube,wherein an insulating minimum distance (id) along an elevation direction of the liquid level sensor is left between the inner capacitor tube base and the probe foot, the capacitor region and the probe foot being thereby separated by such insulating minimum distance (id), the insulating minimum distance (id) being sufficient to prevent a droplet of water on the probe foot from making contact with the inner capacitor tube, and
wherein the inner capacitor tube base completely closes the inner capacitor tube at an end in such a way that an inner capacitor tube trap is defined at an inside of the inner capacitor tube between the inner capacitor tube base and the at least one draining hole defined in a wall of the inner capacitor tube, the inner capacitor tube trap being filled with a filling material for keeping liquids and particles from being retained therein.

US Pat. No. 10,311,202

PROBABILISTIC LOAD AND DAMAGE MODELING FOR FATIGUE LIFE MANAGEMENT

AIRBUS HELICOPTERS DEUTSC...

1. A fatigue life management system for determining a remaining fatigue life of a component of an aircraft, the fatigue life management system comprising:a flight data recorder that generates flight data recordings of the aircraft during the usage of the aircraft, the flight data recorder having a sensor coupled to the component, the sensor monitors the component while the component is being subjected to structural usage caused by operational loads during the usage of the aircraft to generate at least a subset of the flight data recordings;
a first processing circuit that receives the flight data of the aircraft from the flight data recorder and selects portions of the received flight data, the selected flight data of the aircraft including at least portions of the subset of flight data of the aircraft;
a first storage circuit that receives the selected flight data of the aircraft from the first processing circuit and stores the selected flight data of the aircraft;
a second storage circuit that stores regression models for probabilistic prediction of minimum load, maximum load, and timeframe damage of the component; and
a second processing circuit that receives the selected flight data from the first storage circuit and the regression models from the second storage circuit, generates probability density functions of minimum load, maximum load, and timeframe damage for predetermined time intervals based on the selected flight data and the regression models, computes an accumulated fatigue damage estimation based on the probability density functions and a probabilistic fatigue strength model to generate a distribution of the accumulated fatigue damage estimation of the component, compares the distribution of the accumulated fatigue damage estimation with a reliability requirement to determine the remaining fatigue life of the component, and outputs an increased flight-hour-based interval between replacement of the component when the remaining fatigue life of the component is greater than a fatigue life of the component based on a fixed fatigue damage accumulation rate assumed by an original equipment manufacturer (OEM) of the aircraft and outputs a decreased flight-hour-based interval between replacement of the component when the remaining fatigue life of the component is less than the fatigue life of the component based on the fixed fatigue damage accumulation rate assumed by the OEM of the aircraft.

US Pat. No. 10,279,885

HELICOPTER WITH A FUSELAGE AND A COMPOSITE TAIL BOOM

AIRBUS HELICOPTERS DEUTSC...

1. A helicopter with a fuselage and a composite tail boom, the composite tail boom comprising at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face, wherein the mating face is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom, the plurality of tension members being distributed over a perimeter of the composite attachment ring segment, wherein the composite attachment ring segment comprises a clamp ring section with a plurality of tension member accommodations, the clamp ring section defining the mating face of the composite attachment ring segment, wherein the plurality of tension members is at least partly accommodated in the plurality of tension member accommodations, wherein the composite attachment ring segment defines a radial cross section with a neutral line that is essentially oriented in parallel to the longitudinal extension direction and that comprises deviation slopes of at most 1:5 with respect to the longitudinal extension direction, and wherein the clamp ring section comprises fiber layers that are at most deviated from the longitudinal extension direction by a slope of less than 1:5.

US Pat. No. 10,173,783

ROTORCRAFT WITH COWLING ABLE TO ROTATE AND TRANSLATE RELATIVE TO THE FUSELAGE

Airbus Helicopters, Mari...

1. A rotorcraft comprising:a fuselage having an opening,
a cowling suitable for closing the opening,
a fastening system for attaching the cowling to the fuselage, the fastening system comprising:
at least one supporting means pivotally attached to an interior of the fuselage, so that the at least one supporting means can rotate between a closing position and an opening position, the at least one supporting means comprising a projecting region located outside the fuselage when the at least one supporting means is at the opening position and located inside the fuselage when the at least one supporting means is at the closing position,
at least one translation means coupled to the projecting region and to the cowling to enable a translation of the cowling with respect to the projecting region outside of the fuselage when the at least one supporting means is at the opening position and so that rotation of the cowling with respect to the fuselage takes place with rotation of the at least one supporting means whereby the entire cowling is cleared from the fuselage and the opening when the at least one supporting means is at the opening position, and the at least one translation means arranged in such a way that the cowling is at a closed position closing the opening when the at least one supporting means is at the closing position,
wherein pivotal attachments between the interior of the fuselage and the at least one supporting means are located on a first reference axis (F) at the interior of the fuselage, and a second reference axis (S) is provided at the projecting region along which the translation of the cowling with respect to the projecting region outside of the fuselage can take place; and
wherein the first reference axis (F) and the second reference axis (S) extend along a longitudinal direction of the rotorcraft, such that when rotation of the cowling with respect to the fuselage and translation of the cowling with respect to the projection region outside the fuselage take place the cowling can reach a final position in which the entire cowling is cleared from the fuselage and the opening, is longitudinally translated away from the opening, and extends perpendicularly to an elevation direction.

US Pat. No. 10,330,148

BEARING ARRANGEMENT WITH A FIRST BEARING LAYER AND A SECOND BEARING LAYER

AIRBUS HELICOPTERS DEUTSC...

1. A bearing arrangement comprising:a first bearing layer comprising a first bearing support element and a second bearing layer comprising a second bearing support element, the first and second bearing layers being glidingly interconnected by an intermediate glide element,
a first gliding component arranged between the first bearing support element and the intermediate glide element; and
a second gliding component arranged between the second bearing support element and the intermediate glide element, the intermediate glide element being elastically attached to the first bearing support element by a first flexible connector and to the second bearing support element by a second flexible connector,
wherein the first flexible connector and the second flexible connector are physically separated from each other by the intermediate glide element to maintain relative movement between the first and second bearing support elements.

US Pat. No. 10,399,658

AIRCRAFT STRUCTURAL COMPONENT THAT IS ADAPTED FOR ABSORBING AND TRANSMITTING FORCES IN AN AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. An aircraft comprising a force-absorbing structure comprising a plurality of structural components adapted for absorbing and transmitting forces in an aircraft, at least one of the structural components comprising a first panel element, a second panel element, a first reinforcing structure, and a second reinforcing structure, the first and second panel elements and the first and second reinforcing structure comprising fiber reinforced polymers; the first reinforcing structure being rigidly attached to the first panel element such that at least a first cavity is defined between the first panel element and the first reinforcing structure, the second reinforcing structure being rigidly attached to the second panel element such that at least a second cavity is defined between the second panel element and the second reinforcing structure, the aircraft being a rotorcraft and the force-absorbing structure is provided at a fuselage of the rotorcraft; the reinforcing structures being rigidly attached to the panel elements by means of a collective curing with the panel elements; the rotorcraft comprising a wheel landing gear having a rotatable shaft; at least one of the reinforcing structures being provided on either side of each of the two panel elements; the reinforcing structures on either side of each of the first and second panel elements pivotally bearing on the fuselage a bearing of the rotatable shaft of a wheel landing gear.

US Pat. No. 10,189,563

BEAM FOR A ROTORCRAFT ROTOR AND ROTORCRAFT ROTOR

AIRBUS HELICOPTERS DEUTSC...

1. A beam for attaching a blade to a hub of a rotor for a rotorcraft, the blade having a longitudinal axis extending radially from a rotation axis of the hub, the beam comprising:a hub connection portion for connecting the beam to the hub of the rotor;
a blade connection portion for connecting the beam to the blade of the rotor;
a first flexure portion located between the hub connection portion and the blade connection portion and adapted to bend about a first bending axis orthogonal to a longitudinal axis of the blade, a first bending stiffness of the first flexure portion being smaller than a bending stiffness of the hub connection portion and smaller than a bending stiffness of the blade connection portion;
a second flexure portion located between the hub connection portion and the blade connection portion and adapted to bend about a second bending axis, wherein the second bending axis is orthogonal to the longitudinal axis of the blade and non-parallel to the first bending axis, a second bending stiffness of the second flexure portion being smaller than the first bending stiffness of the first flexure portion;
a shear portion located between the hub connection portion and the blade connection portion and adapted to rotate about a shear axis, wherein the shear axis is orthogonal to the first bending axis and parallel to one of the rotation axis of the hub or the second bending axis of the blade;
at least one slot-shaped groove extending into the shear portion and at least a part of the second flexure portion in a direction parallel to one of the rotation axis of the hub or the first bending axis of the blade, or a plane through the longitudinal axis of the blade and orthogonal to one of the rotation axis of the hub or the first bending axis of the blade;
wherein the slot-shaped groove reduces a shear stiffness of the shear portion to be smaller than a shear stiffness of the hub connection portion and a shear stiffness of the blade connection portion.

US Pat. No. 10,486,794

PROPELLER ASSEMBLY WITH AT LEAST TWO PROPELLER BLADES

AIRBUS HELICOPTERS DEUTSC...

1. A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising a leading edge and a trailing edges that define a chord and a quarter chord line thereof,wherein the common pitch axis has an upstream predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, the upstream predetermined offset being in a region defined between the leading edge and the quarter chord line of each one of the at least two propeller blades to produce an additional momentum next to a blade's quarter chord line moment, resulting from a rotation of each one of the at least two propeller blades around the quarter chord line and wherein the associated connection means enables, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis in response to aerodynamic forces acting on the at least two propeller blades.

US Pat. No. 10,507,491

ROTARY WING AIRCRAFT WITH A STRUCTURAL ARRANGEMENT THAT COMPRISES AN ELECTRICALLY CONDUCTIVE CONNECTION

AIRBUS HELICOPTERS DEUTSC...

1. A structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection,wherein the electrically conductive connection comprises at least one sprayed layer formed by spraying of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace, the at least one first fiber reinforced polymer component is electro-conductively connected to a first electrically conductive foil and the at least one second fiber reinforced polymer component is electro-conductively connected to a second electrically conductive foil, the at least one sprayed layer of electrically conductive particles being at least partly formed between the first and second electrically conductive foils and the associated structural component being one of a joggled panel, shell, stringer, rib, frame and beam of a rotary wing aircraft and that the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component being implemented as panels or shells of the rotary wing aircraft, with the interspace exhibiting a width that is comprised in a range between 1 mm and 10 mm.

US Pat. No. 10,556,668

ARTIFICIAL FORCE FEEL GENERATING DEVICE FOR A VEHICLE CONTROL SYSTEM OF A VEHICLE AND, IN PARTICULAR, OF AN AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, the artificial force feel generating device comprising a first force generating device and a second force generating device, wherein the first force generating device and the second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel.

US Pat. No. 10,486,790

MAINTENANCE STEP FOR A HELICOPTER

AIRBUS HELICOPTERS DEUTSC...

1. A maintenance step for a helicopter, comprising:a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, the casing includes a frame which is closed by a rear wall that is provided for closing up the lateral shell, and
a step member that is pivotally mounted to the casing,
wherein
a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section is telescopically mounted to the first section;
wherein the step member is pivotally mounted to the casing around a first axis and the stirrup unit is pivotally mounted to the step member around a second axis, wherein the first axis and the second axis are perpendicular.

US Pat. No. 10,408,327

MOUNTING ARRANGEMENT FOR MOUNTING A GEAR BOX OF A ROTORCRAFT TO A FUSELAGE OF A ROTORCRAFT

Airbus Helicopters Deutsc...

1. A mounting arrangement for mounting at least a gear box of a rotorcraft to a fuselage of a rotorcraft, the mounting arrangement comprising a gear box of a rotorcraft and at least two support plates that are rigidly attached to substantially opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means configured to attach the at least two support plates to a fuselage of a rotorcraft by means of associated struts in order to enable transfer of induced loads occurring in operation, which are directed into a predetermined load direction, via the associated struts; wherein the gear box comprises a housing, the housing defining at least partly a containment surface of the gearbox and the at least two support plates being rigidly attached to the housing by means of associated attachment members, and wherein the at least two support plates define at least partly the containment surface of the gear box.

US Pat. No. 10,384,762

DEFLECTOR ASSEMBLY FOR AN AIRCRAFT

Airbus Helicopters Deutsc...

1. A deflector assembly for an aircraft, the deflector assembly for mounting on a fuselage of the aircraft (A) so as to protect a protuberant body against contact adverse reaction from an external item (ER) outside the fuselage, the protuberant body mounted on and extending outwards from the fuselage, the deflector assembly comprising at least:one adjoined anchorage for rigidly securing to the protuberant body,
one remote anchorage for securing to the fuselage, and
one deflector ramp extending from the adjoined anchorage and towards the remote anchorage along a longitudinal direction (X) of the deflector assembly, wherein an innermost end of the deflector ramp cooperates with the adjoined anchorage and an outermost end of the deflector ramp cooperates with the remote anchorage, the deflector ramp having a central oblique section that extends along an axis that is intersecting a longitudinal direction (X) of the deflector assembly and extends with an oblique angle (SG) relative to the longitudinal direction (X), to act as a sliding guide for the external item (ER),
wherein the adjoined anchorage includes a socket face that internally has a sliding bearing in which is housed the innermost end, the sliding bearing having a linear translation axis (LT) along which the innermost end of the deflector ramp is slidably guided relative to the adjoined anchorage to have one translational degree of freedom along the linear translation axis (LT) after the deflector ramp is connected to the adjoined anchorage,
wherein the remote anchorage has a support bracket for demountably mounting the remote anchorage to the fuselage;
wherein a frontage cam track is fixedly secured to the deflector ramp and is locally covering the central oblique section and partly the innermost end of the deflector ramp; and
wherein the socket face has a clearance cavity extending along the linear translation axis (LT) for receiving an end portion of the frontage cam track aside the innermost end, the end portion of the frontage cam track being locally housed freely into the clearance cavity, so that when the deflector ramp translates relative to the socket face, the ending portion of the frontage cam track respectively slides inside the clearance cavity.

US Pat. No. 10,527,000

AIRCRAFT WITH A HOT AIR EXHAUST THAT COMPRISES TWO PIVOTALLY MOUNTED EXHAUST SECTIONS

AIRBUS HELICOPTERS DEUTSC...

1. An aircraft with a fuselage that defines at least one drive system accommodating region, the drive system accommodating region accommodating at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the hot air flow, the at least one hot air exhaust comprising at least one first exhaust section and at least one second exhaust section, the at least one second exhaust section mounted in a rotatable manner to the at least one first exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided, the actuating member adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle;wherein the actuating member is adapted for applying a turning moment on the basis of a current operation temperature of the actuating member, wherein the actuating member comprises a temperature-sensitive actuator equipped with an expandable fluid, gas or rigid material adapted for expanding if the current operation temperature of the actuating member increases.

US Pat. No. 10,526,064

ACTUATING SYSTEM FOR AN ACTUATABLE DOOR AND AN ACTUATABLE DOOR HAVING SUCH AN ACTUATING SYSTEM

AIRBUS HELICOPTERS DEUTSC...

1. An actuating system for an actuatable door, the actuating system comprising an actuatable rotatable latching shaft and at least one latching device, the at least one latching device comprising a latching hook, an associated pivot bearing, a pivotable mechanical transmission element and a coupling link, wherein the latching hook is adapted for locking the actuatable door in a closed position, the latching hook being pivotally mounted to the associated pivot bearing and connected to the pivotable mechanical transmission element via the coupling link, the coupling link being pivotally mounted to the latching hook and to the pivotable mechanical transmission element, the pivotable mechanical transmission element being coupled to the rotatable latching shaft such that rotation of the rotatable latching shaft in operation upon actuation results in pivoting of the pivotable mechanical transmission element and pivoting of the latching hook around the associated pivot bearing, wherein the pivotable mechanical transmission element is mounted onto the rotatable latching shaft;wherein an overcentering adjustment device is provided, the overcentering adjustment device being adapted for pivoting the pivotable mechanical transmission element in operation at least from an in-line position into an overcentered position, the in-line position corresponding to a first position wherein the latching hook is in locked state and unlocking due to a back driving force acting on the latching hook is possible, and the overcentered position corresponding to a second position wherein the latching hook is in the locked state and unlocking due to a back driving force acting on the latching hook is prevented;
wherein the overcentering adjustment device comprises at least one overcentering bolt that is rigidly mounted to the rotatable latching shaft, the at least one overcentering bolt passing at least partly through an overcentering hole provided in the pivotable mechanical transmission element;
wherein the overcentering hole is provided as a long hole oriented at least approximately perpendicular to a longitudinal extension of the rotatable latching shaft;
wherein the at least one overcentering bolt and the long hole are movable relative to each other;
wherein at least one overcentering slider is provided, the overcentering slider being coupled to the at least one overcentering bolt;
wherein the at least one overcentering slider comprises at least one overcentering guide opening, the at least one overcentering guide opening being embodied as a long hole that is oriented transversely to the overcentering hole; and
wherein the at least one overcentering slider is movably arranged on the pivotable mechanical transmission element, wherein a longitudinal movement of the overcentering slider in operation is transformed into pivoting of the pivotable mechanical transmission element relative to the rotatable latching shaft.

US Pat. No. 10,427,775

AIRCRAFT WITH A FUSELAGE THAT DEFINES AT LEAST AN INTERIOR REGION AND A DRIVE SYSTEM ACCOMMODATING REGION

AIRBUS HELICOPTERS DEUTSC...

1. A rotary-wing aircraft comprising:a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region disposed inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement comprising a plurality of interconnected fire protection walls,
at least one engine disposed within the at least one fire protection zone within the at least one associated firewall arrangement such that the at least one associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage,
at least one heat generating auxiliary device distinct from the at least one engine and generating a hot air flow;
at least one auxiliary exhaust nozzle;
the at least one associated firewall arrangement comprising at least one air duct forming at least part of the at least one associated firewall arrangement and arranged between, and in fluid communication with, the at least one heat generating auxiliary device and the at least one auxiliary exhaust nozzle so that the hot air flow that is generated by the at least one heat generating auxiliary device in operation of the aircraft is ducted through the at least one air duct separately from air carrying heat generated by the operation of the at least one engine, wherein the at least one associated firewall arrangement includes the at least one air duct such that the at least one air duct is integral with the at least one associated firewall arrangement, the plurality of interconnected fire protection walls comprising a front fire protection wall, a rear fire protection wall, and a lower fire protection wall.

US Pat. No. 10,577,083

METHOD OF CONTROLLING AN ARTIFICIAL FORCE FEEL GENERATING DEVICE FOR GENERATION OF AN ARTIFICIAL FEELING OF FORCE ON AN INCEPTOR OF A VEHICLE CONTROL SYSTEM

AIRBUS HELICOPTERS DEUTSC...

15. A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system that comprises an automatic flight control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via associated flight control kinematics, wherein the artificial force feel generating device comprises at least one force generating device that is mechanically connected to the inceptor via a mechanical connection for generating a tactile cue force acting in operation on the inceptor, the method comprising at least the steps of:monitoring usage of the inceptor and the mechanical connection during operation of the artificial force feel generating device,
determining a current accumulated fatigue of the inceptor and/or the mechanical connection on the basis of the monitored usage,
determining a fatigue prediction for the inceptor and/or the mechanical connection on the basis of the current accumulated fatigue,
re-configuring protections of the automatic flight control system on the basis of the current accumulated fatigue,
re-configuring the at least one force generating device on the basis of the current accumulated fatigue, anddetermining an applicable overhaul interval of the inceptor and a mechanical linkage on the basis of the determined fatigue prediction.

US Pat. No. 10,532,811

METHOD OF MANUFACTURING A CONTROL CUFF FOR A ROTOR BLADE OF A HINGE AND BEARINGLESS ROTOR

Airbus Helicopters Deutsc...

1. A method of manufacturing a control cuff for a rotor blade of a hinge- and bearingless rotor, the control cuff being adapted for accommodation of a flexbeam element of the rotor and comprising a control rod attachment for connection to an activatable control rod that is activatable for rotating the control cuff in operation around its associated longitudinal axis for setting a current pitch or a blade angle of the rotor blade, the method comprising at least the steps of:manufacturing an outer shell of the control cuff,
manufacturing a stiffener member by means of an automated process,
inserting the stiffener member into the outer shell, and
bonding the stiffener member to the outer shell, in a region of the control rod attachment.

US Pat. No. 10,457,373

AIRCRAFT WITH A FUSELAGE AND A COMPOSITE TAIL BOOM

AIRBUS HELICOPTERS DEUTSC...

1. A composite tail boom for an aircraft, the composite tail boom comprising at least partly a tubular tail boom cone with an outer skin and an inner skin, characterized in that the inner skin delimits a hollow interior of the composite tail boom, wherein a plurality of rod-shaped stiffening elements and a plurality of ring-shaped stiffening elements are arranged between the outer skin and the inner skin, the plurality of rod-shaped stiffening elements being oriented in longitudinal direction of the composite tail boom and the plurality of ring-shaped stiffening elements being distributed along the longitudinal direction in the tubular tail boom cone, and wherein at least one of the plurality of ring-shaped stiffening elements comprises an associated thickness in radial direction of the tubular tail boom cone that is smaller than an associated thickness of at least one of the plurality of rod-shaped stiffening elements in radial direction of the tubular tail boom cone.

US Pat. No. 10,654,559

PITCH CONTROL DEVICE FOR A DUCTED TAIL ROTOR OF A ROTORCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A pitch control device for a ducted tail rotor of a rotorcraft, comprising:a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and
a control transfer member comprising a ring-shaped connector rigidly attached in a releasable manner to the at least two connecting arms of the control input member; the control transfer member comprising at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor;
wherein the at least two connecting arms of the control input member are rigidly attached to the ring-shaped connector of the control transfer member and the control input member comprises a composite material, the control transfer member comprising metal; and wherein a bushing is provided as an interface between each one of the at least two connecting arms and the ring-shaped connector.

US Pat. No. 10,625,848

ATTACHMENT OF A LANDING GEAR

AIRBUS HELICOPTERS DEUTSC...

1. An attachment bracket of a landing gear to a cabin of a helicopter, the attachment bracket comprising:a bracket for connecting a traverse of the landing gear to the cabin of the helicopter, the traverse extending in a transverse direction being perpendicular to a longitudinal direction of the cabin;
a landing gear retainer for fixation around the traverse coaxially to the longitudinal direction of the traverse; and
a pendulum extending below the landing gear traverse, the pendulum comprising:
an upper bolt hinged to the landing gear retainer with the upper pendulum bolt in the upper pendulum bearings; and
a lower pendulum bolt hinged to the cabin with the lower pendulum bolt in the lower pendulum bearings, the upper and lower pendulum bolts defining rotational axes parallel to the longitudinal direction of the cabin and thereby providing mobility of the cabin in the transverse direction about the rotational axes; and
compound springs oriented transverse to the pendulum bolts to decrease movement of the landing gear once the pendulum moves in the direction of the compound springs.

US Pat. No. 10,518,874

MULTI-BLADE ROTOR FOR A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A multi-blade rotor for a rotary wing aircraft, comprising:a plurality of rotor blades that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is extending in a longitudinal direction of the flex-beam element and being approximately L-shaped or shoe-shaped and comprising a single-sided longitudinal extension oriented at least approximately towards the associated rotor head, the asymmetrical flexbeam root being mounted to the associated rotor head.

US Pat. No. 10,695,995

METHOD OF CORRECTING AN INAPPROPRIATE COUNTERSINK IN A COMPOSITE COMPONENT

AIRBUS HELICOPTERS DEUTSC...

1. A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of:preparing a repair patch with a repair patch opening having a second opening diameter that is at most equal to the first opening diameter;
arranging the repair patch on the composite component in an area surrounding the inappropriate countersink, such that the repair patch opening and the fixation opening are at least approximately aligned;
pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and
fixing the repair patch in the inappropriate countersink.

US Pat. No. 10,683,087

SHROUDED ROTARY ASSEMBLY FROM SEGMENTED COMPOSITE FOR AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A manufacturing method for making a stator hollow structure for a shrouded propulsion rotary assembly in an aircraft, the method comprising:forming at least three angular segments separately of composite material, each angular segment integrally formed as a single-piece with a central hub arc fragment, a peripheral rim arc fragment and a pair of vane slice segments extending between the central hub arc fragment and the peripheral rim arc fragment;
securing the at least three angular segments together at central radial angles relative to each other, wherein the central hub arc fragments define a cylindrical hub casing, the peripheral rim arc fragments define a hollow cylindrical duct concentric to the cylindrical hub casing, and the pairs of vane slice segments define at least three guide vanes fixed between the cylindrical hub casing and the hollow cylindrical duct; and
mounting at least one U-shaped spoiler at least partly covering one of the at least three guide vanes.

US Pat. No. 10,556,662

ROTARY WING AIRCRAFT WITH A FUSELAGE THAT COMPRISES AT LEAST ONE STRUCTURAL STIFFENED PANEL

AIRBUS HELICOPTERS DEUTSC...

1. A rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel, the structural stiffened panel comprising a stressed skin and a stiffening framework that is rigidly attached to the stressed skin, wherein the stressed skin comprises an inner skin, an outer skin and a core element assembly arranged between the inner skin and the outer skin, the core element assembly comprising at least one viscoelastic core element and at least one intermediate core element that are tessellated, wherein the at least one viscoelastic core element is provided for noise and vibration damping, the at least one intermediate core element arranged in an attachment area between the inner skin and the outer skin, the inner skin rigidly attached via the at least one intermediate core element to the outer skin in the attachment area, and the at least one intermediate core element comprising a grid of longitudinal components and transversal components that define at least one intermediate free space, the at least one viscoelastic core element arranged in the at least one intermediate free space.

US Pat. No. 10,711,487

AIRCRAFT WITH A PLURALITY OF AIRCRAFT DOORS

AIRBUS HELICOPTERS DEUTSC...

1. A vehicle door comprising:a door structure;
at least one lock lever moveably mounted to the door structure;
a counterpart mounted to the door structure and engageable with the at least one lock lever in an engaged state for locking the vehicle door of an associated vehicle, and
a real-time monitoring device configured for generating a real-time representation of the at least one lock lever and the counterpart, the real-time representation being suitable for determining whether the at least one lock lever is in the engaged state;
wherein the real-time monitoring device comprises an image formation device attached to the door structure.

US Pat. No. 10,647,403

ACTUATABLE EMERGENCY EXIT DOOR AND AN AIRCRAFT OR SPACE CRAFT WITH A PRESSURIZED CABIN HAVING SUCH AN ACTUATABLE EMERGENCY EXIT DOOR

AIRBUS HELICOPTERS DEUTSC...

1. An actuatable emergency exit door actuatable between different operating positions relative to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the door having a door actuating device that comprises at least two connection rods, at least one goose neck-shaped structure and at least one spring member, wherein the at least two connection rods are pivotally mountable to the associated structural frame and being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein the at least one goose neck-shaped structure is enabling an initial translational opening movement and subsequently a swiveling opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening,wherein the at least one goose neck-shaped structure is door-mounted by being at least rigidly attached to a door corpus of the actuatable emergency exit door, at least one of the at least two connection rods is pivotably mountable to the associated structural frame and coupled to the at least one spring member, the at least one spring member is rigidly attached to the door corpus and is provided for biasing the actuatable emergency exit door during opening into a fully opened position in which the actuatable emergency exit door entirely frees exit through the associated structural frame.

US Pat. No. 10,807,706

JETTISONABLE EMERGENCY EXIT FOR A VEHICLE

AIRBUS HELICOPTERS DEUTSC...

1. A jettisonable emergency exit for a vehicle, comprising:a jettisonable panel having an outer peripheral edge that is adapted to be received in an opening of a frame provided in a vehicle,
at least one emergency exit retention means integrated into the outer peripheral edge of the panel, the at least one emergency exit retention means comprising at least one non-retractable pivot finger around which the jettisonable panel is rotatable in an emergency mode,
at least one emergency exit locking device integrated in the outer peripheral edge and comprising at least one locking hook that is adapted for locking the jettisonable panel in a locking position in normal operation mode and for releasing the jettisonable panel in a retracted position in the emergency mode,
an emergency activation strap connected to the at least one locking hook, wherein actuation of the strap moves the hook from the locking position into the retracted position.

US Pat. No. 10,940,933

DOOR OPENING SYSTEM WITH A DECELERATION MECHANISM

AIRBUS HELICOPTERS DEUTSC...

15. A method for controlling an opening of a door module that separates compartments of an aircraft and comprises a door panel and a door frame, when a predetermined air pressure difference threshold between the compartments of the aircraft is exceeded using a door opening system, the method comprising:determining whether a difference between a first air pressure of a first compartment and a second air pressure of a second compartment exceeds the predetermined air pressure difference threshold;
in response to determining that the difference between the first air pressure of the first compartment and the second air pressure of the second compartment exceeds the predetermined air pressure difference threshold, disabling a door locking system that keeps the door panel in a closed position;
unwinding a first portion of a strap from a first spool that guides a first move of the door panel from the closed position to a first predetermined position;
activating a braking apparatus in a second spool;
unwinding a second portion of the strap with the second spool that guides a second move of the door panel from the first predetermined position to a second predetermined position; and
stopping the door panel using at least one mechanical end stop that guides a third move of the door panel from the second predetermined position to a third predetermined position.

US Pat. No. 10,737,766

THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING

AIRBUS HELICOPTERS DEUTSC...

1. A thrust producing unit for producing thrust in a predetermined direction, comprising:a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis,
wherein the first rotor axis is inclined by an associated first inclination angle with respect to the predetermined direction, the first inclination angle being longitudinal and in a range between +1° and +60°, and the first rotor assembly being arranged outside of the internal volume of the shrouding and above the second rotor assembly that is arranged lower than the first rotor assembly; the second rotor assembly being arranged inside of the internal volume of the shrouding;
the second rotor axis being inclined by an associated second inclination angle with respect to the predetermined direction, such that the second inclination angle is longitudinal and less than the range of the first inclination angle.

US Pat. No. 10,982,332

METHOD OF MANUFACTURING A STRUCTURAL ARRANGEMENT WITH A FIBER REINFORCED POLYMER COMPONENT AND A COLD GAS SPRAYED ELECTRICALLY CONDUCTIVE LAYER

AIRBUS HELICOPTERS DEUTSC...

1. A method of manufacturing a structural arrangement from a fiber reinforced polymer component, comprising the steps of:providing a fiber reinforced polymer component;
fixing a polyether sulfone foil on the fiber reinforced polymer component, at least in a region where an electrically conductive layer is to be formed; and
performing a cold gas spraying process for spraying electrically conductive particles onto the polyether sulfone foil in order to create the electrically conductive layer.

US Pat. No. 10,967,965

ELASTIC FLAPPING HINGE FOR CONNECTING A ROTOR BLADE TO A ROTOR HUB OF A ROTARY WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members are stacked on top of each other at the rotor hub, and the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle;wherein the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by the predetermined divergence angle such that a V-shaped gap is formed in the elastic flapping hinge area between the at least two elastic flapping hinge members;
wherein the at least two flapping hinge members comprise a first elastically deformable plate having first and second indentation regions in the connection area and a second elastically deformable plate having first and second indentation regions in the connection area.

US Pat. No. 10,870,484

ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR

Airbus Helicopters Deutsc...

1. A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis, the at least one rotor blade being provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever,wherein the associated pitch-control lever has a pitch horn that forms and defines a bushing accommodation that extends through the pitch horn, the bushing accommodation being provided with an exchangeable bushing that provides the accommodation of the associated pitch-control lever so that the predetermined distance is adjustable in order to adjust the pitching angle of the corresponding blade and thereby adjust of track and balance of the multi-blade rotor independent from an adjustment of a length of the pitch link rod.

US Pat. No. 10,870,488

BRACED WING AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root, wherein the at least one upper wing comprises at least one upper wing spar that extends from the associated upper wing root to the predetermined transition region, and wherein the at least one lower wing comprises at least one lower wing spar that extends from the predetermined transition region to the associated lower wing root, wherein at least one transition spar is provided at the predetermined transition region, the at least one transition spar connecting the at least one upper wing spar to the at least one lower wing spar, and wherein the at least one upper wing spar, the at least one lower wing spar, and the at least one transition spar are arranged in a single spars plane that is inclined relative to a vertical aircraft axis.

US Pat. No. 10,836,475

MULTIROTOR AIRCRAFT WITH AN AIRFRAME AND AT LEAST ONE WING

AIRBUS HELICOPTERS DEUTSC...

1. A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units for producing thrust in a predetermined direction, the at least four thrust producing units being arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region,the air duct being cylindrical, wherein the air duct comprises a front side duct wall, a board side duct wall, a rear side duct wall, and a star board side duct wall, wherein at least the front side duct wall and the board side and star board side duct walls exhibit different heights in axial direction of the air duct, wherein the different heights define an undulated geometry, and wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

US Pat. No. 10,807,697

ROTARY WING AIRCRAFT WITH AN INTERFACE FRAME JOINING THE FUSELAGE TAIL BOOM AND THE TAIL CONE

AIRBUS HELICOPTERS DEUTSC...

1. A rotary wing aircraft comprising:a fuselage tail boom extending longitudinally along a longitudinal axis, the fuselage tail boom having a tail boom inner surface, which delimits the interior of the fuselage tail boom, and a tail boom outer surface opposite the tail boom inner surface,
a tail cone extending longitudinally along the longitudinal axis,
an interface frame in turn having:
a connecting sleeve extending longitudinally along the longitudinal axis; the connecting sleeve comprising a connecting sleeve inner surface, which delimits the interior of the connecting sleeve, and a connecting sleeve outer surface opposite the connecting sleeve inner surface; the connecting sleeve outer surface overlapping the tail boom inner surface so that the connecting sleeve and the fuselage tail boom fit axially; the connecting sleeve and the fuselage tail boom being directly attached by means of at least one boom mechanical connection, and
a connecting structure directly attached to the tail cone by means of at least one tail cone mechanical connection,the interface frame, the fuselage tail boom and the tail cone are all made of the same composite material, the interface frame joining the fuselage tail boom and the tail cone; the at least one boom mechanical connection being shear loaded and comprising a boom bushing lining a boom through-hole drilled in the fuselage tail boom and a frame bushing lining a frame through-hole drilled in the interface frame; the frame bushing being provided with a frame flange extending over the connecting sleeve outer surface, and the boom bushing being provided with a boom flange extending over the tail boom inner surface such that the frame flange and the boom flange form a stop for one another resulting in separating the connecting sleeve outer surface from the tail boom inner surface by a circumferential gap.

US Pat. No. 10,787,264

VIBRATION FILTER MECHANISM FOR ARRANGING BETWEEN A PIECE OF EQUIPMENT AND AN AIRCRAFT FUSELAGE, AND A SEAT FITTED WITH SUCH A MECHANISM

AIRBUS HELICOPTERS, Mari...

1. A vibration filter mechanism for arranging at the interface between a fuselage of an aircraft and a piece of equipment of the aircraft, the filter mechanism comprising a pair of filter members each secured respectively firstly with a first structure that is to be connected to the fuselage and secondly with a second structure of the piece of equipment, each filter member being secured with the first structure via a first pivot type connection having one degree of freedom to move in rotation and with the second structure via a second pivot type connection having one degree of freedom to move in rotation, the filter mechanism including resilient return means suitable for deforming during relative movement in rotation between at least one of the filter members and the first structure, the resilient return means presenting predetermined stiffness suitable for generating a return force opposing the relative movement in rotation between the filter member(s) and the first structure, wherein the filter members co-operate with the resilient return means to form an elastically deformable one-piece unit.

US Pat. No. 10,981,650

MULTIROTOR JOINED-WING AIRCRAFT WITH VTOL CAPABILITIES

AIRBUS HELICOPTERS DEUTSC...

1. A multirotor aircraft that is adapted for vertical take-off and landing, comprising a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip,wherein the at least one upper wing is joined to the at least one lower wing in a joined-wing configuration,
wherein a first thrust producing unit of the thrust producing units assembly is non-tiltably mounted to the at least one upper wing and provided for generating lift at least during vertical taking-off and landing, the first thrust producing unit being arranged near a leading edge of the at least one upper wing, and
wherein a second thrust producing unit of the thrust producing units assembly is non-tiltably mounted to the at least one lower wing and provided for generating lift at least during vertical taking-off and landing, the second thrust producing unit being arranged near a trailing edge of the at least one lower wing,
wherein the at least one upper wing is downwardly inclined by a predetermined negative dihedral angle, and
wherein the at least one upper wing comprises an upper wing inboard section that is connected to the vertical fin and an upper wing outboard section that forms the upper wing tip, wherein the upper wing outboard section is downwardly inclined by the predetermined negative dihedral angle relative to the upper wing inboard section.

US Pat. No. 10,974,815

MULTIROTOR AIRCRAFT WITH A THRUST PRODUCING UNIT THAT COMPRISES AN AERODYNAMICALLY OPTIMIZED SHROUDING

AIRBUS HELICOPTERS DEUTSC...

1. A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam and an aft beam which both connect the carrier beam to the airframe, the forward beam and the aft beam being arranged outside of the cylindrical air duct, wherein the forward beam comprises a forward flange, and wherein the aft beam comprises an aft flange, the forward flange and the aft flange being attached to the airframe, and wherein the at least one electrical engine is mounted to the carrier beam.

US Pat. No. 10,940,957

HAPTIC ALERT MECHANISM FOR ALERTING AN AIRCRAFT PILOT, AND AN AIRCRAFT

AIRBUS HELICOPTERS, Mari...

1. A haptic alert mechanism configured to exert a force on a lever in order to indicate tactilely that an operating limit has been exceeded, the mechanism comprising an actuator;wherein the mechanism further comprises:
at least one arm of a movable stopping piece, the arm being caused to move in rotation about an axis of rotation by the actuator; and
a spring box provided with an enclosure inside which a pre-stressed torsion spring is arranged, the spring box being mounted to be movable in rotation about the axis of rotation, the enclosure including at least one lug that is mounted to be movable in rotation about the axis of rotation, the enclosure having a front flank, the torsion spring extending from a first end that is secured to the enclosure to a finger, the finger passing through an elongate orifice in the front flank and extending in part outside the enclosure by forming a movable, resilient stop that is overridable and adjustable, the mechanism having a rest position for the finger about the axis of rotation in the absence of any force exerted on the finger by the lever, which rest position is adjustable by moving the stopping piece, the rest position representing the operating limit when the lug is in contact with the at least one arm, the finger being movable in the orifice by compressing the torsion spring when the lever exerts a force on the finger with a view to overriding the operating limit.

US Pat. No. 10,919,613

VEHICLE WITH A FOLDABLE FAIRING INTEGRATED FOOTSTEP UNIT

AIRBUS HELICOPTERS DEUTSC...

1. A vehicle with a fairing and a sliding door that is glidingly mounted to the vehicle, wherein the sliding door is associated with a foldable fairing integrated footstep unit, and wherein the foldable fairing integrated footstep unit comprises:an outer shell that is integrated into the fairing of the vehicle, the outer shell comprising an exterior surface that creates in closed state of the foldable fairing integrated footstep unit an aerodynamic surface with the fairing,
wherein an unfolding and folding unit connects the outer shell to the vehicle, the unfolding and folding unit comprising:
a sliding mechanism that is adapted for being engaged by the sliding door at least during an opening gliding movement and a closing gliding movement of the sliding door, and
a guiding link that connects the outer shell to the sliding mechanism;
the unfolding and folding unit being provided for unfolding the foldable fairing integrated footstep unit into an opened state during the opening gliding movement of the sliding door and for folding the foldable fairing integrated footstep unit into the closed state during the closing gliding movement of the sliding door.

US Pat. No. 10,871,013

LOAD TRANSFER INTERFACE FOR A VEHICLE DOOR, IN PARTICULAR FOR AN AIRCRAFT CABIN DOOR

AIRBUS HELICOPTERS DEUTSC...

1. A load transfer interface for a pressurized vehicle door that comprises an outer skin and a plurality of beams spaced parallel and connected to the outer skin, wherein the outer skin and the plurality of beams define a vehicle door plane, each beam having at least two door stop fittings to transfer pressure loads from the vehicle door to a vehicle structural frame,wherein the plurality of beams are arranged in parallel and the door stop fittings are rotatable in a rotation plane, substantially parallel to the vehicle door plane,
each of the door stop fittings being mounted in a non-rotatable manner to an actuating lever, each actuating lever connected by a lateral linkage to at least another of the door stop fittings of another of the beams, each lateral linkage connected to at least two door stop fittings from two different beams, each lateral linkage arranged in parallel, the lateral linkage providing mechanical linkages actuatable via a handle,
the handle being rotatable so that rotation of the handle results in movement of the lateral linkages into movement directions, which force the door stop fittings arranged in parallel to rotate.

US Pat. No. 10,829,212

RETRACTION / EXTENSION OF A LANDING GEAR IN AN AIRCRAFT

AIRBUS HELICOPTERS DEUTSC...

1. A telescoping strut for extension/retraction/damping of a landing gear in an aircraft, the telescoping strut comprising at least an extension chamber, a retraction chamber and a damper chamber, each of the extension, retraction and damper chambers being formed by tubes slidably telescoping along a longitudinal direction of the telescoping strut, the telescoping strut comprising two attachment connectors for securing the telescoping strut to the landing gear and to a body structure of the aircraft,wherein the tubes comprise an upper medium tube and an innermost lower tube forming together a sealed outer shell for the extension chamber that is central and pre-pressurized, the central extension chamber lengthening centrally in the telescoping strut between a top end of the upper medium tube and a bottom end of the innermost lower tube along the longitudinal direction; a top end of the innermost lower tube being slidably guided in an intermediate portion between ends of the upper medium tube along the longitudinal direction, the upper medium tube being rigidly secured to one of the attachment connectors and the innermost lower tube being rigidly secured to the other attachment connector;
the telescoping strut further comprising an outermost damping tube and a floating upper intermediate tube, an outer shell of the upper medium tube and an inner shell of the floating upper intermediate tube forming together the surrounding retraction chamber that is radially surrounding the central extension chamber locally, the telescoping strut having only one fluid input/output passage for fluid circulation from an hydraulic source in an hydraulic generation architecture of the aircraft to the surrounding retraction chamber for opposing an extension positive pressure in the central extension chamber so that the surrounding retraction chamber counteracts the extension positive pressure to provoke a longitudinal shortening of the central extension chamber operating retraction of the telescoping strut when the surrounding retraction chamber is fed through the fluid input/output passage with an overcoming fluid pressure overwhelming the extension positive pressure; and
the floating upper intermediate tube being slidably guided around the upper medium tube and being slidably guided in the outermost damping tube, the outermost damping tube being rigidly secured to one of the attachment connectors; the outermost damping tube and the floating upper intermediate tube forming together a first chamber that is pre-pressurized at a first pre-loaded pressure; the outermost damping tube and the innermost lower tube forming together a second chamber that is pre-pressurized with a fluid at a second pre-loaded pressure and that is selectively communicable with the first chamber.

US Pat. No. 10,829,214

ELASTIC TORSION ELEMENT FOR CONNECTING A ROTOR BLADE TO A ROTOR HUB OF A ROTOR

AIRBUS HELICOPTERS DEUTSC...

1. An elastic torsion element for connecting a rotor blade to a rotor hub of a rotor, the elastic torsion element comprising at least two elastically deformable plates, wherein each one of the at least two elastically deformable plates comprises fiber reinforced polymers, wherein respective fibers of the fiber reinforced polymers of each one of the at least two elastically deformable plates are at least arranged along one of a first and a second dominant fiber directions, wherein the first dominant fiber direction crosses the second dominant fiber direction in a predetermined fiber direction crossing region, and wherein the elastic torsion element comprises an integrated elastic lead-lag hinge that is formed at the predetermined fiber direction crossing region.

US Pat. No. 10,723,450

PASSIVE PITCH ANGLE ADJUSTMENT APPARATUS

AIRBUS HELICOPTERS DEUTSC...

1. A passive pitch angle adjustment apparatus for a rotor with rotor blades that rotate around a rotor axis in a rotor plane, comprising:a first lever that is connected to a first rotor blade of the rotor blades and rotates the first rotor blade around a first pitch axis;
a second lever that is connected to a second rotor blade of the rotor blades and rotates the second rotor blade around a second pitch axis;
characterized by first and second rods that mechanically link the first and second levers via a central point that is located outside the rotor plane; and
a central rod that connects the central point with a base point that is located in a longitudinal direction of the rotor axis, wherein a change of a first pitch angle of the first rotor blade in reaction to aerodynamic forces causes a first rotation of the first rotor blade around the first pitch axis, and wherein the first lever through the first rod, the second rod, and the second lever in connection with the central rod adjusts a second pitch angle of the second rotor blade through a second rotation of the second rotor blade with the second lever around the second pitch axis.

US Pat. No. 10,527,000

AIRCRAFT WITH A HOT AIR EXHAUST THAT COMPRISES TWO PIVOTALLY MOUNTED EXHAUST SECTIONS

AIRBUS HELICOPTERS DEUTSC...

1. An aircraft with a fuselage that defines at least one drive system accommodating region, the drive system accommodating region accommodating at least one engine that generates a hot air flow in operation of the aircraft, wherein at least one hot air exhaust is provided for exhausting the hot air flow, the at least one hot air exhaust comprising at least one first exhaust section and at least one second exhaust section, the at least one second exhaust section mounted in a rotatable manner to the at least one first exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided, the actuating member adapted for applying a turning moment to the at least one second exhaust section in operation of the aircraft in order to displace a longitudinal axis of the at least one second exhaust section with respect to a longitudinal axis of the at least one first exhaust section by a predetermined displacement angle;wherein the actuating member is adapted for applying a turning moment on the basis of a current operation temperature of the actuating member, wherein the actuating member comprises a temperature-sensitive actuator equipped with an expandable fluid, gas or rigid material adapted for expanding if the current operation temperature of the actuating member increases.