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Airbus Helicopters Deutschland Gmbh patents


Recent patent applications related to Airbus Helicopters Deutschland Gmbh. Airbus Helicopters Deutschland Gmbh is listed as an Agent/Assignee. Note: Airbus Helicopters Deutschland Gmbh may have other listings under different names/spellings. We're not affiliated with Airbus Helicopters Deutschland Gmbh, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "A" | Airbus Helicopters Deutschland Gmbh-related inventors


Seat bench device with a seat bench component and at least one restraining unit

A seat bench device with a seat bench component and at least one restraining unit. The seat bench component comprising a seating surface and a backrest, and the at least one restraining unit comprising a harness for restraining a seat bench occupant on the seat bench component, wherein at least two guide elements are provided and wherein the at least one 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 operating position, in which the harness is operational for buckling up of a seat bench occupant.. ... Airbus Helicopters Deutschland Gmbh

Aircraft with an airframe that comprises a load carrying framework

An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. ... Airbus Helicopters Deutschland Gmbh

Aircraft with an airframe and at least one electrically powered thrust producing unit

An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.. . ... Airbus Helicopters Deutschland Gmbh

Actuatable emergency exit door and an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door

An actuatable emergency exit door with a door actuating device that comprises at least two connection rods that are pivotally mountable to an associated structural frame that is adapted for accommodating the actuatable emergency exit door in closed state, the at least two connection rods being provided for enabling an opening movement of the actuatable emergency exit door with respect to the associated structural frame during opening, wherein at least one door-mounted goose neck-shaped structure is mountable to the associated structural frame for 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. The invention is further related to an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door.. ... Airbus Helicopters Deutschland Gmbh

Aircraft with a plurality of aircraft doors

An aircraft with a plurality of aircraft doors, each aircraft door comprising at least one lock lever that is provided for engaging a counterpart in an engaged state for locking a respective aircraft door relative to the aircraft, wherein a real-time monitoring device is provided 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.. . ... Airbus Helicopters Deutschland Gmbh

Device for three-dimensionally positioning a coupling component and actuator system

The invention pertains to a device for 3-dimensionally positioning a coupling component, which forms part of an actuator-driven coupling structure, wherein said device comprises at least a first coupling element that extends in a first longitudinal direction and can be bidirectionally displaced along its first longitudinal direction by means of a first actuator, a second coupling element that extends in a second longitudinal direction and can be bidirectionally displaced along its second longitudinal direction, which extends orthogonal to the first longitudinal direction, by means of a second actuator, and a lever with a longitudinal lever direction that is mounted pivotably about a pivoting axis, which divides the lever into a work arm and a power arm. The longitudinal lever direction of the lever either extends along the first longitudinal direction and its work arm is on its end fixed on the second coupling element such that it can be pivoted about the second longitudinal direction or the longitudinal lever direction of the lever extends along the second longitudinal direction and its work arm is on its end fixed on the first coupling element such that it can be pivoted about the first longitudinal direction. ... Airbus Helicopters Deutschland Gmbh

Rotary wing aircraft with a structural arrangement that comprises an electrically conductive connection

A rotary wing aircraft that comprises 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, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.. . ... Airbus Helicopters Deutschland Gmbh

Adjustment of track and balance of a multi-blade rotor

A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is 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 predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.. . ... Airbus Helicopters Deutschland Gmbh

Rotorcraft with cowling able to rotate and translate relative to the fuselage

A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling.. . ... Airbus Helicopters Deutschland Gmbh

Aircraft with an emergency floatation system

An aircraft with an emergency flotation system, the emergency flotation system being activated upon an emergency landing of the aircraft on water, for preventing at least sinking of the aircraft, characterized in that a capsizing avoidance buoyancy system is provided, the capsizing avoidance buoyancy system being activated if predetermined activation criteria are satisfied and only after activation of the emergency flotation system upon an emergency landing of the aircraft on water, for preventing at least capsizing of the aircraft.. . ... Airbus Helicopters Deutschland Gmbh

Control system for controlling at least collective pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft

A control system for controlling at least collective pitch of rotor blades, of a multi-blade rotor with a rotor shaft in a rotary-wing aircraft, the control system comprising a non-rotating sliding sleeve that is mountable to the rotor shaft such that the non-rotating sliding sleeve is axially displaceable coaxially to an associated rotor axis on the rotor shaft, at least one actuator arm that is pivotally mounted to the non-rotating sliding sleeve and adapted for axially displacing the non-rotating sliding sleeve that is mounted to the rotor shaft upon activation, and at least one hinge support that is adapted for a hinged support of the at least one actuator arm.. . ... Airbus Helicopters Deutschland Gmbh

Rotary wing aircraft with a fuselage that comprises at least one structural stiffened panel

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 that is 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.. . ... Airbus Helicopters Deutschland Gmbh

Load transfer interface for a vehicle door, in particular for an aircraft cabin door

A load transfer interface for a vehicle door that comprises an outer skin and at least one beam that is connected to the outer skin, wherein the outer skin and the at least one beam define a vehicle door plane, the load transfer interface comprising at least one door stop fitting that is provided to transfer pressure loads from the vehicle door to an associated vehicle structural frame, the at least one door stop fitting being provided for rotation in an associated rotation plane, wherein the associated rotation plane is at least approximately parallel to the vehicle door plane. The invention is further related to an aircraft cabin door having such a load transfer interface, as well as to an aircraft having such an aircraft cabin door.. ... Airbus Helicopters Deutschland Gmbh

Aircraft with a fuselage and a composite tail boom

An aircraft with a composite tail boom that comprises at least partly a tubular tail boom cone with an outer skin and an inner skin, wherein 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.. . ... Airbus Helicopters Deutschland Gmbh

12/28/17 / #20170369159

Rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear

A rotary wing aircraft with a fuselage and a non-retractable skid-type landing gear that is mounted to the fuselage, the non-retractable skid-type landing gear comprising at least one landing box, the at least one landing box being provided with a skid-type landing base member and an associated box shell that delimits an internal volume of the at least one landing box.. . ... Airbus Helicopters Deutschland Gmbh

11/30/17 / #20170341742

Multi-blade rotor for a rotary wing aircraft

A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor 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 mounted to the associated rotor head.. . ... Airbus Helicopters Deutschland Gmbh

11/30/17 / #20170341738

Retraction / extension of a landing gear in an aircraft

A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. ... Airbus Helicopters Deutschland Gmbh

11/30/17 / #20170341322

Method of correcting an inappropriate countersink in a composite component

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; arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; 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.. . ... Airbus Helicopters Deutschland Gmbh

11/16/17 / #20170327200

Rotary wing aircraft with an interface frame joining the fuselage tail boom and the tail cone

A rotary wing aircraft comprising a fuselage tail boom, a tail cone and an interface frame, the interface frame in turn having a connecting structure directly attached to the tail cone by means of a tail cone mechanical connection and a connecting sleeve fitting axially the fuselage tail boom, the connecting sleeve and the fuselage tail boom being directly attached by means of a one boom mechanical connection; the interface frame thereby joining the fuselage tail boom and the tail cone.. . ... Airbus Helicopters Deutschland Gmbh

10/26/17 / #20170305003

Extraction device for extracting a trim weight from a rotor blade

An extraction device for extracting a trim weight from a rotor blade, comprising a supporting tube that is at least partly provided with a female thread, and a threaded rod that is at least partially arranged in the supporting tube, wherein the threaded rod is coupled to a fixing element that is adapted for being detachably fixed to the trim weight and that is at least partially provided with a male thread which engages at least partially the female thread of the supporting tube, and wherein the threaded rod is at least partly plastically deformable.. . ... Airbus Helicopters Deutschland Gmbh

10/12/17 / #20170293712

Probabilistic load and damage modeling for fatigue life management

A fatigue life management system for determining a remaining fatigue life of a component of an aircraft. The fatigue life management system may generate probability density functions of minimum load, maximum load, and timeframe damage for predetermined time intervals based on selected flight data of the aircraft and regression models for probabilistic prediction of minimum load, maximum load, and timeframe damage of the component. ... Airbus Helicopters Deutschland Gmbh

10/05/17 / #20170283051

Method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor

A method of manufacturing a control cuff for a rotor blade of a hinge and bearingless rotor. The method comprises at least the steps of: manufacturing an outer shell, 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.. ... Airbus Helicopters Deutschland Gmbh

07/13/17 / #20170197709

Compound rotorcraft

A compound rotorcraft with a fuselage and at least one main rotor, 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 at least one propeller is provided and 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.. . ... Airbus Helicopters Deutschland Gmbh

06/22/17 / #20170175673

Aircraft with a hot air exhaust that comprises two pivotally mounted exhaust sections

An aircraft with 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 generated hot air flow, the at least one hot air exhaust comprising at least one first exhaust section that is mounted in a rotatable manner to at least one second exhaust section via an associated off-axis swivel joint, wherein an actuating member is provided that is 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.. . ... Airbus Helicopters Deutschland Gmbh

05/04/17 / #20170121008

Maintenance step for a helicopter

A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, 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 being telescopically mounted to the first section.. . ... Airbus Helicopters Deutschland Gmbh

03/30/17 / #20170089443

Mounting arrangement for mounting a gear box of a rotorcraft to a fuselage of a rotorcraft

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 at least approximately opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means that are adapted to allow attachment of 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.. . ... Airbus Helicopters Deutschland Gmbh

03/02/17 / #20170057617

Deflector assembly for an aircraft

A deflector assembly for the rope/cable hanging from a hoist mounted on an aircraft (a). The deflector assembly has an adjoined anchorage that includes a socket face that internally has a sliding bearing in which is housed an innermost end, so that the innermost end is slidably guided relative to the adjoined anchorage to have one degree of freedom along a linear translation axis (lt). ... Airbus Helicopters Deutschland Gmbh

02/16/17 / #20170045391

Liquid level sensor with insulating region over the probe foot

A 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 surface of a liquid tank, wherein a capacitor region arranged to hold a liquid is defined between the outer capacitor tube and the inner capacitor tube, and wherein an insulating minimum distance is left between the inner capacitor tube base and the probe foot, the insulating minimum distance being sufficient to prevent a droplet of water on the probe foot from making contact with the inner capacitor tube.. . ... Airbus Helicopters Deutschland Gmbh

02/09/17 / #20170037927

Vibration isolating device for an elastic coupling of two components

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 and the second elastically deformable plate comprising a second curvature, wherein the first and second curvatures are respectively located in a region between the at least two separate connecting points and arranged such that a gap is defined between the first and second elastically deformable plates.. . ... Airbus Helicopters Deutschland Gmbh

02/02/17 / #20170028698

Method for joining thermoset components

A method for joining one or more first-type thermoset components to a second-type thermoset component, each first-type thermoset component being manufactured by providing an uncured starting thermoset component on which a thermoplastic material layer is placed, such that an interpenetrating network forms between the thermoset polymer of the starting thermoset component and the corresponding thermoplastic material layer when each first-type thermoset component is cured; and each first-type thermoset component being then placed on an uncured second-type thermoset component so that when the latter is cured, a further interpenetrating network forms between each thermoplastic material layer and the thermoset polymer of the second-type thermoset component; this results in a strong joint between the first-type and the second-type thermoset components.. . ... Airbus Helicopters Deutschland Gmbh

01/26/17 / #20170021791

Energy absorbing system for absorbing energy of an object in a vehicle in a crash situation

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. A mass-dependent self-adjusting mechanism is provided, 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.. ... Airbus Helicopters Deutschland Gmbh

01/05/17 / #20170001710

Airfoils for rotor blades of rotary wing aircrafts

An airfoil for a rotor blade of a rotary wing aircraft, the airfoil having a predetermined maximum thickness to chord ratio and comprising, between a leading edge and a trailing edge, an extrados and an intrados, the intrados being defined by predetermined intrados coordinate value pairs and the extrados being defined by predetermined extrados coordinate value pairs, wherein a maximum error of each one of the predetermined intrados coordinate value pairs and the predetermined extrados coordinate value pairs amounts to ±3%.. . ... Airbus Helicopters Deutschland Gmbh








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