Patents Assigned to Eurocopter
  • Turboengine air intake provided with a controlled filter system
    Patent number: 8361209
    Abstract: An air intake (2) for a turbine engine, and a method implemented by the air intake (2) are disclosed. The air intake (2) is provided with a filter system (10) including foldable filter elements (11), arranged at the inlet section (3) of the air intake (2). In addition, the filter system (10) includes control elements (11) that exert a force along a first direction (Y) on the free end (11?) of the foldable filter elements (11) to adjust the filtering power of the filter system (10), guide members (12) of the filter system (10) serving to guide the movement of the free end (11?) induced by the control elements (13).
    Type: Grant
    Filed: November 26, 2008
    Date of Patent: January 29, 2013
    Assignee: Eurocopter
    Inventor: Marc Colaprisco
  • Door lock for doors of aircraft, especially of helicopters
    Patent number: 8360483
    Abstract: The invention relates to a door lock comprising a door catch system for double door-type helicopter doors that can, when being closed, additionally be displaced perpendicularly to the plane of the door opening into the closed position (flush fitting). Said door lock comprises a catch element (30) associated with the latch element (31) and actively linked therewith, said catch element maintaining the door ‘caught’ directly in front of its locked position when the door is manually closed until the door is translated to its final closed position via the latch element (31).
    Type: Grant
    Filed: November 26, 2007
    Date of Patent: January 29, 2013
    Assignee: Eurocopter Deutschland GmbH
    Inventors: Klaus Koppel, Alexander Rowbut
  • Method of assisting piloting, piloting assistance means, and a piloting assistance device for a rotorcraft using said piloting assistance means to implement said piloting assistance method
    Patent number: 8342455
    Abstract: The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).
    Type: Grant
    Filed: June 14, 2010
    Date of Patent: January 1, 2013
    Assignee: EUROCOPTER
    Inventors: Jean-Marie Allieta, Bruno Chaduc, Jean-Francois Lafisse, Olivier Honnorat
  • Energy adsorber device that adapts automatically to the weight it supports
    Patent number: 8342300
    Abstract: The present invention relates to an energy absorber device (1) for damping the movements of a load support (2) relative to a stationary base (3), the load support being connected to the stationary base (3) via a hydromechanical connection. The device includes automatic and self-contained setting elements serving firstly to adapt under static conditions to the weight of the loads supported by the support (2), and secondly under dynamic conditions, e.g. in the event of a sudden movement of the crash type, to subject the subassembly including the support (2) and the loads to acceleration or deceleration values that are below a threshold value.
    Type: Grant
    Filed: November 7, 2008
    Date of Patent: January 1, 2013
    Assignee: Eurocopter
    Inventor: Gérard Guillon
  • FATIGUE MANAGEMENT SYSTEM
    Publication number: 20120323410
    Abstract: A fatigue management system for determining the individual life of an aircraft, particularly the individual life of components of a helicopter, by means of an on board virtual load sensor and a method of operating a fatigue management system.
    Type: Application
    Filed: June 12, 2012
    Publication date: December 20, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventors: Stefan Bendisch, Falk Hoffmann, Antoine Rabourdin
  • NAVIGATION SYSTEM FOR AN AIRCRAFT AND METHOD OF OPERATING SUCH A NAVIGATION SYSTEM
    Publication number: 20120316724
    Abstract: The invention relates to an onboard navigation system for an aircraft (10), particularly a navigation system for a helicopter and to a method of operating such a navigation system allowing improvement of safety of an aircraft and its crew.
    Type: Application
    Filed: June 1, 2012
    Publication date: December 13, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventor: Grégoire Verlut
  • TECHNICAL METHOD, A MAINTENANCE DEVICE, AND AN AIRCRAFT
    Publication number: 20120316832
    Abstract: The present invention relates to a maintenance method for a piece of equipment (2) of a vehicle (1) including an anti-vibration system (3). In the method, a device (10) determines a first number (D1) of hours of operation of said equipment (2) while said anti-vibration system (3) was operating in a normal mode of operation and a second number (D2) of hours of operation while said anti-vibration system (3) was operating in a degraded mode of operation. Said second number (D2) is then converted into a third number (D3) by applying a predetermined conversion relationship. Under such circumstances, action is taken on said equipment (2) when the sum of the first number (D1) plus the third number (D3) reaches a predetermined threshold (D0).
    Type: Application
    Filed: May 31, 2012
    Publication date: December 13, 2012
    Applicant: EUROCOPTER
    Inventor: Richard Piré
  • PILOTING ASSISTANCE SYSTEM AND AN AIRCRAFT
    Publication number: 20120314034
    Abstract: The present invention relates to a piloting assistance system (10) for an aircraft (1) that is provided with determination means (20) for determining piloting information. The system comprises at least one display system (40) wearable on the head of a pilot, the display system (40) being provided with left display means (41) suitable for being viewed by a left eye of said pilot and right display means (42) suitable for being viewed by a right eye of said pilot, said determination means (20) including first processor means (21) for processing said information and second processor means (22) for processing said information, the processor means including stored instructions for causing said information to be displayed simultaneously and respectively on the left display means (41) and on the right display means (42).
    Type: Application
    Filed: June 4, 2012
    Publication date: December 13, 2012
    Applicant: EUROCOPTER
    Inventors: Adrien Ott, Serge Germanetti, Pierre Boudier
  • T-PROFILE JUNCTION OF COMPOSITE MATERIALS
    Publication number: 20120315431
    Abstract: A T-profile junction of composite materials with a T-profile (1) and a base plate (2). The T-profile (1) comprises a web (3) and at least two flanges (4-7). The flanges (4-7) are angled with respect to the web (3). A fillet (11, 12) is provided between the web (3) and each of the flanges (4-7). At least one tension bar (16, 32, 40, 50, 65) is releasably mounted to the base plate (2). The web (3) is provided with at least one passage (23, 24, 33, 34). Said at least one tension bar (16, 32, 40, 50, 65) reaches through the at least one passage (23, 24, 33, 34). The at least one tension bar (16, 32, 40, 50, 65) is biased against the base plate (2) and the respective flanges (5, 6) of said T-Profile (1).
    Type: Application
    Filed: June 4, 2012
    Publication date: December 13, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventor: Ahmet-Ender Cetiner
  • Supporting strut for supporting an intermediate deck that is arranged in an aircraft fuselage
    Patent number: 8328138
    Abstract: A supporting strut for supporting an intermediate deck (2) that is arranged in an aircraft fuselage (1), includes a hollow cylindrical rod body (3) that includes a fiber reinforced material, with the two ends of the rod body (3) being designed as attachment sections for detachable attachment to the aircraft fuselage (1) or to the intermediate deck (2), wherein the rod body (3) includes at least one first reinforcement layer (10a) made from a carbon fiber fabric with an identical number of warp- and weft threads in 45° alignment or 90° alignment, as well as at least one second reinforcement layer (10b, 10c) made from a carbon fiber fabric including a higher number of warp threads than weft threads in 0° alignment, as well as a final layer including glass fiber, which together with artificial resin form a compact fiber reinforced material.
    Type: Grant
    Filed: May 5, 2009
    Date of Patent: December 11, 2012
    Assignee: Eurocopter Deutschland GmbH
    Inventors: Anton Bergmann, Marinus Sedlmeier
  • Connection element for power transmission between a flap actuator and a flap mounted on a wing of an aircraft so as to swivel
    Patent number: 8328134
    Abstract: A connection element for power transmission between a flap actuator and a flap mounted swivelably on a wing of an aircraft includes a first section joined to the flap actuator and a second section joined to the flap. The first and second sections are formed by a strap made of a fiber composite material.
    Type: Grant
    Filed: March 13, 2008
    Date of Patent: December 11, 2012
    Assignee: Eurocopter Deutschland GmbH
    Inventor: Alois Wagner
  • TWIST MECHANISM FOR TWISTING A ROTOR BLADE FOR A ROTORCRAFT, AND A BLADE
    Publication number: 20120308384
    Abstract: A twist mechanism for twisting a rotary-wing blade (2). A twist member (8) is movable by an actuator (11) of the centrifugal force type, which twist member has at least one flyweight (14) for driving a rotary member (13) about a pivot axis (A). The flyweight (14) is radially movable on the rotary member (13) by movement means. The centrifugal force FC to which the flyweight (14) is subjected as a result of the blade (2) being caused to rotate induces drive torque CM for causing the rotary member (13) to pivot, thereby causing the twist member (8) to be moved. The twist member (8) is in engagement with the blade (2) at its free end and is connected to the rotary member (13) via remote mechanical transmission means (12).
    Type: Application
    Filed: May 23, 2012
    Publication date: December 6, 2012
    Applicant: EUROCOPTER
    Inventor: Jean-Francois Hirsch
  • METHOD OF DETERMINING THE STATIC FORCE DEVELOPED BY A SERVO-CONTROL
    Publication number: 20120303296
    Abstract: The present invention relates to a method of determining the static force developed by a servo-control (10) having an actuator (20) and a hydraulic distributor control valve (30), said actuator (20) including at least one cylinder (21) and a slidable element (25).
    Type: Application
    Filed: May 22, 2012
    Publication date: November 29, 2012
    Applicant: EUROCOPTER
    Inventor: Jean-Romain Bihel
  • ELECTRICAL POWER SUPPLY DEVICE FOR ELECTRICALLY POWERING AT LEAST ONE ITEM OF EQUIPMENT ON A ROTARY ROTOR OF AN AIRCRAFT, AND AN AIRCRAFT
    Publication number: 20120299450
    Abstract: An electrical power supply device (10) for electrically powering equipment on a rotary rotor (2) of an aircraft (1), which rotor is driven by a shaft (5), said device (10) comprising a removable stick (11). The stick (11) includes an upper alternator (20) and an upper tube (12) secured to said shaft (5) so as to be constrained in rotation therewith, said upper alternator (20) having a plurality of upper coils (21) fastened to an upper inside peripheral surface (12?) of said upper tube (12), said stick (11) having a rod (13) carrying an upper permanent magnet (22), said device (10) having a mechanism (30) so that said rod (13) and said upper tube (12) move with distinct rotary movements, said mechanism (30) having connection means (31) so as to be connectable to a reference member (8, 9) of an aircraft (1).
    Type: Application
    Filed: May 21, 2012
    Publication date: November 29, 2012
    Applicant: EUROCOPTER
    Inventors: Vincent Bourget, Serge Giordano, Nicolas Imbert, Charles Chuc
  • AIRCRAFT PROVIDED WITH A DEVICE FOR REDUCING VIBRATION, AND A METHOD THEREFOR
    Publication number: 20120298794
    Abstract: An aircraft (1) provided with a main gearbox (3) fastened to a load-bearing structure (2) via at least three suspension bars (5). An active vibration absorber (10) is fastened around each suspension bar (5), each vibration absorber (10) being provided with a first mass (11) connected to the associated suspension bar (5) via first resilient means (21), and with a second mass (12) connected to the first mass (11) via second resilient means (22), said vibration absorber (10) having a force generator (15) interposed between the first mass (11) and the second mass (12) and inputting a control force on being instructed by a control unit (16) as a function of information coming from at least one first measurement sensor (17) for sensing monitoring parameters for monitoring the associated suspension bar.
    Type: Application
    Filed: May 22, 2012
    Publication date: November 29, 2012
    Applicants: ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS - E.N.S.A.M., EUROCOPTER
    Inventors: Tomasz Krysinski, Francois Malburet
  • DEVICE AND A METHOD FOR CONSTRUCTING A FLIGHT PATH IN ORDER TO REACH A DESTINATION
    Publication number: 20120296499
    Abstract: A device (10) for defining a flight path (2) enabling an aircraft (1) to reach a destination (B), said device (10) including a digital terrain model (21) and a display screen (30), and being provided with generator means (15) for generating a flight path (2) including at least one flight segment (3) associated with a flying altitude. The device (10) includes a digital noise database (20) having volumes that are to be avoided, said device (10) having a computer (11) with a main memory (13) containing instructions for displaying on said display screen (30) and as an overlay on a first representation (31) of said terrain as provided by said digital terrain model (21): a second representation (41) of said volumes to be avoided; and a flight path (2) that has been generated by using said generator means (15).
    Type: Application
    Filed: May 16, 2012
    Publication date: November 22, 2012
    Applicant: EUROCOPTER
    Inventors: Alain Kirchhofer, Patrick Garcia, Francois Mandonnaud
  • DEVICE FOR LAUNCHING AND RECOVERING A DRONE, AND AN ASSOCIATED AIRCRAFT
    Publication number: 20120292430
    Abstract: A device (10) for launching and recovering a drone (5), the device being suitable for being fastened to an aircraft. The device includes docking means (20) for a drone (5), the docking means (20) being provided with securing/releasing means (30) for the drone (5), said docking means (20) being secured to flared guide means (40) for guiding the drone (5) towards said docking means (20).
    Type: Application
    Filed: May 2, 2012
    Publication date: November 22, 2012
    Applicant: EUROCOPTER
    Inventors: Laurence Ferrari, Francois Malburet, Georges Descombes
  • Leaktight frame for a window and a mechanical assembly provided with such a frame
    Patent number: 8312681
    Abstract: A leaktight frame (10) for a window (3) suitable for securing the window (3) to a carrier structure (2), has first and second sealing gaskets (11, 12) respectively suitable for being arranged on a first periphery (3?) of the window (3) and on a second periphery (2?) of the carrier structure (2), the frame (10) being provided with releasable holder elements (20) for clamping the first and second gaskets (11, 12) onto the window (3) and the carrier structure (2).
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: November 20, 2012
    Assignee: EUROCOPTER
    Inventor: Luc Mouton
  • Hollow fiber composite component and intermediate products
    Patent number: 8308882
    Abstract: A three-dimensional hollow fiber component includes a first sheet having first; second, third, fourth and fifth consecutive adjacent sheet sections, the first and fifth sections being end sections, the sheet shaped so as to surround a first chamber such that the first and fifth sections overlap to form a top wall of the first chamber and are stitched to each other by at least one seam and a second sheet having first, second, third, fourth and fifth adjacent consecutive sheet section, the first and fifth sections being end sections, the sheet sections shaped so as to surround a second chamber such that the first and fifth sections overlap to form a top wall of the second chamber and are stitched to each other by at least one seam.
    Type: Grant
    Filed: November 20, 2009
    Date of Patent: November 13, 2012
    Assignee: Eurocopter Deutschland GmbH
    Inventor: Christian Weimer
  • PASSING FROM A NON-SYNCHRONIZED STATE BETWEEN AN ENGINE AND A ROTOR TO A SYNCHRONIZED STATE
    Publication number: 20120277969
    Abstract: In order to regulate a power plant (105) having a gas generator (1) and a free turbine (3) to drive a rotary wing, a first speed of rotation (NTL) of the free turbine (3) is regulated on a first setpoint value (NTL*) equal either to a regulation term (NRc) or to a predetermined setpoint threshold (NTL*). The regulation term (NRc) is a function of a third speed of rotation (NR) of said rotary wing in accordance, where NRc=NR*(1?d), “d” representing a non-zero constant lying in the range 0 to 1.
    Type: Application
    Filed: April 5, 2012
    Publication date: November 1, 2012
    Applicant: EUROCOPTER
    Inventor: Régis Rossotto