Patents Assigned to Eurocopter
  • Blade for reducing the drag movements of said blade, and a method of reducing such a drag movement
    Patent number: 8297928
    Abstract: A blade (10) extending longitudinally from a root (11) of the blade (10) to a free end (12) of the blade (10), the blade (10) having a resonator (13) incorporated therein to reduce the drag movements (F1, F2) of the blade (10), the resonator (13) being provided with a solid and movable heavy element (30) and with resilient retaining element (20) secured to the heavy element (30) and to the blade (10). Furthermore, the resonator (13) includes guide element (40) in which the heavy element (30) is capable of oscillating (F1?, F2?) longitudinally, the guide element (40) being arranged in a longitudinal direction (D1) of the blade.
    Type: Grant
    Filed: June 24, 2009
    Date of Patent: October 30, 2012
    Assignee: Eurocopter
    Inventors: Thomas Manfredotti, Paul Cranga, Julien Guitton
  • ROTOR DAMPER DEVICE, AND AN ASSOCIATED ROTOR AND AIRCRAFT
    Publication number: 20120269630
    Abstract: A damper device (10) for a rotor (2) having a rotary ring (11) and a plurality of levers (12), each lever (12) extending from a first end (12?) connected to said ring (11) by a first mechanical connection (20) to a second end (12?) suitable for being hinged to a blade (4). The damper device (10) includes non-rotary damper means (30) secured to non-rotary fastener means (40) and to a non-rotary member (51) of an interface (50), said interface (50) being interposed between said non-rotary damper means (30) and said ring (11) to convert a rotary movement of a blade (4) transmitted to a lever (12) into a movement in translation acting on said damper means (30).
    Type: Application
    Filed: April 5, 2012
    Publication date: October 25, 2012
    Applicant: EUROCOPTER
    Inventors: Elio Zoppitelli, Etienne Rampal
  • Method of determining and displaying flying indications and a flight indicator for implementing said method
    Patent number: 8295997
    Abstract: The present invention relates to a pilot assistance method for giving assistance in piloting a rotary wing aircraft, the method consisting in using a scale with collective pitch graduations that is movable on a display screen to indicate the position of the collective pitch, in determining the desynchronization pitch, in using a maximum limit value and a minimum limit value for the speed of rotation of the rotor, in transforming the maximum limit value and the minimum limit value in real time and as a function of physical flight parameters respectively into a bottom limit position and a top limit position for the collective pitch, and when a determined difference appears between the real value and the reference value Nr0 for the speed of rotation of the rotor, in displaying at least one item of corrective information about the adjustment of the collective pitch.
    Type: Grant
    Filed: March 11, 2010
    Date of Patent: October 23, 2012
    Assignee: Eurocopter
    Inventors: Karine De Bono, Michel Godard
  • Radial air intake device with integrated bypass for an air inlet
    Patent number: 8292978
    Abstract: A radial air intake device for an engine or a power unit that includes a ring-shaped filter for covering the radial air intake. The ring-shaped filter includes a first fixed part and a second mobile part which is movable with respect to the first fixed part through actuator elements, from a filtering position in which the whole radial air intake is covered by the ring-shaped filter, to a bypass position in which the second mobile part uncovers at least partly the radial air intake.
    Type: Grant
    Filed: March 18, 2010
    Date of Patent: October 23, 2012
    Assignee: Eurocopter Deutschland GmbH
    Inventor: Kornelius Krahl
  • HELICOPTER WITH CYCLOIDAL ROTOR SYSTEM
    Publication number: 20120256042
    Abstract: The invention is related to a helicopter (10) comprising a main rotor (12), a cycloidal rotor (14) and a rotating cylinder (18). The rotating cylinder (18) extends along a longitudinal axis of a tail boom (13). The cycloidal rotor (14) extends at least partly along said same tail boom (13) and rotates outside the rotating cylinder (18).
    Type: Application
    Filed: April 5, 2012
    Publication date: October 11, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventors: Andree Altmikus, Marius Bebesel
  • CONTROL LEVER FOR CONTROLLING A ROTARY WING, A MECHANICAL CONTROL SYSTEM INCLUDING SAID CONTROL LEVER, AND AN AIRCRAFT
    Publication number: 20120255386
    Abstract: A control lever (10) provided with a stick (11) extending axially from a stand (11?) towards grip means (11?) and with a carrier structure (20) for said stick (11) that is hinged about a first hinge axis (AX1) and about a second hinge axis (AX2). The control lever (10) includes phasing means (30) constrained to move in rotation with said stick (11) about said first hinge axis (AX1) and about said second hinge axis (AX2), said phasing means (30) comprising at least three main arms (31, 32, 33), each for controlling a respective power member (8?, 8?, 8??) that is connected to a set (6) of swashplates for controlling a rotary wing (2).
    Type: Application
    Filed: April 2, 2012
    Publication date: October 11, 2012
    Applicant: EUROCOPTER
    Inventors: Gèrard Couderc, Romuald Biest
  • Hybrid engine installation and a method of controlling such an engine installation
    Patent number: 8283796
    Abstract: A hybrid engine installation (200) includes drive element (204) suitable for driving a mechanical element (BTP, BTA) in rotation. In addition, the hybrid engine installation is remarkable in that it includes at least one gas turbine (253, 254) and at least one electric motor (201) mechanically linked to the drive element (204) to drive it in rotation.
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: October 9, 2012
    Assignee: Eurocopter
    Inventor: Bernard Certain
  • Mechanical device for combining first and second control orders, and an aircraft provided with such a device
    Patent number: 8282035
    Abstract: The present invention relates to a mechanical device (1) suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure (10) suitable for being fastened to a support (5) by at least one main fastener pin (13) about which said carrier structure (10) is capable of performing a pivoting movement. In addition, the device includes at least one connection lever (20, 30) per rotary assembly, and at least one secondary fastener pin (25, 35) per connection lever (20, 30), said secondary fastener pin (25, 35) being secured firstly to said carrier structure (10) and being fastened secondly by rotary means (26, 36) to the connection lever (20, 30).
    Type: Grant
    Filed: June 2, 2010
    Date of Patent: October 9, 2012
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Romuald Biest, Guillaume Franchini
  • Absorbent covering
    Patent number: 8282085
    Abstract: An absorbent covering (1) has high damping power, secured on a structure (2) and includes a dissipater mesh made up of a plurality of dissipating elements (3) and of nodes (4) each having its bottom end (4?) secured on the structure (2). In remarkable manner, the bottom ends (4?) of the nodes (4) project from the dissipating elements (3) so as to leave an empty space (5) between the dissipating elements (3) and the structure (2), the absorbent covering (1) including main absorbent elements (6) arranged in the empty space (5), each of the main absorbent elements (6) being secured firstly to a bottom face (3?) of a dissipating element (3) and secondly to the structure (2).
    Type: Grant
    Filed: December 10, 2007
    Date of Patent: October 9, 2012
    Assignee: Eurocopter
    Inventor: Thomas Manfredotti
  • NOISE AND PERFORMANCE IMPROVED ROTOR BLADE FOR A HELICOPTER
    Publication number: 20120251326
    Abstract: A noise reduced and performance improved rotor blade (1) for a helicopter. The blade has three aerodynamic sections (5, 6, 7) along the blade span between a leading edge (8) and a trailing edge (9). An inner rectangular or tapered section (5) next to a blade root for said blade's connection to a rotor hub rotating about a rotor axis of said helicopter. A middle section (6) is adjacent to the inner section (5) and opposed to the blade root. The middle section (6) is forward swept over a distance along the span of the blade (1). An outer section (7) lies between the middle section (6) and the blade tip (11). The outer section (7) is back swept along a further part of the span of the blade (1). The outer section (7) includes a parabolic shape towards the free end of the blade tip (11).
    Type: Application
    Filed: February 7, 2012
    Publication date: October 4, 2012
    Applicant: EUROCOPTER DEUTSCHLAND GMBH
    Inventors: Dieter Schimke, Stefanie Link, Sascha Schneider
  • METHOD AND A DEVICE FOR ASSISTING THE PILOTING OF AN AIRCRAFT, AND AN AIRCRAFT
    Publication number: 20120253560
    Abstract: A method of assisting the piloting of an aircraft (1) comprising a first rotor (5) having a plurality of first blades (6) with a first variable collective pitch, and a second rotor (7) having a plurality of second blades (8) with a second variable collective pitch. According to the method, a computer determines a power limit curve (70) and displays said limit curve (70) in a diagram (60) to inform the pilot of the first and second collective pitch margins available before reaching the limits of at least one operating rating of the power plant of the aircraft.
    Type: Application
    Filed: March 26, 2012
    Publication date: October 4, 2012
    Applicant: EUROCOPTER
    Inventors: Alban Corpron, Stéphane Petit
  • WEATHERPROOF SURROUND FOR SAFELY JETTISONING A REMOVABLE PANEL
    Publication number: 20120248713
    Abstract: A weatherproof surround, for a jettisonable panel (5) of a vehicle (1) such as a helicopter, possesses four confinement flanges (17-20) integrally formed with a projecting ridge for spring-clipping a corresponding locking strip. Longitudinal foldable shoulders connect the confinement flanges (17-20) to a central trunk (13). Each confinement flange (17-20) can be folded back through pivot angle (31) of at least 90°.
    Type: Application
    Filed: March 27, 2012
    Publication date: October 4, 2012
    Applicant: EUROCOPTER
    Inventor: Nicolas Raspic
  • EMERGENCY PILOTING BY MEANS OF A SERIES ACTUATOR FOR A MANUAL FLIGHT CONTROL SYSTEM IN AN AIRCRAFT
    Publication number: 20120241563
    Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
    Type: Application
    Filed: March 12, 2012
    Publication date: September 27, 2012
    Applicants: EUROCOPTER DEUTSCHLAND GMBH, EUROCOPTER
    Inventors: Bruno Chaduc, Patrick Hellio, Bernard Gemmati, Karsten Krok
  • ELECTRICAL POWER SUPPLY DEVICE FOR A RESISTOR ELEMENT, AND AN ELECTRICAL SYSTEM PROVIDED WITH SAID DEVICE AND SAID RESISTOR ELEMENT
    Publication number: 20120241434
    Abstract: An electrical power supply device (10) provided with electrically-conductive metal electrical connection means (12) secured to an electrical power supply wire (11), said connection means (12) comprising a first portion (13) connected to said power supply wire (11), followed by a second portion (14) that extends longitudinally and that is suitable for being permanently bonded to a resistor element (3) that is provided with a plurality of electrically-conductive layers (4). Said second portion (14) is tapering, presenting thickness (e) that decreases, starting from said first portion (13), said second portion (14) having at least one slot (15) passing through said second portion (14) in said direction in elevation.
    Type: Application
    Filed: March 21, 2012
    Publication date: September 27, 2012
    Applicant: EUROCOPTER
    Inventors: André Amari, Daniel Brunner, Jacques Gaffiero, Cédric Lanouette
  • CYCLIC STICK FOR MECHANICALLY TRANSMITTING COMMANDS FOR CONTROLLING A ROTORCRAFT, THE STICK HAVING A LEVER ARM THAT IS AMPLIFIED SELECTIVELY IN THE EVENT OF AN EMERGENCY
    Publication number: 20120234985
    Abstract: The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick (1) that is mounted to tilt (B1, B2) on a carrier structure (4) and that is in engagement with remote mechanical transmission members (2, 3). The stick (1) is arranged as a telescopic member provided with locking means (20) for locking it in a normal-use retracted position, and is equipped with deployment means (21). Unlocking of the locking means (20) and use of the deployment means (21) depend on an assistance device (17) associated with the stick (1) being in a defective state. In the event of such a defective state being detected, the stick (1) is suitable for being deployed so as to increase the comfort of the pilot while manipulating it.
    Type: Application
    Filed: March 5, 2012
    Publication date: September 20, 2012
    Applicant: EUROCOPTER
    Inventors: Romuald Biest, Robert Convers
  • VEHICLE PANEL PROVIDED WITH A MOVABLE WINDOW, AND AN ASSOCIATED VEHICLE
    Publication number: 20120227325
    Abstract: A vehicle panel (2) having a body (3) that extends longitudinally and in elevation, said body (3) having a movable window (10) and guide means (15) for guiding movement of said window (10) relative to the body (3), said window (10) having a frame (11) within which there is a transparent surface (12). The window (10) includes release means (30) for manually releasing the window (10) from the body (3) in order to provide an emergency exit, the release means (30) co-operating with the guide means (15).
    Type: Application
    Filed: March 5, 2012
    Publication date: September 13, 2012
    Applicant: EUROCOPTER
    Inventors: Xavier Diamant, Jean-Luc Remy, Eric Lambert, Cédric Cristiano
  • METHOD OF MEASURING HEIGHT AND DETECTING OBSTACLES, A RADIOALTIMETER, AND AN AIRCRAFT
    Publication number: 20120229325
    Abstract: A radioaltimeter (5) having a signal generator-receiver (10) and signal transceiver means (20) connected to the generator-receiver (10), and a display member (30), said transceiver means (20) comprising a transceiver main member (21) for sending a signal towards a ground (S) in order to determine the height (H) between said main member (21) and said ground (S), said display member (30) having main display means (31) for displaying said height (H). Furthermore, the radioaltimeter (5) includes switch means (40) together with a control unit (50), and secondary display means (32) of said display member (30).
    Type: Application
    Filed: March 7, 2012
    Publication date: September 13, 2012
    Applicant: EUROCOPTER
    Inventor: Herve Dutruc
  • FASTENER DEVICE, A SEAT PROVIDED WITH SAID DEVICE, AND A VEHICLE
    Publication number: 20120217368
    Abstract: A fastener device (10) for fastening a load to a rail (4) that is provided with a slideway (4?) defined by a bottom wall (5), two side walls (6), and a top wall (7) including a succession of wide slots (8) and of narrow slots (9), said fastener device (10) comprising a base (20) and two shoes (30) suitable for being inserted in said wide slots (8) and for co-operating with the top wall (7) in a narrow slot (9) by shape interference. The device further comprises first and second slides (31, 32), each including one of said two shoes (30), spacer means (40) for spacing apart said first and second slides (31, 32), detector means (50) for detecting a rail (4?), approach means (60) for causing said first and second slides (31, 32) to approach each other, and blocking means (70) for longitudinally blocking said base (20).
    Type: Application
    Filed: February 13, 2012
    Publication date: August 30, 2012
    Applicant: EUROCOPTER
    Inventors: Eric Zunino, Matthias Harer
  • METHOD OF OPTIMIZING THE LOADING OF LOADS IN A VEHICLE
    Publication number: 20120221235
    Abstract: A method of determining the locations of loads in a vehicle in such a manner as to ensure mission safety in terms of loads being retained in the aircraft. On the basis of vehicle parameters, the anchor points available in this type of vehicle for retaining the loads are identified. As a function of the available loading volume(s), a possible loading configuration is calculated using at least some of the available anchor points, at least some of the retaining means, and the characteristics of the loads. The forces that might be exerted on the selected anchor points are verified as being less than maximum limits. The calculated loading configuration is confirmed, otherwise a new loading configuration is calculated.
    Type: Application
    Filed: February 13, 2012
    Publication date: August 30, 2012
    Applicant: EUROCOPTER
    Inventors: Pierre PrudHomme-Lacroix, Laurence Maille
  • Variable damping of haptic feedback for a flight-attitude changing linkage of an aircraft
    Patent number: 8240617
    Abstract: The present invention relates to haptic feedback for operating at least one manual flight control device (21) for controlling the cyclic pitch of the blades (5) of a rotary wing (4) of a hybrid helicopter (1) via power assistance (27). Said operations of said control device (21) are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter (1) in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member (20) between its minimum and maximum thrust values (23, 22).
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: August 14, 2012
    Assignee: Eurocopter
    Inventors: Romuald Biest, Bernard Gemmati, Julien Pruss