Patents Assigned to Eurocopter
  • Patent number: 8606538
    Abstract: A method of preparing a test for an electronic system including a plurality of pieces of equipment interconnected by at least one communications link, in which method, in order to perform the test, use is made of a test bench appropriate for the electronic system under test, which test bench is connected to the system and controlled in application of a command sequence established from at least one informal functional specification; while preparing the test, the informal functional specification, the command sequence, and a link identifying the informal functional specification from which the command sequence was established are all recorded so that after execution of the command sequence and after the test results have been recorded, it is possible to read the link and identify unambiguously the informal functional specification that corresponds to the test results obtained.
    Type: Grant
    Filed: July 11, 2008
    Date of Patent: December 10, 2013
    Assignee: Eurocopter
    Inventors: Gilles Cahon, Christian Gaurel
  • Publication number: 20130316131
    Abstract: A skin-stiffener transition assembly (1) with a skin (4) and two L-shaped fiber-reinforced fabric preforms (2, 3) for a flange and a composite gusset filler (5) integrated between said skin (4) and said two L-shaped fiber-reinforced fabric preforms (2, 3). The skin (4) comprises two separate skin layers (7, 8) and the flange comprises a flange layer (6), each of said skin layers (7, 8) and said flange layer (6) being provided with cut outs (9, 10) along one side. Said skin layers (7, 8) and the flange layer (6) are attached to the composite gusset filler (5) with at least one of its cut-outs (9, 10) to one side of the essentially polygonal cross section of the composite gusset filler (5) and with at least one of its adjacent cut-outs (9, 10) to another side of the essentially polygonal cross section of the composite gusset filler (5).
    Type: Application
    Filed: May 9, 2013
    Publication date: November 28, 2013
    Applicant: Eurocopter Deutschland GMBH
    Inventor: Walter Oefner
  • Patent number: 8590843
    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: Grant
    Filed: March 5, 2012
    Date of Patent: November 26, 2013
    Assignee: Eurocopter
    Inventors: Romuald Biest, Robert Convers
  • Patent number: 8591197
    Abstract: A method of forming a rotorcraft blade is provided. A first support shaft (8) is secured to a rigid attachment filler (1) of the blade that is reversibly fastened to a mandrel (20). Fibers are placed around the assembly comprising said attachment filler (1) and said mandrel (20) in order to fabricate a spar of said blade, said spar (40) then including a succession of fiber layers (31, 32, 33) that hold said attachment filler (1) captive at the root (51) of said blade. Said first shaft (8) is removed after the spar has polymerized.
    Type: Grant
    Filed: October 14, 2011
    Date of Patent: November 26, 2013
    Assignee: Eurocopter
    Inventor: Remi Metivier
  • Patent number: 8579589
    Abstract: The invention provides a mechanism for attenuating torque pulsations between an engine (2) and a rotor (1) of a rotorcraft. Torsion means (5) are interposed between the driving and driven shafts and comprise a torsion shaft (6) axially engaged with the drive shaft (3) and the driven shaft (4) an inlet shaft (9) and an outlet shaft (10) respectively engaged with the drive and driven shafts (3, 4) a lever system (7) that extends radially relative to the torsion shaft (6) and that has the inlet and outlet shafts (9, 10) hinged thereto via points (11, 12) that are spaced apart; and a mass (8) carried by said lever arm (7) at its free end (13) radially farthest away from the axis along which the torsion shaft (6) extends.
    Type: Grant
    Filed: October 4, 2010
    Date of Patent: November 12, 2013
    Assignee: Eurocopter
    Inventors: Thomas Manfredotti, Jerome Chemin
  • Patent number: 8579587
    Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: November 12, 2013
    Assignee: Eurocopter
    Inventor: Gilles Herpin
  • Patent number: 8583295
    Abstract: A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.
    Type: Grant
    Filed: April 18, 2011
    Date of Patent: November 12, 2013
    Assignee: Eurocopter
    Inventors: Paul Eglin, Nicolas Queiras, André Barraco, Francois Malburet
  • Publication number: 20130294884
    Abstract: A device for monitoring the sealing state of a casing (2) of a transmission box (1) of a rotorcraft. An open airflow circuit (7) fitted with a suction generator member (10) is connected to a vent (5) of the casing (2). Regulator means (12) maintain stable suction in the airflow circuit (7) relative to a setpoint threshold (S), the regulator means being controlled in response to a pressure gauge (13) for measuring the suction generated inside the airflow circuit (7). The device is used on the ground to detect a source of leakage in the casing (2) and in flight to retain lubricant inside the casing (2) in the event of there being a source of leakage.
    Type: Application
    Filed: May 1, 2013
    Publication date: November 7, 2013
    Applicant: Eurocopter
    Inventor: Eurocopter
  • Patent number: 8577608
    Abstract: A method essentially comprising a step of storing each plot mesh. Each plot mesh receiving plots sent thereto by detector means and retaining in memory at least the altitude of the highest plot and the number of plots neighboring said highest plot in said mesh. The altitude and the number of plots neighboring are updated each time a new plot is sent to the plot mesh. A step of rejecting plot meshes is presenting a number of neighboring plots that is less than a predetermined rejection threshold value. The rejection threshold value is a function of the position of the mesh relative to the detector means. A step is preparing the local terrain elevation database from the plot meshes (M(i,j)) that are not rejected.
    Type: Grant
    Filed: November 23, 2010
    Date of Patent: November 5, 2013
    Assignee: Eurocopter
    Inventors: Marianne Gillet, Francois-Xavier Filias, Richard Pire
  • Patent number: 8568096
    Abstract: The present invention relates to a control and regulation method for a rotorcraft having at least one variable-pitch propulsive propeller driven by at least one power source, said method consisting in generating at least one mean pitch setpoint ?tcl* for the propeller(s) as a function of a thrust variation control order Tcl, wherein the method consists in defining a plurality of operating modes, including: a direct mode in which the value of the mean pitch value is a direct result of the control order Tcl; a forced mode in which the mean pitch is automatically forced to a calculated pitch value; a regulated mode in which the power of the propulsive propeller(s) is regulated as a function of a power setpoint from a pilot and of servo-controlling the mean pitch of the propeller(s); and a protected mode.
    Type: Grant
    Filed: April 29, 2010
    Date of Patent: October 29, 2013
    Assignee: Eurocopter
    Inventor: Paul Eglin
  • Patent number: 8561629
    Abstract: The present invention relates to a method of draining a tank (2) having a plate, the plate (12) including a canister (19) having an outer casing (20) provided with a base (19?) that is pressed against the plate (12), the base (19?) presenting at least one through orifice (21) suitable for being closed by a movable member (22) of the canister (19), the plate (12) carrying a pump (30) that co-operates with the canister (19) by actuating the movable member (22) to open the through orifice (21), during which method the pump (30) is removed from the canister (19) and then a fluid connector (50) is inserted to take the place of the pump (30), the fluid connector (50) co-operating with the canister (19) by actuating the movable member (22) to release the through orifice (21) in order to drain the tank (2) via the fluid connector (50).
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventor: Stéphane Mougin
  • Patent number: 8562075
    Abstract: An energy absorber element comprises an absorber portion having first and second distal ends and having a first elongate element and a second elongate element facing the first elongate element and connected to the second element solely at the first and second distal ends, a first anchor point secured to the first distal end of the absorber portion, and a second anchor point secured to the second distal end of the absorber portion, wherein each of the first and second elongate elements includes a succession of straight-line segments parallel to one another and at least one circularly-arcuate segment such that at least two successive straight-line segments are connected together by one of the at least one circularly-arcuate segment.
    Type: Grant
    Filed: April 28, 2009
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventors: Olivier Honnorat, Thomas Manfredotti
  • Patent number: 8563078
    Abstract: The present invention relates to a method of fabricating a painted substrate (30) using powder paint (21). The substrate is electrically insulating. The method includes the following steps performed in succession: a) a treatment coating (10) is placed on a mold (1), the treatment coating (10) includes at least one preparation layer having a release agent (15, 15?) in contact with the mold (1); b) the treatment coating (10) is electrostatically covered with powder paint (21) in such a manner that the powder paint (21) is attracted towards the mold (1) and is held against the treatment coating (10); c) the powder paint (21) is transformed at least in part in order to obtain a layer (20) of powder paint (21); and d) the substrate (30) is prepared on the layer (20) of powder paint to form the painted substrate.
    Type: Grant
    Filed: May 14, 2009
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventors: Claire Chairat, Olivier Burel, Jean-Marc Berthier
  • Patent number: 8566018
    Abstract: The present invention relates to a piloting assistance method for an aircraft, the method consisting in using data from at least one active telemeter sensor (A) in order to construct a sensor safety cordon (B) for avoiding the terrain and obstacles that are overflown. The method; defines and calculates angular sectors (w) over the field of regard facing the pilot; constructs a terrain safety cordon (D) using at least one terrain database (C); for at least some of the angular sectors (w), constructs a hybrid safety cordon (E) that, in each of the angular sectors (w) in question, makes use of the higher of the sensor and terrain safety cordons (B, D); and displays one of the cordons selected from: the hybrid safety cordon (E), the terrain safety cordon (D), and the sensor safety cordon (B).
    Type: Grant
    Filed: July 6, 2011
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventor: Francois-Xavier Filias
  • Patent number: 8565940
    Abstract: A method of transferring and processing flight data of an aircraft including recording the aircraft flight data in an onboard avionics system in a digital format so as to obtain digital data, the flight data including safety impact flight data and flight data having no recognized effect on safety. The method further includes recording at least the safety impact flight data in the onboard avionics system in an additional format dissimilar to the digital format so as to obtain additional flight data, storing the digital data and the additional flight data separately, transferring the digital data and the additional flight data to a monitoring computer on the ground, displaying the digital data on a screen in the form of display digital data, and transferring the digital data and the additional flight data to a complementary interpretation unit so as to generate one of display data and print data relating to the additional flight data.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventors: Carine Roquelaure, Florent Daizé, Mathieu Gester
  • Patent number: 8565981
    Abstract: A method of controlling a buoyancy system for an aircraft includes: determining the roll angle ? and the pitching angle ? of the aircraft; verifying whether ??R <+R and whether ??R <?<+?R, where ?R and ?R are predefined limit angles; if at least one of the angles ? and ? is no longer in its above-defined respective range, activating an automatic trigger of the buoyancy system; if the angles ? and ? are in their above-defined respective ranges, determining the altitude A of the aircraft; inhibiting the automatic trigger if A >AR, where AR is a predefined limit altitude; and if AR ?A, and if at least partial immersion of the aircraft has been detected, activating the automatic trigger.
    Type: Grant
    Filed: May 2, 2011
    Date of Patent: October 22, 2013
    Assignee: Eurocopter
    Inventor: Francois-Xavier Filias
  • Patent number: 8561945
    Abstract: The invention relates to a skid-type landing gear (1) for a helicopter (2) comprising bow shaped crosstubes (10-13) directed symmetrically towards a left- and a right-hand side of a longitudinal mid axis (9) of the helicopter (2) with respective skids (14, 15) at outboard ends thereof and main beams (5-8) in a fuselage (4), the crosstubes (10-13) being connected to the main beams (5-8) via supports (16-23) fixed to the main beams (5-8). The skid-type landing gear (1) is retractable. A method for operating such a skid-type landing gear (1) for a helicopter (2) is provided.
    Type: Grant
    Filed: March 24, 2011
    Date of Patent: October 22, 2013
    Assignee: Eurocopter Deutschland GmbH
    Inventors: Alexander Engleder, Stefan Gorlich
  • Patent number: 8552347
    Abstract: A method and a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), the metal fairing (6) is designed to be bonded against the airfoil (7) with the help of an adhesive (9). The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater elements (30) for heating the metal fairing (6).
    Type: Grant
    Filed: July 15, 2008
    Date of Patent: October 8, 2013
    Assignee: Eurocopter
    Inventors: Patrick Boschet, Thomas Navarre, Bruno Lorcet
  • Patent number: 8547252
    Abstract: A method of generating a terrain avoidance warning for a rotary wing aircraft including generating an avoidance trajectory including a proximal segment representative of a transfer time and an avoidance curve including at least one distal segment of a conic section curve following on from the proximal segment, wherein the proximal segment extends in continuation from a predicted trajectory over a distance representing an applicable reaction time, the applicable reaction time being minimized as a function of a route sheet for the aircraft, and wherein the generating includes calculating the at least one distal segment as a function of an instantaneous maneuverability of the aircraft.
    Type: Grant
    Filed: June 22, 2009
    Date of Patent: October 1, 2013
    Assignee: Eurocopter
    Inventors: Serge Germanetti, Alain Ducollet
  • Patent number: 8543281
    Abstract: A method of determining an angular velocity of an aircraft includes measuring the angular velocity using at least one gyro delivering a measured angular velocity signal affected by stochastic noise; measuring the angular acceleration of the aircraft using at least one accelerometer delivering a signal representing the angular acceleration of the aircraft; and using a filtering complementary in a frequency domain to combine a sum of the measured angular velocity signal and the angular acceleration signal so as to obtain a hybrid estimated angular velocity signal with reduced stochastic noise.
    Type: Grant
    Filed: June 9, 2008
    Date of Patent: September 24, 2013
    Assignee: Eurocopter
    Inventors: Jean-Paul Petillon, Marc Salesse-Lavergne