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Eurocopter Patents
Assignee:
Eurocopter
Address:
Marignane Cedex, FR
No. of patents:
275
Patents:


1 2 3 4 5 6










Patent Number Title Of Patent Date Issued
8583295 Method of controlling and regulating the deflection angle of a tailplane in a hybrid helicopter November 12, 2013
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) a
8579589 Mechanism for attenuating torque pulsations between an engine and a rotorcraft rotor driven by t November 12, 2013
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
8579587 Method of reducing or even eliminating the vibration of a rotorcraft lift and propulsion rotor, November 12, 2013
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) comprisin
8577608 Method of obtaining a local terrain elevation database from detector means on board a vehicle November 5, 2013
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 numbe
8568096 Drive control and regulation method and system for a hybrid helicopter October 29, 2013
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 .beta.tcl* for the propeller(s) as a fu
8566018 Piloting assistance method for aircraft October 22, 2013
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; def
8565981 Method of controlling a buoyancy system for an aircraft, and a control system implementing said October 22, 2013
A method of controlling a buoyancy system for an aircraft includes: determining the roll angle .phi. and the pitching angle .theta. of the aircraft; verifying whether -.phi..sub.R <+.sub.R and whether -.theta..sub.R <.theta.<+.theta..sub.R, where .phi..sub.R and .theta..sub.
8565940 Method of ensuring the integrity of flight data and system for implementing said method October 22, 2013
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 eff
8563078 Method of fabricating a painted substrate that is electrically non-conductive October 22, 2013
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 coa
8562075 Energy absorber element October 22, 2013
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
8561629 Method and a device for draining a tank, and a tank and an aircraft fitted with such a device October 22, 2013
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 fo
8297928 Blade for reducing the drag movements of said blade, and a method of reducing such a drag moveme October 30, 2012
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
8295997 Method of determining and displaying flying indications and a flight indicator for implementing October 23, 2012
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 deter
8283796 Hybrid engine installation and a method of controlling such an engine installation October 9, 2012
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) mechan
8282085 Absorbent covering October 9, 2012
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
8282035 Mechanical device for combining first and second control orders, and an aircraft provided with s October 9, 2012
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
8240617 Variable damping of haptic feedback for a flight-attitude changing linkage of an aircraft August 14, 2012
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 defi
8240601 Coupling with slack-takeup, a rotor, and a rotary wing aircraft August 14, 2012
A coaxial rotary coupling (11) includes a hollow inner tube (4) and a hollow outer tube (7), with inner and outer splines (12 and 13) in mutual engagement. The coupling (11) further includes: approach elements for longitudinally approaching the inner and outer tubes (4, 7) together with
8226364 Blade provided with a resonator to reduce the drag movements of said blade, and a method impleme July 24, 2012
Described is 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) being provided with an incorporated resonator (20) for reducing the drag movements (F1, F2) of the blade (10), the resonator (20) being provided
8224503 Method of inspecting the integrity of an avionics system, and an inspection device for implement July 17, 2012
A method of inspecting the integrity of an avionics system (1) installed in an aircraft, by inspecting the integrity in terms of electrical installation and data acquisition and transmission, wherein the method includes: using an Ethernet network (4) connecting the avionics system
8197212 Power-assisted control system for a rotorcraft June 12, 2012
An assisted control system for controlling the attitude of a rotorcraft comprises a flight control device; at least one control member configured to act on an aerodynamic element of the rotorcraft; a mechanical connection connecting the flight control device to the at least one contr
8196865 Foldable step for a vehicle, and a vehicle provided with such a step unit June 12, 2012
The present invention relates to a foldable step unit (10) for a rotorcraft, the step unit being provided with a bottom step (16) and a stationary support (11) that is secured to the structure of the rotorcraft (2). The step unit (10) comprises a left side beam (14) and a right beam
8196857 Variable ratio crank for a manual flight control linkage of a rotary wing aircraft June 12, 2012
The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of sa
8190304 Automatic configuration-tracking apparatus, and a method and a system for such tracking May 29, 2012
An automatic configuration-tracking apparatus for tracking the configuration of a vehicle having a multitude of components for which it is desired to consult and record various items of data specific thereto, and their identification/authentication parameters, history, and operating
8186629 Method and a device for optimizing the operation of propulsive propellers disposed on either sid May 29, 2012
A method of optimizing the operation of left and right propellers disposed on either side of the fuselage of a rotorcraft including a main rotor. Left and right aerodynamic surfaces include respective left and right flaps suitable for being deflected, yaw stabilization of the rotorcr
8181901 Fast hybrid helicopter with long range and proportional drive to the rotor and the propeller May 22, 2012
A hybrid helicopter (1) includes firstly an airframe provided with a fuselage (2) and a lift-producing surface (3), together with stabilizer surfaces (30, 35, 40), and secondly with a drive system constituted by: a mechanical interconnection system (15) between firstly a rotor (10) of
8181550 Rotary actuator incorporating a force relationship, and a method of reducing angular slack in su May 22, 2012
A rotary actuator incorporating a force relationship includes a twistably-deformable structure having a first and a second end plate and a helical spring with a first and a second terminal end secured on the first and the second end plate, respectively, and wherein the first and the
8177508 Helicopter provided with a plurality of lift elements for controlling the angles of incidence of May 15, 2012
A helicopter is fitted with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment elements (11, 21) for attaching it to a hub (2) of the rotor (1). The rotor is also fitted with one lift element (12, 22) per blade (10, 20), each lift
8175758 Method and a device for controlling the ground clearance of an aircraft May 8, 2012
The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft (1) provided with at least one undercarriage (30), said undercarriage (30) being provided with a damper-actuator (2) for performing a damping function and a
8170728 Rotorcraft control system May 1, 2012
A system (100) for controlling a rotorcraft (1) including a rotor (10), at least one variable-pitch propulsion propeller (6L, 6R), and a motor (5) for driving the rotor and the propeller(s), the system includes: a member (101, 101A, 102, 103, 104) for generating a propeller pitch s
8167099 Vehicle damper May 1, 2012
A damper (1) is provided with a body (2) which surrounds an annular compression chamber (3), the damper (1) being furnished with at least one pneumatic compensation chamber (30, 40) and a control piston (4) that can move relative to the body (2), the control piston (4) having a rod (5)
8162264 Method of jettisoning an external load carried by an aircraft, and an associated device April 24, 2012
The present invention relates to a method and an associated device for automatically jettisoning an external load (4) that is reversibly suspended from a release-hook (12) of an aircraft fuselage (2) by a sling (13), which method comprises: measuring the angle (.theta.) between sai
8136764 Device for opposing sloshing in a flexible tank March 20, 2012
A device (D) for opposing sloshing in a flexible tank (21) provided with a top cushion (22) and having a bottom (23) and a plurality of sides (24), the device includes at least first and second ties (1 and 2). The first and second ties (1 and 2) are secured respectively to first and
8123483 To rotorcraft rotors fitted with inter-blade dampers February 28, 2012
The present invention relates to an improvement to rotorcraft rotors (1) fitted with inter-blade drag dampers (15) such that for each blade (4), the two joints (16) connecting said blade (4) to two inter-blade drag dampers (15) are disposed on either side of the pitch variation axis
8121773 Method and an instrument for determining the limiting parameter of a turboshaft engine February 21, 2012
The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means (11) determines a preliminary comfort margin. Thereafter, during a main stage
8113460 Fast hybrid helicopter with long range and an optimized lift rotor February 14, 2012
A hybrid helicopter (1) includes firstly an airframe provided with a fuselage (2) and a lift-producing surface (3), together with stabilizer surfaces (30, 35, 40), and secondly with a drive system including: a mechanical interconnection system (15) between firstly a rotor (10) of r
8096779 Rotorcraft blade provided with a radial segment and with at least one forwardly- and/or rearward January 17, 2012
A rotorcraft blade (P) is provided in succession with a radial segment (1) and then a swept segment (2), the swept segment (2) being provided with at least one forwardly-swept segment (2') and/or rearwardly-swept segment (2''). In addition, the blade has a single spar coming from the
8087723 Crashworthy seat for a vehicle January 3, 2012
A crashworthy seat for a vehicle comprises a stand including a first and a second foot connected mechanically to a first and a second vertical support leg; a pan connected by the stand to a floor wherein the first and the second feet are disposed on each side of the pan, the pan incl
8079242 Crimping system with integrated monitoring December 20, 2011
A crimping tool including a punch carrier, a plurality of punches movable in translation in radial housings of the punch carrier, a thrust member having an inside face co-operating with the outer ends of the punches, the thrust member being pivotally mounted relative to the punch carrier
8075269 Helicopter provided with a plurality of lift elements each provided with a respective tab for co December 13, 2011
The present invention relates to a helicopter provided with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment means (11, 21) attaching it to a hub (2) of the rotor (1). The helicopter is provided with one lift element (12, 22) per
8075249 System and a method for dynamically balancing a blade December 13, 2011
The present invention relates to a rotorcraft blade (1) provided with a dynamic balancing system having a balancing device (10). The balancing device (10) is embedded in the inside (INT) of the body of the blade (1) in such a manner that it does not open to the outside (EXT) of said blad
8074941 Aircraft flight control December 13, 2011
An aircraft flight control (10) includes a control stick (11) with a handle (14) and a root (13) that are interconnected by an intermediate segment (12) of the control stick (11). The flight control (10) includes a pitch shaft (20) and a roll shaft (30) that are mutually perpendicular,
8073587 Diagnostic method for locating a failure in a complex system, and a device for implementing said December 6, 2011
A diagnostic method for locating a failure in a complex system that includes the steps of detecting operating information using a detector device; verifying a performance of the system based on the operating information; determining an operating status of the system to be one of "ope
8070452 Blade provided with a horizontally-wound spar, and a method of fabricating such a spar December 6, 2011
The present invention relates to a rotorcraft blade (1) provided with a distributed spar (10) on a leading edge (4), a suction side (2), and a pressure side (3) of the blade, and the invention also relates to a method of fabricating such a spar. The blade is provided with a fastener
8070089 Hybrid helicopter that is fast and has long range December 6, 2011
A hybrid helicopter (1) includes a central fuselage (2) defining a front end (3) and a rear end (4), the hybrid helicopter (1) having a main lift rotor (10), an additional lift surface (20), a mechanical interconnection system (40), and at least one turbine engine (61, 62) for continuous
8061994 Rotorcraft blade, a rotorcraft rotor provided with said blade, and a method of fabricating said November 22, 2011
A rotorcraft rotor blade (1) has a blade root (1') and a free end opposite from the blade root (1'), the blade (1) being provided at least with a spar (2) laid flat on a suction-side face (3) and a pressure side-face (4) of the blade (1), the main spar (2) being secured to an attachm
8061992 Rigid hydraulic control shaft and a control system for varying the pitch of a propeller November 22, 2011
A rigid hydraulic control shaft for conveying a fluid from a hydraulic valve to a hydraulic chamber of a propeller comprises a main segment. The main segment has a hollow rigid outer tube and a solid rigid inner bar. The inner bar has an outer periphery and at least one longitudinal groo
8061991 Rotorcraft blade provided with a spar incorporating a fastener attachment, and a method of fabri November 22, 2011
A rotorcraft blade is provided with a rigid attachment filler (1) and with a spar (40) that extends from a root (51) of the blade to a free end (52) of the blade, the attachment filler (1) having top, bottom, front, rear, left side, and right side faces (2, 3, 4, 5, 7, and 6). The spar
8061962 Method of optimizing a ducted anti-torque rotor of a rotorcraft, in particular a helicopter, to November 22, 2011
The present invention relates to a method of minimizing the noise emitted by a ducted rail rotor anti-torque device at a frequency FE and perceived at a frequency FP, in which method the diameter D, the number of blades b, and the tangential speed U of the rotor are determined so that th
8052097 Flying control device for a rotorcraft November 8, 2011
The invention relates to a rotorcraft cockpit having a left seat and a right seat placed side-by-side, a console extending between the seats, two side sticks, one situated to the right of the right seat and the other situated to the left of the left seat, enabling the pilot to contro
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