| EUROCOPTER Patent applications |
| Patent application number | Title | Published |
|---|
| 20120116613 | METHOD OF CONTROLLING AN OVERSPEED SAFETY SYSTEM FOR AEROENGINES AND A CONTROL CIRCUIT FOR IMPLEMENTING SAID METHOD - A method of controlling an overspeed safety system for an aircraft having at least two engines. The method includes setting said overspeed safety system for the engines, monitoring the speeds of rotation of the engines, detecting overspeed on one of the engines, shutting down the engine in question in the event of detecting overspeed, and inhibiting the operation of the overspeed safety system for the other engine(s) still in operation. The method also comprises the steps of monitoring safety parameters associated with the operation and/or the shutting down of the engine that has been shut down; and maintaining the inhibition or resetting the overspeed safety system for the other engine(s) still in operation, as a function of one or more safety parameters. | 05-10-2012 |
| 20120109426 | AIRCRAFT POWER PLANT, AN AIRCRAFT, AND A METHOD OF PILOTING SAID AIRCRAFT - A power plant ( | 05-03-2012 |
| 20120104152 | AIRCRAFT PROVIDED WITH HOIST MEANS, AND AN ASSOCIATED METHOD - An aircraft ( | 05-03-2012 |
| 20120080560 | SKID LANDING GEAR AND AN AIRCRAFT PROVIDED WITH SUCH LANDING GEAR - A landing gear ( | 04-05-2012 |
| 20120080558 | UNDERCARRIAGE, AN AIRCRAFT INCLUDING SAID UNDERCARRIAGE, AND A METHOD OF LANDING SAID AIRCRAFT - An undercarriage ( | 04-05-2012 |
| 20120077607 | FLEXIBLE COUPLING MEANS - A coupling means ( | 03-29-2012 |
| 20120075120 | STEPPED INSTRUMENT PANEL FOR AIRCRAFT - An instrument panel for a rotorcraft having two pilot seats, said instrument panel being arranged under an anti-glare shield ( | 03-29-2012 |
| 20120074262 | DE-ICING SYSTEM FOR A FIXED OR ROTARY AIRCRAFT WING - A de-icing system for a fixed or rotary aircraft wing, the system including means for generating ultrasound that is transmitted at least locally to an outside surface of the wing, which means comprise a base structure ( | 03-29-2012 |
| 20120070300 | BLADE WITH MINIMIZED VULNERABILITY | 03-22-2012 |
| 20120068015 | METHOD OF ACTIVATING PROTECTION MEANS FOR PROTECTING AN OCCUPANT OF AN AIRCRAFT, AND AN AIRCRAFT IMPLEMENTING SAID METHOD - A method of activating protection means ( | 03-22-2012 |
| 20120068007 | ROTARY WING AIRCRAFT PROVIDED WITH PROPULSION MEANS, AND A METHOD APPLIED BY SAID AIRCRAFT - An aircraft ( | 03-22-2012 |
| 20120043420 | SKID UNDERCARRIAGE AND A METHOD OF PREVENTING A ROTORCRAFT PROVIDED WITH SUCH AN UNDERCARRIAGE FROM TILTING - An undercarriage ( | 02-23-2012 |
| 20120031544 | METHOD OF FABRICATING A SPAR FOR A ROTORCRAFT BLADE - A method of forming a rotorcraft blade is provided. A first support shaft ( | 02-09-2012 |
| 20120025032 | ELECTRICAL ARCHITECTURE FOR A ROTARY WING AIRCRAFT WITH A HYBRID POWER PLANT - A hybrid power plant ( | 02-02-2012 |
| 20120022835 | METHOD AND A DEVICE FOR SYNTHESIZING AN ELECTRICAL AND ELECTRONIC ARCHITECTURE - A device for synthesizing an electrical and electronic architecture ( | 01-26-2012 |
| 20120018570 | METHOD OF MINIMIZING THE ATTITUDE HUMP PHENOMENON AND A ROTARY WING AIRCRAFT PROVIDED WITH STABILIZER MEANS THEREFOR - A method of minimizing the attitude hump phenomenon relating to a rotary wing aircraft ( | 01-26-2012 |
| 20120016580 | PILOTING ASSISTANCE METHOD FOR AIRCRAFT - 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; | 01-19-2012 |
| 20120012693 | METHOD AND AN AIRCRAFT PROVIDED WITH A SWIVELING TAIL ROTOR - A method of piloting an aircraft ( | 01-19-2012 |
| 20120011840 | SERVO-CONTROL PROVIDED WITH A LIMIT FORCE DETECTOR DEVICE - The present invention relates to a servo-control ( | 01-19-2012 |
| 20120008697 | COMMUNICATIONS NETWORK THAT IS DISTRIBUTED, MODULAR, AND CONFIGURABLE FOR AN ON-BOARD AVIONICS SYSTEM - A communications network for an on-board avionics system for conveying information between at least one on-board computer ( | 01-12-2012 |
| 20120006934 | METHOD AND A ROTARY WING AIRCRAFT THAT ARE OPTIMIZED SO AS TO MINIMIZE THE CONSEQUENCES FOR THE OCCUPANTS OF SAID AIRCRAFT OF AN OFF-SPECIFICATION EMERGENCY LANDING - A method of minimizing the consequences for the occupants of a rotary wing aircraft ( | 01-12-2012 |
| 20110319008 | METHOD OF AVOIDING A GRID CLOGGING, A GRID AND AN AIR INTAKE IMPLEMENTING SUCH A METHOD - The present invention relates to an air intake grid ( | 12-29-2011 |
| 20110315271 | DEVICE FOR FILLING A TANK BY GRAVITY OR UNDER PRESSURE - The present invention relates to a filler device ( | 12-29-2011 |
| 20110313703 | INERTIAL MEASUREMENT DEVICE AND AN AIRCRAFT INCLUDING SUCH A DEVICE - The present invention relates to an inertial measurement device secured to a structure of a vehicle for which it is desired to measure speeds and/or accelerations, the device comprising at least one piece of moving equipment in rotation about a stationary axis of rotation Y relative to the structure, said moving equipment including at least two measurement means having respective sensitivity axes X′ and Z′ that are mutually orthogonal and that lie in a plane perpendicular to the stationary axis of rotation Y, a motor for driving the moving equipment in rotation, means for determining the angular position of the moving equipment, means for responding to the angular position of the moving equipment to determine the projection of the measurements taken in the rotary frame of reference axes X′ and Z′ by the said at least two measurement means onto a vehicle frame of reference X and Z. | 12-22-2011 |
| 20110308905 | DEVICE FOR DAMPING THE VIBRATION OF A STRUCTURE - The present invention relates to a device ( | 12-22-2011 |
| 20110307125 | METHOD OF MONITORING THE EFFECTIVENESS OF A DAMPER, AND A DEVICE FOR IMPLEMENTING SAID METHOD - The present invention relates to a method of monitoring the effectiveness of a damper system, wherein the method consists in measuring the relative movements of two strength members, in filtering the measurements in order to isolate those that relate to the lead-lag resonant frequency of the blade, in rectifying the signal, in recording the signal, in comparing the rectified signal (S) with a threshold value (S | 12-15-2011 |
| 20110290942 | ELECTRICAL POWER SUPPLY AND CONTROL DEVICE FOR EQUIPMENT OF A ROTOR, AND AN AIRCRAFT FITTED WITH SUCH A DEVICE - The present invention relates to an electrical power supply and control device ( | 12-01-2011 |
| 20110290774 | HANDLING AN INSERT TO IMPLANT IT IN A CELLULAR PANEL AND TO WITHDRAW IT FROM THE PANEL - Tooling is organized firstly to implant an insert ( | 12-01-2011 |
| 20110290200 | AIRCRAFT POWER PLANT, AN AIRCRAFT, AND A METHOD OF USING A PISTON ENGINE IN A POWER PLANT HAVING A CONVENTIONAL GEARBOX - The present invention relates to a power plant ( | 12-01-2011 |
| 20110284688 | ROTOR PROVIDED WITH A DEVICE FOR PROTECTING IT AGAINST LIGHTNING, AND AN AIRCRAFT PROVIDED WITH SUCH A ROTOR | 11-24-2011 |
| 20110276232 | METHOD OF CONTROLLING A BUOYANCY SYSTEM FOR AN AIRCRAFT, AND A CONTROL SYSTEM IMPLEMENTING SAID METHOD - The present invention relates to a method of controlling a buoyancy system for an aircraft, wherein the buoyancy system including automatic trigger means and the method consists in:
| 11-10-2011 |
| 20110276202 | SIMPLIFIED FLIGHT CONTROL SYSTEM INCLUDING A DECLUTCHABLE FRICTION DEVICE - The present invention relates to a friction device ( | 11-10-2011 |
| 20110273324 | CONTINUOUS HIGH-ACCURACY LOCATING METHOD AND APPARATUS - Method and apparatus for locating an object ( | 11-10-2011 |
| 20110268573 | DEVICE FOR REDUCING THE VIBRATION GENERATED BY A ROTORCRAFT LIFT ROTOR, AND A ROTOR HUB PROVIDED WITH SUCH A DEVICE | 11-03-2011 |
| 20110260001 | LANDING GEAR PROVIDED WITH ENERGY ABSORBER MEANS, AN AIRCRAFT PROVIDED WITH SAID LANDING GEAR, AND A METHOD OF LANDING - Aircraft landing gear ( | 10-27-2011 |
| 20110260000 | ENERGY ABSORBER SYSTEM FOR AN UNDERCARRIAGE, AND AN AIRCRAFT PROVIDED WITH SAID ENERGY ABSORBER SYSTEM - An energy absorber system ( | 10-27-2011 |
| 20110246975 | CONTROL ARCHITECTURE AND PROCESS FOR PORTING APPLICATION SOFTWARE FOR EQUIPMENT ON BOARD AN AIRCRAFT TO A CONSUMER STANDARD COMPUTER HARDWARE UNIT - The software unit arrangement method is a step of developing a standardized software-hardware abstraction software layer ( | 10-06-2011 |
| 20110236209 | BLADE DAMPER, AND A ROTOR FITTED WITH SUCH A DAMPER - The present invention relates to a damper ( | 09-29-2011 |
| 20110236208 | ROTARY WING BLADE, A ROTARY WING INCLUDING SUCH A BLADE, AND AN AIRCRAFT | 09-29-2011 |
| 20110234425 | ADAPTING SELECTIVE TERRAIN WARNINGS AS A FUNCTION OF THE INSTANTANEOUS MANEUVERABILITY OF A ROTORCRAFT - 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. | 09-29-2011 |
| 20110230304 | MECHANICAL ASSEMBLY PROVIDED WITH MEANS FOR MONITORING FOR A STRUCTURAL ANOMALY, A GEARBOX PROVIDED WITH SUCH A MECHANICAL ASSEMBLY, AND A METHOD OF MONITORING FOR A STRUCTURAL ANOMALY - The present invention relates to a mechanical assembly ( | 09-22-2011 |
| 20110225212 | METHOD AND A DEVICE FOR FLYING SAFELY AT LOW ALTITUDE IN AN AIRCRAFT - The present invention relates to a method of flying safely and at low altitude in an aircraft, in which method unsafe relief (R | 09-15-2011 |
| 20110211959 | BLADE WITH ADAPTIVE TWISTING, AND A ROTOR PROVIDED WITH SUCH A BLADE - A rotor blade ( | 09-01-2011 |
| 20110208973 | OVERALL OPTIMIZATION OF THE CONFIGURATION OF A MESHED WIRELESS NETWORK OF RF DEVICES IN AN AIRCRAFT - The invention relates to overall optimization of an identification system ( | 08-25-2011 |
| 20110204685 | ANTI-CRASH SEAT FOR A VEHICLE - An anti-crash seat ( | 08-25-2011 |
| 20110204182 | ROTARY WING AIRCRAFT PROVIDED WITH AN EMERGENCY UNDERCARRIAGE - A rotary wing aircraft ( | 08-25-2011 |
| 20110203718 | METHOD OF FABRICATING A HONEYCOMB STRUCTURED PANEL - A method of fabricating a panel ( | 08-25-2011 |
| 20110190964 | TURNING-STABILIZED ESTIMATION OF THE ATTITUDE ANGLES OF AN AIRCRAFT - The present invention relates to estimating the attitude angles of an aircraft ( | 08-04-2011 |
| 20110186686 | REMOVABLE SUPPORT FOR OPTIONAL EXTERNAL EQUIPMENT ON AN AIRCRAFT, AND AN AIRCRAFT PROVIDED WITH SUCH A SUPPORT - The present invention relates to a removable support ( | 08-04-2011 |
| 20110180663 | METHOD AND A DEVICE FOR DRAINING A TANK, AND A TANK AND AN AIRCRAFT FITTED WITH SUCH A DEVICE - The present invention relates to a method of draining a tank ( | 07-28-2011 |
| 20110174929 | LOCKING DEVICE FOR LOCKING A STRUCTURAL ELEMENT AGAINST AN ADJACENT STRUCTURE, AN AIRCRAFT PROVIDED WITH SAID DEVICE, AND AN EXTRACTION METHOD IMPLEMENTED BY SAID DEVICE - The present invention relates to a locking device provided with a latch ( | 07-21-2011 |
| 20110155848 | AIRCRAFT UNDERCARRIAGE HAVING A ROCKER LEVER WITH A SWIVEL AND A HINGED TWIN WHEELS - The invention relates to an aircraft undercarriage ( | 06-30-2011 |
| 20110155841 | VIBRATION DAMPER MECHANISM, AND A FLYING MACHINE INCLUDING A CARRIER STRUCTURE AND A ROTOR PROVIDED WITH SUCH A MECHANISM - The present invention provides a mechanism ( | 06-30-2011 |
| 20110151133 | METHOD OF FABRICATING A PAINTED SUBSTRATE THAT IS ELECTRICALLY NON-CONDUCTIVE - The present invention relates to a method of fabricating a painted substrate ( | 06-23-2011 |
| 20110147512 | ROTOR CARRIER STRUCTURE, A FLYING MACHINE PROVIDED WITH SUCH A CARRIER STRUCTURE, AND A METHOD OF AVOIDING UNSTABLE COUPLING BETWEEN RESONANT VIBRATION MODES - The invention provides a carrier structure ( | 06-23-2011 |
| 20110144942 | METHOD OF USING TELEMETRY TO DETECT AT LEAST ONE SUSPENDED THREADLIKE OBJECT, THE OBJECT LYING IN THE DETECTION FIELD OF A TELEMETER MOUNTED ON BOARD A VEHICLE - A method of detecting at least one suspended threadlike object by telemetry, the object lying in the detection field of a telemeter on board a vehicle. The method wherein in step iii), for each vertical plane taken into consideration, and for each set of at least four candidate points close to the vertical plane in question, using the least squares method to calculate the values of three parameters a, b, and c of a catenary having an equation of the form: | 06-16-2011 |
| 20110138817 | METHOD OF INCREASING THE SAFETY OF A POWER PLANT, AND A POWER PLANT SUITABLE FOR IMPLEMENTING THE METHOD - The present invention relates to a method of increasing the safety of a power plant ( | 06-16-2011 |
| 20110137497 | AIRCRAFT PROVIDED WITH A DEVICE FOR ASSISTING THE PILOT WHEN CARRYING AN EXTERNAL LOAD WITH A SLING, AND A METHOD IMPLEMENTED BY SAID DEVICE - The present invention relates to an aircraft ( | 06-09-2011 |
| 20110130895 | METHOD OF OBTAINING A LOCAL TERRAIN ELEVATION DATABASE FROM DETECTOR MEANS ON BOARD A VEHICLE - 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. | 06-02-2011 |
| 20110127377 | TAIL SKID FOR PROTECTING A STRUCTURAL ELEMENT OF AN AIRCRAFT, AN AIRCRAFT PROVIDED WITH SUCH A TAIL SKID, AND AN ANTI-OVERTURNING METHOD IMPLEMENTED BY SAID TAIL SKID - The present invention relates to a tail skid ( | 06-02-2011 |
| 20110121127 | POWER PLANT, A HELICOPTER INCLUDING SUCH A POWER PLANT, AND A METHOD IMPLEMENTED BY SAID POWER PLANT - The present invention relates to a power plant ( | 05-26-2011 |
| 20110115131 | METHOD FOR MANUFACTURING ELECTRICALLY NON-CONDUCTIVE PAINTED SUBSTRATE - The present invention relates to a method of fabricating a painted substrate ( | 05-19-2011 |
| 20110114798 | LONG-RANGE AIRCRAFT WITH HIGH FORWARD SPEED IN CRUISING FLIGHT - The present invention relates to an aircraft ( | 05-19-2011 |
| 20110108676 | AIR INLET FOR AN AIRCRAFT TURBINE ENGINE, AN AIRCRAFT PROVIDED WITH SUCH AN AIR INLET, AND A METHOD OF OPTIMIZING THE OPERATION OF AN AIRCRAFT TURBINE ENGINE WITH THE HELP OF AN AIR INLET - The present invention relates to an air inlet ( | 05-12-2011 |
| 20110097208 | SET OF CYCLIC SWASHPLATES FOR CONTROLLING THE PITCH OF BLADES OF A MAIN ROTOR, AND A ROTOR PROVIDED WITH SUCH A SET | 04-28-2011 |
| 20110097193 | DEVICE FOR REDUCING VIBRATION GENERATED BY ROTORCRAFT ROTOR, AND ROTORCRAFT PROVIDED WITH SUCH DEVICE | 04-28-2011 |
| 20110095572 | HONEYCOMB-STRUCTURED FLOOR PANEL FOR A VEHICLE, THE PANEL INCORPORATING A FASTENER ELEMENT FOR FASTENING EQUIPMENT OF THE VEHICLE - The invention provides a laminated floor panel for a vehicle cabin. The panel comprises a core ( | 04-28-2011 |
| 20110095132 | FILTER MECHANISM FOR FILTERING THE VIBRATION TO WHICH EQUIPMENT IS SUBJECTED IN A MOVING AIRCRAFT, IN PARTICULAR A ROTORCRAFT - The invention provides a vibration filter mechanism for aircraft equipment. A weighted lever arm ( | 04-28-2011 |
| 20110085889 | MECHANISM FOR ATTENUATING TORQUE PULSATIONS BETWEEN AN ENGINE AND A ROTORCRAFT ROTOR DRIVEN BY THE ENGINE - The invention provides a mechanism for attenuating torque pulsations between an engine ( | 04-14-2011 |
| 20110079681 | SEAT FOR POWERED AIRCRAFT, THE SEAT INCORPORATING MEANS FOR PROTECTING ITS PASSENGER IN THE EVENT OF A CRASH - A seat for a powered aircraft, the seat comprising a bucket ( | 04-07-2011 |
| 20110071709 | HIGHLY REPRESENTATIVE REAL-TIME SIMULATION OF AN AVIONICS SYSTEM - Optionally-mixed highly representative real time simulation of at least part of an avionics system ( | 03-24-2011 |
| 20110071708 | ASSISTED PILOTING METHOD AND DEVICE FOR AN AIRCRAFT FOR USE IN THE EVENT OF A FIRST LIMIT INDICATOR BREAKING DOWN - An assisted piloting method for an aircraft having at least two engines ( | 03-24-2011 |
| 20110052395 | FREQUENCY ADAPTER AND RETURN MEANS SUITABLE FOR BEING ARRANGED IN SUCH A FREQUENCY ADAPTER - A frequency adapter ( | 03-03-2011 |
| 20110049295 | REUSABLE ROTORCRAFT BUMPER, AND A ROTORCRAFT HAVING SUCH A BUMPER - A reusable bumper ( | 03-03-2011 |
| 20110047711 | FASTENER TOOL FOR FASTENING A TRANSMISSION SHAFT, AND A BALANCING BENCH INCLUDING SUCH A TOOL - The present invention relates to a fastener tool ( | 03-03-2011 |
| 20110031346 | 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 - The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control ( | 02-10-2011 |
| 20110027082 | METHOD OF REDUCING OR EVEN ELIMINATING THE VIBRATION OF A ROTORCRAFT LIFT AND PROPULSION ROTOR, AND AN AIRFOIL ASSEMBLY AND A ROTOR IMPLEMENTING SAID METHOD - The present invention relates to a method of reducing the vibration of a lift and propulsion rotor ( | 02-03-2011 |
| 20110024551 | VARIABLE DAMPING OF HAPTIC FEEDBACK FOR A FLIGHT-ATTITUDE CHANGING LINKAGE OF AN AIRCRAFT - The present invention relates to haptic feedback for operating at least one manual flight control device ( | 02-03-2011 |
| 20110020592 | INSULATING COATING WITH MASS AMPLIFICATION - An insulating coating ( | 01-27-2011 |
| 20100332123 | METHOD OF ASSISTING PILOTING AT LOW ALTITUDE - A method of assisting the piloting of an aircraft ( | 12-30-2010 |
| 20100331438 | STRIPPING COMPOSITION FOR A MOLD FOR MAKING A COMPOSITE MATERIAL PART, AND METHOD OF PREPARING - A stripping composition, and a method of making the stripping composition. The stripping composition including 100 parts by weight of a base ingredient consisting in epoxy polydimethylsiloxane, 0.5 to 10 parts by weight of a polymerization agent for polymerizing the base ingredient and constituted by a diaryliodonium salt, not more than 30 parts by weight of an anti-adhesion modulator constituted by a silicone polymer; and not more than 40 parts by weight of an anti-stick agent making the composition less tacky prior to polymerization and constituted by at least one vinyl ether compound. | 12-30-2010 |
| 20100319357 | DEVICE AND A METHOD FOR STARTING A TURBINE ENGINE FITTED TO A HELICOPTER, MAKING USE OF AN ELECTRICAL ENERGY SOURCE THAT INCLUDES DISCHARGE BOOSTER MEMBERS - The invention provides a device and a method for starting at least one turbine engine ( | 12-23-2010 |
| 20100310371 | DRIVE CONTROL AND REGULATION METHOD AND SYSTEM FOR A HYBRID HELICOPTER - The present invention relates to a control and regulation method for a rotorcraft having at least one variable-pitch propulsive propeller and at least one power source for driving the propeller(s), said method consisting in generating at least one mean pitch setpoint βtcl 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:
| 12-09-2010 |
| 20100308178 | VARIABLE RATIO CRANK FOR A MANUAL FLIGHT CONTROL LINKAGE OF A ROTARY WING AIRCRAFT - The present invention relates to a bellcrank ( | 12-09-2010 |
| 20100308157 | MECHANICAL DEVICE FOR COMBINING FIRST AND SECOND CONTROL ORDERS, AND AN AIRCRAFT PROVIDED WITH SUCH A DEVICE - The present invention relates to a mechanical device ( | 12-09-2010 |
| 20100308154 | METHOD OF CONTROLLING A HYBRID HELICOPTER IN YAW, AND A HYBRID HELICOPTER PROVIDED WITH A YAW CONTROL DEVICE SUITABLE FOR IMPLEMENTING SAID METHOD - A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades. | 12-09-2010 |
| 20100296931 | DISTRIBUTED-MASS DEVICE FOR REDUCING VIBRATION GENERATED BY A ROTORCRAFT LIFT ROTOR, AND A ROTOR HUB FITTED WITH SUCH A DEVICE - A distributed mass device for reducing the vibration generated by a rotor, includes a support suitable for being constrained in rotation about an axis of rotation of the lift rotor. The distributed mass device further includes at least two main oscillating masses each provided with a through longitudinal recess, and each being connected to the support by respective deformable elements, the main oscillating masses being constrained to move solely in a horizontal plane by the deformable elements. The distributed mass device is provided with a secondary oscillating mass per main oscillating mass, each secondary oscillating mass being suspended inside the recess of the associated main oscillating mass by resilient elements. | 11-25-2010 |
| 20100296930 | CONCENTRATED-MASS DEVICE FOR REDUCING VIBRATION GENERATED BY A ROTORCRAFT LIFT ROTOR, AND A ROTOR HUB FITTED WITH SUCH A DEVICE - The present invention relates to a concentrated-mass device including a main oscillating mass held radially in a horizontal plane by main resilient element inside a casing suitable for being secured to the hub. The device includes a secondary main oscillating mass suspended by secondary resilient element inside a recess in the main oscillating mass to oscillate along a vertical axis perpendicular to the horizontal plane, the secondary oscillating mass being constrained to move in translation together with the main oscillating mass in the horizontal plane. | 11-25-2010 |
| 20100269326 | TOOLING FOR HOLDING THIN METAL PARTS MAKING UP A HOLLOW STRUCTURE IN ORDER TO ENABLE THEM TO BE FRICTION-WELDED TOGETHER - A tooling for holding parts in position to enable them to be friction-welded together in order to construct a hollow structure, the tooling includes:
| 10-28-2010 |
| 20100268414 | METHOD AND SYSTEM FOR ESTIMATING THE ANGULAR SPEED OF A MOBILE - 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. | 10-21-2010 |
| 20100250034 | METHOD OF MANAGING AIRCRAFT WARNINGS, AND A DEVICE FOR IMPLEMENTING SAID METHOD - A method of managing warnings in an aircraft, includes:
| 09-30-2010 |
| 20100247312 | BLADE PROVIDED WITH A DRAG DAMPER, AND A ROTOR PROVIDED WITH SUCH A BLADE - The present invention relates to a rotorcraft blade ( | 09-30-2010 |
| 20100243792 | METHOD AND A DEVICE FOR OPTIMIZING THE OPERATION OF PROPULSIVE PROPELLERS DISPOSED ON EITHER SIDE OF A ROTORCRAFT FUSELAGE - 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 rotorcraft being achieved via first and second pitches respectively of the left and right propellers, and the deflection angles of the left and right flaps are adjusted solely during predetermined stages of flight in order to minimize a differential pitch of the left and right propellers so as to optimize the operation of the left and right propellers, the predetermined stages of flight including stages of flight at low speed performed at an indicated air speed (IAS) of the rotorcraft that is below a predetermined threshold, and stages of yaw-stabilized flight at high speed performed at an indicated air speed of the rotorcraft greater than the predetermined threshold. | 09-30-2010 |
| 20100243714 | METHOD OF ASSEMBLING METAL PARTS BY FRICTION WELDING, WITH THE WELDING TEMPERATURE BEING CONTROLLED USING THERMALLY CONDUCTIVE ELEMENTS - The invention provides a method of assembling together two thin plane parts ( | 09-30-2010 |
| 20100235019 | METHOD OF DETERMINING AND DISPLAYING FLYING INDICATIONS AND A FLIGHT INDICATOR FOR IMPLEMENTING SAID METHOD - 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. | 09-16-2010 |
| 20100232928 | METHOD OF OPTIMIZING A DUCTED ANTI-TORQUE ROTOR OF A ROTORCRAFT, IN PARTICULAR A HELICOPTER, TO MINIMIZE ACOUSTIC ANNOYANCE, AND A DUCTED ANTI-TORQUE ROTOR OBTAINED THEREBY - 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 the perceived frequency FP is less than or equal to the bottom limit frequency FL of a predetermined one-third frequency octave centered on a frequency FC. | 09-16-2010 |
| 20100224720 | FAST HYBRID HELICOPTER WITH LONG RANGE WITH LONGITUDINAL TRIM CONTROL - A hybrid helicopter includes an airframe provided with a fuselage and a lift-producing surface together with stabilizer surfaces and a drive system including:
| 09-09-2010 |
| 20100212326 | POWERPLANT AND A METHOD OF DRIVING A MECHANICAL SYSTEM VIA SAID POWERPLANT - A powerplant ( | 08-26-2010 |
| 20100197415 | COUPLING WITH SLACK-TAKEUP, A ROTOR, AND A ROTARY WING AIRCRAFT - A coaxial rotary coupling ( | 08-05-2010 |
| 20100170759 | ENERGY ADSORBER DEVICE THAT ADAPTS AUTOMATICALLY TO THE WEIGHT IT SUPPORTS - The present invention relates to an energy absorber device ( | 07-08-2010 |
| 20100140412 | METHOD OF JETTISONING AN EXTERNAL LOAD CARRIED BY AN AIRCRAFT, AND AN ASSOCIATED DEVICE - The present invention relates to a method and an associated device for automatically jettisoning an external load ( | 06-10-2010 |
| 20100133375 | HYDRAULIC VALVE, A HYBRID HELICOPTER PROVIDED WITH SUCH A HYDRAULIC VALVE, AND A METHOD IMPLEMENTED BY THE HYDRAULIC VALVE - A hydraulic valve assembly includes a hydraulic valve, a control rod configured to be moved in translation along a first longitudinal axis by flight controls of an aircraft, a servocontrol, and an outlet rod configured to be moved in translation along a second longitudinal axis and configured to transfer a hydraulic fluid between the servocontrol and the hydraulic valve. A blocker device is configured to block a movement of the control rod when a difference between a first movement of the control rod and a second movement of the outlet rod exceeds a predetermined threshold and includes at least one moveable abutment configured to block the movement of the control rod when the predetermined threshold is reached and configured to move in longitudinal translation with the outlet rod, and a differential lever configured to mechanically link the control rod to the outlet rod and to cooperate with the at least one moveable abutment. | 06-03-2010 |
| 20100127121 | ROTARY ACTUATOR INCORPORATING A FORCE RELATIONSHIP, AND A METHOD OF REDUCING ANGULAR SLACK IN SUCH A ROTARY ACTUATOR - A rotary actuator incorporating a three 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 second end plate have a first and a second notch, respectively, and wherein the first and the second notch have a first and a second contact zone, respectively. The rotary actuator further includes an outlet shaft and a motor assembly having an outlet gear configured to drive the twistably-deformable structure so as to drive the outlet shaft in rotation, wherein, the motor assembly, the twistably-deformable structure and the outlet shaft are disposed in succession. The rotary actuator has a first finger constrained to rotate with the outlet gear and a second finger constrained to rotate with the outlet shaft. | 05-27-2010 |
| 20100114410 | METHOD OF ENSURING THE INTEGRITY OF FLIGHT DATA AND A SYSTEM FOR IMPLEMENTING SAID METHOD - 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. | 05-06-2010 |
| 20100114409 | METHOD OF INSPECTING THE INTEGRITY OF AN AVIONICS SYSTEM, AND AN INSPECTION DEVICE FOR IMPLEMENTING SAID METHOD - A method of inspecting the integrity of an avionics system ( | 05-06-2010 |
| 20100086404 | DRIVE DEVICE FOR DRIVING FIRST AND SECOND LIFT ROTORS OF A ROTORCRAFT HAVING TWIN ROTORS IN TANDEM - A drive device (D) for driving first and second lift rotors ( | 04-08-2010 |
| 20100065677 | HYBRID HELICOPTER THAT IS FAST AND HAS LONG RANGE - A hybrid helicopter ( | 03-18-2010 |
| 20100064523 | CABLE-CUTTER DEVICE | 03-18-2010 |
| 20100063933 | METHOD OF OPTIMIZING THE AVAILABILITY OF AN AIRCRAFT OR OF A FLEET OF AIRCRAFT - The present invention provides a method of optimizing the operational availability of at least one aircraft or of a fleet of aircraft as a function of constraints associated with maintenance and with the use of said aircraft, the method consisting in:
| 03-11-2010 |
| 20100051747 | LEAKTIGHT FRAME FOR A WINDOW AND A MECHANICAL ASSEMBLY PROVIDED WITH SUCH A FRAME - A leaktight frame ( | 03-04-2010 |
| 20100037099 | DIAGNOSTIC METHOD FOR LOCATING A FAILURE IN A COMPLEX SYSTEM, AND A DEVICE FOR IMPLEMENTING SAID METHOD - 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 “operational,” “non-operational” and “degraded” based on the operating information; comparing the operating information with predetermined data when the operation status is one of “operational,” “non-operational” and “degraded;” and generating at least one hypothesis as to a location of the failure of the system. | 02-11-2010 |
| 20100023209 | METHOD OF ORGANIZING AIRCRAFT MAINTENANCE - A method of managing maintenance of an aircraft. The method includes defining a recommended maintenance program for the aircraft. Maintenance deadlines for the recommended maintenance program are determined by using primary data from a testing of at least one of pieces of equipment and elements of the aircraft. Utilization data for the aircraft is used and stored. A calculation device is used to implement at least one algorithm to recalculate the maintenance deadlines as a function of the actual utilization data. The recommended maintenance program is updated. | 01-28-2010 |
| 20100013223 | HYBRID ENGINE INSTALLATION AND A METHOD OF CONTROLLING SUCH AN ENGINE INSTALLATION - A hybrid engine installation ( | 01-21-2010 |
| 20090324407 | BLADE PROVIDED WITH A RESONATOR TO REDUCE THE DRAG MOVEMENTS OF SAID BLADE, AND A METHOD IMPLEMENTED BY SAID BLADE - Described is a blade ( | 12-31-2009 |
| 20090324406 | BLADE FOR REDUCING THE DRAG MOVEMENTS OF SAID BLADE, AND A METHOD OF REDUCING SUCH A DRAG MOVEMENT | 12-31-2009 |
| 20090321554 | FAST HYBRID HELICOPTER WITH LONG RANGE - A hybrid helicopter ( | 12-31-2009 |
| 20090317252 | POWER-ASSISTED CONTROL SYSTEM FOR A ROTORCRAFT - 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 control member, the mechanical connection including at least one connecting rod moveable in translation, a crank device pivotably disposed about a stationary support shaft passing through the crank device, and a motor including a drive rotor and a stator configured to facilitate a pivoting movement of the crank device about the stationary support; a motor control device configured to control a rotation of the drive rotor relative to the stator; and at least one sensor configured to measure information representative of an operation performed by the flight control device under pilot control and to deliver a signal to the motor control device. | 12-24-2009 |
| 20090308875 | Device for opposing sloshing in a flexible tank - A device (D) for opposing sloshing in a flexible tank ( | 12-17-2009 |
| 20090283642 | BREAKABLE COUPLING DEVICE, AND AN ASSOCIATED TRIM ACTUATOR - A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque. | 11-19-2009 |
| 20090278740 | HYBRID POSITIONING METHOD AND DEVICE - The invention relates to a method of determining the position of an aircraft by combining inertial data with range data between the aircraft and satellites, in which: a) the range is stored in a FIFO memory so as make delayed range data available at the output from the memory; b) the delayed range data is combined with inertial data to obtain an estimate of position data for the aircraft; and c) a watch is maintained for the appearance of a fault in the range data, and when such a fault is detected, at least some of the data stored in the FIFO memory is modifying so as to be neutralized. | 11-12-2009 |
| 20090267391 | ENERGY ABSORBER ELEMENT - 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. | 10-29-2009 |
| 20090267390 | CRASHWORTHY SEAT FOR A VEHICLE - 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 including a seat proper and a seat back, wherein the seat back has a support element secured to the first and the second vertical support legs configured to support the seat back a guide element configured to guide the pan in translation; an energy absorber device; 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. | 10-29-2009 |
| 20090252608 | SYSTEM AND A METHOD FOR DYNAMICALLY BALANCING A BLADE - The present invention relates to a rotorcraft blade ( | 10-08-2009 |
| 20090230252 | AIRCRAFT FLIGHT CONTROL - An aircraft flight control ( | 09-17-2009 |
| 20090222178 | POWER TRANSMISSION GEARBOX PRESENTING A MODIFIABLE SPEED OF ROTATION AT ITS OUTLET, AND A CORRESPONDING METHOD OF OPERATION - A power transmission gearbox for rotorcraft for transmitting rotary movement from at least two engine members to a main shaft, wherein the gearbox presents at least two transmission systems for imparting rotary movement to the main shaft, each of the transmission systems including: an inlet shaft designed to be driven in rotation by an engine member; at least two reduction stages presenting different reduction ratios; a first gearwheel connected to the inlet shaft via a declutchable freewheel, the gearwheel meshing with a first toothed wheel secured to an intermediate shaft defining at least a first reduction stage; a second gearwheel connected to the inlet shaft via a simple freewheel, the second gearwheel meshing with a second toothed wheel secured to the intermediate shaft defining the second reduction stage; a main freewheel mounted on the intermediate shaft to rotate a complementary toothed wheel secured to the main shaft; and a clutch mechanism for the declutchable freewheel. | 09-03-2009 |
| 20090214344 | RIGID HYDRAULIC CONTROL SHAFT AND A CONTROL SYSTEM FOR VARYING THE PITCH OF A PROPELLER - 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 groove disposed along the outer periphery. The outer periphery is configured to move in rotation and translation with an inner periphery of the outer tube. The main segment is configured to move in rotation and in translation with a piston disposed adjacent to the hydraulic chamber. | 08-27-2009 |
| 20090214342 | HELICOPTER PROVIDED WITH A PLURALITY OF LIFT ELEMENTS EACH PROVIDED WITH A RESPECTIVE TAB FOR CONTROLLING THE ANGLES OF INCIDENCE OF ITS BLADES - The present invention relates to a helicopter provided with a main rotor ( | 08-27-2009 |
| 20090214340 | HELICOPTER PROVIDED WITH A PLURALITY OF LIFT ELEMENTS FOR CONTROLLING THE ANGLES OF INCIDENCE OF ITS BLADES - A helicopter is fitted with a main rotor ( | 08-27-2009 |
| 20090191062 | ROTORCRAFT BLADE PROVIDED WITH A SPAR INCORPORATING A FASTENER ATTACHMENT, AND A METHOD OF FABRICATING SUCH A SPAR - A rotorcraft blade is provided with a rigid attachment filler ( | 07-30-2009 |
| 20090155086 | ROTORCRAFT BLADE, A ROTORCRAFT ROTOR PROVIDED WITH SAID BLADE, AND A METHOD OF FABRICATING SAID BLADE - A rotorcraft rotor blade ( | 06-18-2009 |
| 20090152395 | ABSORBENT STRUCTURE FOR ATTENUATING NOISE PARTICULAR BY A ROTOR-GENERATOR NOISE, AND A ROTOR DUCT INCLUDING SUCH A STRUCTURE - An absorbent structure for reducing the propagation of soundwaves emitted by noisy devices such as rotors or motors, the structure includes a rigid partition ( | 06-18-2009 |
| 20090139200 | TURBOENGINE AIR INTAKE PROVIDED WITH A CONTROLLED FILTER SYSTEM - An air intake ( | 06-04-2009 |
| 20090134276 | Aircraft firewall - The present invention relates to an aircraft firewall ( | 05-28-2009 |
| 20090113871 | ROTORCRAFT FITTED WITH TURBINE ENGINES - The invention relates to a rotorcraft ( | 05-07-2009 |
| 20090095839 | RETRACTION CYLINDER AND ROTORCRAFT UNDERCARRIAGE FURNISHED WITH SUCH A RETRACTION CYLINDER - A retraction cylinder ( | 04-16-2009 |
| 20090095585 | VEHICLE DAMPER | 04-16-2009 |
| 20090093919 | METHOD AND A DEVICE FOR OBTAINING A PREDICTIVE VERTICAL SPEED OF A ROTORCRAFT - The present invention relates to a method and a device for obtaining a predictive vertical speed of a rotorcraft, the device constituting a predictive vertical speed indicator ( | 04-09-2009 |
| 20090089006 | METHOD AND A DEVICE FOR DETECTING AND SIGNALING THAT A ROTORCRAFT IS APPROACHING THE VORTEX DOMAIN - A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes:
| 04-02-2009 |
| 20090078827 | FOLDABLE STEP FOR A VEHICLE, AND A VEHICLE PROVIDED WITH SUCH A STEP UNIT - The present invention relates to a foldable step unit ( | 03-26-2009 |
| 20090065648 | COMPENSATION ACTUATOR FOR A ROTORCRAFT FLIGHT CONTROL - The invention relates to an actuator ( | 03-12-2009 |
| 20090057297 | METHOD AND A DEVICE FOR BONDING A METAL FAIRING TO THE LEADING EDGE OF AN AIRFOIL - The present invention relates to a method and to a device ( | 03-05-2009 |
| 20090029782 | FLEXIBLE DISK, A FLEXIBLE COUPLING PROVIDED WITH SUCH A FLEXIBLE DISK, A MOUNTING FLANGE PROVIDED WITH SUCH A FLEXIBLE COUPLING, AND A TRANSMISSION SHAFT FITTED WITH SUCH A MOUNTING FLANGE - A flexible disk for connecting a transmission shaft to rotate with a mechanical part, the flexible disk being suitable for forming rotary motion about an axis of rotation and including in succession going from its center towards its periphery an empty central zone ( | 01-29-2009 |
| 20090027269 | EMERGENCY BEACON - An emergency beacon includes a housing fitted with a connector for connecting the beacon to an antenna that is external to the housing. Inside the housing, the beacon includes an incident sensor, a transmitter, a detection and control member connected to the sensor and transmitter and arranged to trigger operation of the transmitter when an incident is detected. The beacon further includes, inside the housing, an incorporated antenna, a changeover switch interposed between the transmitter and the connector and also interposed between the transmitter and the incorporated antenna, and a sensitive member sensitive to the electromagnetic power conveyed towards the connector and to the electromagnetic power returned by the connector. The sensitive member is connected to the control member which is connected to the changeover switch and is programmed to deliver the signals from the transmitter to the external or incorporated antenna, depending on the state of the sensitive member. | 01-29-2009 |
| 20090019311 | METHOD OF TESTING AN ELECTRONIC SYSTEM - 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. | 01-15-2009 |
| 20090010764 | BLADE PROVIDED WITH A HORIZONTALLY-WOUND SPAR, AND A METHOD OF FABRICATING SUCH A SPAR - The present invention relates to a rotorcraft blade ( | 01-08-2009 |
| 20080319629 | METHOD AND APPARATUS FOR CONTROLLING AND REGULATING A ROTORCRAFT TURBINE ENGINE - The present invention relates to a method and to apparatus ( | 12-25-2008 |
| 20080294305 | ROTORCRAFT CONTROL SYSTEM | 11-27-2008 |
| 20080293503 | MECHANICAL TRANSMISSION SYSTEM WITH A MAGNETIC DAMPER FOR A ROTORCRAFT - The invention relates to a rotorcraft transmission system that comprises both a transmission shaft ( | 11-27-2008 |
| 20080289487 | HYDRAULIC DISTRIBUTOR PROVIDED WITH A DEVICE FOR DETECTING SEIZING - The present invention relates to a hydraulic distributor ( | 11-27-2008 |
| 20080276678 | TO CRIMPING SYSTEM WITH INTEGRATED MONITORING - 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, such that pivoting of the thrust member causes a contact to be crimped, a tool body having two pivotal handles for causing the thrust member and the punch carrier to pivot mutually, and a member for adjusting the stroke of the punches, a sensor sensitive to the position of the member for adjusting the stroke of the punches, a sensor sensitive to an identity signal from a contact positioning tool, and a memory associated with the position sensor and with the identity sensor and arranged to record the data delivered by the sensors and/or to deliver the data to a data processor unit. | 11-13-2008 |
| 20080275597 | BALANCING THE POWER OF TWO TURBOSHAFT ENGINES OF AN AIRCRAFT - The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M | 11-06-2008 |
| 20080269962 | Method and a system for determining and indicating a sound nuisance level outside an aircraft - A method of determining a sound nuisance level outside an aircraft, in which method:
| 10-30-2008 |
| 20080251642 | METHOD AND A DEVICE FOR DE-ICING AN AIRCRAFT WALL - A device for de-icing an aircraft wall that comprises a composite structure ( | 10-16-2008 |
| 20080237396 | AUXILIARY NOSE UNDERCARRIAGE, A FORCE-TRANSMISSION STRUCTURE, AND A ROTARY WING AIRCRAFT - A steerable auxiliary nose undercarriage ( | 10-02-2008 |
| 20080217469 | ROTORCRAFT AIR CONDITIONER SYSTEM - The invention relates to a method of controlling an air conditioner in a rotorcraft that also includes a cooler for cooling transmission lubricant, in which the temperature of the lubricant is monitored and the capacity of the air conditioner is decreased in the event of the lubricant temperature reaching or exceeding a determined value. | 09-11-2008 |
| 20080206064 | ROTORCRAFT BLADE PROVIDED WITH A RADIAL SEGMENT AND WITH AT LEAST ONE FORWARDLY-AND/OR REARWARDLY-SWEPT SEGMENT - The present invention relates to a rotorcraft blade (P) provided in succession with a radial segment ( | 08-28-2008 |
| 20080203859 | ELECTRIC ACTUATOR FOR AIRCRAFT FLIGHT CONTROL - The invention relates to an actuator ( | 08-28-2008 |
| 20080201026 | METHOD AND A DEVICE FOR CONTROLLING THE GROUND CLEARANCE OF AN AIRCRAFT - The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft ( | 08-21-2008 |
