| AIRCELLE Patent applications |
| Patent application number | Title | Published |
|---|
| 20130121814 | TURBOJET ENGINE NACELLE - A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. | 05-16-2013 |
| 20130119664 | ELECTRIC POWER SUPPLY CIRCUIT FOR A TURBOJET ENGINE NACELLE - The present invention relates to an electric power supply circuit ( | 05-16-2013 |
| 20130112497 | TURBOJET ENGINE NACELLE - A turbojet engine nacelle includes at least one nacelle element having a wall delimiting a main flow channel. The flow channel has a variable flow passage section. The cross-sectional area of at least one first area of the channel is greater than that of at least one second area of the channel. The turbojet engine nacelle further includes at least one secondary flow conduit establishing a fluidic connection between the first area and the second area of the channel and is arranged parallel to the channel. The wall of the nacelle element is at least partly covered by an acoustic damping panel extending in said areas of the channel. The conduit passes through the acoustic damping panel in order to establish the secondary flow via the acoustic damping panel. The present invention can be used in the avionics field. | 05-09-2013 |
| 20130111873 | AIRCRAFT TURBOJET ENGINE FAN CASING - An aircraft turbojet engine fan casing in the form of a box section is provided by the present disclosure. The box section includes a radially interior wall of which is able to form an internal skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted, and a radially exterior wall of which is able to form an external skin of said nacelle, the box forming a module forming an entire thickness of the nacelle, and placed between an upstream portion of the nacelle, forming the air intake, and a downstream casing portion, on which a cascade edge of a thrust reverser can be fixed. | 05-09-2013 |
| 20130091825 | TURBOJET ENGINE NACELLE INCLUDING A DEVICE FOR ABSORBING CIRCUMFERENTIAL STRESSES - A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl. | 04-18-2013 |
| 20130075493 | AIRPLANE JET ENGINE THRUST REVERSER HAVING GRATINGS OR CASCADES - A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm. | 03-28-2013 |
| 20130062462 | NACELLE FOR AN AIRCRAFT ENGINE - A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam. | 03-14-2013 |
| 20130062461 | NACELLE FOR AN AIRCRAFT ENGINE - A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame connected to each other and formed at least partly in composite materials. The half-structure includes a connecting hinge positioned in a junction area of the longitudinal beam and of the half-frame, the hinge being formed by composite materials laid out so that fibres of the composite materials are positioned in alignment with fibres of composite materials forming said front half-frame. | 03-14-2013 |
| 20130062435 | NACELLE FOR AN AIRCRAFT ENGINE WITH CASCADE-TYPE THRUST REVERSER AND VARIABLE-GEOMETRY NOZZLE - An aircraft engine nacelle is provided that includes a fixed front frame, a thrust reverser cowling mounted to slide with respect to the front frame between a direct-jet position and a reversed-jet position, a variable-geometry nozzle positioned in a downstream continuation of the reverser cowling, thrust-reversal jacks interposed between the front frame and the thrust-reverser cowling, adaptive nozzle jacks interposed between said thrust reverser cowling and the variable-geometry nozzle, drive shafts mounted on the front frame, transmission shafts extending along the thrust reverser cowling as far as the variable-geometry nozzle jacks, and mechanical means for coupling said transmission shafts to said drive shafts, and means for locking rotation of said transmission shafts before decoupling of the transmission shafts from their respective drive shafts, and when the decoupling is completed. | 03-14-2013 |
| 20130062434 | ARRANGEMENT OF THRUST REVERSER FLAP LINK RODS ON THE INTERNAL FIXED STRUCTURE OF A TURBOJET ENGINE NACELLE - An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring. | 03-14-2013 |
| 20130062433 | NACELLE FOR AN AIRCRAFT ENGINE WITH VARIABLE CROSS-SECTION NOZZLE - A nacelle for an aircraft engine is provided that includes a thrust reverser cowling slideably mounted between a direct jet position and a reversed jet position, an outlet jet pipe nozzle with variable cross-section positioned in a downstream extension of the reverser cowling, and means for respectively actuating the cowling and the nozzle. The nozzle is slideably mounted on the thrust reverser cowling, and the means includes at least one actuator for actuating said thrust reverser cowling, at least one driving pinion rotatably mounted on a fixed structure of said nacelle, and at least one rack for actuating the nozzle, secured to the nozzle and meshing with the driving pinion when the thrust reverser cowling is in the direct jet position, and escaping from this pinion when said reverser cowling is in the reversed jet position. | 03-14-2013 |
| 20130061572 | HYDRAULIC CONTROL SYSTEM FOR A THRUST REVERSAL DEVICE - A control system of a hydraulic type for a thrust reversal device with which a jet engine nacelle is equipped, and associated with a nozzle variation device, is provided by the present disclosure. The control system includes at least one additional control unit hydraulically connecting actuators together, wherein hydraulic supply lines from the control unit in a nozzle mode and from the control unit in a reverser mode are then able to communicate hydraulically with each other. A plurality of control valves are laid out so that when the unit for driving the actuators in a nozzle mode is active, a corresponding hydraulic signal controls the valves of the control unit in a position such that the hydraulic supply lines of the actuators from the driving unit according to a reverser mode are cut off. | 03-14-2013 |
| 20130056554 | REVERSER WITH DOORS - A thrust reverser with doors having at least one stationary structure is provided, on which at least one door is mounted pivoting between a closed position in which the door closes the reverser and makes up an outer cowling part, and an open position in which the door opens a passage in the stationary structure and can at least partially block a flow of air generated by a turbojet engine so as to reorient the door. The stationary structure includes at least two sets of cascade vanes that can be covered by the door when in the closed position. | 03-07-2013 |
| 20130033204 | SYSTEM FOR CONTROLLING AN ELECTRICAL DEVICE OF A NACELLE - A control system for controlling an electrical device of a nacelle, the device having at least one element that is movable to a closed position and an open position. The control system includes at least one electromechanical member for actuating the movable element, a unit for electrically driving the electromechanical actuation member, and a controlling and monitoring unit for controlling the electrical drive unit so as to move the movable element to the closed and/or open position. The control system further includes a system for recovering braking power from the electrical drive unit during the movement of the movable element to the closed and/or open position. | 02-07-2013 |
| 20130025260 | AIRCRAFT PROPULSION SYSTEM PROVIDED WITH REVERSE THRUST MEANS - The invention relates to a propulsion system including a nacelle and, inside said nacelle, a dual flow turbojet engine that itself includes a fan casing ( | 01-31-2013 |
| 20130009005 | REVERSE THRUST DEVICE - The invention relates to a reverse thrust device including a stationary upstream structure including a front frame ( | 01-10-2013 |
| 20120318380 | TURBOJET ENGINE NACELLE PROVIDED WITH A COOLING ASSEMBLY FOR COOLING A COMPONENT - The invention relates to a turbojet engine nacelle component ( | 12-20-2012 |
| 20120304666 | AIRCRAFT CONTROL SYSTEM - The invention relates to a system ( | 12-06-2012 |
| 20120291937 | PROCESS FOR MANUFACTURING AN ACOUSTIC PANEL FOR AN AIRCRAFT NACELLE - Process for manufacturing an acoustic panel for an aircraft nacelle. The invention relates to a process for manufacturing an acoustic panel ( | 11-22-2012 |
| 20120279635 | METHODS FOR PRODUCING A PART MADE FROM A COMPOSITE MATERIAL, OBTAINED BY DEPOSITING LAYERS OF REINFORCING FIBERS URGED ONTO A MANDREL - The invention relates to a method of fabricating a composite material part in which one or more layers of braided, or woven, or indeed draped reinforcing fibers are applied onto a mandrel having the general shape of a body of revolution. After one or more layers have been applied onto the mandrel, an operation is performed of winding at least one tie helically around and along the assembly constituted by the mandrel and each layer of reinforcing fibers that it carries, so as to press each layer of reinforcing fibers against the mandrel. The invention relates to fabricating composite material parts such as beams, connecting rods, or arms made out of carbon fibers. | 11-08-2012 |
| 20120256051 | STUB FRAME FOR A CASCADE THRUST REVERSER STRUCTURE - The invention relates to a stub frame ( | 10-11-2012 |
| 20120248284 | SUPPORTING STRUCTURE FOR THRUST REVERSER, IN PARTICULAR HAVING CASCADES - The present invention relates to a supporting structure ( | 10-04-2012 |
| 20120247571 | JET ENGINE NACELLE REAR ASSEMBLY - The present invention relates to a nacelle rear assembly ( | 10-04-2012 |
| 20120228403 | ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE COMPRISING A THRUST REVERSAL COWL - The invention relates to an assembly for a turbojet engine which includes a pylon ( | 09-13-2012 |
| 20120228051 | ACOUSTIC SKIN FOR AN AIRCRAFT NACELLE ACOUSTIC PANEL - The invention relates to an acoustic skin ( | 09-13-2012 |
| 20120217372 | ASSEMBLY FOR HOLDING THE INTERFACE OF STATIONARY OUTER STRUCTURE OF A NACELLE AND HOUSING OF A JET ENGINE - The invention relates to an assembly for holding the interface of a stationary outer structure ( | 08-30-2012 |
| 20120217320 | THRUST INVERTER - The present invention relates to a thrust inverter for a turbojet engine nacelle ( | 08-30-2012 |
| 20120193448 | REVERSE THRUST DEVICE - The invention relates to a jet engine nacelle reverse thrust device ( | 08-02-2012 |
| 20120160933 | STRUCTURING ASSEMBLY FOR AN EXHAUST NOZZLE - The invention relates to a structuring assembly ( | 06-28-2012 |
| 20120138707 | THRUST REVERSAL DEVICE - The present invention relates to a thrust reversal device ( | 06-07-2012 |
| 20120125191 | ACTUATOR FOR OPENING AN AIRCRAFT ENGINE NACELLE COWL - Actuator (V) for opening an aircraft nacelle cowl ( | 05-24-2012 |
| 20120118400 | LEADING EDGE STRUCTURE, IN PARTICULAR FOR THE AIR INTAKE OF THE NACELLE OF AN AIRCRAFT ENGINE - The invention relates to a structure of a leading edge ( | 05-17-2012 |
| 20120107109 | AIRCRAFT ENGINE NACELLE COMPRISING A MOBILE COWL MOVED BY ELECTRIC MOTORS - A nacelle for receiving an aircraft engine, the nacelle having a tubular stationary cover and at least one movable portion connected to the stationary cover via movement means for moving the movable portion between a position close to the stationary cover and a position spaced apart therefrom. The movement means have asynchronous motors, each having a stator with windings connected in parallel to a power supply circuit and a rotor having windings, each connected to a resistive load in parallel with a winding of the rotor of each of the other motors. | 05-03-2012 |
| 20120097761 | TWELVE-HOUR STRUCTURE FOR THRUST REVERSER, IN PARTICULAR WITH GRIDS - The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam ( | 04-26-2012 |
| 20120096730 | DEVICE FOR CENTERING AN AIR INLET STRUCTURE ON A CENTRAL STRUCTURE OF A NACELLE - The invention relates to a device ( | 04-26-2012 |
| 20120090311 | ACTUATING SYSTEM FOR A MOVABLE AIRCRAFT ENGINE NACELLE ELEMENT, SUCH AS A THRUST REVERSER COVER - This system for actuating at least one aircraft nacelle element comprises at least two actuators (A | 04-19-2012 |
| 20120082808 | METHOD FOR INSTALLING HEAT SHIELDING ON A FIXED INTERNAL STRUCTURE OF A JET ENGINE NACELLE - The invention relates to a method for installing heat shielding ( | 04-05-2012 |
| 20120067975 | THRUST REVERSING DEVICE - The invention relates to a thrust reversing device ( | 03-22-2012 |
| 20120067024 | THRUST REVERSER FOR A DUAL-FLOW TURBINE ENGINE NACELLE - The invention relates to a thrust reverser ( | 03-22-2012 |
| 20120037723 | TORQUE LIMITER IN PARTICULAR FOR AN ACTUATOR OF THE NACELLE OF AN AIRCRAFT TURBOJET ENGINE - The invention relates to a torque limiter for an actuator including a screw ( | 02-16-2012 |
| 20120036830 | THRUST REVERSAL DEVICE - The invention relates to a thrust reversal device comprising at least one cowl arranged in such a way that it can be moved between a closed position and an open position, said cowl being actuated by at least one actuator that can be driven by at least one electric engine. The invention is characterised in that at least one electric engine is connected to at least two separate power supplies ( | 02-16-2012 |
| 20120031995 | ACTUATOR SYSTEM FOR A MOBILE PANEL OF A NACELLE OF A TURBOJET - The invention relates to a system for actuating a plurality of actuators ( | 02-09-2012 |
| 20120031071 | CONTROL SYSTEM FOR A TURBOREACTOR NACELLE - The invention relates to a system for controlling a plurality of actuators ( | 02-09-2012 |
| 20120031038 | CELLULAR PANEL - The present invention relates to a cellular panel deployable from a compacted form to a deployed form, including, in the compacted form thereof, a plurality of consecutive sheets substantially parallel to one another and substantially perpendicular to an expansion direction, each sheet being discretely joined at a plurality of junction points with the following and/or preceding sheet, the junction points being substantially regularly spaced apart along the lines substantially parallel to the sheets and alternating with the preceding and/or following junction points, characterized in that, on at least one line parallel to the expansion direction, one or more junction points are excised or are not made and the portions of the sheets associated with said excised or unmade junction points are excised. | 02-09-2012 |
| 20120018005 | COUPLING DEVICE FOR CONNECTING THE TWO HALF-SHELLS OF AN AIRCRAFT ENGINE NACELLE, AND NACELLE EQUIPPED WITH SUCH A DEVICE - Coupling device for connecting the two half-shells ( | 01-26-2012 |
| 20120006000 | BENT CONNECTING ROD FITTED WITH AT LEAST ONE SELF-ALIGNING MEANS - The invention relates to a bent connecting rod ( | 01-12-2012 |
| 20120001026 | DE-ICING DEVICE, IN PARTICULAR FOR AN AIRCRAFT NACELLE - The invention relates to a de-icing device ( | 01-05-2012 |
| 20120000179 | REAR SECTION OF AIRCRAFT NACELLE AND NACELLE EQUIPPED WITH SUCH REAR SECTION - The invention relates to a rear section ( | 01-05-2012 |
| 20110308257 | ATTACHMENT STRUCTURE FOR A TURBOJET ENGINE - The present invention relates to an attachment structure ( | 12-22-2011 |
| 20110303298 | METHOD FOR CLOSING A MOBILE CRADLE ELEMENT - The invention relates to a method for closing a mobile element ( | 12-15-2011 |
| 20110293414 | LOCKING DEVICE DESIGNED TO BE ARRANGED IN A JUNCTION REGION OF A NACELLE - The invention relates to a locking device ( | 12-01-2011 |
| 20110293411 | HONEYCOMB CORE STRUCTURE FOR USE IN A STRUCTURAL PANEL FOR A JET ENGINE NACELLE - The invention relates to a honeycomb core structure ( | 12-01-2011 |
| 20110290333 | METHOD FOR MANUFACTURING A STRUCTURE WITH CELLULAR CORES FOR A TURBOJET NACELLE - The invention relates to a method for manufacturing a structure with cellular cores ( | 12-01-2011 |
| 20110285096 | SEALING JOINT WITH INTEGRATED MATING SURFACE - The invention relates to a sealing joint ( | 11-24-2011 |
| 20110284686 | SUSPENSION ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE - The invention relates to a suspension assembly for an aircraft turbojet engine ( | 11-24-2011 |
| 20110284660 | THRUST REVERSER FOR A TURBOFAN ENGINE NACELLE - The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion ( | 11-24-2011 |
| 20110284095 | TURBOJET ENGINE NACELLE - The invention relates to a turbojet engine nacelle ( | 11-24-2011 |
| 20110277443 | ELECTRIC DE-ICING DEVICE AND RELATED MONITORING SYSTEM - The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source ( | 11-17-2011 |
| 20110272533 | JET ENGINE NACELLE INTENDED TO EQUIP AN AIRCRAFT - The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second half-shells ( | 11-10-2011 |
| 20110266366 | SPRING FOR A CASCADE-TYPE THRUST REVERSER SHUTTER FOR AN AIRCRAFT JET ENGINE - This leaf spring ( | 11-03-2011 |
| 20110265446 | SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR OF THE COWLINGS OF A TURBOJET ENGINE THRUST REVERSER - The control system of the invention includes at least one actuator ( | 11-03-2011 |
| 20110262270 | NACELLE EQUIPPED WITH AT LEAST ONE EXCESS PRESSURE FLAP - The present invention relates to a jet engine nacelle ( | 10-27-2011 |
| 20110259435 | JET ENGINE NACELLE EQUIPPED WITH A SYSTEM FOR MECHANICALLY INHIBITING A THRUST REVERSER - The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the one hand, means for deflecting at least part of an air flow of the jet engine and, on the other hand, at least one cowl ( | 10-27-2011 |
| 20110254196 | METHOD FOR MAKING AN ACOUSTIC ATTENTUATION PANEL, IN PARTICULAR FOR AERONAUTICS - The invention relates to a method for making an acoustic attenuation panel, comprising using at least one foam block ( | 10-20-2011 |
| 20110250054 | DEVICE FOR CONTROLLING MAINTENANCE ACTUATORS FOR THE COWLINGS OF A TURBOJET ENGINE NACELLE - The invention relates to a device ( | 10-13-2011 |
| 20110240137 | OVERPRESSURE HATCH INTENDED TO BE MOUNTED ON A WALL OF A TURBOJET ENGINE NACELLE - The invention relates to an overpressure hatch ( | 10-06-2011 |
| 20110233305 | STRUCTURE FOR THRUST INVERTER - The invention relates to a structure for a thrust inverter, that comprises: a boom ( | 09-29-2011 |
| 20110225975 | METHOD FOR CONTROLLING AN ELECTRICAL DEICING SYSTEM - The present invention relates to a method for commanding and controlling at least one resistive heating element ( | 09-22-2011 |
| 20110220218 | TURBOJET ENGINE NACELLE - The invention relates to a nacelle ( | 09-15-2011 |
| 20110219783 | TURBOJET ENGINE NACELLE WITH TRANSLATABLE UPSTREAM COWL - Turbojet engine nacelle ( | 09-15-2011 |
| 20110214747 | NACELLE WITH AN ADAPTABLE OUTLET SECTION - The present invention relates to a jet engine nacelle ( | 09-08-2011 |
| 20110214405 | NACELLE AIR INTAKE STRUCTURE - The invention relates to a nacelle comprising an air intake structure ( | 09-08-2011 |
| 20110204161 | DOOR WITH MOVABLE SPOILER FOR DOOR-TYPE THRUST REVERSER - The present invention relates to a door ( | 08-25-2011 |
| 20110200431 | JET ENGINE NACELLE WITH DAMPERS FOR HALF-SHELLS - The present invention relates to a jet engine nacelle ( | 08-18-2011 |
| 20110192134 | AIR INTAKE STRUCTURE FOR A TURBINE ENGINE NACELLE - The invention relates to an air intake structure ( | 08-11-2011 |
| 20110182728 | NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LOCKING STATE OF A LOCKING DEVICE - The present invention relates to a nacelle comprising a mid-section and an aft-section formed from two half-shells ( | 07-28-2011 |
| 20110182727 | TURBOJET ENGINE NACELLE - The invention relates to a nacelle ( | 07-28-2011 |
| 20110174919 | STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT - This strut ( | 07-21-2011 |
| 20110174899 | NACELLE WITH A VARIABLE NOZZLE SECTION - The invention relates to a nacelle that comprises a fixed structure ( | 07-21-2011 |
| 20110173949 | JET ENGINE NACELLE HAVING DAMPERS FOR HALF-SHELLS - The present invention relates to a jet engine nacelle ( | 07-21-2011 |
| 20110171487 | METHOD FOR MAKING A PART MADE OF A COMPOSITE MATERIAL WITH A METAL MATRIX - The invention relates to a method for making a part made of a composite material with a metal matrix, characterised in that the method includes the steps of: providing, on a preform of the part to be made, at least one assembly of reinforcing fibres, said fibres being previously coated with at least one metal or metal alloy; heating the assembly to a temperature sufficient for diffusing the metal particles surrounding the fibre; after cooling, releasing the part made of the preform and withdrawing the latter. | 07-14-2011 |
| 20110171019 | LOCKING DEVICE COMPRISING A TELESCOPIC CONNECTING ROD EQUIPPED WITH RETURN MEANS - The present invention relates to a locking device ( | 07-14-2011 |
| 20110171014 | NACELLE COMPRISING AT LEAST ONE SURGE TRAP - The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure ( | 07-14-2011 |
| 20110162340 | METHOD FOR MAKING A NACELLE DE-ICING ELEMENT - The invention relates to a method for making a nacelle element ( | 07-07-2011 |
| 20110155855 | METHOD FOR MAKING AN ACOUSTIC PANEL FOR THE AIR INTAKE LIP OF A NACELLE - The invention relates to a method for making an acoustic panel ( | 06-30-2011 |
| 20110139897 | MOBILE THRUST REVERSER COWL AND THRUST REVERSER PROVIDED WITH SUCH A COWL - Said mobile cowl ( | 06-16-2011 |
| 20110139540 | NOISE REDUCTION DEVICE FOR TURBOJET NACELLE WITH MOBILE CHEVRONS, AND ASSOCIATED NACELLE - The invention relates to a turbojet nacelle ( | 06-16-2011 |
| 20110133035 | METHOD FOR MAKING DEICING SYSTEM ON A NACELLE PANEL - The invention relates to a method for making a deicing system on a panel ( | 06-09-2011 |
| 20110133025 | ACOUSTIC ATTENUATION PANEL FOR AIRCRAFT FOR ENGINE NACELLE - This acoustic attenuation panel for an aircraft engine nacelle comprises a structuring skin ( | 06-09-2011 |
| 20110131945 | ASSEMBLY OF COMPONENTS CONNECTED BY A DEVICE THAT MAINTAINS THE INTEGRITY OF THE SURFACE OF ONE OF THE COMPONENTS - This assembly comprises a first component ( | 06-09-2011 |
| 20110120143 | JET ENGINE NACELLE INTENDED TO EQUIP AN AIRCRAFT - The invention relates to a jet engine nacelle intended to equip an aircraft, formed from at least first and second half-shells and equipped with at least one locking system designed to lock one of the half-shells with respect to the other, the locking system being actuable between a locked state and an unlocked state by means of an actuating device ( | 05-26-2011 |
| 20110113837 | LOCKING DEVICE - The invention relates to a locking device ( | 05-19-2011 |
| 20110110705 | COUPLING DEVICE INTENDED TO CONNECT FIRST AND SECOND ELEMENTS WHICH ARE HINGED WITH RESPECT TO ONE ANOTHER - The invention relates to a coupling device ( | 05-12-2011 |
| 20110108357 | ACOUSTIC PANEL FOR AN EJECTOR NOZZLE - The invention relates to an acoustic panel ( | 05-12-2011 |
| 20110103946 | LOCKING DEVICE - The invention relates to a locking device ( | 05-05-2011 |
| 20110103935 | AIRCRAFT ENGINE NACELLE AIR INTAKE ASSEMBLY - This aircraft engine nacelle air intake assembly comprises an air intake structure comprising an air intake lip ( | 05-05-2011 |
| 20110094204 | COUPLING SYSTEM CONNECTING AN INTERNAL STRUCTURE AND AN EXTERNAL STUCTURE OF A JET ENGINE NACELLE - The present invention relates to a turbofan jet engine nacelle intended to be attached to a structure of an aircraft by an engine strut and comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section having an internal structure intended to serve as a casing for an aft portion of the jet engine and, together with an external structure ( | 04-28-2011 |
| 20110088369 | METHOD FOR SYNCHRONIZING THE ACTUATORS OF A MOVABLE THRUST REVERSER COWL - The invention relates to a method for controlling a plurality of actuators ( | 04-21-2011 |
| 20110085897 | CASING COMPRISING A PERIPHERAL SHROUD FOR A TURBOMACHINE ROTOR - The present invention relates to a casing ( | 04-14-2011 |
| 20110081511 | METHOD FOR PRODUCING A PART COMPRISING A HOLLOW BODY MADE FROM A COMPOSITE MATERIAL - The invention relates to a method for producing a part comprising a hollow body made from a composite material, using preforms ( | 04-07-2011 |
| 20110076431 | PREFORM INTENDED TO FORM A HOLLOW STRUCTURAL MECHANICAL PART, RESULTING PART AND METHOD FOR PRODUCING SAID PREFORM - The invention relates to a preform ( | 03-31-2011 |
| 20110068222 | PROPULSION UNIT FOR AN AIRCRAFT AND AIR INTAKE STRUCTURE FOR SUCH A UNIT - This propulsion unit for an aircraft comprises: a fan ( | 03-24-2011 |
| 20110050277 | SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR OF THE COWLINGS OF A TURBOJET ENGINE THRUST REVERSER - The control system of the invention includes at least one actuator ( | 03-03-2011 |
| 20110038725 | COUPLING DEVICE INTENDED TO CONNECT FIRST AND SECOND ELEMENTS WHICH CAN MOVE RELATIVE TO ONE ANOTHER - The invention relates to a coupling device ( | 02-17-2011 |
| 20110036950 | DE-ICING AND/OR ANTI-ICING SYSTEM FOR THE LEADING EDGE OF AN AIRCRAFT WING - The invention relates to a de-icing and/or anti-icing system for the leading edge of an aircraft wing or for the lip ( | 02-17-2011 |
| 20110033286 | NACELLE FOR TURBOJET ENGINE - The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the said fan and to which the air intake structure is attached, the latter structure having at least one peripheral interior panel (41), characterized in that the casing extends around the fan more or less as far as the fan blades (8), the air intake structure being connected to the casing by the interior panel by means of at least one structural peripheral flange (15) capable of providing containment for at least one blade should the latter break off. | 02-10-2011 |
| 20110030338 | BYPASS TURBOJET ENGINE NACELLE - The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl ( | 02-10-2011 |
| 20110024994 | SEAL HAVING A LARGE COMPRESSION RANGE - The invention relates to a seal ( | 02-03-2011 |
| 20110022345 | SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR FOR THRUST REVERSER COWLINGS ON A TURBOJET ENGINE AND METHOD FOR TESTING SAID SYSTEM - The invention relates to a system for controlling at least one actuator ( | 01-27-2011 |
| 20110020119 | JET ENGINE NACELLE INTENDED TO EQUIP AN AIRCRAFT - The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second hath-shells rotatably mounted about an axis such that they can each be deployed between a working position in which the half-shells are drawn towards one another and a maintenance position in which the half-shells are spaced apart, at least the first half-shell ( | 01-27-2011 |
| 20110018213 | DOUBLE SEAL - The invention relates to a seal ( | 01-27-2011 |
| 20110017866 | LOCKING DEVICE - The invention relates to a locking device ( | 01-27-2011 |
| 20110017843 | SYSTEM FOR ACTUATING AND CONTROLLING THE MOBILE COWLING OF A TURBOJET ENGINE NACELLE - The invention relates to a system for actuating and controlling at least one mobile cowling ( | 01-27-2011 |
| 20110016846 | METHOD AND SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR OF THE COWLINGS OF A TURBOJET ENGINE THRUST INVERTER - The invention relates to a control system for at least one actuator ( | 01-27-2011 |
| 20110014044 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that comprises an air intake structure ( | 01-20-2011 |
| 20110014043 | SYSTEM FOR CONTROLLING THE COWL OF A TURBOJET ENGINE NACELLE THRUST REVERSER - A nacelle ( | 01-20-2011 |
| 20110011981 | AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE - The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition ( | 01-20-2011 |
| 20110011972 | PRIMARY STRUCTURE OF A CONNECTING STRUT - The invention relates to an effort recovery structure ( | 01-20-2011 |
| 20110011056 | PIEZOELECTRIC DE-ICING OF AN AIR INLET - The invention relates to a lip assembly ( | 01-20-2011 |
| 20110005188 | AIR INTAKE LIP FOR TURBOJET NACELLE - The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device ( | 01-13-2011 |
| 20100327110 | GUIDING SYSTEM FOR AIRCRAFT NACELLE MAINTENANCE - The invention relates to a nacelle ( | 12-30-2010 |
| 20100325908 | GAUGE FOR MOUNTING A SCREW - This gauge for mounting a screw in a cage nut or in a nut ( | 12-30-2010 |
| 20100320316 | AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE - The invention relates to an air intake for an aircraft nacelle that comprises a shroud ( | 12-23-2010 |
| 20100314501 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that includes an air intake structure ( | 12-16-2010 |
| 20100314198 | AIRCRAFT TURBOJET ENGINE NACELLE AIR INTAKE MAINTENANCE TROLLEY - This maintenance trolley ( | 12-16-2010 |
| 20100314194 | TRAILING EDGE FOR AN AIRCRAFT ENGINE, OF THE TYPE WITH MOVING CHEVRONS - This trailing edge is of the type with moving chevrons ( | 12-16-2010 |
| 20100313546 | CONTROL SYSTEM FOR TURBOJET ENGINE NACELLE - The invention relates to a turbojet engine nacelle that includes a power supply source ( | 12-16-2010 |
| 20100294422 | METHOD FOR JOINING CELLULAR ACOUSTIC PANELS - The invention relates to a method for joining a first acoustic panel ( | 11-25-2010 |
| 20100287910 | NACELLE WITH SIMPLIFIED COWLING ARRANGEMENT - The invention relates to a nacelle ( | 11-18-2010 |
| 20100284806 | SIDE-OPENING JET ENGINE NACELLE - The invention relates to a nacelle including an air intake upstream from the jet engine ( | 11-11-2010 |
| 20100281849 | DOOR-TYPE THRUST REVERSER FOR A JET ENGINE - This thrust reverser comprises at least two doors ( | 11-11-2010 |
| 20100269511 | NACELLE FOR AIRCRAFT ENGINE HAVING A NOZZLE WITH A VARIABLE SECTION - The invention relates to a nacelle for an aircraft engine that comprises a front cowling ( | 10-28-2010 |
| 20100252689 | AIRCRAFT NACELLE GUIDANCE SYSTEM INSTALLATION - The present invention relates to a turbojet engine nacelle ( | 10-07-2010 |
| 20100251693 | CASCADE-TYPE THRUST REVERSER - The invention relates to a grid-type thrust reverser comprising: a fixed structure ( | 10-07-2010 |
| 20100242428 | AIR INTAKE STRUCTURE TO BE MOUNTED UPSTREAM OF A NACELLE MIDDLE STRUCTURE FOR AIRCRAFT ENGINE, AND NACELLE EQUIPPED WITH SUCH AIR INTAKE STRUCTURE - The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall ( | 09-30-2010 |
| 20100229526 | ATTACHEMENT OF A JET ENGINE NACELLE STRUCTURE BY MEANS OF A REINFORCED KNIFE-EDGE/GROOVE COUPLING - The present invention relates to a nacelle ( | 09-16-2010 |
| 20100218480 | ACTUATOR FOR AN AIRCRAFT NACELLE MOBILE STRUCTURE, AND NACELLE COMPRISING AT LEAST ONE SUCH ACTUATOR - This actuator for an aircraft engine nacelle mobile structure ( | 09-02-2010 |
| 20100218479 | LINEAR TELESCOPIC ACTUATOR FOR MOVING A FIRST AND A SECOND ELEMENT RELATIVE TO A STATIONARY ELEMENT - The invention relates to a linear telescopic actuator for moving a first ( | 09-02-2010 |
| 20100212998 | CELLULAR-CORE STRUCTURE FOR AN ACOUSTIC PANEL - The invention relates to a cellular-core structure ( | 08-26-2010 |
| 20100212287 | THRUST REVERSER WITH A SYSTEM FOR BRAKING THE ACTUATORS - The present invention relates to a thrust reverser for a jet engine nacelle comprising at least one movable cowl ( | 08-26-2010 |
| 20100206981 | PROPULSION ASSEMBLY FOR AIRCRAFT - The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine ( | 08-19-2010 |
| 20100205931 | DOUBLE-ACTING TELESCOPIC LINEAR ACTUATOR WITH SINGLE-MOTOR DRIVE SYSTEM - The present invention relates to a telescopic linear actuator for moving a first ( | 08-19-2010 |
| 20100201190 | DEVICE AND METHOD FOR CONTROLLING THE POWER SUPPLY OF AT LEAST ONE AIRCRAFT MAINTENANCE ACTUATOR - The invention relates to a method and a device for controlling the power supply of at least one aircraft maintenance actuator ( | 08-12-2010 |
| 20100192715 | MULTIPLE-ACTING LINEAR ACTUATOR - The present invention relates to a multiple-acting linear actuator ( | 08-05-2010 |
| 20100181418 | SECURING PLATE AND LONGITUDINAL HANDLING MEMBER FOR A ONE-PIECE AIRCRAFT PROPULSION UNIT - The invention relates to a securing plate ( | 07-22-2010 |
| 20100171319 | DEVICE FOR LOCKING AN OPENING PART OF A JET ENGINE NACELLE WITH RESPECT TO A FIXED PART, AND NACELLE EQUIPPED WITH SUCH A DEVICE - This device for locking an opening part ( | 07-08-2010 |
| 20100168982 | METHOD AND SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR FOR ACTUATING THE COWLINGS OF A THRUST INVERTER IN A TURBOJET ENGINE - The invention relates to a method for controlling at least one actuator for actuating the cowlings of a thrust inverter in a turbojet engine, the actuator being driven by an electric motor including a relative position sensor providing information on the evolution of the movement thereof, wherein the motor is controlled based on the instantaneous position of the cowling in at least one portion of the movement thereof between an open position and a closed position, the instantaneous position of the cowling being determined from at least one reference position absolute data and relative position data relative to said reference position provided by the relative position sensor of the motor, wherein in case the actuation is resumed after an interruption, a new determination of the reference position is initiated. | 07-01-2010 |
| 20100164153 | VIBRATION DAMPER FOR AIRCRAFT NACELLE - The invention relates to a vibration damper ( | 07-01-2010 |
| 20100146933 | NACELLE REAR ASSEMBLY FOR TURBOJET ENGINE - The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion ( | 06-17-2010 |
| 20100140332 | BRAZING METHOD AND CORRESPONDING DEVICE - The present invention relates to a method of brazing two materials ( | 06-10-2010 |
| 20100139242 | THRUST REVERSER WITH GRIDS FOR JET ENGINE - The invention relates to a thrust reverser ( | 06-10-2010 |
| 20100132332 | CASCADE-TYPE THRUST REVERSER FOR JET ENGINE - A fan duct ( | 06-03-2010 |
| 20100115916 | NACELLE FOR TURBOJET JET FITTED WITH A SINGLE DOOR THRUST REVERSER SYSTEM - A nacelle for a turbojet includes an air inlet structure capable of channeling an air flow toward a fan of the turbojet, a middle structure designed to surround the fan and a downstream section fitted with a pivoting-door thrust reverser system having a single thrust reverser door mounted so as to pivot between a closed position in which it allows an air flow to travel from the turbojet in a direct jet and in which it ensures the internal and external aerodynamic continuity of the nacelle and an open position in which it pivots toward a position substantially perpendicular to the axis of the nacelle, a downstream portion of the door moving inside the nacelle to close off at least a portion of the air flow of the turbojet and direct it in a direction oriented toward the front of the nacelle, where the downstream section has, downstream of the door, a ring extending over the whole periphery. | 05-13-2010 |
| 20100115915 | METHOD FOR CONTROLLING ELECTRIC MOTORS OF A THRUST REVERSER - The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterised in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor. | 05-13-2010 |
| 20100108435 | METHOD FOR MAKING AN ACOUSTIC ABSORPTION PANEL IN PARTICULAR FOR THE NACELLE OF AN AIRCRAFT ENGINE - The invention relates to a method for making an acoustic absorption panel in particular for the nacelle of an aircraft engine, the panel being of the type comprising a cellular core covered on one side with a so-called outer air-permissive skin and on the other side with a so-called inner perforated skin, the cellular core being formed by the edge-to-edge junction of a plurality of blocks with a cellular core (B | 05-06-2010 |
| 20100107599 | THRUST REVERSER FOR A JET ENGINE - The invention relates to a thrust reverser ( | 05-06-2010 |
| 20100107598 | SELF-CALIBRATION METHOD FOR THE ELECTRIC JACKS OF A TURBOJET NACELLE - The invention relates to a method for the self-calibration of electric jacks ( | 05-06-2010 |
| 20100089191 | ACTUATOR WITH INTEGRATED LOCKING DEVICE - The invention relates to a jack ( | 04-15-2010 |
| 20100084507 | REMOVABLE AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The present invention relates to a nacelle ( | 04-08-2010 |
| 20100064660 | JET ENGINE NACELLE MEMBER - The invention relates to an nacelle member ( | 03-18-2010 |
| 20100059634 | LOCKING SYSTEM FOR A MOVABLE NACELLE COWL - The present invention relates to a locking system ( | 03-11-2010 |
| 20100044466 | GRID THRUST REVERSER COVER COMPRISING A SEAL SUPPORT AND ASSOCIATED SEAL - This grid thrust reverser cover comprises a seal support and a seal mounted in this support by means of two fastening lugs, this seal being capable of interacting with a diversion edge of this thrust reverser. At least one of the said lugs is turned up and the said support has a section matching that defined by the said lugs. | 02-25-2010 |
| 20100040466 | BYPASS TURBOJET ENGINE NACELLE - The nacelle ( | 02-18-2010 |
| 20100031629 | LOCKABLE GUIDING SYSTEM FOR A MOBILE PART OF A NACELLE - The invention relates to a guiding device ( | 02-11-2010 |
| 20100024435 | NACELLE FOR TURBOFAN - The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan ( | 02-04-2010 |
| 20100008772 | NACELLE FOR THE JET ENGINE OF AN AIRCRAFT - The invention relates to a nacelle for a turbojet, of the type comprising a downstream structure having an outer structure ( | 01-14-2010 |
| 20100001123 | TRANSLATABLE THRUST INVERTER FOR JET ENGINE - The invention relates to a thrust inverter with grids ( | 01-07-2010 |
| 20090255271 | STRUCTURAL NACELLE - The present invention relates, on the one hand, to a nacelle ( | 10-15-2009 |
| 20090188233 | THRUST REVERSER FORMING AN ADAPTIVE NOZZLE - The present invention relates to a thrust reverser for the nacelle of a turbojet engine comprising, on the one hand, means ( | 07-30-2009 |
| 20090165463 | Fixing System for a Component of a Turbojet Pod - The invention concerns a fixing system for at least one component of a pod of a turbojet on an engine strut to which the pod is attached and comprising at least one coupling zone provided by the component capable of co-operating with at least one complimentary coupling zone provided by the strut, and fixing means for providing with complementary fixing means a rigid and detachable connection between said component and the strut. The invention is wherein the fixing means and the complementary fixing means are capable of slightly pivoting relative to each other, as well as relative to a corresponding pod. | 07-02-2009 |
| 20090134271 | TURBOJET SUSPENDED FROM AN AIRCRAFT MAST - The present invention relates to a turbojet suspended from an aircraft mast, the turbojet comprising a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX, the mast comprising a structural strut assembly of elongated shape. In said turbojet said strut assembly is attached upstream rigidly to said outer shroud of the intermediate casing by a front attachment comprising a means for transmitting the axial and lateral forces and downstream by a rear attachment to said exhaust casing. | 05-28-2009 |
| 20090065634 | Control system for the nacelle of a turboreactor - The invention relates to an electrical control system for the nacelle of a turboreactor, comprising a plurality of electromechanical manoeuvring elements for a plurality of actuating devices embodied as auxiliary parts of the turboreactor. The invention is characterized in that the control system comprises an electronic control box comprising a plurality of control inlets to be connected to control elements, and a plurality of outlets connected to electromechanical manoeuvring of the auxiliary actuating devices. The control box can translate each instruction received into an operating sequence for at least one corresponding electromechanical manoeuvring element. The invention also relates to a nacelle and an aircraft provided with one such control system. | 03-12-2009 |
| 20080289317 | Control Method For Actuating a Thrust Reverser - The invention relates to a control method for opening or closing a turbojet engine thrust reverser ( | 11-27-2008 |
| 20080197641 | Dynamically Self-Locking Catching Device - The invention concerns a catching device ( | 08-21-2008 |
