AIRCELLE Patent applications |
Patent application number | Title | Published |
20160138623 | METHOD FOR CONTROLLING A LIFTING JACK FOR AN AIRCRAFT ENGINE NACELLE, A JACK-TYPE LIFTING SYSTEM IMPLEMENTING THE METHOD AND THE THUS EQUIPPED NACELLE - The jack-type lifting system includes a valve for modifying a maximum force value of a lifting jack activated by a protrusion for determining a determined portion such as the beginning of the extension stroke of the lifting jack. Thanks to the modification of the maximum force value, a pressure source thus applies the full force of the lifting jack after a start-up stroke so as to protect a lock of a reverser cowl which has been forgotten during maintenance. | 05-19-2016 |
20160131081 | ELECTRIC THRUST REVERSER SYSTEM FOR AN AIRCRAFT ENGINE NACELLE AND AIRCRAFT ENGINE NACELLE EQUIPPED WITH SAME - The present disclosure provides an electric thrust reverser system for an aircraft engine nacelle, including a mechanism for actuating a thrust reverser mechanism. The actuating mechanism includes a first drive cylinder and a second drive cylinder. Each cylinder includes a mechanical connection casing, a primary lock ( | 05-12-2016 |
20160131080 | PROPULSION UNIT FOR AN AIRCRAFT - An aircraft propulsion assembly including a turbojet nacelle, and the nacelle includes a stationary structure and a movable structure. The movable structure includes: a thrust reversal device including a cowl translatable along a substantially longitudinal axis of the nacelle between a retracted position, and a deployed position; and a secondary air flow exhaust nozzle including a device for electrically controlling and actuating the nozzle. In particular, the device for controlling and actuating the nozzle includes an electrical switch suitable for being closed during a direct jet operation of the nacelle and moreover suitable for being open during a reverse jet operation. The electrical switch includes a stationary connector and a movable connector. | 05-12-2016 |
20160115902 | NACELLE FOR A TURBOJET ENGINE WITH A VARIABLE NOZZLE - The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl. | 04-28-2016 |
20160108852 | THRUST REVERSER FOR A TURBOJET ENGINE NACELLE, COMPRISING CASCADES PARTIALLY INTEGRATED IN THE COWLS - A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl. | 04-21-2016 |
20160102633 | CONTROL DEVICE FOR A TURBOJET ENGINE THRUST REVERSER, BLOCKING THE REVERSER - A control device for a thrust reverser of a turbojet engine nacelle, which includes movable portions actuated by actuators, includes: a first blocking control acting on a motor-actuated system; and a second blocking control acting, mechanically, on the movable portions. The second blocking control may inhibit, when activated, a deployment of the movable portions. The control device further includes a device inhibiting disengagement of the first blocking control when a mechanical control is activated. | 04-14-2016 |
20160102610 | DE-ICING AND CONDITIONING DEVICE FOR AN AIRCRAFT - The present disclosure provides a device for de-icing an air inlet lip of an aircraft nacelle. The device includes a pre-exchanger, an intake orifice of taking in low-pressure air downstream from a fan, and two high-pressure air intake orifices downstream from a compressor in addition to controlled valves and check valves installed in an air flow network. In particular, the pre-exchanger includes a low-pressure air outlet capable of opening into the air inlet lip of the aircraft nacelle via a pipe of the air flow network. | 04-14-2016 |
20160101871 | ASSISTANCE DEVICE FOR OPERATING A COWL AND A NACELLE FOR TURBOJET ENGINE EQUIPPED THEREWITH - An assistance device is provided to maneuver of a cover of a nacelle of a turbojet engine. The assistance device includes a joint collinear with an existing joint or hinge for a fitting of the cover, and the joint of the device is rigidly secured to an angled part of which one end bears on the fitting of the cover and of which one point is hinged to a compression spring in order to apply assistance momentum to the fitting of the cover when the cover is raised. | 04-14-2016 |
20160076485 | TURBOJET ENGINE NACELLE INCLUDING A THRUST REVERSING DEVICE WITH DOORS, INCLUDING INNER FLANKS ON THE SIDES OF AN OPENING - A turbojet engine nacelle includes a thrust reversing device having doors that swing to brake a direct gas flow, guiding it through counter-thrust openings, and the inside of each door has, at the front, a cavity receiving a spoiler turned towards the front when this door is open. The nacelle includes a fixed structure upstream from each door supporting a deflection edge that partially covers the cavity. In particular, the fixed structure supports, on each side, counter-thrust openings, a flank disposed in the continuation of the deflection edge and extending behind the cavity, which is incorporated into a leaf of the door. | 03-17-2016 |
20160076484 | TURBOJET ENGINE NACELLE THRUST REVERSER COMPRISING CASCADES SECURED TO THE MOBILE COWLS - A thrust reverser of a turbojet engine nacelle includes mobile cowls which retreat with respect to a front frame while causing via cylinders the tipping of the shutters initially folded inside these cowls, so as to substantially close an annular stream of cold air, and cascades disposed around the annular stream which receive the cold air flow in order to send it towards the front. In particular, the cascades are secured to the mobile cowls and slide. | 03-17-2016 |
20160053720 | MECHANICAL INHIBITING DEVICE INTEGRATED INTO A DEFENCE LINE OF A THRUST REVERSER - The present disclosure provides a thrust reverser device for a nacelle of a by-pass turbojet engine, including: a cowl moving alternately between a deployed position in which the cowl opens a passage within the nacelle and a retracted position in which the cowl closes the passage; a locking/unlocking system to lock and unlock the cowl, the locking/unlocking system moving alternately between a closed position in which a bolt cooperates with a striker so as to hold the cowl in the retracted position, and an open position in which the bolt releases the striker, so as to allow a switching of the cowl from the retracted position to the deployed position; and a device for mechanically inhibiting the cowl from a movement, holding in the retracted position. In particular, the mechanical inhibition device holds the locking/unlocking system in the closed position. | 02-25-2016 |
20160042675 | DEVICE FOR DISPLAYING A LUMINOUS MESSAGE ON THE FAIRING OF AN AIRCRAFT - A device for displaying an luminous message on the fairing of an aircraft includes: an electroluminescent sheet plated against the fairing; a means for attaching the electroluminescent sheet onto the fairing; a means for supplying the electroluminescent sheet with electricity; a means for electrically connecting the electroluminescent sheet to the means for supplying electricity; and a means for controlling the electroluminescent sheet in an powered-on state, in which the electroluminescent sheet is supplied with electricity and emits light, or in a powered-off state, in which the electroluminescent sheet is inoperative. | 02-11-2016 |
20160040624 | NACELLE JET PIPE DEVICES FOR REGULATING PRESSURE - A nacelle jet pipe is equipped with a device for regulating the pressure of a flow of air leaving the jet pipe. The device includes an annular element surrounding the downstream end of the jet pipe, and an adjuster to adjust the position of part of the annular element in relation to the downstream end of the jet pipe. In particular, the annular element forms, with the downstream end of the jet pipe, a constricted zone the widest part of which is situated upstream of the narrowest part and the profile of which can be varied according to the position of the annular element. | 02-11-2016 |
20160039528 | NACELLE FOR AN AIRCRAFT TURBOJET ENGINE WITH AN EXTENDED FRONT LIP - A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange | 02-11-2016 |
20160032863 | NOZZLE FOR AN AIRCRAFT TURBOPROP ENGINE WITH AN UNDUCTED FAN - The present disclosure provides a nozzle for an aircraft turboprop engine with an unducted fan, including: an inner wall, an outer wall radially spaced apart from the inner wall and concentric with the inner wall, a junction area of the inner and outer walls including an opening contained in a plane transverse to a longitudinal axis of the nozzle. In particular, the junction area of the inner and outer walls includes two connecting plates and a member to secure the two connecting plates together, or in another form, the junction area includes a pad secured to the inner wall, and a pad secured to the outer wall, facing the pad of the inner wall of the nozzle. | 02-04-2016 |
20160031032 | BRAZING WITHOUT TOOLS - A method for assembling a set including an inner wall, a shrouded outer wall and an intermediate element, each presenting substantially circular sections, the shrouded outer wall presenting a shape substantially complementary to a shape of outer and inner surfaces of the intermediate element, and whose inner surface covers the outer surface of the intermediate element. In particular, the method includes a step of placing a brazing sheet, whose melting temperature is lower than melting temperatures of other elements of the set, over an assembly surface in contact with another assembly surface, and a step of heating, by a furnace, a set including the outer or inner walls and the intermediate element between which is interposed a brazing sheet so as to fix the outer or inner wall by brazing on the intermediate element. | 02-04-2016 |
20160025039 | THRUST REVERSER DEVICE - A thrust reverser device for an aircraft turbojet engine includes: a movable cowl, translating cascades connected to the movable cowl, a mast; and a front suspension to suspend the turbojet engine. The cascades translates between a direct jet position where the cascades are retracted in a fan casing, and an indirect jet position where the cascades are brought out of the fan casing. In particular, the cascades have a sliding connection with the mast by means of at least one spacer connected to the mast downstream of the front suspension. | 01-28-2016 |
20160023771 | AIRCRAFT ELEMENT REQUIRING AN ANTI-FROST TREATMENT - The present disclosure provides an aircraft element including a leading edge section and a trailing edge section, and the leading edge section includes an anti-frost treatment device. This aircraft element is remarkable in that the trailing edge section includes a superhydrophobic surface. | 01-28-2016 |
20160017751 | COOLING DEVICE FOR A TURBOJET ENGINE OF AN AIRCRAFT NACELLE - The present disclosure provides a cooling device for a turbo engine of an aircraft nacelle, including: a heat exchanger and an air outlet pipe. The nacelle includes a front housing that has a front lip forming a hollow leading edge that delimits an annular de-icing chamber. In particular, the cooling device further includes a pipe for supplying pressurized air that extends from an inlet end linked to a pressurized air source, to an outlet end forming an air ejection nozzle opening into the de-icing chamber, and the outlet pipe of the heat exchanger has an air outlet section that is arranged in the de-icing chamber in a position designed such that the pressurized air ejection nozzle forms an air suction pump in the outlet pipe of the exchanger. | 01-21-2016 |
20150377132 | NACELLE EQUIPPED WITH AN OIL-COOLING CIRCUIT COMPRISING AN INTERMEDIATE HEAT EXCHANGER - The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air. | 12-31-2015 |
20150354500 | ACTUATOR FOR AIRCRAFT ENGINE NACELLE - The present disclosure provides an actuator for an aircraft turbojet engine nacelle, which is interposed between a stationary front part of the nacelle and a moveable rear part of the nacelle. The actuator includes a main actuating arm, and a secondary actuating arm which axially extends from a rear section suitable for being connected on the moveable rear part of the nacelle, to a front section secured to a main nut screwed on a worm drive, in particular, the secondary actuating arm being designed for overcoming a breakdown of the main actuating arm. | 12-10-2015 |
20150354499 | TURBOJET ENGINE NACELLE HAVING A VARIABLE NOZZLE - A turbojet engine nacelle has a thrust reverser device and an actuating system for said thrust reverser device, and the thrust reverser device includes a moving cowl mounted translatably alternating between a closed position and an open position, and a jet nozzle section for gases that extends the moving cowl. In particular, the jet nozzle section includes a nozzle flap mounted movable between a closed position and an open position in which the nozzle flap opens a leakage passage toward the outside of the nozzle section. The actuating system has an actuator shared with the moving cowl and the nozzle flap to activate the translational movement of the moving cowl and to pivot the nozzle flap between three following positions: an idle position, an open position of the nozzle flap and an open position of the moving cowl. | 12-10-2015 |
20150354105 | MULTI-FEED WEAVING LOOM, A WEAVING METHOD USING SUCH A WEAVING LOOM AND AN APERTURED FABRIC OBTAINED THEREBY - A weaving loom includes a system for inserting weft threads in a plurality of layers and a system for inserting and sequencing warp threads in such a way as to produce a multilayer fabric having a defined weave. It includes at least two feed systems of which the speed and traction force are controlled such that, at least locally, one portion of the layers of fabric is driven by the feed mechanism of same at a different speed to at least one other portion of the layers of multilayer fabric so as to produce at least one aperture on the multilayer fabric. | 12-10-2015 |
20150354103 | FIBER STRUCTURE FOR AN AXISYMMETRIC COMPONENT MADE OF COMPOSITE MATERIAL WITH A VARYING DIAMETER, AND COMPONENT COMPRISING SAME - A single-piece woven fiber structure for fabricating an axisymmetric part of varying diameter made out of composite material, the fiber structure having a portion of frustoconical shape with a large diameter and a small diameter, the ratio between the large diameter and the small diameter being not less than 2. The fiber structure is formed by winding layers of warp and weft yarns that are woven on a mandrel having a profile that is defined as a function of the profile of the part to be fabricated with warp yarn take-up. For each layer of yarns, the weft yarns are angularly distributed on a single diameter in a zone of the large diameter of the portion of frustoconical shape and on at least two different diameters in a zone of the small diameter of the portion of frustoconical shape in order to form at least two superposed plies of weft yarns. | 12-10-2015 |
20150354102 | WEAVING LOOM WITH SIDE-BY-SIDE FRAMES, WEAVING METHOD USING SUCH A LOOM AND PREFORMS WOVEN THEREBY - The weaving loom of the present disclosure includes a warp thread supply system, a frame type warp thread sequencing system, a reed and a weft thread insertion system. The present disclosure also provides a weaving method using the weaving loom. The method includes: a step of designing a flat fabric which are multilayered and presenting several adjacent sections in a weft direction whose weave and layout are different; a step of designing a set of side-by-side frames for enabling a weaving of the adjacent sections in a continuity of a weft according to designed weaves and layouts; and a step of carrying out the weaving. | 12-10-2015 |
20150336180 | DEVICE FOR DRILLING AN ACOUSTIC COMPONENT, CASETTE, ACOUSTIC DRILLING METHOD AND METHOD OF MANUFACTURING AN ACOUSTIC COMPONENT - A device for drilling an acoustic component including a drilling head, and the drilling head has a support unit including at least two autonomous drilling cassettes. Each cassette includes at least one drill bit, a stationary frame with respect to the support unit, and a bit support moveable along the main axis (Δ) of the cassette between a retracted position and a deployed position. In particular, each bit support is equipped with a device for sensing the skin of the acoustic component to be drilled allowing to automatically control the drilling depth of the bits of each cassette. | 11-26-2015 |
20150314553 | REINFORCED STRUCTURAL COMPONENT MADE OF COMPOSITE MATERIAL - A structural component is made of composite material, including at least one assembly orifice, the component being composed of a stack of plies of fibers which include at least one layer of plies of regular fibers and at least one reinforcing ply. The reinforcing ply is composed of a woven composite textile preform formed by a weave obtained by assembling a plurality of circumferential warp fibers that form a path around the assembly orifice and weft fibers that extend radially with respect to the center of the orifice. | 11-05-2015 |
20150285185 | CASCADE-TYPE THRUST REVERSER WITH ONE-PIECE MOBILE COWL - A thrust reverser for a nacelle of a turbojet engine includes deflecting cascades and an external cowl which translates from a closure position to an opening position by a set of control cylinders being attached by their ends to the external cowl. The deflecting cascades are supported by a front frame and a rear frame respectively and are enclosed in an envelope formed by a fan carter and by a fan cowl. The thrust reverser further includes a lock which is able to connect or disconnect the deflecting cascades to the external cowl. When the lock is unlocked, the set of control cylinders translate the external cowl alone in downstream direction while in the lock position, the control cylinders translates the external cowl and the deflecting cascades together in downstream direction. | 10-08-2015 |
20150267560 | ASSEMBLY CENTERING DEVICE FOR TURBOJET ENGINE NACELLE - The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel. | 09-24-2015 |
20150260126 | NACELLE THRUST REVERSER AND NACELLE EQUIPPED WITH AT LEAST ONE REVERSER - The present disclosure relates to a turbojet engine nacelle equipped with at least one thrust reverser. The thrust reverser includes: two half-cowls forming an outer cowl which is articulated on hinges and translates between closed and open positions, a first actuator to translationally actuate a downstream frame, a second actuator to rotationally actuate each half-cowl, and a lock capable of locking or unlocking the half-cowls relative to one another. In particular, the thrust reverser includes cascades vanes supported at their upstream end by an upstream frame and at their downstream end by the downstream frame, and a connector between the downstream frame and the external cowl. The cascade vanes are enclosed in a shroud formed by a fan casing and a fan cowl. | 09-17-2015 |
20150176528 | THRUST REVERSER DEVICE - A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device. | 06-25-2015 |
20150113944 | THRUST REVERSER DOORS HAVING SIDE OPENINGS - A door for a door-type thrust reverser is able to move between a direct jet mode of a nacelle and a reverse jet mode. The door includes an inner wall being integrated into a flow path of an air flow generated by a turbojet engine, an outer wall, at least one side wall connecting the inner wall to the outer wall of the door, and a deflector to deflect the air flow. In particular, the deflector includes a cavity of the door which is shaped to convey a fraction of the air flow from one air inlet rigidly secured to the inner wall of the door to one air outlet rigidly secured to the side wall of the door, so as to redirect, during operation of the nacelle in the reverse jet mode, a part of the air flow upstream from the inner wall of the door. | 04-30-2015 |
20150030446 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced. | 01-29-2015 |
20150030445 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls. In particular, the internal return area allows the circulation of part of the injected auxiliary flow and the drawn-in auxiliary flow | 01-29-2015 |
20140326536 | STRUCTURAL ACOUSTIC ATTENUATION PANEL - An acoustic attenuation panel includes a resistive skin having acoustic holes, a solid skin and an acoustic structure. The acoustic structure includes a sound-absorbing material and is arranged between the resistive skin and the solid skin. In particular, the solid skin is structural and forms a transverse spacer between the solid skin and the resistive skin. | 11-06-2014 |
20140324384 | METHOD FOR MEASURING THE THICKNESS OF A COATING LAYER BY INDUCING MAGNETIC FIELDS - A method of measuring the thickness of a coating layer of a workpiece, the layer being formed on a substrate of the workpiece. The method comprises several steps. First, feeding a probe alternating electrical signal to induction device in order to induce a magnetic field in the workpiece. Second, measuring at least one physical characteristic that varies as a function of the magnetic field induced in the workpiece. Third, determining first and second values of an indicator, the values being determined respectively from measurements of the physical characteristic taken when the electrical signal has first and second given frequencies. Forth, calculating the difference between the first and second values of the indicator and determining the thickness of the coating layer as a function of the difference and of predetermined data correlating: the difference between the values of the indicator; and corresponding values for thicknesses of the coating layer. | 10-30-2014 |
20140319243 | REVERSER HAVING MOVABLE CASCADES, AND TRANSLATABLY VARIABLE NOZZLE - The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value. | 10-30-2014 |
20140299654 | SETUP FOR ASSEMBLING A PANEL BY BRAZING - A setup for assembling, by brazing, a composite panel including at least two parts separated by a filler material and joined together by brazing. The setup includes a furnace to achieve a brazing temperature for brazing the panel, and an assembly device which has a form having a shape similar to the final shape of the panel to be brazed. In particular, the assembly device further includes a pressing device to apply mechanical pressure to at least part of the surface of the panel in a direction allowing the panel to be permanently deformed into a shape which matches that of the form. The pressing device is moved under the action of a spring, and the forces applied by the spring being determined so that, at the brazing temperature, the spring applies the force necessary for deforming the panel against the form. | 10-09-2014 |
20140286764 | COMPOSITE PANEL HAVING A BUILT-IN SAMPLING SCOOP - A composite panel includes an inner skin and an outer skin and has an opening for receiving a sampling scoop, which forms a channel and the sampling opening of which is in communication with the outer skin. In particular, the outer skin is shaped such that, at the opening, same forms at least a portion of a flow surface of the sampling scoop. | 09-25-2014 |
20140271163 | ACUTATOR FOR AIRCRAFT TURBINE ENGINE NACELLE WITH NOTABLY ONE-PIECE ANNULAR REAR PART - An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part. | 09-18-2014 |
20140255178 | AIRCRAFT ENGINE AIR FLOW STRAIGHTENING VANE AND ASSOCIATED FLOW STRAIGHTENING STRUCTURE - A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin. | 09-11-2014 |
20140252686 | METHOD FOR DETECTING THE PRESENCE OF BUBBLES DURING OPERATIONS OF INJECTING RESIN FOR THE MANUFACTURE OF FIBRE COMPOSITE COMPONENTS - A method of detecting bubbles during operations for injecting resin for the manufacture of fibre composite components, is noteworthy in that the electrical capacitance or conductivity of at least one part of the medium formed by the fibres and the liquid is measured. | 09-11-2014 |
20140245743 | DOUBLE-ACTING LINEAR ACTUATOR - The present disclosure relates to a double-acting linear actuator for moving an inner part and an outer part of a cowl relative to a fixed frame. The linear actuator includes a first tubular body housing a first drive shaft and a second tubular body housing a second drive shaft. In particular, the first and second tubular bodies are mounted in series by the second drive shaft which is mounted on the first tubular body. The second drive shaft translates the second tubular body relative to the first tubular body when a lock of the first tubular body is in a locked position, and the first drive shaft translates both the first tubular and second tubular bodies when the lock is in an unlocked position. | 09-04-2014 |
20140245716 | TWIN-DOOR THRUST REVERSER - A thrust reverser for a turbojet aircraft engine nacelle includes a pair of twin doors including an upstream door and a downstream door which is connected to the upstream door by a connecting rod. The thrust reverse also includes an actuating cylinder for operating the upstream door between a direct jet position in which the two doors are closed and a reversed jet position in which the two doors are open and deflects a portion of a cold air stream flowing inside the nacelle. A locking system of the thrust reverser locks the upstream and downstream doors relative to one another by the operation of the actuating cylinder alone. | 09-04-2014 |
20140234090 | REAR NACELLE ASSEMBLY FOR A TURBOJET ENGINE - A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis. | 08-21-2014 |
20140234089 | ACTUATING ASSEMBLY FOR A THRUST REVERSER OF AN AIRCRAFT ENGINE - An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even. | 08-21-2014 |
20140217290 | METHOD FOR THE NON-DESTRUCTIVE INSPECTION OF AN ORGANIC-MATRIX COMPOSITE MATERIAL - A method for the non-destructive inspection of a part made from an organic-matrix composite material (CMO) includes the steps of: a) carrying out a surface inspection of the part by Fourier transform infrared spectroscopy (FTIS), b) if step a) reveals a defect, carrying out in-depth inspections of the organic-matrix composite material according to two complementary ultrasound techniques. | 08-07-2014 |
20140217234 | AIRCRAFT PROPULSION ASSEMBLY - An aircraft propulsion assembly includes a turbojet engine, a support providing a transfer of force torque to an aircraft from a suspension assembly, and the suspension assembly interposed between the support and the turbojet engine. The suspension assembly includes a device for absorbing thrust forces, an upstream suspension fasteners mounted on a fan housing and an intermediate housing of the turbojet engine. In particular, the suspension assemble further includes a main upstream suspension fastener to absorb a moment (Mx) along an axis (X) of the turbojet engine and forces (Fy and Fz) in a plane perpendicular to the axis (X), and a pair of additional upstream suspension fasteners separate from the main upstream suspension fastener to absorb a moment (Mz) along an axis (Z) and a moment (My) along an axis (Y) and forces (Fx) along the axis (X). | 08-07-2014 |
20140217233 | AIRCRAFT PROPULSION ASSEMBLY - An aircraft propulsion assembly includes a support providing a transfer of a force torque to an aircraft from a suspension assembly which is interposed between the support and a turbojet engine. The suspension assembly is mounted on an intermediate housing, a main housing or a fan housing, and on the support. In particular, the suspension assembly includes following suspension fasteners: —a first suspension fastener having a device for absorbing thrust forces and forces “Fz” along an axis “Z”, —a second suspension fastener to absorb, with the first suspension fastener, a moment “Mx” around an axis “X” and forces “Fy” along an axis “Y”, —a third suspension fastener to absorb, with the first suspension fastener, a moment “My” along the axis “Y” and forces “Fx” along an axis “X”. A moment “Mz” along the axis “Z” is absorbed by one of the suspension fasteners. | 08-07-2014 |
20140216846 | METHOD OF MANUFACTURING A SOUND ABSORBING PANEL - The present disclosure provides a method of manufacturing a sound absorbing panel in which a reflective wall on one of faces of a set of sound absorbing cells. In particular, a passage on a portion of a thickness (E) of the set of sound absorbing cells is formed on an opposite face of the one of the faces, while the passage forming a main channel for a communication between sound absorbing cells and for a circulation of a de-icing fluid. | 08-07-2014 |
20140209592 | LIP UNIT FOR AN ELECTRICALLY DEICED TURBOJET ENGINE NACELLE - A lip assembly of a turbojet engine nacelle is equipped with at least one electric de-icing system. The lip assembly includes at least one electric heating member, electrically powered through at least one power conductor. Each power-supply conductor is associated with a neutral conductor or “ground” arranged in a regrouped manner adjacent to a corresponding power-supply conductor. | 07-31-2014 |
20140202789 | INTERMEDIATE ACOUSTIC SKIN AND THE IMPLEMENTATION THEREOF - A septum includes two septum plates and the edges of the septum plates are brought into contact at one of the junction edges of the septum plates. In particular, an angle (α) between one of the junction edges of the septum plates and one of the sides of the septum plates adjacent to the one of the junction edge is less than 90°. | 07-24-2014 |
20140178145 | DEVICE FOR HANDLING A LOAD - A device for handling a load provided with a thread includes a screw assembly equipped with a gripper and capable of connecting to the load, a first screwing indicator secured to the screw assembly, a second screwing indicator movable in translation relative to the first screwing indicator, and a spring. In particular, the spring is inserted between the first screwing indicator and the second screwing indicator and has an effect of returning the second screwing indicator such that the second screwing indicator abuts against the load, so that a coincidence between the first and second screwing indicator indicates a sufficient screwing of the device onto the load. | 06-26-2014 |
20140174251 | TUBULAR MECHANICAL CONNECTING ROD - A tubular connecting rod includes a hollow body including at least one end provided with an opening and a connecting rod head arranged to be fitted through the opening. The connecting rod head includes at least one shoulder arranged to position the connecting rod head relative to the opening of the hollow body in a predetermined locked position. In particular, the end of the hollow body is provided with at least one slot. | 06-26-2014 |
20140165574 | EXHAUST PLUG FOR AN AIRCRAFT TURBOJET ENGINE - An exhaust plug for an aircraft turbojet engine is provided. The exhaust plug includes a front part being attached to a rear part, and the front and rear parts each have an outer skin. In particular, the front part and the rear part are connected by a connecting flange which is shared by the front and rear parts. The outer skins of the front and rear parts are placed side by side on the connecting flange. | 06-19-2014 |
20140158458 | EXHAUST CONE FOR AIRCRAFT TURBOJET ENGINE - An exhaust cone for an aircraft turbojet engine includes a front part which has a front end and a rear end. The front end is equipped with a front connecting flange connecting to an outlet of a turbojet engine and the rear end is equipped with a rear connecting flange connecting to a rear part of the exhaust cone. In particular, the front part is further equipped with a sound attenuation structure including an outer skin, and the outer skin overlaps the front connecting flange and the rear connecting flange. | 06-12-2014 |
20140154064 | THRUST REVERSER DEVICE - A thrust reverser device of a nacelle includes a thrust reversal cowl which moves alternately from a closed position to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers a flow deflector, and a rear frame supporting deflecting cascades. The flow deflector includes first deflecting cascades distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through the first deflecting cascades, when the thrust reverser device is in reverse jet. In particular, the rear frame has an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet. | 06-05-2014 |
20140145060 | COMPOSITE BEAM FOR TURBOJET ENGINE NACELLE SUPPORT STRUCTURE - A longitudinal beam for a turbojet engine nacelle support structure is provided. The longitudinal beam is primarily made from composite materials and in the shape of an L and includes a longitudinal web contacting with an attachment pylon of the nacelle and a sole. More specifically, the sole produces a receiving part capable of cooperating directly or indirectly by embedding with an end of an associated front frame. | 05-29-2014 |
20140137541 | AIRCRAFT PROPULSION UNIT INCLUDING AT LEAST ONE TURBOJET ENGINE AND A NACELLE - The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream. | 05-22-2014 |
20140133977 | DEVICE FOR CONNECTING A FRONT FRAME TO A FAN CASING - A device for connecting a front frame of a turbojet engine nacelle to a fan casing includes a locking pin connected to a first assembly flange and a retaining flange that is movably mounted and has at least one opening. In particular, the locking pin has a shank passing through an orifice of a second assembly flange secured to the fan casing. The opening is crossed through by the shank of the locking pin and interacts with an end groove of said locking pin. When the retaining flange is in the unlocking position, the opening has dimensions larger than those of the shank of the locking pin, and when the retaining flange is in the locking position, the opening has dimensions larger than a thickness of the locking pin at its groove but smaller than an overall thickness of the shank of the orifice of the second flange. | 05-15-2014 |
20140131480 | THRUST REVERSER DEVICE WITHOUT A CONTROL ROD IN THE STREAM - A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means. | 05-15-2014 |
20140131479 | AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A LOWER NUMBER OF ACTUATORS - This cascade-type thrust reverser with one-piece moving cowl includes rails able to slide in guideways positioned on each side of a suspension pylon. This thrust reverser includes just two actuators positioned near the rails and able to cause this cowl to slide on the guideways between its direct-jet and reverse-jet positions. It also has means capable of compensating for forces that have a tendency to misalign the rails with respect to the guideways, thus preventing them from jamming in one another. | 05-15-2014 |
20140130889 | AIR INLET STRUCTURE FOR TURBOJET ENGINE NACELLE - The present disclosure relates to an air inlet structure for a turbojet engine nacelle. The air inlet structure has a stationary internal wall to be attached to one element of a mid-section of the nacelle, and a longitudinal external wall extended by an air inlet lip connected to the stationary internal wall. In particular, one portion forming the air inlet lip is provided with depressurizing openings for a part of the air inlet lip. | 05-15-2014 |
20140099481 | METHOD FOR APPLYING A PATTERN, SUCH AS A LOGO, ONTO THE OUTER SKIN OF AN AIRCRAFT ELEMENT - The present disclosure relates to a method for applying a pattern, such as a logo, onto the outer skin of an aircraft element, which includes the following steps: a) applying a coat of paint onto the aircraft element; b) applying a top coat (base coat) onto the coat of paint; c) applying a first coat of transparent varnish (clear coat) onto the base coat; d) applying the pattern onto the first coat of transparent varnish; and e) applying a second coat of transparent varnish (clear coat) onto the pattern. | 04-10-2014 |
20140086738 | NACELLE FOR AN AIRCRFT BYPASS TURBOJET ENGINE - A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means. | 03-27-2014 |
20140086678 | ASSEMBLY FOR AN AIRCRAFT NACELLE - An assembly for an aircraft nacelle includes a reinforcing plate and a flange that includes one first portion and one second portion. The first portion of the flange is attached to another flange, and the second portion extends transversely relative to the first portion and is attached onto a panel of the assembly. In particular, the reinforcing plate is attached directly, or optionally indirectly, onto the flange via an intermediate plate attached between the reinforcing plate and the flange. The reinforcing plate has a beveled portion opposite the second portion of the flange. | 03-27-2014 |
20140083798 | METHOD FOR MANUFACTURING A SOUND ATTENUATION PANEL - The present disclosure provides a method for manufacturing a sound attenuation panel having a first cellular core structure and a second cellular core structure joined in a junction area (J), the first and second cellular core structures. The method includes: a) a joining edge of the first cellular core structure is joined to a corresponding joining edge of the second cellular core structure, thereby forming the junction area; b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel. | 03-27-2014 |
20140076999 | TERTIARY LOCKING ASSEMBLY FOR A THRUST REVERSER - A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch. | 03-20-2014 |
20140061332 | THRUST REVERSER FOR AN AIRCRAFT JET ENGINE - An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway. | 03-06-2014 |
20140053649 | MONITORING UNIT AND METHOD FOR DETECTING STRUCTURAL DEFECTS WHICH CAN OCCUR IN AN AIRCRAFT NACELLE DURING USE - The present disclosure relates to a monitoring assembly for detecting structural detects. The monitoring assembly includes a composite sandwich structure with two distinct strata, a calculation unit and a plurality of sensors for generating signals representative of an amplitude or frequency of vibrations produced in a structure. Each sensor is formed by an electromechanical microsystem including a converter for converting mechanical energy into electrical energy. In particular, the calculation unit evaluates differences between a current transfer function resulting from the signals and a predetermined nominal transfer function, compares each of the differences with a respective detection threshold, and evaluates a size or a position of the structural defect in the structure. | 02-27-2014 |
20140050545 | MULTIPURPOSE DRILLING TOOL AND ASSOCIATED CASE - A multipurpose drilling tool includes a guide head, a drilling cutter, and a shank for mounting on a chuck. These three elements are assembled with one another removably so as to allow each of them to be replaced by a similar element of different dimensions. In particular, the drilling cutter has a bore, and the guide head includes a pilot that comes into abutment at the entrance of the bore and a stem that passes along the bore and is screwed into the mounting shank. | 02-20-2014 |
20140030079 | LOCKING DEVICE WITH MECHANICAL DETECTION OF CLOSURE AND OPENING - A locking device between a first structure and a second structure includes a bolt to lock the first and second structures, an indicator as to whether the bolt has locked/unlocked the structures, and a connecting system. The bolt includes a lock bolt attached to the first structure and able to engage a hook which is attached to the second structure. In particular, the connecting system connects the bolt with the lock bolt to the indicator, and the hook is mounted such that it can move between a first position in which it is engaged with the lock bolt and allows the indicator to be locked, and a second position in which the hook is free of the lock bolt and allows the indicator to be unlocked. | 01-30-2014 |
20140026974 | PROCESS OF MANUFACTURING A TURBOJET ENGINE NACELLE PART - A method for manufacturing a nacelle air intake lip including a plurality of components includes the following steps. The first step is positioning, inside a mold, two components within a set of fibrous layers encompassing all or part of the components so that a preform is formed. Next step is performing impregnation of the obtained preform to obtain molding of the nacelle air intake lip. | 01-30-2014 |
20140026582 | ANTI-FIRE SEAL ASSEMBLY AND NACELLE COMPRISING SUCH A SEAL - A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure. | 01-30-2014 |
20140000238 | LOCKING/UNLOCKING DEVICE FOR A THURST REVERSER WITH A SLIDING COVER AND ADAPTIVE NOZZLE FOR AIRCRAFT ENGINE NACELLE | 01-02-2014 |
20130315657 | UNIT FOR AN AIRCRAFT THRUSTER - A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule. | 11-28-2013 |
20130313229 | GAS SHIELDING DEVICE - A gas shielding device used during a welding step in a controlled atmosphere of a sound attenuation panel includes an inert gas injector to inject inert gas onto the panel and a housing to receive a welding torch. The inert gas injector comprises an inert gas diffuser mounted on the periphery of the housing for receiving the welding torch. | 11-28-2013 |
20130313039 | METHOD FOR REPAIRING A SOUND ATTENUATION PANEL - A method for repairing a sound attenuation panel is disclosed. The panel includes a structuring skin in metal material, a resistive layer in metal material and a honeycomb structure as acoustic absorption material directly added onto the structuring skin and resistive layer. The method includes a step in which one reinforcing pin is inserted into the thickness of the attenuation panel and a step in which the reinforcing pin is secured by welding in a controlled atmosphere to the structuring skin and resistive layer respectively. | 11-28-2013 |
20130312263 | METHOD FOR MANUFACTURING AN AIR INTAKE STRUCTURE FOR A TURBOJET ENGINE NACELLE - A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used. | 11-28-2013 |
20130305911 | METHOD FOR BRAIDING REINFORCING FIBRES WITH VARIATION IN THE INCLINATION OF THE BRAIDED FIBRES - The invention relates to a method of braiding reinforcing fibers on a mandrel ( | 11-21-2013 |
20130292489 | THRUST REVERSER HAVING A LOCKABLE VARIABLE NOZZLE SECTION - The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl. | 11-07-2013 |
20130280031 | THRUST REVERSER - A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser. | 10-24-2013 |
20130277454 | AIRCRAFT PROPULSION ASSEMBLY - The disclosure relates to an aircraft propulsion assembly including a nacelle having an intermediate housing and a front frame that is to be mounted downstream of an outer envelope of the intermediate housing. The front frame includes a deviation edge and an element forming a direct or indirect support for at least one flow deviation vanes, in particular, the deviation edge and the support-forming element are built into the outer envelope of the intermediate housing. | 10-24-2013 |
20130266448 | AERODYNAMIC ELEMENT FOR AN AIRCRAFT NACELLE - An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end. | 10-10-2013 |
20130266423 | SELF-MOUNTED CASCADE FOR A THRUST REVERSER - The present disclosure relates to a self-mounted cascade for a thrust reverser of an airplane jet engine nacelle. The cascade includes an upstream portion and an opposite downstream portion, along with respective connection means so that two adjacent cascades are directly connected to one another only in the respective downstream portions by downstream connection means thereof. The downstream portion corresponds to an area extending from a downstream side edge over a length less than or equal to N times the length of the last cavity located along said downstream side edge, where N is less than 3. The present disclosure is of use in the field of airplane jet engine nacelles. | 10-10-2013 |
20130263600 | ASSEMBLY INCLUDING A REVERSE THRUST DEVICE AND SYSTEM FOR ACTUATING SAID DEVICE - A reverse thrust device and a system for actuating the reverse thrust device is provided by the present disclosure. The device includes at least one cowl that is translatably mounted in a direction substantially parallel to a longitudinal axis of a nacelle. The actuation system includes an actuation means that is capable of activating translational and rotational movement of the cowl and a panel of a nozzle. The actuation system also includes a downstream locking means for the nozzle and the cowl. The downstream locking means includes at least two reversible states, one of the states being a locked state in which the downstream locking means is suitable for locking the panel of the nozzle into a position for varying the section for outputting the nozzle with the cowl. | 10-10-2013 |
20130252013 | METHOD OF MANUFACTURING A TUBULAR MECHANICAL LINK ROD AND LINK ROD OBTAINED USING SUCH A METHOD - A method relates to manufacturing a tubular link rod comprising a hollow body and, at each of the ends of this body, a connecting end. This method includes the following steps: a) manufacturing a one-piece component having the hollow body and a first end part that forms one of the connecting ends of a tubular link rod, b) assembling a second end part at the other end of the hollow body, and c) inspecting and/or machining an assembly zone on the inside of the hollow body, via a bore of the second end part establishing communication between the outside and the inside of the hollow body. This second end part forms the other connecting end of the link rod. | 09-26-2013 |
20130251519 | TURBOJET CASING AND TURBOJET RECEIVING SUCH CASINGS - A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means ( | 09-26-2013 |
20130243589 | TURBOJET ENGINE NACELLE REINFORCING STRUCTURE - A turbojet engine nacelle includes a fixed structure, which has a fan casing of the turbojet engine and a front frame mounted downstream of the fan casing and directly or indirectly supporting cascade vanes. The front frame is able to collaborate with a thrust reverser cowling sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means. At least one reinforcing structure of the engine nacelle transmits load between the fan casing and the front frame. The reinforcing structure extends along the longitudinal axis of the nacelle and supports a third line of defense and/or an inhibiting device between the front frame and the thrust reverser cowling. | 09-19-2013 |
20130236294 | TURBOJET ENGINE NACELLE WITH VARIABLE VENTILATION OUTLET CROSS SECTION - A turbojet engine nacelle includes a rear section having an internal structure. The internal structure surrounds a rear part of an engine compartment and delimits, with an ejection jet pipe, an outlet cross section for the ventilation of the engine compartment. The engine nacelle includes a moving element associated with a corresponding controller. The moving element is able to move between a withdrawn position in which the outlet cross section for ventilation is at a maximum and an engaged position in which the moving element partially reduces the outlet cross section for ventilation by comparison with the retracted position. The controller is capable of moving the moving element between the retracted and engaged positions. | 09-12-2013 |
20130234447 | LOCKING DEVICE WITH MECHANICAL DETECTION OF CLOSING AND OPENING - A locking device includes a bolt capable of engaging with a corresponding hook, the bolt being mounted against a resilient return spring that tends to return the bolt into a spaced apart position. The locking device further includes a detection linkage, which is moveable between a first position and a second position. In the first position, the linkage enables unlocking of the bolt and the hook. In the second position, the linkage engages with a portion of the locking pair so as to block the unlocking. | 09-12-2013 |
20130230391 | NACELLE FOR AN AIRCRAFT BYPASS TURBOJET ENGINE - The invention relates to a nacelle ( | 09-05-2013 |
20130230390 | LEADING EDGE STRUCTURE, IN PARTICULAR FOR AN AIR INLET OF AN AIRCRAFT ENGINE NACELLE - A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing. | 09-05-2013 |
20130227963 | ASSEMBLY FOR ATTACHING THE HANGERS FROM WHICH AN AIRCRAFT PROPULSION UNIT IS SUSPENDED - An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing. | 09-05-2013 |
20130227962 | DEVICE FOR CONNECTING A THRUST REVERSER FRONT FRAME TO A FAN CASING AND NACELLE INCORPORATING SUCH A DEVICE - A device for connecting a thrust reverser front frame to a fan casing includes a crenulated flange secured to the front frame, an annular component to accept this flange secured to the fan casing, and a crenulated annulus of a shape that complements the flange and pivot-mounted on the annular component. The crenulated flange, the annular component and the crenulated annulus are designed in such a way that a rotation of the annulus with respect to the annular component has the effect of locking this flange against this annular component through the collaboration between the respective crenulations of the flange and of the annulus. | 09-05-2013 |
20130213560 | METHOD FOR PRODUCING PARTS MADE FROM COMPOSITE MATERIALS WITH A BRAIDED COVERING - The invention relates to a method of making a composite material part, the method comprising the steps of:
| 08-22-2013 |
20130171000 | TURBOJET ENGINE BLADE, IN PARTICULAR A GUIDE BLADE, AND TURBOJET ENGINE RECEIVING SUCH BLADES - A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements:
| 07-04-2013 |
20130161415 | BEAM FOR A CASCADE THRUST REVERSER - The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material. | 06-27-2013 |
20130126638 | THRUST REVERSER HAVING AN AERODYNAMIC COUPLING FOR A FRONT FRAME - A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap. | 05-23-2013 |
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 |