Entries |
Document | Title | Date |
20080197233 | Engine Mounting Structure For an Aircraft - An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body. | 08-21-2008 |
20080210811 | Aircraft Engine Unit - An engine assembly for an aircraft including a turbojet, a suspension pylon, and a plurality of engine suspensions. The plurality of suspensions include a first forward suspension and a second forward suspension fixed to an engine fan case and located symmetrically about a plane defined by a longitudinal axis of the turbojet and its vertical direction, the first and second suspensions each configured to resist forces applied along a longitudinal direction of the turbojet and along its vertical direction. Furthermore, the plurality of suspensions also include an engine aft suspension configured to resist forces applied along the vertical direction. | 09-04-2008 |
20080217467 | Assembly For Aircraft Comprising a Wing System Element as Well as an Attachment Mast - An assembly for an aircraft including a wing element, a suspension pylon, a mechanism of attaching the pylon onto the element, including two forward half-attachments, each including a shackle and configured to resist forces applied along a vertical direction. The shackle is mounted firstly articulated onto a first fitting fixed to a forward spar of the element extending along the direction of the width, and is secondly mounted articulated onto a second fitting fixed to the rigid structure of the pylon. The two shackles are arranged in the same plane parallel to the direction of the width. | 09-11-2008 |
20080217468 | MAST FOR AN AIRCRAFT NACELLE INCORPORATING MEANS FOR LIMITING THE APPEARANCE OF VIBRATIONS, IN PARTICULAR IN CERTAIN FLIGHT REGIMES, AT A HIGH MACH NUMBER AND LOW LIFT - A mast for connection between a power plant and the rest of an aircraft that includes an outside surface ( | 09-11-2008 |
20080223983 | Method for Mounting an Aircraft Engine on a Rigid Structure of a Strut for Locking the Engine - The invention concerns a method to mount an aircraft engine on a rigid structure of an engine mount, comprising a securing step, on the structure, to secure an attachment body ( | 09-18-2008 |
20080237394 | Engine Mounting Structure Interposed Between an Aircraft Wing System and Said Engine - A device for suspension of an engine, configured to be inserted between an aircraft wing and the engine. The device includes a rigid structure and a forward aerodynamic structure mounted fixed on the structure through a suspension mechanism. The forward aerodynamic structure is configured to carry engine fan casings and to be inserted between the rigid structure and the wing. The suspension mechanism includes at least one adjustable length connecting rod of which one end is mounted on the rigid structure, and the other end is mounted on the forward aerodynamic structure. | 10-02-2008 |
20080245926 | Engine Assembly for an Aircraft Comprising an Engine as Well as an Engine Mounting Structure for Such an Engine - An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including an outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the outlet of the heat exchanger system is provided on an outlet pipe connected to the exchanger and passing through a structural block fixed on a box, between the box and the engine. | 10-09-2008 |
20080251633 | Engine Assembly for an Aircraft Comprising an Engine as Well as an Engine Mounting Structure for Such an Engine - An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension. | 10-16-2008 |
20080251634 | Rigid Framework for Aircraft Engine Mounting Structure and Engine Mounting Structure Comprising Same - The invention relates to a rigid structure ( | 10-16-2008 |
20080272228 | Jet Engine Nozzle Exit Configurations, Including Projections Oriented Relative To Pylons, and Associated Systems and Methods - Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections. | 11-06-2008 |
20080272229 | Strut for Locking the Engine of an Aircraft - An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib. | 11-06-2008 |
20080272230 | Engine Assembly for Aircraft - An aircraft engine assembly including a turbojet engine, an engine mount, and a plurality of engine attachments. The engine attachments include first and second forward attachments fixed to a fan case and located symmetrically in relation to a plane defined by a longitudinal axis of the turbojet engine and a vertical direction thereof, both forward attachments configured to transfer loads exerted in a longitudinal direction of the turbojet engine and in the vertical direction thereof. Moreover, each of the two forward attachments includes a shear pin mounted on the case and going through two walls of a clevis fixed on the engine mount. | 11-06-2008 |
20080296430 | System For Connecting a Crossbar to an Aircraft Engine Pylon - An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely. | 12-04-2008 |
20080302907 | Fan Variable Area Nozzle Positional Measurement System - A positional measurement system for a fan variable area nozzle (FVAN) remotely determines the position of each flap or set of flaps relative a core nacelle. The positional measurement system includes a sensor system with a multiple of transceivers located within the core nacelle to remotely measure the position of each flap or set of flaps without the heretofore necessity of moving measurement components. | 12-11-2008 |
20080315033 | Turbojet Engine Mounting Structure For Aircraft - A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively. | 12-25-2008 |
20080315034 | Turbojet Engine Nacelle with Lateral Opening of Covers - The present invention relates to a nacelle ( | 12-25-2008 |
20090020643 | AIRCRAFT HAVING REDUCED ENVIRONMENTAL IMPACT - Aircraft having reduced environmental impact. According to the invention, said aircraft comprises at least one engine ( | 01-22-2009 |
20090065634 | Control system for the nacelle of a turboreactor - The invention relates to an electrical control system for the nacelle of a turboreactor, comprising a plurality of electromechanical manoeuvring elements for a plurality of actuating devices embodied as auxiliary parts of the turboreactor. The invention is characterized in that the control system comprises an electronic control box comprising a plurality of control inlets to be connected to control elements, and a plurality of outlets connected to electromechanical manoeuvring of the auxiliary actuating devices. The control box can translate each instruction received into an operating sequence for at least one corresponding electromechanical manoeuvring element. The invention also relates to a nacelle and an aircraft provided with one such control system. | 03-12-2009 |
20090072079 | Aircraft having a pivotable powerplant - Aircraft including an airframe having a fuselage extending between a forward end and an aft end opposite the forward end. The aircraft further includes a powerplant pivotally connected to the fuselage adjacent the aft end. The powerplant produces exhaust during operation of the aircraft. The powerplant is selectively pivotable to direct exhaust at multiple angles with respect to the fuselage. | 03-19-2009 |
20090078819 | Turbojet for aircraft, aircraft equipped with such a turbojet, and method for mounting such a turbojet on an aircraft - The disclosed embodiments relates to a jet engine for an aircraft, characterized in that it bears at least one stabilizer, the stabilizer being fastened on the rigid structure of said jet engine so as to form a one-piece assembly. The jet engine can also bear one or more auxiliary devices required for the operation of the jet engine. The disclosed embodiments also relates to an aircraft provided with such a jet engine, and to a method of mounting such a jet engine on an aircraft. | 03-26-2009 |
20090084893 | PYLON FOR SUSPENDING AN ENGINE BENEATH AN AIRCRAFT WING | 04-02-2009 |
20090090811 | Arrangement for mounting an engine on the airframe of an aircraft - Arrangement for mounting a propulsive system on an aircraft airframe | 04-09-2009 |
20090108127 | METHOD FOR FIXING AN ENGINE STRUT TO AN AIRPLANE WING - The inventive fixing system comprises a front attachment ( | 04-30-2009 |
20090114766 | ANNULAR TORSIONAL RIGID STATIC COMPONENT FOR AN AIRCRAFT ENGINE - In an annular torsional rigid static component for an aircraft engine, the component includes at least one arrangement for mounting the engine to an aircraft. The mounting arrangement comprises a body formed in a composite material. | 05-07-2009 |
20090134270 | MEANS FOR PREVENTING THE ROTATION OF A PIN SUPPORTING A TURBINE ENGINE SUSPENSION MEMBER - The present invention relates to a device for mounting a suspension member on the casing of a turbine engine comprising a yoke with at least one lug, secured to the casing, a pin fixed to said yoke supporting said member via a ring surrounding the pin, said device comprising a rotation-prevention means comprising a counter-rotation plate attached to the lug. The device is one wherein said plate and the pin comprise an assembly consisting of a peg and of a cutout or a hole, into which said peg fits in order to prevent the pin from rotating in the yoke. | 05-28-2009 |
20090134271 | TURBOJET SUSPENDED FROM AN AIRCRAFT MAST - The present invention relates to a turbojet suspended from an aircraft mast, the turbojet comprising a front fan, an intermediate casing downstream of the fan with an outer shroud and a hub connected together by radial arms and an exhaust casing with an outer shroud, the two casings being aligned on one and the same axis XX, the mast comprising a structural strut assembly of elongated shape. In said turbojet said strut assembly is attached upstream rigidly to said outer shroud of the intermediate casing by a front attachment comprising a means for transmitting the axial and lateral forces and downstream by a rear attachment to said exhaust casing. | 05-28-2009 |
20090134272 | AIR INLET LIP FOR A POD WITH ELECTRIC DEFROSTING - The present invention relates to a lip ( | 05-28-2009 |
20090184197 | PYLON AND ENGINE MOUNT CONFIGURATION - A mounting arrangement for a gas turbine engine includes a pylon mount structure that has a fore mount portion and an aft mount portion. A first engine mount beam is integrally formed with the fore mount portion as a single-piece component, and a second engine mount beam is integrally formed with the aft mount portion as a single-piece component. The first engine mount beam is attachable to the engine case at a fore attachment interface, and the second engine mount beam is attached to the engine case at an aft attachment interface. | 07-23-2009 |
20090184198 | CONNECTING A PROPULSION SYSTEM TO A STRUCTURAL ELEMENT OF AN AIRCRAFT - An aircraft propulsion system ( | 07-23-2009 |
20090189013 | NON-HANDED ENGINE COWL DOORS FOR FUSELAGE MOUNTED TURBINE ENGINES - An engine cowl door assembly is provided for fuselage mounted turbine engines to minimize manufacturing costs and part counts. In one embodiment, the engine cowl door assembly includes at least one non-handed engine cowl door, a pylon apron coupled to the fuselage of an aircraft and providing an attachment point for a first portion of the engine cowl door and a fairing coupled to the turbine engine and providing a latching point for a second portion of the engine cowl door to the turbine engine. The pylon apron, positioned on an inboard side of the turbine engine, and the fairing, positioned on an outboard side of the turbine engine, are identically shaped to provide interchangeability of the engine cowl door from a turbine engine mounted on a first side of an aircraft fuselage to a turbine engine mounted on a opposed second side of an aircraft fuselage. | 07-30-2009 |
20090189014 | ATTACHMENT OF A MULTIFLOW TURBOJET ENGINE TO AN AIRCRAFT - The invention relates to the suspension of a multi-flow turbojet engine provided with an intermediate casing and an exhaust casing from a pylon that can be attached to the structure of an aircraft, comprising forward means of attachment between the hub of the intermediate casing and said pylon and a rear means of attachment between the exhaust casing and the pylon. This suspension is one which also comprises a means of connection rigidly connecting the intermediate casing to the pylon, and is one wherein the rear means of attachment comprises a means such as an actuator for compensating for the variations in diameter of the exhaust casing so as to keep the axis of the exhaust casing coaxial with the axis of the intermediate casing through the various phases of flight of the aircraft. | 07-30-2009 |
20090194633 | ICING PROTECTION FOR AIRCRAFT AIR INLET SCOOPS - Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air duct is positioned. The fairing has a forward end which surrounds the air inlet of the air duct. At least one tube is provided having an inlet end in communication with a heated air chamber associated with an airframe structure of the aircraft, and an outlet end in communication with the interior fairing space. Heated air in the heated chamber is directed through the tube to the interior fairing space so as to provide icing protection to the air duct. The air scoop icing protection systems may advantageously be employed so as to provide icing protection to air scoops associated with an aircraft engine nacelle using the residual heat from the nacelle's inlet lip primary bleed air system. | 08-06-2009 |
20090200418 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE - A device for attaching an aircraft engine including a rigid structure forming a structure box, and a device for absorbing thrust loads including a main fitting fixedly mounted on one of the spars forming the structure box, by a fixing mechanism. The fixing mechanism includes a fixing peg mounted on the spar and including a main portion located on the outside relatively to the box, the fitting being crossed by the portion of the peg and pressed against the spar by a bell-shaped supporting washer surrounding the main portion and stressed by a screw crossing it, the latter being screwed into a barrel nut housed in a bore made within the main portion. | 08-13-2009 |
20090200419 | AIRCRAFT ENGINE ATTACHMENT DEVICE COMPRISING TWO THRUST-REACHING LINK RODS THAT FIT TOGETHER TRANSVERSELY - A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure. | 08-13-2009 |
20090212154 | Aircraft wing, fastening arrangement, and intermediate support - The invention relates to an aircraft wing, a fastening arrangement, and an intermediate support. A support structure of a wing ( | 08-27-2009 |
20090212155 | ENGINE PYLON MADE FROM COMPOSITE MATERIAL - A load-bearing structure, such as a pylon or strut, comprising a monolithic tubular-shaped first central structure composed of composite material and a plurality of metal fittings for supporting an engine on an airframe structure of an aircraft, such as a wing. Most of the fittings are integrated into the load-bearing structure through bonding. The metal fittings carry the high bearing loads that are transmitted into the pylon at the engine-pylon and wing-pylon interfaces. The load-bearing structure may also comprise a second central structure of a tubular shape composed of composite material and integrated with one end portion of the first central structure by bonding and/or mechanical fastening means. | 08-27-2009 |
20090218441 | Device for Fastening A Turbojet Engine to an Aircraft Fixing Strut - A front attachment device for fastening a turbojet engine to an aircraft fixing strut. The attachment device is adapted to absorb the turbojet engine thrust loads, and includes a top bracket, and a lower bracket. A thrust load absorption vector results from a first convergence point of primary vectors passing through primary fixing points that couple the top bracket to the lower bracket and a second convergence point of secondary vectors passing through secondary fixing points that couple the lower bracket to the turbojet engine. The thrust load absorption vector transmits the turbojet engine thrust loads to the fixing strut, and extends along a longitudinal axis of the turbojet engine. | 09-03-2009 |
20090236469 | MOUNTING SYSTEM FOR A GAS TURBINE ENGINE - A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine. | 09-24-2009 |
20090261198 | PYLON FOR SUSPENDING A TURBOENGINE - Suspension mast for a turbine engine. | 10-22-2009 |
20090266932 | ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING A SUPPORT CRADLE FOR A FAN SHROUD MOUNTED ON TWO SEPARATE ELEMENTS - The present invention relates to an aircraft engine assembly comprising an engine, an engine mounting structure ( | 10-29-2009 |
20090266933 | ENGINE MOUNTING APPARATUS - An engine mounting apparatus for attaching an engine to a suspension pylon includes a mounting block, first and second links connectable between the engine and the mount block and first and second fixings connectable between the suspension pylon and the mount block. The apparatus further has a catcher link, located between the first and second links, that is connectable to the engine at a first end and to the suspension pylon at a second end via a third fixing with a clearance between the catcher link and the engine such that no load is transferred between the engine and the suspension pylon in normal operation. The apparatus also has a catcher fixing between the mount block and the catcher link, the catcher fixing having a clearance with respect to the mount block such that no load is transferred between the mount block and the catcher link in normal operation. | 10-29-2009 |
20090272842 | DEVICE TO HANDLE AND LOCK A COVER OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe ( | 11-05-2009 |
20090283631 | ENGINE ASSEMBLY FOR AIRCRAFT COMPRISING AN AERODYNAMIC COUPLING FAIRING MOUNTED ON TWO SEPARATE ELEMENTS - An aircraft engine assembly including an engine, an engine mounting structure, and a nacelle surrounding the engine and including an air intake and fan cowls. The assembly further includes a cradle supporting the fan cowls, fixedly mounted on the mounting structure or else on an entity including a fan case and the air intake attached to the case. The engine assembly further includes a junction aerodynamic fairing including a first mounting mechanism mounted on the cradle, and including a second mounting mechanism mounted on the other of the elements from among the mounting structure and the entity. | 11-19-2009 |
20090294579 | PRIMARY ENGINE STRUT STRUCTURE OF AN AIRCRAFT - The disclosed embodiments relate to a primary engine strut structure of an aircraft characterized in that it includes single-piece composite panels while replacing the metallic spars and metal panels, the composite panels having a lay-up of fibers oriented along crosswise directions whereby integrating, in the width of the skin of the panles, a lattice structure that replaces longitudinal and transversal stiffeners of the spars and metal panels. | 12-03-2009 |
20090294580 | THRUST FORCE TAKE-UP DEVICE FOR AN AIRCRAFT ENGINE PYLON ENGINE MOUNTING STRUCTURE, COMPRISING LATERAL LINK RODS WITH INTEGRAL SPREADER BAR STOPS - The invention relates to a device ( | 12-03-2009 |
20090308972 | ENGINE MOUNTING APPARATUS - An engine mounting apparatus that includes thrust struts, a balance yoke, and primary and secondary mount blocks. The thrust struts are connected to the balance yoke and the primary mount block has at least one thrust load connection connectable to the balance yoke for transferring thrust loads from an engine during normal operation of the engine mounting apparatus. The engine mounting apparatus is, characterised in that the secondary mount block is connected to the balance yoke via at least one thrust load catcher connection, the at least one thrust load catcher connection being arranged to be unloaded during normal operation of the engine mounting arrangement and to transfer the thrust loads from the engine in the event of a failure condition of the primary mount block. | 12-17-2009 |
20090314881 | ENGINE MOUNT SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE - A mount system for a gas turbine engine includes an aft mount which reacts at least a portion of a thrust load at an engine case generally parallel to an engine axis. | 12-24-2009 |
20100001123 | TRANSLATABLE THRUST INVERTER FOR JET ENGINE - The invention relates to a thrust inverter with grids ( | 01-07-2010 |
20100012775 | Torsionally De-Coupled Engine Mount System - A torsionally de-coupled engine mount system for use in tilt rotor aircraft applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount that is a simple bi-pod fitting. The forward mount counteracts forces and moments in six degrees of freedom, but the aft mount only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount. The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions. | 01-21-2010 |
20100038471 | Suspension system for aircraft auxiliary power unit with elastomeric member - The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric member and a second motion control nonelastomeric member, a first motion control elastomer member disposed to operatively interconnect the first motion control nonelastomeric member and the second motion control nonelastomeric member. The first motion control elastomer member includes an exterior surface coating formed from an elastomeric polymer dissolved in an organic solvent and the elastomeric polymer dissolved in the solvent is applied to an exterior surface of the first motion control elastomer member, the solvent evaporates, and the elastomeric polymer crosslinks. | 02-18-2010 |
20100038472 | AIRPLANE WITH REAR ENGINES - An aircraft has at least two jet-propulsion engines mounted laterally on the fuselage in a symmetrical design in the aft part of the fuselage. Each jet engine is mounted on the fuselage some distance from the vertical plane of symmetry of the aircraft, so that the jet engine, in a so-called half-buried configuration, is partly inside an envelope surface of a theoretical fuselage. The half-buried, jet engines are mounted on a main boom fitted on the vertical plane of symmetry of the aircraft, inside the fuselage in back, of a forward main frame. The tail sections are mounted on the main boom and the boom is integral with structures for transmitting forces into the forward part of the fuselage. The structure is advantageously made of fiber-reinforced composite materials. | 02-18-2010 |
20100044502 | BEAM MOUNTED REAR PROPULSION SYSTEM FOR AN AIRCRAFT AND AIRCRAFT WITH SUCH SYSTEM - A propulsive system for an aircraft including an auxiliary jet engine is integrated into a tail cone of a fuselage. A carrying structure of the jet engine is primarily formed with beams and frames or half-frames to which the auxiliary jet engine is fixed by lateral beams. The beams are interdependent of the frames and half-frames, and the beams are overhanging behind a frame behind which is fixed the engine. Each beam includes a lower half-beam and a higher half-beam, separated on at least a part of its length ahead from attachments of the jet engine to determine a space free of structure impediment for lateral air intakes. | 02-25-2010 |
20100044503 | JET ENGINE NACELLE FOR AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH A NACELLE - A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening. | 02-25-2010 |
20100051743 | REAR LOWER AERODYNAMIC FAIRING FOR THE ATTACHMENT DEVICE OF AN AIRCRAFT ENGINE - A rear lower aerodynamic fairing for an attachment device for an aircraft engine, including two side panels assembled together with transverse stiffening inner ribs spaced apart from each other along a longitudinal direction of the fairing, and a heat protection floor to be closely followed by a primary flow of the engine. The floor includes plural floor segments distributed along the direction and non-rigidly bound to each other, and the fairing further includes an assembling mechanism assembling the floor segments, offsetting the latter of the ribs to which are connected the assembling mechanism. | 03-04-2010 |
20100051744 | ENGINE PYLON FOR THE SUSPENSION OF A TURBO ENGINE UNDER AN AIRCRAFT WING - According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing. | 03-04-2010 |
20100072318 | PROPULSION DEVICE FOR OPERATION WITH A PLURALITY OF FUELS FOR AN AIRCRAFT - The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a propulsion unit and an energy converter. The energy converter is adapted for providing propulsion energy to the propulsion unit by a first fuel. Furthermore, the energy converter is adapted for providing propulsion energy to the propulsion unit by a second fuel. The propulsion unit adapted for generating forward thrust by the propulsion energy. | 03-25-2010 |
20100090056 | PYLON CAISSON ATTACHMENT ON A WING, GRIPPING A LATERAL PANEL OF THE CAISSON - An aircraft assembly including a wing element and an attachment pylori of a turboengine, including a rigid structure forming a caisson defined externally by a first longeron, a second longeron, and two lateral panels. The assembly also includes an attachment mechanism of the structure on the wing element, fitted with two front attachments, each including two first fittings solid with the associated lateral panel. For each front attachment, the two first fittings are arranged respectively on either side of their associated lateral panel. | 04-15-2010 |
20100096495 | AIRCRAFT WITH RECIPROCATING ENGINES PARTIALLY EMBEDDED IN THE FUSELAGE - Aircraft provided with turbojet engines of which the nacelles are partially embedded in the fuselage of the aircraft, characterised in that it comprises on engine nacelles an internal space comprising a platform capable of supporting personnel and maintenance equipment, with the portions of the nacelles located inside the aircraft comprising trapdoors or means for accessing inside the engines from the platform. | 04-22-2010 |
20100108802 | SAIL WING AIRCRAFT WHICH INCLUDES AN ENGINE MOUNTED ON A PYLON - Sail wing aircraft which includes a wing ( | 05-06-2010 |
20100116926 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE AND AIRCRAFT COMPRISING AT LEAST ONE SUCH DEVICE - A device for attaching an aircraft engine including a thrust force take-up device that includes a main fitting to be fixed to an engine mounting beam fixed to a box structure, an additional fitting fixed to the main fitting, and two load reacting link rods connected to the main fitting by a balance beam, each of the link rods being connected to the balance beam by a first longitudinal end by a first mechanical connection that has at least one axis of rotation, each of the link rods being connected to the additional fitting by a second longitudinal end by a second mechanical connection that has at least one axis of rotation, the second mechanical connection having play, the first and second mechanical connections having at least one axis of rotation in common. | 05-13-2010 |
20100127116 | NACELLE AND METHOD OF ASSEMBLING THE SAME - A method of assembling a nacelle for a gas turbine engine that includes an inlet end, an exhaust end, and an axis that extends through the engine from the inlet end through the exhaust end is provided. The method includes providing a cowl sized to cover at least a portion of the engine and coupling the cowl to the engine such that the cowl is slideable along the axis toward at least one of the inlet end and the exhaust end. | 05-27-2010 |
20100127117 | ATTACHMENT PYLON FOR AIRCRAFT HAVING A REAR ENGINE ATTACHMENT BEAM OFFSET FROM THE CAISSON - An engine attachment pylon for an aircraft including an intermediate piece interposed between a crossbar support and a rigid caisson, a first shear slug passing through a first interface fixing plane between the piece and the caisson, and a second shear slug passing through a second interface fixing plane between the piece and the support. Also, in side elevation, the intersection point between an axis of the pin and the plane, as well as the intersection point between an axis of the pin and the plane, are located on the common axis of two lateral thrust force collection connecting rods articulated on the crossbar. | 05-27-2010 |
20100127118 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE AND AIRCRAFT COMPRISING AT LEAST ONE SUCH DEVICE - An attachment device for an aircraft engine that includes a rigid structure and an attachment mechanism of the engine to the rigid structure. The attachment mechanism includes a device reacting to thrust forces generated by the engine, the reacting device including two link rods mechanically connected to a balance beam at a rear end by a first mechanical connection, a main fitting fixed to the rigid structure to which the balance beam is mechanically connected, and two additional fittings fixed to the rigid structure to which the link rods are mechanically connected with play. The mechanical connections between the balance beam and the main fitting and between the link rods and the additional fittings each include a pin orthogonal to a mid-plane of transmission of the forces. | 05-27-2010 |
20100133376 | AIRCRAFT ENGINE MOUNTING PYLON COMPRISING A TAPERED SHIM TO SECURE THE FORWARD ENGINE ATTACHMENT - A mounting pylon for an aircraft engine. The pylon includes a rigid structure forming a box including an inclined lower spar and an upper spar, and an engine mounting system mounted fixedly on the structure and including a forward attachment including an attachment body including a horizontal securing surface lying flat against a horizontal securing surface of the rigid structure. The horizontal securing surface of the rigid structure is defined by a tapered shim mounted on the inclined lower spar, externally relative to the box. | 06-03-2010 |
20100147996 | FAIL SAFE EXTENDED TORQUE BOX STRUT-TO-WING MOUNT - An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link. | 06-17-2010 |
20100147997 | AIRCRAFT ENGINE ATTACHMENT PYLON HAVING A REAR ENGINE ATTACHMENT PROVIDED WITH A SELF-LOCKING NUT - An aircraft engine attachment pylon including a rigid structure forming a caisson, and a rear engine attachment including an attachment body and at least one lateral fitting arranged on either side of the caisson. Each fitting includes a first portion pierced by first assembly holes enabling it to be fixed to the caisson, and a second portion defining a fixing surface of the body. The second portion includes a housing orifice receiving a self-locking nut cooperating with a screw supported against the body and, in transversal section, an axis of the screw passes through the first holes. | 06-17-2010 |
20100155525 | MONOLITHIC STRUCTURE FOR MOUNTING AIRCRAFT ENGINE - Assembly includes an integral monolithic structure for mounting an engine to an aircraft. The monolithic structure includes a nacelle portion and a support structure. The nacelle portion includes an inlet region and a fan case region defining an annular wall about an axial channel. A ring member disposed in the axial channel is connected through a plurality of radial elements to the annular wall. The support structure portion includes a forward section integral with the nacelle portion and an aft section including at least one aircraft mount region for mounting the monolithic structure to an aircraft. The forward section includes an inlet stiffening region radially outward of the annular wall. When mounted on the aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the aircraft instead of through the engine core. | 06-24-2010 |
20100163671 | A MOUNTING ELEMENT FOR A GAS TURBINE ENGINE, AND A STRUCTURE AND AN AIRCRAFT WITH SUCH A MOUNTING ELEMENT - A mounting element for transferring loads between a gas turbine engine and an airframe is provided, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a pin or a bolt. The mounting element includes a collapsible element surrounding the hole, and is adapted to operate in a first mode, and to operate, upon a collapse of the collapsible element, in a second mode, in which the stiffness of the mounting element is lower than in the first mode. In a second aspect of the invention the energy absorption capacity of the mounting element is higher in the second mode than in the first mode. | 07-01-2010 |
20100170980 | ENGINE MOUNTING STRUCTURE FOR AIRCRAFT WITH A REAR ENGINE ATTACHMENT BEAM FORMING A SPREADER BEAM - An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system. | 07-08-2010 |
20100176239 | DEVICE FOR MOUNTING AN AIRCRAFT TURBOPROP ENGINE COMPRISING HYDRAULIC ATTACHMENTS - An engine unit for an aircraft including a turboprop engine and its device for mounting on to a wing surface. The device includes a rigid structure and a mechanism for fastening the turboprop engine on to this structure. The fastening mechanism includes six mutually independent hydraulic systems, each one exclusively dedicated to the transfer, to the rigid structure, of efforts exerted respectively according to one of the six degrees of freedom of movement. Each hydraulic system includes at least one hydraulic jack with a piston attached to one of the two elements, i.e. either the turboprop engine or the rigid structure, together with a cylinder housing the piston and attached to the other of the two elements. | 07-15-2010 |
20100181417 | ATTACHMENT DEVICE FOR AIRCRAFT ENGINE AND AIRCRAFT COMPRISING AT LEAST ONE SUCH DEVICE - An attachment device for an aircraft engine including a rigid structure and an attachment mechanism of the engine onto the rigid structure. The attachment mechanism includes two thrust take-up connecting rods mechanically connected to a spreader, a connection fitting fixed to the rigid structure to which the spreader is mechanically connected by a junction fitting by a connection pin, and an additional fitting to which the connecting rods, the spreader, and the connection fitting are mechanically connected. A clearance is provided at the mechanical link between the connecting rods and the additional fitting, the link between the additional fitting and the connection fitting being made using the connection pin being inserted laterally, orthogonal to the median plane of the attachment device. | 07-22-2010 |
20100181418 | SECURING PLATE AND LONGITUDINAL HANDLING MEMBER FOR A ONE-PIECE AIRCRAFT PROPULSION UNIT - The invention relates to a securing plate ( | 07-22-2010 |
20100181419 | ENGINE MOUNTING STRUCTURE FOR AIRCRAFT HAVING A BEAM SPREADER CONNECTED AT FOUR POINTS - An engine mounting structure for aircraft including an engine mounting system including a device for transmission of the thrust efforts fitted with two lateral connecting rods and with a spreader beam mounted in connected fashion on a support element, through a principal connecting device defining a principal spreader beam hinge line positioned in a plane. The spreader beam is also mounted in connected fashion with some play on the element, using a secondary connecting device located at some distance, as seen from above, from the device, and defining a secondary spreader beam hinge line, which is also positioned in a plane. The rotation of the spreader beam is stopped by device coming into contact with the spreader beam. | 07-22-2010 |
20100193627 | ASSEMBLY FOR AN AIRCRAFT INCLUDING A WING ELEMENT AND A SUSPENSION PYLON - The invention relates to an assembly for an aircraft comprising a wing element ( | 08-05-2010 |
20100193628 | CONTINUOUS COMPOSITE FAN DUCT AND THRUST REVERSER - A duct having a continuous C-shaped cross section slidably attached to a strut supporting an aircraft engine. The duct may comprise an inner wall, an outer wall, a first end wall, a second end wall, at least one slider, a thrust reverser, and an outer cowl panel of a thrust reverser. The inner wall may comprise a forward section and an aft section. The aft section may be integral with the first end wall, the second end wall, the outer wall, and the at least one slider. The forward section may comprise a right half and a left half which may be pivotally attached to the strut and may pivot to an open position when the rest of the fan duct is slid aftward away from the engine. The duct, excluding the forward section of the inner wall, may slide aftward on its at least one slider, providing engine access. | 08-05-2010 |
20100206981 | PROPULSION ASSEMBLY FOR AIRCRAFT - The invention relates to a propulsion assembly for an aircraft, that comprises: a turbojet engine ( | 08-19-2010 |
20100288874 | ENGINE MOUNT BEARING SLEEVE REPAIR - Bearing bores for engine mount components must be periodically repaired. A component is disassembled and a bearing is removed from the bearing bore. An inner surface of the bearing bore is machined to remove any damage. A sizing sleeve is selected to have a press fit with the machined inner surface of the bearing bore and with the outer surface of a new bearing. The bearing is press fit into the sizing sleeve and the sizing sleeve is press fit into the bearing bore. The outer surfaces of the sizing sleeve and the bearing are swaged to assist in retaining and preventing relative movement between the bearing, sizing sleeve and engine mount component. | 11-18-2010 |
20100301159 | Mounting set, system and method - A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided. | 12-02-2010 |
20100301160 | Method and Apparatus for Improved Vibration Isolation - A vibration isolator is disclosed having a housing which defines a fluid chamber. A piston, which is movable to and from a down position, is disposed within the housing. A vibration isolation fluid is disposed within the fluid chamber. A passage having a predetermined diameter extends through the piston to permit the vibration isolation fluid to flow from one fluid chamber to the other. An elastic element is provided for reducing transmission of vibrations from the piston to the housing when the piston is at the down position. | 12-02-2010 |
20100314491 | AIRCRAFT ENGINE PYLON ATTACHMENT - An aircraft engine mounting structure comprising a pylon box having an upper surface and at least one attachment element configured to be attached to a front spar of an aircraft wing box, the front spar having a lower surface, the attachment element being configured to attach the rear face of the pylon box to the front spar such that at least a portion of the upper surface of the pylon box lies above the lower surface of the front spar. | 12-16-2010 |
20100327110 | GUIDING SYSTEM FOR AIRCRAFT NACELLE MAINTENANCE - The invention relates to a nacelle ( | 12-30-2010 |
20110001002 | SUSPENSION FOR MOUNTING A TURBOJET ENGINE ON AN AIRCRAFT - The present invention relates to an isostatic suspension for mounting a turbojet engine on a pylon of an aircraft, the turbojet engine comprising a front fan, an intermediate casing downstream of the fan with an outer shell and a hub interconnected by radial arms, and an exhaust casing with an outer shell on the same axis XX, the suspension comprising a front attachment on the intermediate casing, a rear attachment with at least two rear attachment links connected to the outer shell of the exhaust casing, a pair of thrust bars being fixed at their upstream ends to the hub of the intermediate casing. It is characterized in that the plane formed by the two links of the rear attachment is inclined with respect to the plane of the exhaust casing. | 01-06-2011 |
20110011972 | PRIMARY STRUCTURE OF A CONNECTING STRUT - The invention relates to an effort recovery structure ( | 01-20-2011 |
20110017866 | LOCKING DEVICE - The invention relates to a locking device ( | 01-27-2011 |
20110036942 | ENGINE ATTACHMENT PYLON COMPRISING MEANS OF FASTENING SPARS AND PANELS LOCATED OUTSIDE THE INNER SPACE IN THE BOX - An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box. | 02-17-2011 |
20110036943 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING A BOX WITH A CIRCULAR OR ELLIPTICAL SHAPED SECTION - An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape. | 02-17-2011 |
20110049291 | MOUNTING DEVICE FOR MOUNTING AN ENERGY SUPPLY DEVICE ON A STRUCTURAL COMPONENT OF AN AICRAFT AND AIRCRAFT WITH A MOUNTING DEVICE - An aircraft featuring: a fuselage with a fuselage section, an energy supply device, at least two supporting devices that are arranged on the fuselage section and serve for fastening the energy supply device, a mounting device for mounting an energy supply device on a structural component of an aircraft and an aircraft with a mounting device, as well as to a mounting device for mounting an energy supply device on a structural component of an aircraft and to an aircraft with a mounting device. | 03-03-2011 |
20110062279 | HYBRID BEAM FOR A THRUST REVERSER UNIT - Latch beams and hinge beams of an aircraft thrust reverser and a method for manufacturing the beams. The latch and hinge beams may comprise a plurality of hollow composite tubes joined with a plurality of machined metal fittings in alternating succession. The metal fittings may comprise at least one of hinge fittings and latching fittings. The latch and hinge beams may further comprise slider tracks configured to slidably attach to a translating sleeve of the thrust reverser. The hinge beams may each be rotatably attached to an engine strut or pylon of the aircraft, and the latch beams may each be mechanically latched with each other. Each of the latch and hinge beams may also be fixedly attached to an inner engine cowling of the thrust reverser. | 03-17-2011 |
20110079679 | DEVICE FOR LOCKING AN ENGINE ON AN AIRCRAFT PYLON - The device for locking an engine ( | 04-07-2011 |
20110108662 | ATTACHMENT PYLON FOR AN AIRCRAFT TURBO-SHAFT ENGINE WITH CONCENTRIC HOT AIR CHANNELS - The invention relates to a pylon ( | 05-12-2011 |
20110114786 | DEVICE FOR ATTACHING AN AIRCRAFT ENGINE COMPRISING A THRUST FORCE TAKE-UP DEVICE WITH A COMPACT DESIGN - An aircraft engine attachment device including a rigid structure and a mechanism attaching the engine on the rigid structure, the attachment mechanism including a rear engine attachment and a device for taking-up thrust forces generated by the engine. The rear engine attachment is attached to the rigid structure by two lateral fittings attached to the rigid structure. The force take-up device includes two connecting rods mechanically connected to a spreader beam by a mechanical connection, a connection fitting attached to the rear engine attachment and mechanically connected to the rigid structure by a thrust pin, the lateral fittings including a stop mechanism to limit pivoting of the spreader beam if a connecting rod breaks and ensuring transmission of thrust forces to the rigid structure. | 05-19-2011 |
20110121132 | TRUSS-SHAPED ENGINE PYLON AND METHOD OF MAKING SAME - An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall. | 05-26-2011 |
20110127367 | FAN COWL SUPPORT FOR A TURBOFAN ENGINE - A fan cowl support for an aircraft having an engine pylon, an engine fan case and an engine fan cowl. The fan cowl support includes a support having a forward end connected to the engine fan case and an aft end connected to the engine pylon. At least a portion of the engine fan cowl is connected to the support. | 06-02-2011 |
20110127368 | SINGLE PLANE MOUNT SYSTEM FOR GAS TURBINE ENGINE - A mounting system for a gas turbine engine assembly includes a plurality of mounting links attached the gas turbine engine along a single plane transverse to the engine centerline for separating the loads from the core engine. | 06-02-2011 |
20110127369 | FAN COWL SUPPORT CRADLE MOUNTED ON THE ATTACHMENT PYLON AND ON THE AIR INLET OF THE NACELLE - An engine unit for an aircraft including an engine, a device for hooking the engine, and a nacelle surrounding the engine and provided with fan cowls, the device for hooking including a rigid structure and a front aerodynamic structure whereon the fan cowls are articulated, the front aerodynamic structure including a cradle with a rear mechanism of hooking mounted on the rigid structure. The cradle also includes a front mechanism of hooking mounted on an air inlet of the nacelle. | 06-02-2011 |
20110127370 | FAN COWL SUPPORT FOR A TURBO FAN ENGINE - A fan cowl support for an aircraft having an engine pylon, an engine fan case and an engine fan cowl. The fan cowl support includes a support having a forward end connected to the engine fan case and an aft end connected to the engine pylon with a spherical connector. At least a portion of the engine fan cowl is connected to the support. | 06-02-2011 |
20110127371 | ENGINE MOUNT OF AIRCRAFT AND AIRCRAFT - An engine mount of an aircraft and an aircraft are provided, which can reduce a size of an engine mount and can effectively use a space in an engine nacelle even in an engine with a high bypass ratio. An engine core section | 06-02-2011 |
20110139925 | ARRANGEMENT FOR THE SUSPENSION OF A JET ENGINE TO A SUPPORTING STRUCTURE - An arrangement ( | 06-16-2011 |
20110155847 | AFT PYLON FAIRING FOR AN AIRCRAFT ENGINE SUSPENSION SYSTEM - This invention relates to an aft pylon fairing ( | 06-30-2011 |
20110168836 | AIRCRAFT ENGINE SUPPORTING PYLON | 07-14-2011 |
20110168837 | AIRCRAFT PROPULSION SYSTEM - An aircraft propulsion system including a bypass turbojet engine surrounded by a nacelle together with a mechanism attaching the engine to a pylon of an aircraft. The nacelle includes an inner structure forming a body of revolution including a rigid framework formed by an upstream annular frame fastened to an intermediate casing of the engine, a downstream annular frame supporting the exhaust casing of the engine, and longitudinal arms connecting the frames together, the annular downstream frame being fastened to the pylon by a flexible or hinged suspension mechanism. | 07-14-2011 |
20110174918 | DEVICE FOR FASTENING A TURBOPROP, PREFERABLY UNDER AN AIRCRAFT WING - The present invention relates to an engine assembly for an aircraft comprising an attachment means, a turboprop on an attachment mast, this means including a plurality of front engine attachments ( | 07-21-2011 |
20110174919 | STRUT DESIGNED TO SUPPORT AN AIRCRAFT TURBOJET ENGINE, AND NACELLE COMPRISING SUCH A STRUT - This strut ( | 07-21-2011 |
20110192933 | MAST FOR SECURING AN ENGINE TO AN AIRCRAFT WING - A securing mast for securing an engine to the wing of an aircraft, wherein the device includes two fasteners, a first eng of each fastener being secured to the engine and the second end of each fastener being secured to the wing, wherein the fasteners include hinged junction means capable of modifying the geometry of the aforementioned fasteners in order to modify a distance between the engine and the wing. | 08-11-2011 |
20110204179 | ENGINE PYLON FOR AIRCRAFT - An engine pylon for an aircraft that includes a primary structure including aircraft mounting points arranged symmetrically relative to a middle vertical longitudinal plane of the pylon. The primary structure is asymmetrical relative to the middle vertical longitudinal plane and has respective fundamental modes of vibration in a vertical direction that are uncoupled from the fundamental modes of vibration thereof in a transverse direction. | 08-25-2011 |
20110215193 | HYBRID TORQUE BOX FOR A THRUST REVERSER - A hybrid torque box comprising a plurality of composite tubes and metal fittings attached together in alternating succession and configured to attach a thrust reverser to an engine fan case of an aircraft. The hybrid torque box may be substantially hollow and may comprise two V-blades for attaching the torque box to the engine fan case. The hybrid torque box may also be attached to or integral with a bull nose fairing configured for attachment with a cascade of the thrust reverser. Furthermore, the hybrid torque box may comprise and/or attach to a cowl interface flange configured for interfacing with an outer cowl of the thrust reverser. | 09-08-2011 |
20110226893 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, CONNECTED TO THE FUSELAGE BY AT LEAST ONE BLOCKING ELEMENT UNDER COMPRESSION LOADING - A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure. | 09-22-2011 |
20110226894 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, EXTENDING THROUGH THE FUSELAGE AND CONNECTED THERETO BY AT LEAST ONE CONNECTING ROD - A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings. | 09-22-2011 |
20110233326 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, EXTENDING THROUGH THE FUSELAGE AND CONNECTED THERETO BY AT LEAST ONE CONNECTING ROD - A rear part of an aircraft, including a support structure for supporting engines, extending through the fuselage, through two openings distributed on either side of a vertical median plane of the aircraft. The support structure includes a first half-structure and a second half-structure respectively extending through the first and second fuselage openings, the first and second half-structures being joined to each other so that they can be disassembled in an inside space defined by the fuselage. | 09-29-2011 |
20110248116 | ATTACHMENT PYLON FOR AIRCRAFT TURBOSHAFT ENGINE, COMPRISING A REAR FLAP WITH MOBILE INCIDENCE - The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon ( | 10-13-2011 |
20110259996 | AIRCRAFT PROPULSION SYSTEM - An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane. | 10-27-2011 |
20110259997 | SUSPENSION RUDDER BAR FOR AN AIRCRAFT TURBOJET AND A SUSPENSION WITH FAN HANGER PROVIDED THEREWITH - This invention aims at making a rudder bar with a reduced master-couple in the case of a breaking of a connecting rod. To this end, this invention provides shifting the contact areas to the interior of the rudder bar and thereby reducing the transversal bulk thereof. | 10-27-2011 |
20110259998 | CONFIGURATION OF A REAR FUSELAGE TAIL CONE OF AN AIRCRAFT WITH AN AUXILIARY POWER UNIT - Configuration of a rear fuselage tail cone of an aircraft with an auxiliary power unit, whereby a fire compartment of the rear fuselage tail cone defines a housing for the auxiliary power unit in which the auxiliary power unit is housed laterally and asymmetrically with respect to a longitudinal axis (X) of the rear fuselage tail cone and the auxiliary power unit is directly fasten attached to a structural skin wall of the housing. Additionally, by struts or rods attached to opposite side and upper structural skin wall of the fire compartment. | 10-27-2011 |
20110266389 | PIN SYSTEM FOR THE CONNECTION ASSEMBLY OF AN ENGINE PYLON UNDERNEATH A WING OF AN AIRCRAFT - The invention relates to a connection assembly of an engine pylori underneath an aircraft wing, the wing being provided with a fitting ( | 11-03-2011 |
20110284686 | SUSPENSION ASSEMBLY FOR AN AIRCRAFT TURBOJET ENGINE - The invention relates to a suspension assembly for an aircraft turbojet engine ( | 11-24-2011 |
20110290934 | AIRCRAFT ENGINE ASSEMBLY COMPRISING AN ANNULAR LOAD-TRANSFER STRUCTURE SURROUNDING THE CENTRAL CASING OF A TURBOJET ENGINE - An aircraft engine assembly including an annular load-transfer structure surrounding the central casing and being mechanically connected to a plurality of substantially planar structures arranged externally with respect to the plurality of substantially planar structures, and biasing it at a plurality of load application points. At least one connecting rod is associated with each of the load application points, the connecting rod being positioned tangentially with respect to the casing, and including an inner end connected to this casing, and an outer end connected to the structure so that it has extending through it an imaginary plane in which the annular structure is located and extends through the load application point. | 12-01-2011 |
20110290935 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a stiffening transverse internal rib for an aerodynamic fairing of an engine mounting device, including:
| 12-01-2011 |
20110290936 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs ( | 12-01-2011 |
20110309188 | RIGID AIRCRAFT PYLON STRUCTURE IN CONTACT WITH A FUSELAGE LATERAL EXTENSION FOR ATTACHMENT - An aft part of an aircraft, including at least one engine assembly including a turbine engine and a turbine engine mounting pylon. A rigid structure of the mounting pylon includes a longitudinal central box and a connection box carried by the box and projecting from the box. The aircraft structure includes a fuselage lateral extension projecting from it, and the connection box is pressed into contact with the fuselage extension, below it, an attachment mechanism being arranged between these two entities. | 12-22-2011 |
20110309189 | RIGID AIRCRAFT PYLON FITTED WITH A RIB EXTENSION FOR TAKING UP THE MOMENT IN THE LENGTHWAYS DIRECTION - An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly. | 12-22-2011 |
20110315813 | TURBOMACHINE SUPPORT PYLON FOR AIRCRAFT - The invention relates to an aircraft support pylon ( | 12-29-2011 |
20110315814 | ASSEMBLY COMPRISING A GAS TURBINE ENGINE AND A SUPPORTING PYLON - A gas turbine engine | 12-29-2011 |
20120001019 | PYLON FOR ATTACHING A GAS TURBINE ENGINE - A pylon is provided for attachment of a gas turbine engine to a wing of an aircraft. The gas turbine engine comprises a core fairing surrounding a core generator and defining a nozzle for discharging a core gas flow, and a fan nacelle surrounding the core fairing to define an annular bypass duct therebetween for discharging fan air. The pylon has a trailing edge which is rearward of the trailing edge of the core fairing and the trailing edge of the fan nacelle. The pylon further has having two laterally-spaced side faces which span the bypass duct between the fan nacelle and the core fairing and extend in the rearward direction of the engine to end at the trailing edge of the pylon. Each side face has a bottom edge which extends in a rearward direction of the engine from the core fairing to the bottom end of the trailing edge of the pylon. The bottom edges merge at a merging position between the trailing edge of the fan nacelle and the trailing edge of the pylon such that the bottom edges form a single bottom edge from the merging position to the bottom end of the trailing edge of the pylon. The pylon is intended to exert control on the bypass flow of a gas turbine engine. Other pylons are also provided which can also exert such control. | 01-05-2012 |
20120006936 | ENGINE ASSEMBLY FOR AIRCRAFT INCLUDING A MODULAR RIGID STRUCTURE FOR MOUNTING PYLONS - An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine. | 01-12-2012 |
20120006937 | REAR PART OF AN AIRCRAFT INCLUDING AN ENGINE SUPPORT STRUCTURE ASSEMBLED SO AS TO OSCILLATE ON THE FUSELAGE - A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings. | 01-12-2012 |
20120012694 | FAIL-SAFE AIRCRAFT ENGINE MOUNTING APPARATUS - A mounting apparatus for an aircraft engine that provides load path redundancy includes a forward mount that attaches the aircraft engine to a pylon at a forward position of the aircraft engine, an aft mount that attaches the aircraft engine to the pylon at an aft position of the aircraft engine and a thrust assembly connected to the forward mount, and the aft mount. The forward mount includes an aircraft engine attachment assembly and a fail-safe assembly. The aft mount includes an aircraft engine attachment assembly and a fail-safe assembly. | 01-19-2012 |
20120018575 | AIRCRAFT ENGINE MOUNTING SYSTEM AND METHOD OF MOUNTING AIRCRAFT ENGINES - In an embodiment the invention includes an aircraft engine mounting system ( | 01-26-2012 |
20120018576 | LINKING DEVICE FOR LINKING A FIRST BODY TO A SECOND BODY, IN PARTICULAR FOR AN AIRCRAFT ENGINE ASSEMBLY | 01-26-2012 |
20120018577 | ENGINE MOUNTING WITH AN ADAPTED LOAD/DEFORMATION CURVE - The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling within a predetermined range ([CA, CB]) is less than the stiffness of the mounting for load values that fall below or above the predetermined range; considering a first load value (CS | 01-26-2012 |
20120056033 | PYLON FOR ATTACHING AN AIRCRAFT TURBINE ENGINE COMPRISING ALIGNED FRONT WING TIES - The invention relates to a pylon for attaching a turbine engine for an aircraft, having a rigid structure ( | 03-08-2012 |
20120061510 | Aircraft Engine Exhaust Nozzle System for Jet Noise Reduction - The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft. | 03-15-2012 |
20120080554 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING TWO FRONT WING SYSTEM ATTACHMENTS WITH ORTHOGONAL SHEARING PINS - The present invention relates to an aircraft assembly ( | 04-05-2012 |
20120080555 | TAKE-UP DEVICE FOR THRUST FORCES WITH CONNECTING RODS FOR AIRCRAFT ENGINE ATTACHMENT PYLON, INTEGRATING THREE ALIGNED BALL JOINTS - The present invention relates to a take-up device for thrust forces ( | 04-05-2012 |
20120085859 | SUSPENSION FOR AN ENGINE ON AN AIRCRAFT STRUT INCLUDING A SUSPENSION ARCH - A suspension for an engine on an aircraft strut, the suspension comprising a beam with a plate provided with fixing means for fixing to said strut and a suspension arch linked to the beam by at least one pivot link whose axis is intended to be parallel to the axis of the engine, the suspension arch having, at each of its ends, fixing means for fixing to a case of the engine. | 04-12-2012 |
20120091265 | SUPPORT STRUCTURE - A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular frame attaches to the pylon via a first attachment arrangement at the first attachment position. Two thrust struts respectively extend from the other two vertices of the triangular frame and attach to the pylon via a second attachment arrangement at the second attachment position. Three engine connection formations extend from the respective vertices of the triangular frame to positions on the engine casing to connect the support structure to the engine casing. | 04-19-2012 |
20120104162 | PYLON ARRANGEMENT FOR OPEN STRUCTURE - An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut. | 05-03-2012 |
20120111995 | ENGINE ASSEMBLY FOR AN AIRCRAFT THE ENGINE ATTACHMENT STRUT OF WHICH INCLUDES A STRUCTURAL CASE FORMING AN INTERNAL RADIAL DELIMITATION OF THE SECONDARY FLOW - An engine assembly for an aircraft including a dual-flow turbomachine and an attachment strut. The turbomachine includes a structural case extending downstream of the hub of an intermediate casing, the case contributing to the internal radial delimitation of a passage for a secondary flow of the turbomachine. Also, the primary structure includes a structural case, assembled on the structural case and positioned directly downstream of the structural case such that it also contributes to the internal radial delimitation of the passage for the secondary flow. The primary structure also includes an offset structure positioned in the passage, and configured to connect the case to an element of the aircraft. The structural case also includes a thrust reversal system. | 05-10-2012 |
20120111996 | ASSEMBLY FOR AN AIRCRAFT COMPRISING A TURBOMACHINE ATTACHMENT STRUT OF WHICH THE MEANS FOR ATTACHMENT TO THE WING ARE ARRANGED IN A T SHAPE - An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment. | 05-10-2012 |
20120119019 | Inverted Airfoil Pylon For An Aircraft - An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location. | 05-17-2012 |
20120138736 | AIRPLANE WITH A TAILCOAT TAIL ASSEMBLY AND REAR ENGINE - An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage. | 06-07-2012 |
20120145824 | PYLON FOR FIXING AN AIRCRAFT ENGINE HAVING UNDUCTED PUSHER PROPELLERS - A pylon for fixing an aircraft engine having unducted pusher propellers, the pylon ensuring the fixation of a propulsive system on the boattail of the aircraft, the pylon having a trailing edge, with an upper face and a lower face, for an airflow encountered by the pylon, wherein at least one of the two faces of the upper face and the lower face of the trailing edge is inclinable, at least in part. | 06-14-2012 |
20120160957 | AIRCRAFT AND EXTERNAL POD FOR AIRCRAFT - One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 06-28-2012 |
20120168558 | AIRCRAFT ASSEMBLY INCLUDING AN ELEMENT FOR MOUNTING AN ENGINE AND ASSOCIATED AIRCRAFT - An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations. | 07-05-2012 |
20120175462 | AIRCRAFT ENGINE MOUNTING STRUCTURE, ASSEMBLY COMPRISING THIS STRUCTURE AND ASSOCIATED AIRCRAFT - An engine is suspended from a main linear portion of a structure mounted on a fuselage or a wing surface of an aircraft. A connection includes flat symmetrical wings at an angle to one another, to support an attaching flange on which the engine is mounted, directly or through a mounting element. The flat shape of the wings makes them easy to manufacture, and enables them to resist the forces satisfactorily. The intermediate element resists overhang forces of the mounting satisfactorily. Flexible connections filter the engine's vibrations and prevent irregular forces being transmitted. | 07-12-2012 |
20120211597 | SYSTEM FOR ATTACHING AN IMPELLER ENGINE - The invention relates to a system for attaching an element ( | 08-23-2012 |
20120234970 | AIRCRAFT ENGINE ATTACHMENT PYLON - The invention relates to an aircraft engine attachment pylon, comprising a box formed by the assembly of a first spar ( | 09-20-2012 |
20120241555 | SUPPORT BLOCK FOR A MOTOR OF A ROTARY WING DRONE - The support block ( | 09-27-2012 |
20120273609 | STREAMLINED PROFILE REDUCING THE SPEED DEFICIT IN ITS WAKE - The invention relates to a streamlined profile reducing the speed deficit in its wake, a pylon comprising such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile comprises a device ( | 11-01-2012 |
20120273610 | ENGINE PYLON COMPRISING A VORTEX GENERATOR, AND METHOD FOR THE PRODUCTION THEREOF - The invention relates to a method for manufacturing an engine pylon ( | 11-01-2012 |
20120305700 | SYSTEM AND METHOD FOR MOUNTING AN AIRCRAFT ENGINE - A mounting system and method capable of reducing backbone deflection in a high-bypass turbofan engine. The system includes a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to an engine support structure of the aircraft. The first and second links are configured to define a focal point thereof at a location that is a distance from a centerline of the engine of not more than 15% of an inlet diameter at an inlet of the engine, and is located aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver. The location of the focal point is such that a moment of a thrust load of the engine and a moment of the inlet load oppose each other, thereby reducing backbone bending of the engine during the climb maneuver. | 12-06-2012 |
20120325958 | AIRCRAFT WITH REAR ANNULAR TAIL - A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area. | 12-27-2012 |
20130001356 | REINFORCED AIRCRAFT FUSELAGE - Aircraft having attached to the rear fuselage ( | 01-03-2013 |
20130015291 | FIRE RESISTANT STRUCTURAL MOUNT YOKE AND SYSTEMAANM DeDe; Brian C.AACI San DiegoAAST CAAACO USAAGP DeDe; Brian C. San Diego CA USAANM Lau; DavidAACI San DiegoAAST CAAACO USAAGP Lau; David San Diego CA USAANM Jewess; Gordon F.AACI RzeszowAACO PLAAGP Jewess; Gordon F. Rzeszow PL - A mount yoke assembly comprises a first main hanger bracket and a first anchor bracket. The first main hanger bracket includes a first receiving portion for a first auxiliary power unit (APU) mount with first and second hanger arms. The first hanger arm includes a first hanger flange extending proximate a distal end of the first hanger arm. The first anchor bracket includes a first plurality of anchor holes and a first anchor flange. The first plurality of anchor holes are disposed substantially along a length of the first anchor bracket for securing the mount yoke assembly to a component of an APU assembly. The first anchor flange extends from the first anchor bracket for hingeably securing the first anchor bracket to the first main hanger bracket. | 01-17-2013 |
20130032662 | AERODYNAMIC AFT FAIRING OF AN AIRCRAFT ENGINE SUSPENSION PYLON - The invention relates to an aerodynamic aft fairing of an engine pylon ensuring the mounting of an engine ( | 02-07-2013 |
20130032663 | DEVICE FOR REDUCING NOISE FROM JET-PYLON INTERACTIONS ON JET ENGINES - An aircraft pylon for mounting a dual-flow or triple-flow jet engine, the pylon including an upper surface for connection to the aircraft, two side flanks, and a flange on the lower portion of the pylon. The pylon further includes at least one portion that extends downstream from the cold flow nozzle of the jet engine and lies in the cold flow and, on the portion thereof extending into the cold flow beyond the nozzle, at least one opening, positioned on one of the flanks of the pylon, by which an air stream is injected into or drawn from the gas flow that flows along the flanks of the pylon. | 02-07-2013 |
20130062460 | FUSELAGE AND METHOD FOR REDUCING DRAG - Aircraft engineering applicable for improving aerodynamic quality of helicopters, airplanes, including big airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, by reducing contact area between the external fuselage tail section surface and a high-speed air flow, area of contact is reduced by increasing surface area of holes in the fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is convex upwards, for example, curved upwards according to the shape of the airfoil convex side. The upper hole for the aerodynamic channel in the fuselage skin may be located along the fin middle portion divided lengthwise by the fin to right and left, in two. The aerodynamic channel is made through and may be open. The upper front edge aligned hole of the aerodynamic channel has a greater surface area than the rear hole aligned with the fuselage end. | 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 |
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 |
20130099051 | TURBOSHAFT ENGINE ATTACHED TO A PYLON OF THE FUSELAGE OF AN AIRCRAFT BY A FAILSAFE SUSPENSION SYSTEM - A suspension system including a front suspension plane located at an intermediate turboshaft engine casing and connecting same to a pylon, a rear suspension plane located at an exhaust casing of the turboshaft engine and connecting same to the pylon, and a failsafe intermediate suspension plane located between the front and rear planes and including at least one connecting rod connecting the turboshaft engine having a structural outer casing to the pylon, the connecting rod mounted on the turboshaft engine with a predetermined clearance that renders the connecting rod inoperable while the suspension system of the rear plane is operating. The connecting rod is advantageously arranged between the outer casing and the pylon, and an element made of a flexible material is combined with the connecting rod to create the predetermined clearance by an elastically deformable nature thereof. | 04-25-2013 |
20130105622 | AFT PYLON FAIRING FOR AIRCRAFT ENGINE SUSPENSION SYSTEM, COMPRISING A HEAT SHIELD CAPABLE OF EXPANDING FREELY | 05-02-2013 |
20130119191 | LOAD-BEARING STRUCTURES FOR AIRCRAFT ENGINES AND PROCESSES THEREFOR - Load-bearing structures constructed from polymer matrix composite (PMC) materials, and processes for their production. The structures are produced from at least one shaped panel formed of a continuous fiber reinforcement in a thermoplastic resin matrix. The shaped panel has been thermoformed to have a substantially constant cross-sectional thickness and portions that lie in different planes and are interconnected by one or more bends. The shaped panel is machined to alter its shape, and optionally to produce multiple separate subcomponents therefrom. The machined shaped panel can constitute the entire structure, or the structure can be formed by joining the machined shaped panel with other shaped panels or by joining two or more of the subcomponents. The structure can be installed on an aircraft engine to secure components to the engine. | 05-16-2013 |
20130119192 | ANTIVIBRATION SUSPENSION MEANS FOR A TIE BAR OF AN AIRCRAFT POWER TRANSMISSION GEARBOX, AN ANTIVIBRATION SUSPENSION DEVICE, AND AN AIRCRAFT - An antivibration suspension device ( | 05-16-2013 |
20130134257 | RESILIENT AIRCRAFT ENGINE MOUNTS AND AIRCRAFT ENGINE MOUNTING SYSTEMS INCLUDING THE SAME - Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces. | 05-30-2013 |
20130161446 | HINGING CRADLE FOR FAN COWLS SUPPORTED BY SAID COWLS IN CLOSED POSITION - The invention relates to an engine assembly for aircraft in which the coupling device comprises a fore aerodynamic structure having a cradle equipped with an aerodynamic cowling, the cradle being hinge mounted on the air intake of the engine, and the fan cowls being mounted to move on the cradle so as to be able to occupy an open position as well as a closed position in which they are supported by the air intake and by a thrust reverser. According to the invention, when the cowls are in open position, the cradle adopts a first configuration in which its aft end rests on a span of the engine mounting structure, and when the cowls are in closed position, the cradle, borne by said cowls, adopts a second configuration in which it is lacking any direct mechanical link with the other elements of the engine mounting structure. | 06-27-2013 |
20130175389 | Mechanically Optimized Liquid Inertia Vibration Eliminator and Aircraft Pylon System - A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft. | 07-11-2013 |
20130175390 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL - An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | 07-11-2013 |
20130200211 | GAS TURBINE ENGINE MOUNTING STRUCTURE WITH SECONDARY LOAD PATHS - A connection for mounting an aircraft engine to an aircraft pylon includes a plate to be connected to a portion of an engine, and a body that extends rearward from the plate. A back-up connection, including a pin positioned within a slotted hole, is provided between the portion of the engine and the body. When there is a normal connection between the plate and the body, there is clearance between the pin and the slotted hole. | 08-08-2013 |
20130221154 | Motor Pylons For A Kite And Aiborne Power Generation System Using Same - A motor pylon system adapted for use with an airborne power generations system is disclosed. The pylons may support turbine driven generators for wind based electrical power generation which also function as electric motors in some aspects. The pylons may be designed to provide side force useful for turning a tethered flying wing flying in a circular cross wind flight path. The pylons may be designed to minimize air flow disruptions over the main wing. | 08-29-2013 |
20130221155 | ENGINE ATTACHMENT PYLON - An engine attachment pylon for mounting an aircraft engine to an aircraft structure while minimising vibrations induced into the engine attachment pylon during flight and operation of the engine. The engine attachment pylon according to the present invention comprises a rigid box like structure housing a resonator which is tuned to attenuate tension and compression vibrations, experienced by the engine attachment pylon. The engine attachment pylon is primarily used in combination within another identical engine attachment pylon, both being linked together on a vertical plane within the fuselage by a hinge like junction, and each engine attachment pylon being raised approximately 30° from the horizontal axis of the fuselage. | 08-29-2013 |
20130240666 | Engine Mounting System for an Aircraft - A method and apparatus comprising a frame, a first linking system connected to the frame, and a second linking system connected to the frame. The frame may be configured to be connected to a support structure for an engine of an aircraft. The first linking system may be configured to be connected to a fan case in the engine. The second linking system is configured to be connected to an engine core case in the engine. | 09-19-2013 |
20130256453 | RAM AIR TURBINE STOW ABORT ASSEMBLY - An example ram air turbine stow abort assembly includes a release pin movable between an engaged position that prevents rotation of a drive shaft and a released position that allows rotation of the drive shaft. A release lever is rotatable about an axis in response to the release pin being in the engaged position or the released position. A pawl has a link to the release lever. The link causes the pawl to move toward the axis from a locking position to a clearance position. The pawl is positioned to engage a lock when in the locking position to prevent movement of the ram air turbine assembly to a stowed position when the turbine blades are misaligned. | 10-03-2013 |
20130270389 | FIBROUS STRUCTURE FOR A PART MADE OF COMPOSITE MATERIAL HAVING ONE OR MORE ARCHSHAPED PORTIONS - A reinforcing fiber structure for a composite material part is woven as a single piece by multilayer weaving between plural layers of weft yarns and plural layers of warp yarns arranged in adjacent manner between two faces of the structure. The fiber structure includes at least one arcuate portion extending over one of the faces of the fiber structure, the arcuate portion including at least some of the warp yarns continuous with at least two adjacent warp yarn layers present on one of the faces of the structure. The warp yarns of the arcuate portion are of a length that is longer than the warp yarns of at least two underlying warp yarn layers of the structure. In addition, the warp yarns of the arcuate portion are not interlinked with other warp yarns of the fiber structure. | 10-17-2013 |
20130320134 | AUXILIARY FIRE RESISTANT MOUNT SYSTEM FOR AN AUXILIARY POWER UNIT - An auxiliary power unit is composed of a gas turbine engine, a gearbox, and a gearbox driven generator. A mount bracket is mechanically attached to the gearbox. The bracket is for connecting to an aircraft strut system. The aircraft strut system connects to the aircraft structure. The mount bracket has an upper mechanical attachment point and a lower mechanical attachment point to the gearbox. The gearbox includes an oil reservoir, and the lower attachment point is beneath the oil level within the oil reservoir such that said lower attachment point will be cooled by oil in the oil reservoir. | 12-05-2013 |
20130320135 | AFT AERODYNAMIC FAIRING WITH IMPROVED THERMAL RESISTANCE FOR A PYLON FOR ATTACHING AN AIRCRAFT PROPELLING ASSEMBLY - An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use. | 12-05-2013 |
20130327885 | ELECTROMECHANICAL ACTUATOR LUBRICATION SYSTEM FOR RAM AIR TURBINE - An actuator for a ram air turbine includes a housing that supports a piston rod arranged in a cylinder. The piston rod and the cylinder are slideably moveable relative to one another between retracted and deployed positions. A can surrounds the cylinder and is loosely fixed relative to the housing. The can is permitted to pivot relative to the housing and cylinder relative to the cylinder in a radial direction during operation. In operation, the ram air turbine is deployed by initiating a deploy sequence. The piston rod and the cylinder are extended relative to one another to the deployed position. The method includes pivoting a can that surrounds the cylinder and the piston rod. | 12-12-2013 |
20130327886 | NACELLE - A nacelle configured to be coupled to an underside of a wing so as to form a clearance space therebetween includes at least a lip defining an inlet and a first cowling disposed aft of the lip. The first cowling has an outer surface with at least one concave region that is depressed relative to another region of the outer surface. In some aspects, the depressed region can be disposed on an inboard side of the wing, for example, on an upper surface of the first cowling facing a wing. The nacelle can include a second cowling disposed between the lip and the first cowling and the first cowling can translate in a longitudinal direction relative to the second cowling. | 12-12-2013 |
20140021292 | INTERMEDIATE STRUCTURE FOR INDEPENDENTLY DE-MOUNTABLE PROPULSION COMPONENTS - An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module. | 01-23-2014 |
20140042268 | SELF-RETAINING SHEAR PIN FOR BLIND MOUNT LOCATION - A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing. A lock member is positioned between an inner end of the bushing and the bolt head. The lock member is radially expandable, and has a free radially outer dimension that is smaller than an inner dimension of the inner bore. The lock member is expandable to have an expanded radially outer dimension that is greater than the inner dimension of the inner bore. A nut is tightened on the outer end of the bolt. The nut causes the bushing to move relative to the bolt, and causes the lock member to expand radially. A shackle connection for a gas turbine engine and an aircraft are also disclosed. | 02-13-2014 |
20140054413 | AIRPLANE HAVING A REAR PROPULSION SYSTEM - An aeroplane comprising a fuselage elongated in a longitudinal direction of the aeroplane is provided. The aeroplane includes a wing attached to the fuselage in a midsection of said fuselage in the longitudinal direction, such that part of the fuselage extends forward of the wing toward a front extremity of the fuselage, and part of the fuselage extends from the rear of the wing toward a rear extremity of the fuselage. A rear fuselage section includes at least one engine attached to the fuselage and located to the rear of the wing. The one or more engines attached to the fuselage are attached in a rear position such that only parts of the aeroplane located in a projection space of the one or more engines attached to the fuselage and the rear fuselage does not include any aerodynamic surfaces intended to assure stability and/or aerodynamic control of the aeroplane. | 02-27-2014 |
20140061375 | ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO A PYLON - An assembly for mounting a turbine engine to a pylon includes a mounting beam, a plurality of fasteners, a first mounting linkage and a second mounting linkage. The mounting beam includes a mount beam fitting that extends axially between a first mount beam end and a second mount beam end, and a mount beam flange that extends radially out from the mount beam fitting at the first mount beam end. A first fastener aperture extends radially through the mount beam fitting, and a second fastener aperture extends axially through the mount beam flange. The fasteners connect the mounting beam to the pylon. A first of the fasteners is mated with the first fastener aperture, and a second of the fasteners is mated with the second fastener aperture. The first mounting linkage connects the first mount beam end to a first engine attachment. The second mounting linkage connects the second mount beam end to second engine attachments. | 03-06-2014 |
20140077027 | DEVICE FOR SUSPENDING A TURBINE ENGINE FROM AN AIRPLANE - A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes. | 03-20-2014 |
20140117152 | Twin Tip Turbine Propulsors Powered by a Single Gas Turbine Generator - A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed. | 05-01-2014 |
20140145026 | Unmanned Aerial Device - Unmanned aerial device are disclosed herein which include a flight element comprising a central structural component configured to protect electronic circuitry, and structural beams, extending generally horizontally from opposing sides of the structural component, each beam being configured to contain electric wiring and a motor and to support a propeller. The device also includes a platform element, extending below the flight element, configured to support a video capturing device and a battery pack. In some implementations multiple vibration-dampening elements connect the flight element to the platform element to create a bi-deck vibration dampening system. | 05-29-2014 |
20140151497 | ENGINE PYLON FOR AN AIRCRAFT - An engine pylon for attaching an engine to an aircraft, where the engine pylon includes a monolithic support structure having a body that includes multiple spaced bulkheads, multiple longerons connecting the bulkheads to define multiple bays and skins provided on the frame to at least partially enclose at least one of the multiple bays. | 06-05-2014 |
20140183296 | Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and With a Bypass - A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed. | 07-03-2014 |
20140183297 | BOOMERANG LINK WITH VIBRATION FILTERING ABILITY AND AIRCRAFT ENGINE MOUNT PROVIDED WITH SUCH LINK - A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon. | 07-03-2014 |
20140183298 | FLEXIBLE LINKING DEVICE FOR AN AIRCRAFT PROPULSION SYSTEM - A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane. | 07-03-2014 |
20140191080 | AIRCRAFT PROPULSION SYSTEM COMPRISING AN AFT PYLON FAIRING WITH LATERAL WALLS THAT ARE PROFILED FOR INJECTING COOL AIR ALONG A THERMAL PROTECTION FLOOR - The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear. | 07-10-2014 |
20140217232 | MECHANICALLY OPTIMIZED LIQUID INERTIA VIBRATION ELIMINATOR AND AIRCRAFT PYLON SYSTEM - A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft. | 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 |
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 |
20140231582 | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage - A lower hull | 08-21-2014 |
20140252159 | ENGINE INSTALLATION - A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other. | 09-11-2014 |
20140312167 | Ram Air Fan Mounting Bracket - A bracket has an axial rear wall to be secured to a housing for a ram air fan and a base floor defined between lateral sidewalls. The base floor has a slot extending for an axial length and for a lateral width, with a ratio of the length to the width being between 1.24 and 1.29. A ran air fan, a system and a method are also disclosed. | 10-23-2014 |
20140319269 | INNER COWL STRUCTURE FOR AIRCRAFT TURBINE ENGINE - An inner cowl structure for circumscribing at least a portion of a jet engine extending from an aircraft includes an apron configured to mount directly to the engine independent of the pylon and overly an upper portion of the jet engine, and an inner body configured to circumscribe a portion of the jet engine not circumscribed by the apron. | 10-30-2014 |
20140339357 | SYSTEM AND METHOD FOR COOLING AN AIRCRAFT WING - An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure. | 11-20-2014 |
20140361119 | MOUNTING SYSTEM FOR MOUNTING ENGINE NACELLE COMPONENTS AND ASSOCIATED METHOD - The mounting system can be used in mounting a turbofan gas turbine engine having a nacelle including two halves, each half having a hinged end hingedly connected to the pylon and a free end lockingly engageable with the engine structure. The mounting system can include a primary connection connecting the engine structure to the pylon, and a flexible connection provided between the hinged connections and the pylon, the flexible connection being elastically deformed when a significant force is exerted in a transversal plane upon one of the halves in the closed position. | 12-11-2014 |
20150048201 | AIRCRAFT PYLON AND AIRCRAFT - To provide an aircraft pylon capable of being mounted to a wing without exertion of preload while ensuring that redundancy is provided in the pylon. An aircraft pylon | 02-19-2015 |
20150048202 | FIREWALL, PYLON OF AIRCRAFT, AND AIRCRAFT - In order to provide a firewall that is capable of preventing flame passage through a through-hole without any sealant in a connecting part of a component in which a fastener through-hole is formed, a firewall | 02-19-2015 |
20150069176 | AIRCRAFT ENGINE MOUNT - An engine mount, for mounting the casing of an aircraft engine to the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support formations on the engine casing and aircraft mounting structure. Each of the first and second links is typically connected by a pin between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector formation of the second link. The connector formations are joined by an intermediate link. The mount allows lateral forces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link may also provide a failsafe catcher arrangement in the event that the first or second link fail. | 03-12-2015 |
20150097079 | METHOD FOR AIRBORNE KINETIC ENERGY CONVERSION - Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a method to harvest renewable energy includes providing an aircraft suitable for untethered flight in an open airspace and an airborne kinetic energy conversion system attached to the airframe, the airborne kinetic energy conversion system comprising a turbine, a generator connected to the turbine, and electrical storage means connected to the generator; flying the aircraft; gaining excess kinetic energy; and converting excess kinetic energy into electricity using the kinetic energy conversion system. | 04-09-2015 |
20150115098 | Mechanical connection device - An aircraft comprising a mechanical connection device including a body that extends along a longitudinal axis. The body comprises two opposite end portions disposed along the longitudinal axis and adapted to receive external axial loads in compression and in tension, a spring member that is adapted to be compressed axially, and a mechanism which, in the event of external axial loads in compression or in tension on the end portions, is able to transmit to the spring member compression forces oriented in opposite directions according to whether the external axial loads are in compression or in tension. This device forms a flexible connection that accommodates equally well external loads in compression and in tension. | 04-30-2015 |
20150122943 | INTEGRATED PYLON STRUCTURE FOR PROPULSION SYSTEM - An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section ( | 05-07-2015 |
20150136900 | HELICOPTER TRANSMISSION MOUNT SYSTEM - A mount system for supporting a transmission in an aircraft can include a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis; a second link coupled between the structure of the aircraft and the transmission, the second link having second axis; a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis; and a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis. A forward focal point of the first axis and the second axis has a different waterline component compared to an aft focal point of the third axis and the fourth axis. | 05-21-2015 |
20150144732 | AERODYNAMIC FAIRING DIVIDED INTO SUB-PORTIONS - An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor. | 05-28-2015 |
20150144733 | Motor Pylons for a Kite and Airborne Power Generation System Using Same - A motor pylon system adapted for use with an airborne power generations system is disclosed. The pylons may support turbine driven generators for wind based electrical power generation which also function as electric motors in some aspects. The pylons may be designed to provide side force useful for turning a tethered flying wing flying in a circular cross wind flight path. The pylons may be designed to minimize air flow disruptions over the main wing. | 05-28-2015 |
20150307199 | ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ATTACHMENT PYLON PRIMARY STRUCTURE FORMED WITH THREE INDEPENDENT ELEMENTS - In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams. | 10-29-2015 |
20150321765 | AIRCRAFT PROPELLING ASSEMBLY INCLUDING A DUCT FORMING A THERMAL BARRIER INTEGRATED IN THE CAISSON OF THE RIGID STRUCTURE OF THE ENGINE MOUNTING SYSTEM - Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role. | 11-12-2015 |
20150321766 | Nacelle-To-Pylon Fairing - A nacelle-to-pylon fairing formed over at least a portion of an inter-region between a nacelle and a pylon of an aircraft may include a longitudinal axis, a lateral axis and a transverse axis, an upper end incorporated to the pylon at a fairing-to-pylon interface, and a lower end incorporated to the nacelle at a fairing-to-nacelle interface, wherein the fairing defines a surface between the upper end and the lower end. | 11-12-2015 |
20150329212 | AERODYNAMIC FAIRING - An aerodynamic fairing for a pylon of a turbojet engine, the fairing including: a frame oriented in a plane transverse to a longitudinal axis of the pylon, wherein the frame includes an upper edge, opposite side edges and a lower edge; a deck attached to the lower edge of the frame; a downstream portion of the deck includes a front edge region overlapping a rear edge portion of an upstream portion of the deck, wherein an upper surface of the front edge region is joined to the lower edge of the frame such that the front edge portion is sandwiched between the lower edge of the frame and the rear edge region of the upstream portion of the deck, and a flange extends between and attaches the upstream portion of the deck and the frame and a gap is between the lower edge of the frame and the upstream portion of the deck. | 11-19-2015 |
20150336678 | ENGINE FASTENER FOR AN AIRCRAFT - An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle. | 11-26-2015 |
20150344140 | AERODYNAMIC FAIRING - An aerodynamic fairing whose floor has absolutely no contact with respect to the lateral panels over the entire length of the fairing along the longitudinal axis. A free space e is provided between the floor and the lower edge of each panel. There is a longitudinal mechanical gap between the floor and each of the lateral panels. The absence of any rigid mechanical connection between the floor and the lateral panels allows the transfer of the thermomechanical stresses from the floor to the lateral panels and therefore preventing the deformation of the fairing. | 12-03-2015 |
20150360788 | SUSPENSION STRUCTURE WITH VARIABLE GEOMETRY OF A TURBOPROP ENGINE ON A STRUCTURAL ELEMENT OF AN AIRCRAFT - A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold. | 12-17-2015 |
20150361879 | GAS TURBINE ENGINE WITH EMBEDDED DISTRIBUTED FANS - An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed. | 12-17-2015 |
20150367946 | PROPULSION UNIT FOR AN AIRCRAFT - The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail. | 12-24-2015 |
20150367947 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING AT LEAST ONE BRUSH SEAL RESISTANT TO HIGH-TEMPERATURE - A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation. | 12-24-2015 |
20150367948 | SYSTEM AND METHOD FOR AFT MOUNT OF GAS TURBINE ENGINE - The present disclosure is applicable to all vehicles having an engine mounted therein. In one embodiment, an aft mount system for a gas turbine engine is disclosed. The aft mount system includes a vehicle chassis and at least one flexible mounting member disposed within the vehicle chassis, wherein when a gas turbine engine is received within the vehicle chassis, an exhaust portion of the gas turbine engine is substantially mounted within the vehicle chassis through engagement with the at least one flexible mounting member. | 12-24-2015 |
20160031567 | A SYSTEM FOR RECOVERING AND CONVERTING KINETIC ENERGY AND POTENTIAL ENERGY AS ELECTRICAL ENERGY FOR AN AIRCRAFT - The invention relates to an electrical energy generator system ( | 02-04-2016 |
20160046381 | Aircraft Engine Mounting System - An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves. | 02-18-2016 |
20160052637 | METHODS AND APPARATUS FOR SUPPORTING ENGINES AND NACELLES RELATIVE TO AIRCRAFT WINGS - Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing. | 02-25-2016 |
20160107756 | AIRCRAFT BATTERY CONTAINMENT PODS - A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight material, the size and shape of the interior cavity designed to accommodate one or more battery packs. A smooth exterior coating covers the exterior shape of the body, and an attachment structure formed in or on the body allows the body to be coupled to a flight vehicle. Other implementations are disclosed and claimed. | 04-21-2016 |
20160107757 | STRESS-RELIEVING JOINT BETWEEN MATERIALS WITH DIFFERING COEFFICIENTS OF THERMAL EXPANSION - A composite component may be coupled to an aluminum component with a plurality of fasteners. An expansion strap may be located between the composite component and the aluminum component. The expansion strap may have a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the composite component, and less than the coefficient of thermal expansion of the aluminum component. A first set of fasteners may be inserted through the composite component, the expansion strap, and the aluminum component. A second set of fasteners may be inserted through the composite component and the expansion strap. The expansion strap may decrease stress in the composite component at the fastener locations. | 04-21-2016 |
20160122029 | AIRCRAFT ENGINE ATTACHMENT DEVICE, AND CORRESPONDING AIRCRAFT - A device for attaching an aircraft engine to a pylon secured to the aircraft, the attachment device comprising a beam secured to the pylon and a first clevis mount comprising two cheeks connected to one another by a first clevis pin. A second clevis mount is secured to the engine and comprises two cheeks connected to one another by a second clevis pin. A shackle is rotatably connected to the first and second pins by first and second spherical joints. The attachment device further comprises at least one pair of washers positioned around one of the pins, one washer on each side of the shackle, and separating the shackle from the cheeks of the clevis mount bearing the one of the pins. The shackle, in its extreme positions of rotation about the one of the pins passing through the two spherical joints, coming into contact with the washers. | 05-05-2016 |
20160122030 | FRONT ENGINE ATTACHMENT FOR AN AIRCRAFT ENGINE - A front engine attachment, intended to fix an engine to a structure of an aircraft, includes a first attachment including a base intended to be fixed to the structure, a first fixture articulated on the base, two first connecting rods, each being articulated by a first end to the engine and by a second end to the fixture, and a first cylindrical nose mounted on the base. The front engine attachment includes a second attachment including a cradle including an orifice into which the cylindrical nose is fitted, and a second cylindrical nose being threaded into a piercing of the engine, and two second connecting rods, each being intended to be articulated by a first end to the engine, and by a second end to the cradle. | 05-05-2016 |
20160130008 | HELICOPTER ENGINE MOUNTING SYSTEM AND METHODS - In an embodiment the invention includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P). | 05-12-2016 |
20160130009 | ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ATTACHMENT PYLON PRIMARY STRUCTURE FORMED WITH THREE INDEPENDENT ELEMENTS - In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams. | 05-12-2016 |
20160137306 | MOTOR BRACKET FOR MULTICOPTER FLYING ROBOT - Disclosed is a motor bracket of a multicopter flying robot. The motor bracket for the multicopter flying robot disclosed in the present invention includes: a body | 05-19-2016 |
20160144967 | INTEGRATED PUSHER TURBOFAN FOR AIRCRAFT - A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing. | 05-26-2016 |
20160144970 | TURBINE ENGINE ASSEMBLY AND METHOD OF MANUFACTURING THEREOF - A turbine engine assembly is provided. The assembly includes a stationary component, a drive shaft, and a gearbox coupled along the drive shaft, and coupled to the stationary component. The assembly also includes a vibration-reducing mechanism coupled between the stationary component and the gearbox. The vibration-reducing mechanism is configured to isolate a vibratory response of the gearbox from the stationary component. | 05-26-2016 |
20160159486 | A STRUCTURE FOR SUSPENDING A TURBOPROP HAVING TWO UNDUCTED PROPELLERS ON A STRUCTURAL ELEMENT OF AN AIRPLANE - The invention provides a suspension structure for suspending a turboprop ( | 06-09-2016 |
20160159487 | AIRCRAFT ENGINE PYLON - An aircraft engine pylon having an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting and the upper panel, and tension fasteners at least partially coupling the upper fitting and the upper panel with the shear pin defining a shear force load path and the tension fasteners defining tension force load paths. | 06-09-2016 |
20160167797 | ENGINE MOUNT | 06-16-2016 |
20160167798 | VARIABLE PITCH MOUNTING FOR AIRCRAFT GAS TURBINE ENGINE | 06-16-2016 |
20160176519 | FLOW RESTRICTION SYSTEM FOR REGULATING DYNAMIC PRESSURE LOSS | 06-23-2016 |
20160176532 | PROPELLER FOR AN AIRCRAFT TURBOMACHINE, INCLUDING A BLADE RETAINING STRUCTURE THROUGH WHICH THE AERODYNAMIC PART OF EACH BLADE PASSES | 06-23-2016 |
20160176533 | REMOVABLE AUXILIARY POWER DEVICE FOR AIRCRAFT AND AIRCRAFT ADAPTED TO USE AT LEAST ONE SUCH DEVICE | 06-23-2016 |
20160185459 | Auxiliary Device for High-Flying Aircraft - An auxiliary device is provided for a high-altitude airplane. The auxiliary device includes a drive, which is independent of the airplane, for the ascent of the airplane into the stratosphere. The airplane is releasably coupled to the auxiliary device. The auxiliary drive is releasable from the airplane altitude on the latest on reaching a predetermined mission. | 06-30-2016 |
20160376016 | SUSPENSION STRUCTURE FOR SUSPENDING A TURBOPROP HAVING TWO UNDUCTED PROPELLERS FROM A STRUCTURAL ELEMENT OF AN AIRCRAFT WITH RIGID FASTENING OF THE AIR INTAKE STRUCTURE - A suspension structure for suspending a turboprop including two unducted propellers from a structural element of an aircraft, the structure including a suspension frame for fastening to a structural element of the aircraft and including a main beam extending parallel to a longitudinal axis of the turboprop, the suspension frame being fastened to an air intake structure of the turboprop by an attachment frame. | 12-29-2016 |
20170233060 | AIRCRAFT AND EMPENNAGE SECTION OF AN AIRCRAFT | 08-17-2017 |
20180022459 | LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT | 01-25-2018 |
20180022462 | Tip Rib Mounted Pylon Assemblies | 01-25-2018 |
20190144125 | AIRCRAFT COMPRISING AT LEAST ONE ENGINE ASSEMBLY LINKED TO THE FUSELAGE OF THE AIRCRAFT BY TWO CONNECTING RODS POSITIONED AT LEAST PARTIALLY IN AN AIR INLET OF THE ENGINE ASSEMBLY | 05-16-2019 |