Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/06—Varying effective area of jet pipe or nozzle
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
  • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • B64F5/40—Maintaining or repairing aircraft
  • B64F5/45—Repairing leakages in fuel tanks
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
  • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • B64F5/50—Handling or transporting aircraft components
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
  • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/74—Reversing at least one flow in relation to at least one other flow in a plural- flow engine
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
  • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49826—Assembling or joining
  • Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
  • Y10T29/49901—Sequentially associating parts on stationary aligning means
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49998—Work holding
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/53—Means to assemble or disassemble
  • Y10T29/53087—Means to assemble or disassemble with signal, scale, illuminator, or optical viewer
  • Y10T29/53091—Means to assemble or disassemble with signal, scale, illuminator, or optical viewer for work-holder for assembly or disassembly

Definitions

• the present invention relates to a device for assembling a fixed thrust reverser structure of an aircraft propulsion assembly, and to a method for assembling such a fixed structure.
• An aircraft is moved by several propulsion units, each suspended to a fixed structure of the aircraft, for example under a wing or on the fuselage of the aircraft, by means of a suspension pylon.
• Each propulsion unit comprises in a known manner on the one hand a turbojet engine equipped with a fan and a motor, and on the other hand a nacelle enveloping the turbojet engine and housing a thrust reverser.
• a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround the fan of the turbojet engine, a downstream section housing the thrust reverser and intended to surround a combustion chamber and the turbines of the engine.
• turbojet and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
• a thrust reverser is adapted to, during landing of the aircraft, improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the corresponding turbojet engine.
• a thrust reverser generally comprises an external fixed structure called OFS (Outer Fixed Structure in Anglo-Saxon terms), an internal fixed structure called IFS (Inner Fixed Structure in Anglo-Saxon terms) which surrounds the engine behind the fan, and a mobile structure comprising for example movable covers.
• the external and internal fixed structures define a vein intended for the circulation and the escape of a flow of cold air.
• the external fixed structure of a thrust reverser comprises, in a known manner, a peripheral front frame intended to be mounted on a fan casing of the corresponding turbojet engine, a peripheral rear frame, and a plurality of flow deflection grids fixed between the frames. front and rear and extending substantially parallel to the longitudinal geometric axis of the thrust reverser.
• the front and rear frames are arranged transversely to the longitudinal geometric axis of the thrust reverser.
• the external fixed structure furthermore comprises a large number of equipment mounted on the front frame and on both sides of it. last, such as actuating cylinders of the movable structure of the thrust reverser, actuator actuator guide tubes, actuator actuator mounting fittings, actuator connecting rod fittings for actuating locking flaps belonging to the moving structure of the thrust reverser.
• O (O-Duct) structure thrust reversers have been developed.
• the fixed external structure of an O-structure thrust reverser extends substantially from one side of the corresponding suspension pylon to the other side of the latter.
• Such a method of assembly induces a large number of reversals of the front frame to have access on both sides of the front frame for the assembly of the different equipment, which requires the availability of appropriate handling tools and complicates the assembly of the thrust reverser.
• such an assembly method requires having bridges and scaffolding to access the center of the front frame, which generates a large footprint of the assembly area of such a thrust reverser.
• this assembly method results in inappropriate postures for the operators performing the assembly of such thrust reversers. This results in a difficult and expensive assembly for such thrust reversers O structure.
• the present invention aims to remedy these disadvantages.
• the technical problem underlying the invention therefore consists in providing a device for assembling a fixed thrust reverser structure which is of simple and economical structure, while allowing an easy and fast assembly of an inverter of thrust.
• the present invention relates to a device for assembling a fixed thrust reverser structure of an aircraft propulsion unit, the fixed structure comprising a front frame intended to be mounted on a fan casing.
• a turbojet engine of the propulsion unit the assembly device comprising: a frame intended to rest on a flat support,
• a support element mounted to rotate with respect to the frame about an axis of rotation
• a positioning assembly mounted integral in rotation on the support element and on which the front frame is intended to be positioned
• immobilization means arranged to immobilize the front frame on the positioning assembly, the assembly device being configured such that, in the immobilization position on the positioning assembly, the front frame extends transversely to the plane support, and the positioning assembly and the immobilizing means are arranged such that, in the immobilization position on the positioning assembly, the front frame extends transversely to the axis of rotation of the support element.
• Such a configuration of the assembly device according to the invention allows an operator to easily access both sides of the front frame in the immobilization position on the positioning assembly, and therefore to easily assemble on the frame before, and on both sides of the latter, the different equipment forming the fixed structure of the thrust reverser.
• This assembly is all the easier as the operator can position the front frame in the most appropriate position to perform the assembly of each equipment, and this simply by rotating the support member about its axis of rotation. rotation.
• Such a configuration of the assembly device according to the invention also makes it possible to reduce the bulk of the assembly area of the fixed structure.
• the assembly device is configured such that, in the immobilization position on the positioning assembly, the front frame extends substantially perpendicular to the plane support.
• the positioning assembly is removably mounted on the support member.
• the axis of rotation of the support member is substantially horizontal in conditions of use of the assembly device.
• the angle of inclination of the axis of rotation of the support element relative to the horizontal is between -20 and + 20 °, preferably between -10 and + 10 °, and preferably between -5 and + 5 °.
• the positioning assembly and the immobilizing means are arranged such that, in the immobilization position on the positioning assembly, the front frame extends substantially perpendicularly to the axis of rotation of the element. of support.
• the angle of inclination of the axis of rotation of the support member relative to the front frame in the immobilized position is between 70 and 110 °, preferably between 80 and 100 °, and advantageously between 85 and 95 °.
• the assembly device is arranged such that, in the immobilization position on the positioning assembly, the front frame is substantially centered with respect to the axis of rotation of the support element.
• the support element comprises a longitudinal axis substantially centered on the axis of rotation of the support element.
• the support member comprises a substantially cylindrical outer ring of axis substantially centered on the axis of rotation of the support member.
• the positioning assembly comprises at least one positioning element having a peripheral mounting wall on which is intended to be mounted the front frame.
• the front frame is intended to bear against the peripheral mounting wall.
• the peripheral mounting wall may be delimited by a substantially cylindrical surface portion.
• the peripheral mounting wall may be substantially centered on the axis of rotation of the support member.
• the positioning assembly comprises a connecting armature mounted on the support element, the at least one positioning element being mounted on the connecting armature.
• the positioning assembly comprises two positioning elements.
• each positioning element extends in an arc.
• the peripheral mounting wall comprises a plurality of mounting holes arranged to cooperate with the immobilizing means.
• the mounting holes provided on the wall peripheral mounting are oblong and preferably extend substantially parallel to the axis of rotation of the support member.
• the immobilizing means comprise at least one immobilizing member, such as an immobilization pin, mounted movably between an immobilization position of the front frame in which the at least one an immobilizing member is arranged to extend through an opening in the front frame and one of the mounting holes belonging to the peripheral mounting wall, and a release position of the front frame.
• immobilizing member such as an immobilization pin
• the immobilizing means comprise at least one clamping member movably mounted between a clamping position of the front frame in which the at least one clamping member is arranged to exert a pressure against the front frame so as to press the front frame against the peripheral mounting wall, and a release position of the front frame.
• the immobilizing means comprise a plurality of immobilization elements angularly offset from each other with respect to the axis of rotation of the support element.
• Each immobilizing element comprises for example at least one clamping member and / or at least one immobilizing member.
• each immobilizing element comprises an actuating lever connected to the at least one clamping member and / or the at least one corresponding immobilizing member, the actuating lever. being pivotally mounted between a first position in which the at least one clamping member and / or the at least one corresponding immobilizing member are in their release position, and a second position in which the at least one locking member clamping and / or the at least one corresponding immobilizing member are in their clamping and immobilizing position, the actuating lever being arranged such that a movement of the actuating lever between its first and second positions causes a displacement of the at least one clamping member and / or the at least one corresponding immobilizing member between their release position and their clamping and immobilizing position.
• each immobilization element is preferably mounted on the positioning assembly, and for example on the at least one positioning element.
• the assembly device comprises holding means mounted on the support element and arranged to hold the front frame on the support element.
• the holding means are for example removably mounted on the support member.
• the holding means comprise a plurality of holding arms angularly offset from one another relative to the axis of rotation of the support member.
• each holding arm comprises a connecting portion provided with a fixing eye for the passage of a fixing pin.
• each arm extends substantially radially with respect to the longitudinal axis of the support member.
• the arms are for example mounted on the outer shell of the support member.
• the assembly device comprises rotational drive means arranged to rotate the support assembly about its axis of rotation.
• the rotary drive means comprise a longitudinal axis drive shaft substantially coinciding with the axis of rotation of the support assembly, and a driving wheel coupled to the drive shaft and arranged to rotate the drive shaft about its longitudinal axis.
• the immobilization means comprise fastening means arranged to attach the ends of the front frame to the positioning assembly.
• the fixing means comprise for example:
• a first and a second fixing portion mounted on the positioning assembly and each provided with a fixing orifice
• a first and a second fixing pin intended to extend respectively, on the one hand, through an opening formed in a support portion of the front frame on which flow deflection gates are intended to be mounted, and on the other hand, the fixing hole belonging to one of the first and second fixing portions.
• the assembly device comprises locking means mounted on the positioning assembly and arranged to lock in position two maintenance rails with respect to the front frame for mounting on the frame. before, said maintenance rails being intended to be slidably mounted in the suspension pylon for receiving the propulsion unit.
• the present invention further relates to a method of assembling a fixed thrust reverser structure of an aircraft propulsion unit, comprising the steps of:
• the assembly step comprising at least one step of rotating the support member about its axis of rotation.
• the positioning step consists of centering the front frame on the axis of rotation of the support element.
• the front frame extends substantially in an arc. According to one embodiment of the invention, the front frame extends over an angle of between 270 and 340 °.
• the front frame has for example a substantially annular shape.
• the assembly step comprises at least one step of fixing a rear frame of the fixed structure on the front frame by means of spacer pieces fixed by a part on the front frame and secondly on the rear frame.
• the assembly step comprises the steps of:
• the connecting piece has a section substantially in J.
• the method comprises a step prior to the step of positioning the front frame of assembling a connecting piece on the front frame, said connecting piece being intended to be mounted on the fan casing of the turbojet engine of the propulsion unit.
• the assembly step comprises a step of moving the assembly device successively along different assembly stations.
• the assembly method comprises a step of moving the assembly device to a mounting station of the fixed structure on the turbojet engine of a propulsion unit.
• Figure 1 is a front perspective view of an assembly device according to the invention.
• Figure 2 is a rear perspective view of the assembly device of Figure 1.
• Figure 3 is a front perspective view of the assembly device of Figure 1 on which is mounted a front frame of a fixed structure of a thrust reverser.
• Figure 4 is a partial perspective view from above of the assembly device of Figure 1.
• Figure 5 is a perspective view, on an enlarged scale, of an immobilizing element of the assembly device of Figure 1.
• Figure 6 is a partial rear perspective view of the assembly device of Figure 1 on which are mounted the front and rear frames of a fixed structure of a thrust reverser.
• Figure 7 is a partial perspective view from above of the assembly device of Figure 1 showing locking means of maintenance rails.
• Figure 8 is a partial rear perspective view of the assembly device of Figure 1.
• Figures 9 and 10 are front perspective views of the assembly device of Figure 1, respectively showing the assembly device equipped and without its positioning assembly.
• Figure 1 1 is a schematic sectional view of a front frame equipped with a connecting piece and held on a support member of the assembly device of Figure 1.
• Figure 12 is a schematic sectional view of a front frame equipped with a connecting piece and immobilized on the positioning assembly of the assembly device of Figure 1.
• Figure 13 is a perspective view of a thrust reverser comprising a fixed structure assembled using the assembly device of Figure 1.
• Figures 1 and 2 show an assembly device 2 of a fixed structure thrust reverser O structure of an aircraft propulsion assembly, and more particularly an external fixed structure called OFS.
• the assembly device 2 comprises a frame 3 and a platform 4 resting on the frame 3.
• the frame 3 including a substantially vertical upright 5 and a beam 6 secured to the upright 5 and substantially horizontal.
• the frame 3 is in particular equipped with support pads 7 intended to rest on the ground.
• the assembly device 2 also comprises a substantially horizontal longitudinal axis A drive shaft 8 extending through the beam 6, and a driving wheel 9 coupled to the drive shaft 8, for example by through a gearbox 1 1.
• the driving wheel 9 is arranged to rotate the drive shaft 8 about its longitudinal axis.
• the assembly device 2 further comprises a support drum 12 integral in rotation with the drive shaft 8.
• the support drum 12 comprises a substantially cylindrical shell 13 with an axis centered on the longitudinal axis A of the drive shaft 8.
• the support drum 12 comprises a plurality of fixing plates 14 fixed on the outer surface of the shell 13 and extending substantially radially relative to the shell 13.
• Each mounting plate 14 is advantageously provided with at least one fixing orifice 15.
• the assembly device 2 further comprises a connecting armature 16 extending substantially perpendicular to the longitudinal axis A of the drive shaft 8, and more particularly substantially vertically.
• the connecting armature 16 is removably mounted on the support drum 12.
• the connecting armature 16 preferably comprises a plurality of fixing plates 17 each provided with at least one fixing orifice 18.
• Each mounting plate 17 is arranged to be fixed by screwing or bolting on one of the fixing plates 14 of the support drum 12.
• the assembly device 2 further comprises two positioning elements 19 integral with the connecting armature 16, and arranged symmetrically with respect to the support drum 12.
• the connecting armature 16 and the two positioning elements 19 form advantageously a removable positioning assembly.
• Each positioning element 19 extend substantially vertically.
• Each positioning element 19 has a substantially circular arc shape, and comprises a peripheral mounting wall 21 on which is intended to bear directly or indirectly a front frame of the fixed structure of a thrust reverser.
• the peripheral mounting wall 21 of each positioning element 19 is delimited by a cylindrical surface portion centered on the longitudinal axis A of the drive shaft 8.
• the mounting wall 21 of each positioning element 19 comprises a plurality of mounting holes 22 distributed longitudinally on the peripheral mounting wall 21.
• Each mounting 22 may for example be oblong and extend substantially parallel to the longitudinal axis A of the drive shaft 8.
• the assembly device 2 also comprises immobilization means arranged to immobilize the front frame on the positioning elements 19 and the positioning armature 16.
• the immobilizing means comprise a plurality of immobilization elements 23 mounted on the positioning elements 19, and angularly offset from each other with respect to the longitudinal axis A of the drive shaft 8.
• Each immobilizing element 23 comprises an immobilizing member 24, such as an immobilizing pin, mounted movably between a position immobilizing the front frame in which the immobilizing member 24 is arranged to extend through an opening in the front frame and one of the mounting holes 22 formed on the peripheral mounting wall 21 of the corresponding positioning element 19, and a release position of the front frame in which the immobilizing member 24 is located at a distance from the corresponding positioning element 19.
• Each immobilizing element 23 also comprises two clamping members 25 disposed on either side of the immobilizing member 24 corresponding.
• the two clamping members 25 of each immobilizing element 23 are movably mounted between a clamping position of the front frame in which the clamping members 25 are arranged to exert pressure against the front frame so as to press the front frame against the peripheral mounting wall 21 of the corresponding positioning element 19, and a release position of the front frame in which the clamping members 25 are located at a distance from the corresponding positioning element 19.
• Each immobilizing element 23 also comprises an actuating lever 26 connected to the corresponding immobilizing and clamping means 24, 25.
• the actuating lever 26 of each immobilizing element 23 is pivotally mounted between a first position in which the immobilizing and clamping members 24, 25 are in their release position, and a second position in which the locking members 24 and 25 corresponding immobilization and clamping are in their position of immobilization and clamping.
• the actuating lever 26 is advantageously arranged in such a way that a displacement of the actuating lever 26 between its first and second positions results in a displacement of the corresponding immobilization and clamping elements 24, 25 between their release position and their position. position of immobilization and clamping.
• each immobilizing element 23 advantageously forms a clamping locator.
• each immobilizing element 23 comprises a frame 27 mounted on the corresponding positioning element 19, the corresponding actuating lever 26 being pivotally mounted on the frame 27 about a pivot axis.
• Each immobilizing element 23 also comprises a support member 28 pivotally mounted on the frame 27 around a pivot axis parallel to the pivot axis of the corresponding actuating lever 26, the immobilizing and clamping members 24, 25 being mounted on the support member 28.
• Each immobilizing element 23 comprises in addition at least one rod 29 whose ends are mounted articulated respectively on the support member 28 and the corresponding actuating lever 26.
• the immobilizing means also comprise fixing means arranged to fix the ends of the front frame on the connecting armature 16.
• the fixing means advantageously comprise two fasteners 31 mounted on the connecting armature 16, and two fixing pins 32 intended to extend respectively through firstly an opening in a support portion of the front frame on which flow deflection gates are intended to be mounted, and on the other hand a fixing orifice (not visible in the figures) formed in one of the fastening pieces 31.
• the assembly device 2 further comprises holding means removably mounted on the support drum 12, and arranged to hold the front frame on the support drum 12.
• the holding means comprise a plurality of holding arms 33 angularly offset from each other with respect to the longitudinal axis A of the drive shaft 8.
• Each holding arm 33 comprises an attachment portion 33a mounted on the outer surface of the shell 13 of the support drum 12, and extending substantially radially from the shell 13.
• Each holding arm 33 further comprises a connecting portion 33b integral with the portion 33a corresponding attachment, and extending substantially parallel to the longitudinal axis A of the drive shaft 8 towards the positioning elements 19.
• Each holding arm 33 further comprises a connecting portion 33c mounted articulated on the corresponding connecting portion 33b about an axis of articulation substantially perpendicular to the longitudinal axis A of the drive shaft 8, and this to facilitate the fixing said holding arm 33 on the front frame.
• each holding arm 33 is preferably intended to cooperate with a fixing yoke mounted on the front frame.
• the connecting portion 33c is advantageously provided with a fixing eyelet for the passage of a fixing pin 34 adapted to cooperate also with the corresponding fixing screed.
• the assembly device 2 further comprises locking means mounted on the connecting armature 16 and arranged to lock in position two maintenance rails with respect to the front frame in view of their mounting on the latter.
• Such maintenance rails are intended to be slidably mounted in a suspension pylon of an aircraft.
• the locking means advantageously comprise two clamping members 35 each provided with a receiving housing 36 for receiving a rim of the corresponding maintenance rail, and a pressure member 37 opening into the receiving housing 36 corresponding and arranged to exert pressure against the edge of the corresponding maintenance rail.
• the assembly method comprising the following steps consisting of:
• the step of assembling the different equipment comprises at least one step of rotating the support drum 12 with the aid of the driving wheel 9 in order to position the front frame 42 in an appropriate position, so as to facilitate the assembly of different equipment.
• the assembly step of the different equipment includes in particular the following steps consisting of:
• fixing fixing fittings 46 on the front frame 42 (see FIG. 8), said fixing brackets 46 being intended for fixing actuating rods adapted to actuate locking flaps belonging to the mobile structure 70 of the thrust reverser,
• each bracing piece 48 having a first end fixed to the front frame 42 and a second end fixed to the frame 47, each spacer piece 48 having a length corresponding to the length of the flow deflection gates intended to equip the fixed structure,
• each mounting fitting 52 being provided with a passage lumen 53,
• the step of assembling the different equipment includes in particular the following steps consisting of:
• connecting piece 56 such as an annular flange, having a section J, also called J-ring, on the front frame 42 (see Figure 1 1), said connecting piece 56 being intended to be mounted on the blower housing of the turbojet engine of the propulsion unit,
• the assembly method comprises a step of moving the assembly device 2 successively along different assembly stations, and this in order to achieve the assembly of the fixed structure of the thrust reverser.
• the assembly method comprises a step of moving the assembly device 2 to a mounting station of the fixed structure on the turbojet engine of a propulsion unit.
• the connecting piece 56 could be mounted on the front frame 42 prior to its positioning on the positioning elements 19.
• the front frame 42 is mounted on the positioning elements 19 by means of said connecting piece 56.
• each positioning element 19 comprises a mounting portion 19a mounted on the connecting armature 16, and a positioning portion 19b secured to the mounting portion 19b and on which is to be mounted the connecting piece 56.
• each immobilizing element 23 may comprise a clamping member 58 arranged to exert pressure against the piece connecting piece 56 so as to press the connecting piece 56 against the mounting portion 19b.
• the invention is not limited to the sole embodiment of this assembly device, described above as an example, it encompasses all the variants.
• the assembly device could be used to assemble the fixed structure of a thrust reverser of the C-duct type.

Applications Claiming Priority (2)

Publications (1)

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ID=46889241

Family Applications (1)

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• 2012
  • 2012-06-25 FR FR1255990A patent/FR2992292B1/fr active Active
• 2013
  • 2013-06-14 CA CA2874024A patent/CA2874024A1/fr not_active Abandoned
  • 2013-06-14 RU RU2015101350A patent/RU2015101350A/ru not_active Application Discontinuation
  • 2013-06-14 BR BR112014029901A patent/BR112014029901A2/pt not_active IP Right Cessation
  • 2013-06-14 EP EP13737313.0A patent/EP2864203A1/de not_active Withdrawn
  • 2013-06-14 CN CN201380033929.8A patent/CN104411588B/zh not_active Expired - Fee Related
  • 2013-06-14 WO PCT/FR2013/051392 patent/WO2014001685A1/fr active Application Filing
• 2014
  • 2014-12-12 US US14/568,582 patent/US9518533B2/en active Active

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