• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a pivot axis (68) for an aircraft engine fastener, comprising: - a tubular main axis (74) having at one end (74.1) a head (78) and at a second end (74.1). end (74.2) a threaded portion (80) on which a first nut (82) is screwed; - a spare axis (76) configured to be pivotally mounted within the main axis (74) and having a first end (76.1) a head (104) and at a second end (76.2) a threaded portion (106) on which is screwed a second nut (108), - the spare axis (76) being connected by an axial connection (120) to the first nut (82). The spare axis being connected to the first nut, it is necessarily inserted in the main axis when the first nut is screwed on the main axis.
    公开号:FR3074146A1
    申请号:FR1761142
    申请日:2017-11-24
    公开日:2019-05-31
    发明作者:Stephane Combes；Jean GELIOT；Thomas Deforet；Adeline Soulie；Benoit ORTEU
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    IMPROVED PIVOTING AXIS FOR AN AIRCRAFT ENGINE MOUNT
    The present application relates to an improved pivot axis for an aircraft engine mount.
    According to a configuration visible in FIGS. 1 and 2, an aircraft 10 comprises several engine assemblies 12 which are positioned under the wing 14 of the aircraft 10.
    An engine assembly 12 comprises an engine 16, a nacelle (not shown in FIG. 2) positioned around the engine 16 and a mast 18 which provides the connection between the engine 16 and the rest of the aircraft 10, in particular the wing 14.
    The mast 18 comprises a primary structure 20 which is connected to the engine 16 by a rear engine mount 22, a front engine mount 24 and a couple of thrust rods 26 which ensure the resumption of the thrust forces.
    As illustrated in FIG. 3, the rear engine mount 22 comprises a triangular plate 28 interposed between the primary structure 20 of the mast 18 and the engine 16.
    The rear engine mount 22 also includes a yoke 30, integral with the primary structure 20, connected to the triangular plate 28 by a pivot axis 32.
    According to an embodiment visible in FIG. 4, the pivot axis 32 supports in the central part a ball joint 34, connecting the pivot axis 34 and the triangular plate 28, and two smooth bearings 36, 36 ', arranged on the side and on the other side of the ball 34, connecting the pivot axis 34 and the branches of the yoke 30.
    The pivot axis 32 comprises a first tubular axis 38, called the main axis, and a second tubular axis 40, called the backup axis (or fail safe in English), coaxial with the main axis 38 and mounted inside this last.
    The external diameter of the emergency axis 40 is slightly smaller than the internal diameter of the main axis 38 so as not to engage the emergency axis 40 inside the main axis 38 in normal operation.
    The main axis 38 comprises, at a first end, a head 42 configured to bear in operation against a first branch of the yoke 30 and / or a first plain bearing 36 and, at a second end, a threaded portion 44 on which a nut 46 fitted with a braking system is screwed. When tightened, this nut 46 bears against a second branch of the yoke 30 and / or a second smooth bearing 36 '.
    The emergency axis 40 comprises, at a first end, a head 48 configured to bear in operation against the head 42 of the main axis 38 and, at a second end, a threaded portion 50 on which a nut 52 equipped with 'a braking system is screwed. When tightened, this nut 52 bears against the second end of the main axis 38.
    To be able to tighten the nut 46, the head 42 of the main axis 38 has, on its face oriented towards the head 48 of the emergency axis 40, two diametrically opposed recesses 54 configured to receive two pins 56 secured to the head 48 of the emergency axis 40. In addition, the head 48 of the emergency axis 40 comprises, at the periphery, two flats to hold it, using a key, immobile in rotation.
    In normal operation, only the main axis 38 is loaded.
    During a check of the proper functioning of the pivot axis 32, after the removal of the nut 52, an operator tries to pivot the spare axis 40 inside the main axis 38. If the the spare axis 40 cannot pivot, this means that the main axis 38 has failed and that the pivot axis 32 must be repaired.
    After the check, it is imperative that the emergency axis 40 is correctly reassembled.
    However, the presence of the emergency axis 40 is not necessary to mount and tighten the main axis 38 if a lug wrench cooperating with the recesses 54 of the head 42 is used to immobilize the main axis 38 during the tightening the nut 46.
    Furthermore, even if the emergency axis 40 is inserted in the main axis and it is immobilized in rotation with a key to immobilize in rotation the main axis 38, the emergency axis 40 can, in operation, leave the main axis 38 if the operator forgets to screw the nut 52 fitted with its braking system.
    The present invention aims to remedy the drawbacks of the prior art.
    To this end, the subject of the invention is a pivot axis for an aircraft engine mount, comprising:
    a tubular main axis which has a head at a first end and a threaded portion at a second end, a first nut configured to be screwed onto the threaded portion of the main axis, a spare axis configured to be pivotally mounted to the inside the main axis and having at a first end a head and at a second end a threaded portion, and a second nut configured to be screwed onto the threaded portion of the emergency axis.
    According to the invention, the emergency axis and the first nut are connected by an axial link configured to immobilize in translation one with respect to the other the emergency axis and the first nut, while allowing movement of rotation of one relative to the other of the first nut and the spare axis.
    The invention makes it possible to prevent the emergency axis from coming out of the main axis if the second nut is not screwed.
    In addition, the first nut and the emergency axis being connected, the emergency axis is necessarily present in the main axis when the first nut is screwed onto the main axis.
    According to another characteristic, the head of the emergency axis is pressed against the first nut of the main axis.
    According to another characteristic, the first nut comprises:
    a tubular body provided on an inner face with a thread configured to be screwed onto the threaded portion of the main axis, a head secured to a first end of the tubular body, an extension secured to a second end of the tubular body, in projection relative to the second end of the main axis when the first nut is screwed and tightened.
    According to another characteristic, the extension has an internal cylindrical surface with an internal diameter greater than the internal diameter of the main axis and less than the external diameter of the threaded portion of the main axis, a terminal face opposite the tubular body. and a transverse face connecting the inner cylindrical surface of the extension and the inner face of the tubular body, the transverse face and the inner face of the tubular body delimiting a housing configured to accommodate the second end of the main axis.
    According to a first embodiment, the axial link comprises a retaining ring, a first groove on the emergency axis, configured to partially accommodate the retaining ring and a second groove on the first nut, configured to partially accommodate the stop ring.
    According to this first embodiment, the first and second grooves are positioned so that the first nut is in contact against the head of the emergency axis when the emergency axis and the first nut are immobilized in translation by the stop ring.
    According to a second embodiment, the axial connection comprises a circlip and a groove on the emergency axis configured to partially accommodate the circlip.
    According to this second embodiment, the groove is positioned relative to the head of the emergency axis so that the first nut is in contact with the head of the emergency axis when the emergency axis and the first nut are immobilized in translation by the circlip.
    The subject of the invention is also an engine mount of an aircraft comprising a pivot axis according to the invention as well as an aircraft which comprises engine mount.
    Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with reference to the appended drawings among which:
    FIG. 1 is a perspective view of an aircraft,
    FIG. 2 is a schematic representation of a propulsion unit connected to a wing which illustrates an embodiment,
    FIG. 3 is a perspective view of a rear engine mount which illustrates an embodiment,
    FIG. 4 is a section in perspective of a pivot axis of a motor attachment which illustrates an embodiment of the prior art,
    FIG. 5 is a perspective section of a pivot axis of a motor attachment which illustrates a first embodiment of the invention,
    FIGS. 6A to 6E are perspective sections which illustrate the different stages of mounting an emergency axis of the pivot axis visible in FIG. 5,
    FIG. 7 is a perspective section of a pivot axis of a motor attachment which illustrates a second embodiment of the invention, and
    FIG. 8 is a detailed view of an emergency axis of the pivot axis visible in FIG. 7.
    According to an embodiment illustrated in FIG. 5, a rear engine attachment 60 comprises a yoke 62, integral with a primary structure of an aircraft mast, connected by a link 64 to a triangular plate 66 connected itself to an aircraft engine. The connection 64 comprises a pivot axis 68, which supports in the central part a ball joint 70 connecting the pivot axis 68 and the triangular plate 66, and two plain bearings 72, 72 ', arranged on either side of the ball joint 70, connecting the pivot axis 68 and the branches 62.1, 62.2 of the yoke 62. Thus, the pivot axis 68 of the invention can be mounted on new engine mounts as well as existing ones.
    With the exception of the pivot axis 68, the other elements of the connection 64 may be identical to those of the prior art previously described.
    Furthermore, although described applied to a rear engine mount, the pivot axis 68 of the invention can be used for the other engine mountings.
    For the remainder of the description, a longitudinal direction is parallel to the axis A68 of the pivot axis 68.
    The pivot axis 68 comprises a first axis, called the main axis 74, and a second axis, called the backup axis 76, coaxial with the main axis 74 and mounted inside the latter. The external diameter of the emergency axis 76 is slightly smaller than the internal diameter of the main axis 74 so as not to engage the emergency axis 76 inside the main axis 74 in normal operation.
    The main axis 74 comprises, at a first end 74.1, a head 78 configured to bear in operation against a first branch 62.1 of the yoke 62 and / or a first plain bearing 72 and, at a second end 74.2, a threaded portion 80 on which a nut 82 fitted with a braking system 84 is screwed. When tightened, this nut 82 bears against a second branch 62.2 of the yoke 62 and / or a second smooth bearing 72 '.
    According to one embodiment, the head 78 is in the form of a collar.
    As illustrated in FIGS. 6B and 8, the nut 82 comprises a first section 86 which has a tubular body 88, provided on its inner face 89 with a thread 90 configured to be screwed onto the threaded portion 80 of the main axis 74, and a head 92, integral with a first end of the tubular body 88, configured to bear against the second branch 62.2 of the yoke 62 and / or the second smooth bearing 72 '. According to one embodiment, the head 92 is in the form of a collar.
    This first section 86 of the nut 82 may be identical to the nut of a main axis of the prior art. Likewise, the braking system 84 may be identical to that of the prior art. According to a feature of the invention, the nut 82 comprises a second section 94 in the form of an extension 95 secured to a second end of the tubular body 88, in projection relative to the second end 74.2 of the main axis 74 when the nut 82 is screwed and tightened. Consequently, the main axis 74 and the tubular body 88 have lengths such that the extension 95 projects from the second end 74.2 of the main axis 74 when the nut 82 is screwed and tightened.
    According to one embodiment, the extension 95 has an approximately tubular shape and has an external cylindrical surface 96 with an external diameter substantially equal to the external diameter of the tubular body 88 of the first section 86 and an internal cylindrical surface 98 with a slightly greater internal diameter the inside diameter of the main axis 74 and less than the outside diameter of the threaded portion 80 of the main axis 74.
    The extension 95 also has an end face 100 which connects the outer and inner cylindrical surfaces 96, 98, opposite the first section 86, and a transverse face 102 which connects the inner cylindrical surface 98 of the extension 95 and the inner face 89 of the tubular body 88 of the first section 86. Thus, this transverse face 102 corresponds to the bottom of a housing 103 delimited by the transverse face 102 and the inner face 89 of the tubular body 88 of the first section 86 and configured to accommodate the second end 74.2 of the main axis 74.
    The emergency axis 76 comprises, at a first end, a head 104 and, at a second end, a threaded portion 106 on which a nut 108 equipped with a braking system 109 is screwed. This nut 108 and its braking system 109 may be identical to those of the prior art. According to one embodiment, the head 104 is in the form of a collar.
    According to a feature of the invention, the head 104 of the emergency axis 76 is configured to bear against the nut 82 of the main axis 74 and more particularly against its end face 100. When it is tightened, the nut 108 bears against head 78 of main axis
    74.
    Each head 78, 104 of the main axis 74 and of the emergency axis 76 comprises a means (flat, imprint, other) to immobilize it in rotation when the nuts 82 and 108 are tightened.
    According to a first embodiment visible in FIG. 5, the emergency axis 76 is connected to the nut 82 of the main axis by a stop ring 110. For this purpose, the emergency axis 76 comprises a first groove 112 configured to partially house the stop ring 110 and the nut 82 comprises a second groove 114 configured to partially house the stop ring 110.
    The second groove 114 is produced at the level of the internal cylindrical surface 98 of the second section 94 of the nut 82.
    The first groove 112 and the head 104 of the emergency axis are separated by a distance substantially equal to the distance separating the second groove 114 and the end face 100 of the nut 82 so that the end face 100 of the nut 82 is in contact against the head 104 of the emergency axis 76 when the latter and the nut 82 are immobilized in translation by the stop ring 110.
    The diameter of the section of the retaining ring 110 is substantially equal to half the difference between the diameter of the internal surface 98 of the second section 94 of the nut 82 and the external diameter of the emergency axis 76.
    According to a second embodiment visible in Figures 7 and 8, the emergency axis 76 is connected to the nut 82 of the main axis by a circlip 116. For this purpose, the emergency axis 76 comprises a groove 118 configured to partially house the circlip 116.
    The groove 118 and the head 104 of the emergency axis 76 are separated by a distance substantially equal to the distance separating the end face 100 and the transverse face 102 of the nut 82 so that the end face 100 of the nut 82 is in contact with the head 104 of the emergency axis 76 when the latter and the nut 82 are immobilized in translation by the circlip 116. Whatever the embodiment, the emergency axis 76 and the nut 82 of the main axis 74 are connected by an axial link 120 configured to immobilize, according to a translation parallel to the axis A68 of the pivot axis 68, the emergency axis 76 relative to the nut 82, while allowing a rotational movement, around the axis A68 of the pivot axis 68, of the nut 82 relative to the emergency axis 76. Once the pivot axis is mounted, the head 104 of the spare axis 76 is pressed against the nut 82 of the main axis 74.
    According to the first embodiment, the axial connection 120 comprises the stop ring and the first and second grooves 112 and 114. According to the second embodiment, the axial connection comprises the circlips 116 and the groove 118.
    The mounting of the pivot axis 68 is described with reference to FIGS. 6A to 6E.
    During a first step, the main axis 74 is inserted into the plain bearings 72, 72 ′ and the ball joint 70, as illustrated in FIG. 6A.
    During a second step, the retaining ring 110 is positioned in the groove 112 of the emergency axis 76 and the nut 82 is fitted on the emergency axis 76, as illustrated in FIG. 6B, until so that the end face 100 of the nut 82 bears against the head 104 of the emergency axis 76 and that the retaining ring 110 is housed in the groove 114 of the nut 82, as illustrated in the figure 6C.
    In the case of a cirlips 116, the nut 82 is fitted onto the emergency axis 76 until it comes into abutment against the head 104 of the emergency axis 76 then the circlip 116 is positioned in the groove 118 of the emergency axis 76 using a specific pliers, the circlip 116 being positioned at the bottom of the housing 103.
    During a third step visible in FIG. 6D, the emergency axis 76 is introduced into the main axis 74. When the braking system 84 of the nut 82 is in the form of a lock washer, this last is fitted onto the emergency axis 76 before the latter is introduced into the main axis 74. Next, the nut 82 is screwed onto the main axis 74 until the main axis 74 is tight. The braking system 84 is then locked to immobilize the nut 82 in rotation relative to the main axis 74.
    At this stage, the emergency axis 76 is still free to rotate but it is blocked in translation and can no longer leave the main axis 74.
    During a fourth step visible in FIG. 6E, the nut 108 and its braking system 109 are positioned on the end of the emergency axis 76 and the nut 108 is screwed until the axis 76 is completely blocked. The braking system 109 is then locked to immobilize the nut 108 in rotation relative to the main axis 74.
    The invention makes it possible to prevent the emergency axis 76 from coming out of the main axis 74 if the nut 108 of the emergency axis 76 is not screwed.
    In addition, the nut 82 of the main axis 74 and the emergency axis 76 being connected, the emergency axis 76 is necessarily present in the main axis 74 when the nut 82 is screwed onto the main axis 74.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Pivot axis (68) for an aircraft engine mount, comprising:
    a tubular main axis (74) which has at a first end (74.1) a head (78) and at a second end (74.2) a threaded portion (80), a first nut (82) configured to be screwed onto the threaded portion (80) of the main axis (74), a spare axis (76) configured to be pivotally mounted inside the main axis (74) and having at a first end (76.1) a head (104) and at a second end (76.2) a threaded portion (106), and a second nut (108) configured to be screwed onto the threaded portion (106) of the spare axis (76), characterized in that the axis emergency (76) and the first nut (82) are connected by an axial link (120) configured to immobilize in translation one with respect to the other the emergency axis (76) and the first nut (82) , while allowing a rotational movement of one relative to the other of the first nut (82) and the spare axis (76).
    [2" id="c-fr-0002]
    2. A pivot axis according to claim 1, characterized in that the head (104) of the emergency axis (76) is pressed against the first nut (82) of the main axis (74).
    [3" id="c-fr-0003]
    3. Pivot axis according to claim 1 or 2, characterized in that the first nut (82) comprises:
    a tubular body (88) provided on an inner face (89) with a thread (90) configured to be screwed onto the threaded portion (80) of the main axis (74), a head (92) integral with a first end of the tubular body (88), an extension (95) integral with a second end of the tubular body (88), in projection relative to the second end (74.2) of the main axis (74) when the first nut (82) is screwed and tightened.
    [4" id="c-fr-0004]
    4. pivot axis according to the preceding claim, characterized in that the extension (95) has an inner cylindrical surface (98) with an inner diameter greater than the inner diameter of the main axis (74) and less than the outer diameter of the threaded portion (80) of the main axis (74), an end face (100) opposite the tubular body (88) and a transverse face (102) connecting the internal cylindrical surface (98) of the extension (95) and the inner face (89) of the tubular body (88), the transverse face (102) and the inner face (89) of the tubular body (88) delimiting a housing (103) configured to accommodate the second end (74.2) of the main axis (74).
    [5" id="c-fr-0005]
    5. Pivot axis according to one of the preceding claims, characterized in that the axial connection (120) comprises a stop ring (110), a first groove (112) on the emergency axis (76), configured for partially accommodating the retaining ring (110) and a second groove (114) on the first nut (82), configured to partially accommodate the retaining ring (110).
    [6" id="c-fr-0006]
    6. pivot axis according to the preceding claim, characterized in that the first and second grooves (112, 114) are positioned so that the first nut (82) is in contact against the head (104) of the axis emergency (76) when the emergency axis (76) and the first nut (82) are immobilized in translation by the retaining ring (110).
    [7" id="c-fr-0007]
    7. pivot axis according to one of claims 1 to 4, characterized in that the axial connection (120) comprises a circlip (116) and a groove (118) on the emergency axis (76) configured to partially accommodate the circlip (116).
    [8" id="c-fr-0008]
    8. Pivot axis according to the preceding claim, characterized in that the groove (118) is positioned relative to the head (104) of the spare axis (76) so that the first nut (82) is in contact with the head (104) of the emergency axis (76) when the emergency axis (76) and the first nut (82) are immobilized in translation by the circlip (116).
    [9" id="c-fr-0009]
    9. An engine mount of an aircraft comprising a pivot axis according to one of the preceding claims.
    [10" id="c-fr-0010]
    10. Aircraft comprising an engine mount according to the preceding claim.
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    同族专利:
    公开号 | 公开日
    CN109850166A|2019-06-07|
    US20190161198A1|2019-05-30|
    EP3492383B1|2020-02-19|
    FR3074146B1|2019-10-18|
    EP3492383A1|2019-06-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    US4435100A|1981-12-21|1984-03-06|Mcdonnell Douglas Corporation|Fail-safe zero-load hinge/pivot|
    EP0309129A1|1987-09-18|1989-03-29|British Aerospace Public Limited Company|Lock nut assemblies|
    US20080296430A1|2005-09-05|2008-12-04|Airbus France|System For Connecting a Crossbar to an Aircraft Engine Pylon|
    FR2958262A1|2010-04-02|2011-10-07|Airbus Operations Sas|Connection assembly for engine nacelle stub under aerofoil of aircraft, has locking units assembled around external main axle, secondary axle and lag screw at free ends of axle system, where secondary axle is assembled in main axle|
    FR2958267B1|2010-04-02|2012-03-23|Airbus Operations Sas|AXIS SYSTEM FOR LINK ASSEMBLY OF MAT-REACTOR UNDER AN AIRCRAFT VESSEL|
    US8985604B2|2010-07-07|2015-03-24|Ford Global Technologies, Llc|Cross axis joint with elastomeric isolation|
    KR101293976B1|2011-07-29|2013-08-07|현대자동차주식회사|Bush for suspension of vehicle|
    GB201118548D0|2011-10-27|2011-12-07|Airbus Operations Ltd|Plain journal bearing|
    US9587668B2|2013-03-12|2017-03-07|Harnischfeger Technologies, Inc.|Pin retention system|
    FR3003896B1|2013-03-29|2015-03-20|Snecma|JOINT JOINT DEVICE FOR SUSPENDING A TURBOMACHINE TO A PYLONE OR SUSPENSION OF EQUIPMENT TO THE BODY OF THE TURBOMACHINE|
    FR3014973B1|2013-12-12|2016-01-22|Airbus Operations Sas|ASSEMBLY COMPRISING A JOINT AXLE SUPPORTED BY A CAP AND IMMOBILIZED IN TRANSLATION BY A LOCKING DEVICE INCORPORATING A DOUBLE ANTI-ROTATION SYSTEM|
    FR3014970B1|2013-12-12|2016-01-22|Airbus Operations Sas|ASSEMBLY COMPRISING A JOINT AXLE SUPPORTED BY A CAP AND IMMOBILIZED IN TRANSLATION BY A LOCKING DEVICE INCORPORATING A DOUBLE ANTI-ROTATION SYSTEM|
    FR3014972B1|2013-12-12|2016-04-22|Airbus Operations Sas|ASSEMBLY COMPRISING A JOINT AXLE SUPPORTED BY A CAP AND IMMOBILIZED IN TRANSLATION BY A LOCKING DEVICE INCORPORATING A DOUBLE ANTI-ROTATION SYSTEM|
    GB201417202D0|2014-09-30|2014-11-12|Rolls Royce Plc|Gas Turbine Engine Mounting Arrangement|
    FR3077560B1|2018-02-06|2020-01-10|Airbus Operations|ASSEMBLY FOR AN AIRCRAFT ENGINE MOUNT COMPRISING A HINGE AXIS SUPPORTED BY A SCREED AND MOVABLE IN TRANSLATION|US10634092B2|2017-09-08|2020-04-28|United Technologies Corporation|Linkage assembly preventing axial rotation of the link rod|
    FR3070967B1|2017-09-14|2019-08-30|Airbus Operations|COMPACT THERMAL EXCHANGE DEVICE INCORPORATED IN AN AIRCRAFT MAT|
    US10597144B2|2017-12-01|2020-03-24|Hadie Fotouhie|Under the wing-mounted jet engine with pivotal swivel joint to produce directional thrust vectoring thru swivel angle|
    FR3077560B1|2018-02-06|2020-01-10|Airbus Operations|ASSEMBLY FOR AN AIRCRAFT ENGINE MOUNT COMPRISING A HINGE AXIS SUPPORTED BY A SCREED AND MOVABLE IN TRANSLATION|
    法律状态:
    2018-11-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-05-31| PLSC| Publication of the preliminary search report|Effective date: 20190531 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-08-06| ST| Notification of lapse|Effective date: 20210706 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1761142A|FR3074146B1|2017-11-24|2017-11-24|IMPROVED PIVOTING AXIS FOR AN AIRCRAFT ENGINE ATTACHMENT|
    FR1761142|2017-11-24|FR1761142A| FR3074146B1|2017-11-24|2017-11-24|IMPROVED PIVOTING AXIS FOR AN AIRCRAFT ENGINE ATTACHMENT|
    EP18204982.5A| EP3492383B1|2017-11-24|2018-11-07|Improved pivoting axis for an aircraft engine attachment|
    US16/195,971| US20190161198A1|2017-11-24|2018-11-20|Pivoting axis for an aircraft engine attachment|
    CN201811398019.0A| CN109850166A|2017-11-24|2018-11-22|Turn round shaft member and aircraft engine attachment and aircraft|
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