• 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 an aircraft engine support mast, comprising two side panels (17, 18) and an upper spar (19) and a lower spar (21) assembled to form a box extending in a longitudinal direction. (AX) corresponding to a direction of advance of the aircraft and an internal reinforcing structure comprising a plurality of reinforcements. The carrier mast according to the invention comprises a reinforcing zone on each side panel (17, 18) and a front housing (42) for receiving a front median main reinforcement (27) and a rear housing (43) for receiving a main reinforcement rear median (26).
    公开号:FR3042475A1
    申请号:FR1559830
    申请日:2015-10-16
    公开日:2017-04-21
    发明作者:Frederic Journade；Eric Bouchet；Gerard Coudouent；Bogdan Sina；Sylvain Cros；Romain Terral；Jerome Puech；Cyrielle Rogeron
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    The invention relates to an aircraft engine-carrying mast.
    Conventionally, a support mast comprises a mechanical structure which ensures the transfer of forces between the engine and the wing and a fairing surrounding this mechanical structure.
    As represented in FIG. 1, the mechanical structure of such a support mast 1 has a general box shape delimited by an upper spar 2, comprising a front portion 3 and a rear portion 4, a lower spar 5, and two side panels. 6 and 7.
    This box is connected to the wing by a front wing attachment 8 and a rear wing attachment not shown. This box is also linked to the engine by a front engine attachment 9 and a rear engine attachment not shown.
    This box contains structural elements comprising a main reinforcement before 11 called pyramid, a median main reinforcement 12 and a rear main reinforcement not shown. The main reinforcements are located at the engine attachments and wing attachments and ensures the transmission of the main efforts of the engine to the wing. Each main reinforcement is thus secured to the two side panels 6, 7 and the upper and lower rails 2 and 5 and optimizes the transmission of forces.
    This box also contains a plurality of secondary reinforcements 13, regularly spaced along a longitudinal axis AX of the support mast to provide the box with additional rigidity. Each secondary reinforcement 13 is also secured to the side panels 6, 7 and the longitudinal members, to provide the required rigidity between these components.
    Thus, such a support mast 1 comprises many elements (up to 30 elements depending on the type of aircraft). Generally, these elements are made of metallic materials and increase the total weight of the aircraft.
    The present invention proposes a carrier mast remedying all or part of the disadvantages of the prior art. For this purpose, the object of the invention is an aircraft engine-carrying mast, comprising a main front reinforcement, a rear main reinforcement, two side panels as well as an upper spar and a lower spar assembled to each other. to form a box extending in a longitudinal direction, each side panel having an inner face facing the interior of the box and an outer face facing outwardly of the box. The mast according to the invention is remarkable in that each side panel comprises on its inner face a reinforcing zone comprising a network of stiffeners arranged in at least two distinct directions and crossing zones stiffeners and a front housing for receiving a side edge of a front medial main reinforcement and a rear housing for receiving a side edge of a rear medial main reinforcement.
    Advantageously, the reinforcement zone is delimited by an upper longitudinal rib along an upper edge of the lateral panel and a lower longitudinal rib along a lower edge of the lateral panel, the upper and lower longitudinal ribs being connected at one of their ends by a front rib. and at the other of their ends by a rear rib.
    According to an alternative embodiment, the mast according to the invention comprises at least two panel fittings each integrated with a side panel and at least two reinforcing brackets integrated in the rear main median reinforcement and each contiguous to one of the at least two panel fittings. .
    According to another embodiment, the mast according to the invention comprises at least two rear fittings each integrated with a side panel and at least two reinforcing brackets integrated in the rear main reinforcement and each contiguous to one of the at least two rear fittings.
    Preferably, each of the reinforcing brackets extends to the right of a lateral edge of the rear middle main reinforcement in a direction perpendicular to the longitudinal direction and each of the panel fittings extends from the upper longitudinal rib to the right of the rear housing.
    Advantageously, each of the rear fittings extends in the extension of the rear rib in a direction substantially normal to the longitudinal direction.
    According to an alternative embodiment, the mast according to the invention comprises at least two protuberances each located at a front edge of the side panel, each of the two protuberances having at least one wall extending in a direction parallel to the longitudinal direction , the wall being provided with a through bore configured to receive a fastener such as a rod or a bolt or a cam.
    According to an alternative embodiment, the mast according to the invention also comprises a rear engine attachment comprising a plate extending to the right of the front housing in the extension of the lower longitudinal rib and a consolidation zone comprising an extra thickness along the face. external side panel at the platen.
    Advantageously, the plate comprises at least a first hole configured to receive a fastening element such as a rod or a bolt or a cam and the consolidation zone comprises at least one second hole configured to receive a fastener element such as a fastener. rod or bolt or cam.
    Preferably, the network of stiffeners comprises a plurality of edges arranged in a repeated pattern constituting a regular mesh over the entire surface of the reinforcement zone. Other characteristics, details and advantages of the invention will emerge more clearly from the detailed description given below as an indication in relation to drawings in which: FIG. 1 is an exploded view of a primary structure of a support mast of the prior art; Figure 2 is an exploded view of a carrier pole structure according to the invention; Figure 3 is a perspective view showing the right side panel of the support mast according to the invention; Figure 4 is a side view of the inner side of a right panel of the carrier mast according to the invention shown alone; Figure 5 is a side view showing the longitudinal members and the main reinforcements of the support mast according to the invention; Figure 6 is a side view showing the right panel provided with main reinforcements and spars; Figure 7 is a detail view of a fastening of the support mast according to the invention; Figures 8a and 8b are detail views of the rear end of the support mast according to the invention; Figure 9 is a detail view of the outer side of the front end of a right panel of the support mast according to the invention; - Figures 10a and 10b are detailed views of a side portion of a mast panel according to the invention.
    As shown in Figure 2, there is shown a support mast 16 according to the invention having a right side panel 17 and a left side panel 18, a main front reinforcement 28 and a rear main reinforcement 22 and an upper spar 19 and a lower spar 21. These elements 17, 18, 19, 21, 22 and 28, shown exploded in Figure 2, are intended to be secured to each other to form a box extending in a longitudinal direction AX corresponding to the direction of advance of the aircraft.
    As illustrated in the figures, the various elements of the support mast 16 have symmetrical shapes with respect to a vertical median plane parallel to the direction AX and located midway between the side panels 17 and 18. These side panels 17 and 18 are thus symmetrical to each other.
    A rear main reinforcement 22 of generally rectangular shape has two reinforcing brackets 52 and 53 along an edge, called the upper edge. The reinforcing brackets 52, 53 are conventionally eyelet-shaped and pierced at their center with a circular orifice.
    The carrier mast 16 also comprises a rear middle main reinforcement 26, a front median main reinforcement 27 and two intermediate reinforcements 29, intended to be positioned between the front median main reinforcement 27 and the main front reinforcement 28, during the assembly of the mast. 16. Reinforcements 26-29 serve to transmit the forces coming from the engine to the caisson and to the wing.
    Each medial main reinforcement 26 and 27 is a machined structural part of generally rectangular base shape of normal orientation to the longitudinal direction AX. Each medial main reinforcement 26, 27 is hollowed in its central region, and reinforced especially its periphery.
    More particularly, the rear middle main reinforcement 26 comprises two reinforcing brackets 46, 47. As can be seen in the figures, each reinforcing bracket 46, 47 comprises two parallel planar lobes spaced from one another, and each having a shape eyelet pierced with a circular orifice at its center in a direction normal to the direction AX.
    Each side panel 17, 18 has an outline whose shape is that of a convex hexagon composed of two trapezoids joined by their large base and which defines a front edge 30, an upper edge 34, a rear edge 30b and a lower edge 37 Each side panel 17, 18 extends in a direction parallel to AX and has an inner face 17a, 18a shown more clearly in Figures 3 and 4, and an outer face, 17b, 18b substantially parallel to the inner face. Advantageously, the upper edge 34 and the lower edge 37 are symmetrical to one another with respect to a median axis parallel to the direction AX. The leading edge 30 is smaller than the trailing edge 30b.
    Each side panel 17, 18 comprises, at the front edge 30, an outgrowth 31 which will be described later in the text with reference to FIG. 9.
    Each side panel 17, 18 is a steel or titanium part comprising a reinforcing zone 40. The reinforcing zone 40 comprises a network of stiffeners (such as ribs or ridges). Each side panel 17, 18 also comprises structural elements such as inspection holes 41 or housings 42, 43. Advantageously, the reinforcement zone 40 and the structural elements 41, 42, 43 are machined in the mass. Thus the side panels of the support mast 16 are self-stiffened.
    More particularly, the outer face 17b, 18b of each side panel 17, 18 is substantially smooth, that is to say free of reliefs, as can be seen in FIG. 2 (side panel 18) and the internal face 17a, 18a comprises the reinforcing zone 40 (visible on the side panel 17 of FIG. 2).
    As illustrated in FIGS. 3 and 4, each side panel 17, 18 has an upper longitudinal rib 33 which runs along the upper edge 34 of the side panel 17, 18 and a lower longitudinal rib 36 which runs along the lower edge 37 of the side panel 17, 18. These two ribs are connected to one another at one of their ends by a front rib 38, and at the other of their ends by a rear rib 39
    Advantageously, as illustrated in FIGS. 3 and 8, the rear rib 39 of the right side panel 17 comprises a rear fitting 51. The rear fitting 51 extends in the extension of the rear rib 39 beyond the upper longitudinal rib 33 and is in the form of eye generally plane orientation substantially normal to the longitudinal direction AX, and pierced at its center with a circular orifice. Symmetrically, the left side panel 18 has an identical rear fitting (not shown for reasons of clarity).
    The four ribs 33, 34, 38 and 39 of each side panel 17, 18, shown in Figure 3, increase the mechanical rigidity of the side panel 17,18. These ribs additionally constitute fixing supports for the upper and lower spars 19 and 19 during the assembly of the support mast 16.
    The four ribs 33, 34, 38 and 39 of the same side panel 17, 18 delimit the reinforcement zone 40. The interior of this reinforcement zone 40 comprises a network of stiffeners comprising a plurality of edges 40a. , 40b arranged in two distinct directions and having crossing areas of the stiffeners. Preferably, the plurality of edges is arranged in a repeating pattern. This pattern is here of hexagonal form, isogrid type or the like. Each side of the hexagon is materialized by a lateral edge 40a, and each vertex of the hexagon is connected to the opposite vertex by a transverse edge 40b. These lateral 40a and transverse edges 40b constitute a regular mesh extending substantially over the entire reinforcement zone 40. Thus, each side panel 17, 18 has a significantly higher mechanical rigidity than that of the side panels of the prior art.
    According to the embodiment shown, each side panel 17, 18 also comprises three inspection holes 41 regularly spaced from each other and each reinforced on their periphery. These inspection holes 41 allow access to the interior of the box to perform for example a maintenance operation, without having to dismantle the components of the box.
    The inner face of each side panel 17, 18 also has a front housing 42 for receiving a lateral edge of the front middle main reinforcement 27, and a rear housing 43 for receiving a lateral edge of the rear middle main reinforcement 26.
    Each housing 42, 43 is delimited by two vertical ribs 44 extending perpendicular to the direction AX and spaced from each other by a distance identical to the thickness of the lateral edge of the median main reinforcement that the housing 42 , 43, receives. The bottom of each housing 42, 43 is smooth. Thus, the lateral edge of the median main reinforcement 26, 27 housed in the housing 42, 43 is blocked in this housing 42, 43. Therefore, a strong connection between the median main reinforcements 26, 27 and the side panels 17, 18 is performed during the assembly of the support mast 16.
    As seen in FIG. 2, each side panel 17, 18 also has a panel fitting 32, 48 of identical shape to the reinforcing bracket 46, 47. Each panel fitting 32, 48 extends from the upper longitudinal rib 33 the right to rear housing 43.
    Thus, thanks to all these structural elements, the side panels 17,18 are mechanically reinforced, that is to say self-stiffened, with respect to the side panels of the prior art. Such side panels 17, 18 contribute to reducing the number of reinforcing elements of the support mast. Such an arrangement of stiffeners provides greater cohesion to the box whose side panels are reinforced, so that the amount of internal reinforcements can be significantly reduced. This makes it possible to reduce the number of components of the carrier mast, and thereby its cost of manufacture and assembly.
    As illustrated in FIGS. 5 and 6, the assembly of the support mast 16 is made by housing the median main reinforcements 26 and 27 in the recesses 42, 43 of a first lateral panel, for example the right side panel 17. By following , the various reinforcements 22, 26-29 are fixed to the right side panel 17. Then the housings 42, 43 of the second side panel, here the left side panel 18, are nested on the median main reinforcements 26 and 27 before fixing the panel left side 18 to all the reinforcements. The upper spar 19 is then positioned on this assembly, attached to the longitudinal upper ribs 33 of each side panel 17, 18 to be assembled to the other elements of the support mast 16. Similarly, the lower spar 21 is attached to the longitudinal lower ribs 36 of each side panel 17,18 to be assembled to the other elements of the support mast 16.
    Thus, each median main reinforcement 26, 27 is secured around its entire periphery to the side panels 17, 18 and the longitudinal members 19,21, and thus transmits the engine forces to the box and to the wing.
    Fixing the various elements to each other is provided by any known fastening means, in this case rivets, screws and others.
    During the assembly of the elements of the support mast 16, the panel fittings 32, 48 of the side panels 17, 18 are contiguous with the reinforcing brackets 46, 47 of the rear middle main reinforcement 26.
    Advantageously, the four circular orifices have the same diameter and the centers of the circular orifices of each fitting are aligned.
    As a result, the four fittings 32, 46, 47, 48 constitute two double fittings. For the sake of clarity, only the double fitting made by the brackets 46 and 32 is shown in FIG. 6 and illustrated more clearly in FIG. 7.
    Advantageously, in the support mast 16 according to the invention, the four fittings 32, 46, 47 and 48 together constitute part of a front wing attachment of the support mast 16. This front wing attachment comprises a first half-wing attachment front 49 (visible in FIG. 7) located on the side of the right side panel 17 and comprising the panel fitting 32 and the reinforcing fitting 46 joined to one another, and a second front wing half-fastener (not shown on the FIG. figures), located on the side of the left-hand side panel 18, comprising the panel fitting 48 and the reinforcing fitting 47 contiguous to each other.
    The panel fitting 32 of the right side panel 17 receives a flat fixing cam in the space between the two parallel lobes. The reinforcement fitting 46 of the rear middle main reinforcement 26 has the same shape and the same orientation as the panel fitting 32, to which it is contiguous, and receives a second flat fixing cam engaging in the space between the two parallel lobes. Thus, the fixing of the support mast 16 is carried out by inserting a same bolt transversely in the circular orifices of the two fittings 32, 46 of this fastener to form the first wing half-attachment 49. Similarly, the second half-wing attachment front is constituted by the fittings 47 and 48.
    Part of a rear wing attachment is similarly made with double fittings. During the assembly of the support mast 16, the rear main reinforcement 22 is pressed against the rear rib 39 of the right side panel 17 so that the reinforcing fitting 52 is contiguous to the rear fitting 51 and the centers of the circular orifices aligned to constitute a first half-attachment rear wing, as shown in Figure 8b. Similarly, the reinforcing fitting 53 is contiguous to the rear fitting of the rear rib present on the left side panel 18. Thus, the fixing of the support mast 16 to the wing is carried out by means of bolts or the like passing through the circular orifices of the double fittings, similar to the attachment of the carrier mast 16 to the engine.
    Advantageously, the side panel 17, 18 of the support mast 16 according to the invention incorporates front engine attachment elements. More particularly, the front engine attachment comprises the protrusion 31 of the side panel 17, 18. Preferably, as illustrated in FIG. 9, the protrusion 31 has the general shape of a rectangular box open on a first face that is merged with the external face 17b, 18b of the side panel 17, 18 and on a second face that merges with the edge. upper 34 of the side panel 17,18. The protrusion 31 thus has a bottom coincident with the internal face 17a, 18a of the side panel 17, 18 and a bottom wall 56 which extends parallel to the longitudinal direction AX, and which is provided with a through hole 57 configured to receiving a motor attachment means (not shown) to the support mast 16.
    Referring to Figures 10a and 10b, each side panel 17, 18 also incorporates elements of a rear engine attachment 58. These rear engine attachment members 58 are located on the lower longitudinal rib 36 of the side panel 17, 18 at the rear end. of the front housing 42. The rear engine attachment elements 58 comprise a plate 60 and a consolidation zone 59. The plate 60 extends the lower longitudinal rib 36 of the side panel 17, 18, from the internal face of the side panel 17, 18 and extends between the two ribs 44 of the front housing 42. The plate 60 has a set of bores 63 configured to receive a first rear engine attachment member. The consolidation zone 59 includes an excess thickness 61 along the outer face 17b, 18b of the side panel 17, 18 at the plate 60. The consolidation zone 59 has a plurality of bores 62, configured to receive a motor fixing means (not shown) at the support mast 16.
    Thus, the side panels 17, 18 of the support mast 16 according to the invention incorporates front wing attachment elements, rear wing attachment elements, front engine attachment elements and rear engine attachment elements. Consequently, the forces are transferred directly from the engine to the wing via the side panels 17, 18, which makes it possible to eliminate elements used in the prior art such as the main reinforcement before 11 called pyramid or the engine attachment brackets back called shovel. In general, the new support mast structure 16 according to the invention makes it possible to introduce the forces of the connection of the engine to the wing, together with the level of the self-stiffened and reinforced side panels and at the level of the main reinforcements that encloses the box, which improves the distribution of mechanical stresses in the structure.
    The support mast structure 16 according to the invention, comprising machined metal panels which are reinforced and stiffened, simplifies the architecture to reduce the number of constituent components of the box and to reduce the cost of production and assembly.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    An aircraft engine-supporting mast, comprising a front main reinforcement (28), a rear main reinforcement (22), two side panels (17, 18) and an upper spar (19) and a lower spar (21). ) connected to each other to form a box extending in a longitudinal direction (AX), each side panel (17,18) having an inner face (17a, 18a) facing inwardly of the box and an outer face ( 17b, 18b) oriented towards the outside of the box, the support mast being characterized in that each side panel (17, 18) comprises on its inner face (17a, 18a): - a reinforcing zone (40) comprising a network stiffeners arranged in at least two distinct directions and crossing areas of the stiffeners; and - a front housing (42) for receiving a side edge of a front medial main reinforcement (27) and a rear housing (43) for receiving a side edge of a rear median main reinforcement (26).
    [2" id="c-fr-0002]
    2. Mast according to claim 1, characterized in that the reinforcing zone is delimited by an upper longitudinal rib (33) along an upper edge (34) of the side panel (17, 18) and a lower longitudinal rib (36) along a lower edge (37) of the side panel (17, 18), the upper longitudinal ribs (33) and the lower one (36) being connected at one of their ends by a front rib (38) and at the other of their ends by a rear rib (39)
    [3" id="c-fr-0003]
    3. Mast according to one of claims 1 or 2, characterized in that it comprises at least two panel fittings (32, 48) each integrated with a side panel (17, 18) and at least two reinforcing brackets ( 46, 47) integrated in the rear middle main reinforcement (26) and each contiguous to one of the at least two panel fittings (32, 48).
    [4" id="c-fr-0004]
    4. Mast according to one of claims 1 to 3, characterized in that it comprises at least two rear brackets (51) each integrated with a side panel (17,18) and at least two reinforcing brackets (52, 53). ) integrated in the rear main reinforcement (22) and each contiguous to one of at least two rear brackets (51).
    [5" id="c-fr-0005]
    5. Mast according to one of claims 3 or 4, characterized in that each of the reinforcing brackets (46, 47) extends in line with a lateral edge of the rear middle main reinforcement (26) in a direction perpendicular to the longitudinal direction (AX) and each of the panel fittings (32, 48) extends from the upper longitudinal rib (33) to the right of the rear housing (43).
    [6" id="c-fr-0006]
    6. Mast according to one of claims 4 or 5, characterized in that each of the rear brackets (51) extends in the extension of the rear rib (39) in a direction substantially normal to the longitudinal direction (AX).
    [7" id="c-fr-0007]
    7. Mast according to one of the preceding claims, characterized in that it comprises at least two protuberances (31) each located at a front edge (30) of the side panel (17, 18), each of the two protuberances having at least one wall (56) extending in a direction parallel to the longitudinal direction (AX), the wall being provided with a through bore (57) configured to receive a fastener such as a rod or bolt or a cam.
    [8" id="c-fr-0008]
    8. Mast according to one of the preceding claims, characterized in that it comprises a plate (60) extending to the right of the front housing (42) in the extension of the lower longitudinal rib (60) and a consolidation zone (59) comprising an extra thickness (61) along the outer face (17b, 18b) of the side panel (17, 18) at the plate (60).
    [9" id="c-fr-0009]
    9. Mast according to the preceding claim, characterized in that the plate (60) comprises at least a first bore (63) configured to receive a fastener such as a rod or a bolt or a cam and the consolidation zone comprises at least one second bore (62) configured to receive a fastener such as a rod or bolt or a cam.
    [10" id="c-fr-0010]
    10. Mast according to one of the preceding claims, characterized in that the network of stiffeners comprises a plurality of edges (40a, 40b) arranged in a repeated pattern constituting a regular mesh over the entire surface of the reinforcing zone (40). ).
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    同族专利:
    公开号 | 公开日
    US20170106990A1|2017-04-20|
    CN106585999A|2017-04-26|
    CN106585999B|2021-12-14|
    US10351254B2|2019-07-16|
    FR3042475B1|2018-07-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2889505A1|2005-08-05|2007-02-09|Airbus France Sas|PRIMARY STRUCTURE OF PERFECTED AIRCRAFT ENGINE MAT|
    FR2891252A1|2005-09-28|2007-03-30|Airbus France Sas|Box-type aircraft engine e.g. jet engine, mounting structure, has monolithic framework covered with mechanically assembled covering panels, and fixed with reinforcement fittings mechanically secured to engine and/or wings fastening points|
    WO2009118469A2|2008-03-28|2009-10-01|Aircelle|Primary structure of a connecting strut|
    US20110121132A1|2009-11-23|2011-05-26|Spirit Aerosystems, Inc.|Truss-shaped engine pylon and method of making same|EP3476740A1|2017-10-27|2019-05-01|Airbus Operations |Primary structure of mast for supporting an aircraft drive unit in a box, formed by joining two half-shells|
    EP3476739A1|2017-10-27|2019-05-01|Airbus Operations S.A.S.|Primary structure of mast for supporting a drive unit for an aircraft comprising a u-shaped lower portion formed integrally or by welding|FR2891803B1|2005-10-07|2007-11-30|Airbus France Sas|RIGID STRUCTURE FOR AN AIRCRAFT ENGINE HANDLING MACHINE, AND MATT COMPRISING SUCH A STRUCTURE|
    FR2892252B1|2005-10-17|2008-01-25|Oberthur Card Syst Sa|METHOD AND DEVICE FOR CREATING A GROUP SIGNATURE AND METHOD AND DEVICE FOR VERIFYING AN ASSOCIATED GROUP SIGNATURE.|
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    FR2964364B1|2010-09-03|2012-09-28|Airbus Operations Sas|AIRCRAFT TURBOJET ENGINEERING MACHINE COMPRISING FRONT VANE FRONT FASTENERS|
    US9027875B2|2010-10-28|2015-05-12|Spirit Aerosystems, Inc.|Pylon arrangement for open structure|
    EP2530010B1|2011-06-02|2013-09-18|Bell Helicopter Textron Inc.|Integrally stiffened panel|
    US9248921B2|2013-07-11|2016-02-02|Spirit Aerosystems, Inc.|Method for mounting a pylon to an aircraft|
    WO2015047539A1|2013-09-27|2015-04-02|United Technologies Corporation|Mounting systems for gas turbine engines|
    US9238511B2|2014-03-04|2016-01-19|Mra Systems, Inc.|Engine pylon structure|
    FR3032180B1|2015-01-30|2018-05-18|Airbus Operations|PROPELLANT ASSEMBLY COMPRISING A TURBOJET ENGINE AND A COUPLING MAT FOR A NEW DISTRIBUTION OF EFFORTS BETWEEN THE TURBOJET AND THE VIL|FR3052745B1|2016-06-15|2018-05-25|Airbus Operations|AIRCRAFT MAT COMPRISING AT LEAST ONE LATERAL LATERAL FRAME AND AIRCRAFT COMPRISING THE SAME|
    FR3069848B1|2017-08-02|2019-08-30|Airbus|LOW PRIMARY STRUCTURE FOR AN AIRCRAFT ENGINE HITCHING MAT|
    CN107963225B|2017-11-30|2021-06-04|中国商用飞机有限责任公司|Aircraft engine hanger and hanging box section thereof|
    CN109606703A|2019-01-16|2019-04-12|中国商用飞机有限责任公司|Aircraft static determinacy hangar system|
    法律状态:
    2016-10-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-21| PLSC| Publication of the preliminary search report|Effective date: 20170421 |
    2017-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559830A|FR3042475B1|2015-10-16|2015-10-16|MATERIAL AIRCRAFT ENGINE|
    FR1559830|2015-10-16|FR1559830A| FR3042475B1|2015-10-16|2015-10-16|MATERIAL AIRCRAFT ENGINE|
    US15/292,173| US10351254B2|2015-10-16|2016-10-13|Aircraft engine pylon|
    CN201611270954.XA| CN106585999B|2015-10-16|2016-10-14|Aircraft engine pylon|
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