• 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:
    In order to optimize the space requirement of a primary structure (6) of an aircraft engine mounting pylon, and to favor the installation of the engine as close as possible to the wing element, the invention provides a assembly (1) for an aircraft comprising a wing element (2), a motor (10) with a double flow and an attachment pylon (4) of the engine, the engine comprising a rear part arranged under the wing element (2) equipped with a wing structure (21), the mast comprising a primary structure (6) for transmitting the forces of the engine to the wing structure (21), this primary structure comprising a mast box (6a), and the assembly further comprising hooking means (7) of the primary structure (6) on the engine. According to the invention, the wing structure (21) comprises two wing boxes (21a, 21b) succeeding one another in a span direction (9) of the wing member (2), and the mast box (6a ) is arranged between these boxes (21a, 21b) and fixed on each of them.
    公开号:FR3032421A1
    申请号:FR1550955
    申请日:2015-02-06
    公开日:2016-08-12
    发明作者:Olivier Pautis；Wolfgang Brochard
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] Description: The present invention relates to the field of aircraft assemblies comprising a wing element, a double-flow motor as well as an airfoil unit. a motor attachment pylon, the latter being intended to be arranged partly under the wing element.
    [0002] The invention also relates to an aircraft equipped with such an assembly. It applies preferentially to commercial aircraft. STATE OF THE PRIOR ART On existing aircraft, dual flow engines such as turbojets are suspended below the wing by complex attachment devices, also called "EMS" (of the English "Engine Mounting Structure") , or even hanging mast. The attachment devices usually employed have a primary structure, also called rigid structure, often made in the form of a single box, that is to say constituted by the assembly of lower and upper beams connected together by a plurality transverse ribs located inside the box. The spars are arranged in lower and upper faces, while side panels close the box side faces. In addition, the attachment pylon is arranged in the upper part of the engine, between the latter and the wing box. This position is called "at 12 o'clock". In known manner, the primary structure of these masts is designed to allow the transmission to the wing static and dynamic forces generated by the engines, such as weight, thrust, or the various dynamic forces, including those related to the cases of failures such as loss of light (FBO), deletion of the nosewheel, dynamic landing, etc.
    [0003] In the attachment masts known from the prior art, the transmission of forces between its primary structure, known as a single box, and the wing is conventionally provided by a set of fasteners comprising a front fastener, a fastener rear, and an intermediate fastener in particular for taking up the thrust forces generated by the engine. In recent twin-flow engines, the high dilution ratio sought leads to extremely high bulk, since an increase in the dilution ratio inevitably leads to an increase in the diameter of the engine, and more particularly to an increase in the diameter of its crankcase. blower.
    [0004] Also, with a ground clearance that is set so as to remain acceptable from a safety point of view, the space remaining between the wing element and the engine is increasingly restricted or non-existent for high-speed engines. dilution. Therefore, it may be difficult to implement the attachment mast and the various wing fasteners in this remaining vertical space, usually dedicated to this implementation.
    [0005] The evolution of the dual-flow motors has therefore had the detrimental consequence of imposing a reduction in the vertical dimensions of the suspension pylon, in particular so as to be able to maintain sufficient space to place the fastening hardware. The large dimensions of certain fasteners are imposed by the need to take up the thrust forces of the engine, that is to say those oriented in the longitudinal direction of this engine, as well as those oriented in the transverse direction of the latter. As an indication, it is recalled that the longitudinal direction of the motor corresponds to the direction of the main axis of rotation of the propulsion system. However, the possibilities of reducing the vertical dimensions of the pylon are limited. Indeed, the rigid structure of this mast, also referred to as the primary structure, must have sufficient dimensions to provide a mechanical resistance capable of withstanding the passage of the forces of the engine towards the wing element, with a low deformation under stress in the not to degrade the aerodynamic performance of the propulsion system. In the prior art, multiple solutions have been proposed to bring the engine closer to the wing element to which it is suspended, and this in order to maintain the ground clearance required, especially vis-à-vis the risk of ingestion and collision, also known as Foreign Object Damage (FOD) risk. However, these solutions need to be continuously improved to accommodate ever higher fan case diameters, retained to meet dilution rate requirements. DISCLOSURE OF THE INVENTION The object of the invention is therefore to propose an aircraft assembly at least partially remedying the problems mentioned above, encountered in the solutions of the prior art.
    [0006] To do this, the subject of the invention is an assembly for an aircraft comprising a wing element, a dual-flow engine and an engine attachment pylon, said engine comprising a rear part arranged under the wing element. which being equipped with a wing structure, the mast comprising a primary structure for transmitting the forces of the engine to the wing structure, said primary structure comprising a mast box, and the assembly further comprising hooking means of the primary structure on the engine. According to the invention, the wing structure comprises two wing boxes succeeding one another in a span direction of the wing element, and the mast box is arranged between said wing boxes and fixed on each of them.
    [0007] The invention thus breaks with the existing solutions by implanting the mast box directly within the wing structure, which is then split into two boxes arranged on either side of the mast box. The specific solution to the invention makes it possible to obtain an excellent compromise in terms of size, simplicity of design, and ability to approach the engine as close as possible to the wing element. Indeed, the size is reduced in that the primary structure of the mast no longer requires multiple structural elements. The integration of the mast box within the wing structure also contributes to reducing this size, as well as the quantity and mass of secondary structures to be put in place on the mast.
    [0008] Thanks to this reduced size of the mast, the implantation of the surrounding elements is facilitated by the design of the invention. For example, the nacelle and its thrust reverser system can come closer to the crankcase, because it is no longer hindered by the presence of the connecting arches and side beams, as in the document FR In addition, systems can be more easily integrated into the mast, around the mast box. In addition, the design is simplified, in particular because the presence of conventional wing fasteners is no longer required, the fixing of the mast on the wing element now being carried out more simply, by connecting the different caissons the to each other. Finally, the integration of the mast box into the wing structure makes it possible to approach the engine as close as possible to the wing element, thus ensuring a satisfactory ground clearance, even with engines having high levels of dilution.
    [0009] Preferably, the invention also comprises at least one of the following optional technical characteristics, taken separately or in combination. The two wing boxes form an inner box and an outer box, said inner box being delimited by an outer side panel and said outer box being delimited by an inner side panel, said mast box 20 being delimited by an outer side panel as well as by an inner side panel, and the assembly comprises a first mechanical connection between the outer side panel of the inner wing box and the inner side panel of the mast box, and a second mechanical connection between the inner side panel of the outer box. wing and the outer side panel of the mast box.
    [0010] The outer side panel of the inner wing box is pressed against the inner side panel of the mast box, and the inner side panel of the outer wing box is pressed against the outer side panel of the mast box. The first and second mechanical links are each made by means of bolts and / or shear pins, said bolts and / or shear pins preferably having axes substantially parallel to the span direction. Said mast box and the inner and outer wing boxes are each delimited by lower and upper spars, the lower spars of the mast box providing surface continuity between the lower spars of the inner and outer wing boxes, and the spars. Mast box upper sections providing surface continuity between the upper longitudinal members of the inner and outer wing boxes. Alternatively, breaks in surface continuity can be observed when the mast box has a height greater than that of the 10 wing boxes. Said mast box has transverse internal stiffening ribs of the box. Said mast box extends forward beyond said inner and outer wing boxes. Also, it may extend beyond the leading edge 15 of the wing member. Said mast box and the inner and outer wing boxes are each delimited by a rear closing rib, the rear closing rib of the mast box providing a surface continuity between the rear closing ribs of the inner and outer wing box. Alternatively, a break in surface continuity can be observed when the mast box extends rearward beyond the wing boxes. Said mast box has a cross section in overall quadrilateral shape, preferably square or rectangular, said cross section being dimensionally scalable along the mast box.
    [0011] Said primary structure also comprises an intermediate structure interposed between the mast box and said attachment means of the primary structure on the engine, said intermediate structure taking the form of a fitting, preferably in the general shape of a pyramid. Said mast casing carries, at its front end, a portion of said attachment means of the primary structure on the engine.
    [0012] A front portion of said attachment means of the primary structure on the engine is attached to an outer shell of an intermediate casing of the engine, said outer shell extending in the axial rear extension of a fan casing, or Although in an alternative embodiment, this front portion of the attachment means of the primary structure on the engine is reported on an inner ring of said intermediate casing of the engine. The invention also relates to a mounting method of an assembly according to any one of the preceding claims, characterized in that it comprises the following successive steps; A) attaching at least a portion of the mast box to the inner wing box; then b) fixing the outer wing box on said at least a portion of the mast box. Preferably, said mast box is delimited by upper rails 15 mounted on the assembly after step b) above. Finally, the invention also relates to an aircraft comprising at least one such assembly. In this regard, it is noted that when a wing element is equipped with two engines, it then has three wing boxes succeeding one another in the span direction, the two attachment masts associated with the two engines then being 20 each. housed between two directly consecutive wing boxes. Other advantages and features of the invention will become apparent in the detailed non-limiting description below. BRIEF DESCRIPTION OF THE DRAWINGS This description will be made with reference to the accompanying drawings; - Figure 1 shows a side view of an aircraft comprising an assembly according to the invention; FIG. 2 represents a refined perspective view of the assembly equipping the aircraft shown in the previous figure; Figure 3 is a schematic side view of the assembly shown in Figure 2; FIG. 4 represents a sectional view taken along the line IV - IV of FIG. 3; 5 - to 5e schematically a method of assembly of the assembly shown in the preceding figures; FIG. 6 represents a schematic side view similar to that of FIG. 3, with the assembly being in the form of a second preferred embodiment; and FIG. 7 is a sectional view taken along the line VII-VII of FIG. 6. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS Referring firstly to FIG. 1, there is shown an aircraft 100 comprising one or more sets 1 according to a preferred embodiment of the invention. Overall, this assembly 1 comprises a wing element 2 corresponding to a wing of the aircraft, a double-flow engine 10 such as a turbojet engine surrounded by a nacelle, and a latching pylon 4 of the engine 10. Referring in Figures 2 to 4, there is shown the assembly 1, according to a first preferred embodiment of the present invention.
    [0013] Overall, this assembly 1 comprises a wing element 2 corresponding to a wing of the aircraft, a double-flow engine 10 such as a turbojet engine, and a latching pylon 4 of the engine 10. Moreover, the assembly 1 comprises attachment means 7 of the turbojet engine 10 to a primary structure 6 of the mast 4. Throughout the following description, by convention, the direction X 25 corresponds to the longitudinal direction of the mast 4, which is also comparable to the longitudinal direction of the turbojet engine 10 and the assembly 1. This direction X is parallel to a longitudinal axis 5 of this turbojet engine 10. On the other hand, the direction Y corresponds to the direction transversely oriented relative to the mast 4 and also comparable to the transverse direction of the turbojet engine 10, while the direction Z 3032421 8 corresponds to the vertical direction or the height. These three directions X, Y and Z are orthogonal to each other and form a direct trihedron. On the other hand, the terms "front" and "rear" are to be considered in relation to a direction of advancement of the aircraft encountered following the thrust exerted by the turbojets 10, this advancement direction being represented schematically by the boom 19. The wing 2 comprises a wing structure 21 extending in a span direction 9 of the wing 2, which is substantially oriented parallel to the Y direction described above. This structure 21 is intended to form the structural part of the wing. It presents here a particular design, being segmented into two wing boxes, namely an inner wing box 21a and an outer wing box 21b. The inner box 21a is located on the inner side of the wing, that is to say it is arranged closer to the fuselage than the outer box 21b. According to the invention, the wing structure 21 is also equipped with a mast box 15 arranged between the two wing boxes 21a, 21b, as will be detailed below. The inner wing box 21a is bounded forward by a front spar 34a, and bounded to the rear by a rear spar 36a, also called closing rib. The two spars 34a, 36a, which extend substantially in the full thickness of the wing, are oriented in a conventional manner in the span direction 9. In addition, the box 21a is closed upwards by the extrados of the wing, using upper rails 35a, also called "internal wing box upper panel". Similarly, the box 21a is closed downwards by the lower section of the same wing, with the lower side members 37a also called "bottom panel internal wing box".
    [0014] The spars 34a, 36a are internally fixed to the spars 35a, 37a, which form the aerodynamic surfaces of the wing. In addition, the inner box 21a is delimited by an outer side panel 38a, also called "connecting rib", and extending over the entire cross section of the box 21a. Here as well as in the remainder of the description, in order to define certain constituent elements of each box, reference is made to "spars" since each element concerned can indeed be obtained by means of several assembled spars. to each other, in the continuity of each other. However, each component of the boxes can alternatively be obtained using a single spar made in one piece without departing from the scope of the invention.
    [0015] The outer wing box 21b has a design similar to that of the inner wing box 21a, while adopting smaller dimensions. Therefore, this box 21b will not be further described, except that it is delimited by an inner side panel 38b also called "connecting rib", this panel 38b being oriented towards the box 21a. In the figures, the elements of the box 21b similar to those of the box 21a respectively bear the same reference numerals, with the extension "b" replacing the extension "a". In Figures 2 to 4, only the primary structure 6 of the attachment pylon 4 has been shown, accompanied by the aforementioned attachment means 7. The other non-represented constituent elements of this mast 4, of the secondary structure type ensuring the segregation and maintenance of the systems while supporting aerodynamic fairings, are conventional elements similar to those encountered in the prior art. Therefore, no detailed description will be given. The primary structure 6, or rigid structure, allows the transmission to the wing structure 21 static and dynamic forces generated by the turbojet 10. It comprises as main element a mast box 6a, extending over the entire length of the primary structure 6, in the direction X. The mast box 6a has a conventional design, namely that it is delimited upwards by upper longitudinal members 40, downwards by lower longitudinal members 42, laterally by an outer side panel 44 and an inner side panel 46, rearwards by a rear closure rib 48, and forwardly by a front closure rib 50. As an indication, it is noted that the upper longitudinal members 40 are also referred to as " upper mast box panel ", and the lower rails 42 are also referred to as" bottom mast box panel ". In addition, the side panels 44, 46 are also referred to as "connecting ribs".
    [0016] In addition, the mast box 6a is equipped with transverse transverse stiffening ribs 52, preferably recessed and parallel to the ribs 48, 50 for closing the box, therefore preferably arranged in YZ planes and uniformly distributed in the X direction. This box 6a has a cross section YZ generally square or rectangle shape, dimensionally scalable along the direction X. This cross section may remain substantially constant for the rear portion located at the wing structure 21, but then narrows forwards to its forward end with a front engine attachment 7b. This front engine attachment 7a is attached to an outer shell 13b of an intermediate casing 13a of the turbojet engine 10. This shell 13b extends in the rear axial extension of a fan casing 17, substantially with the same diameter. Alternatively, the front engine attachment 7a could be attached to an inner shell 13c of the intermediate casing 13a, without departing from the scope of the invention. In addition, the attachment means 7 comprise a rear engine attachment 7b carried by an intermediate structure 6b of the primary structure 6. This intermediate structure 6b is a generally pyramid shaped fitting, projecting downwards from the longitudinal members lower 42 of the mast box 6a. The intermediate structure 6b is arranged in front of the leading edge 30 of the wing, and narrows in section downwards. At its low end, it carries the rear engine attachment 7b, which is also attached to a turbine casing 25 of the turbojet engine. In addition, the attachment means 7 comprise rods for taking up the thrust forces 7c. These rods, one of which has been schematized in FIG. 3, are two in number and are connected to the front independently and symmetrically on either side of the X axis, to the inner ring 13c of the casing. intermediate 13a. At the rear, the rods 7c are concurrent and connected to the bracket 6b of the rear engine attachment 7b, generally via a hinged boom on the bracket 6b. This arrangement constitutes what is commonly called the push path. The attachment means 7 are here only constituted by elements 7a, 7b and 7c above, forming together an isostatic system of recovery 30 efforts. Thanks to this isostatic recovery of the forces, arranged on two separate planes 3032421 11 offset from one another in the X direction, the operations of installation / removal of the engine are facilitated and the deformations of the engine are decreased, which reinforces the overall engine performance. As indicated above, one of the peculiarities of the invention lies in the fact that the rear part of the mast box 6a is integrated with the wing structure 21. It is interposed between the two wing boxes 21a, 21b in the span direction 9, while the front portion of this mast box 6a protrudes forward beyond the leading edge 30 of the wing. In other words, the rear part of the mast box 6a is arranged between the two wing boxes 21a, 21b and fixed on each of them 10 in a manner which will now be detailed with reference to FIG. 4 The fixing of the three boxes 6a, 21a, 21b is effected by means of their side panels 44, 46, 38a, 38b, clad in pairs. Firstly, a first mechanical connection 54 is provided between the side panels 38a, 46. It is made using bolts and / or shear pins having axes 56 substantially parallel to the span direction 9 The bolts / shear pins are for example distributed along a first line and a second line of direction X, the first being located near an upper end of the panels 38a, 46, while the second line is arranged near a low end of these same panels. Because of the line distribution of bolts / pions that compose them, these mechanical links are usually called "piano link". To strengthen the connection 54, a longitudinal angle 60 may be associated with each line, being traversed by pins / bolts and located inside the box 21a.
    [0017] Similarly, a second mechanical connection 64 is provided between the side panels 38b, 44. It is made using bolts and / or shear pins having axes 66 substantially parallel to the span direction 9. The bolts / shear pins are distributed along a first line and a second X-direction line, the first being located near an upper end of the panels 38b, 44, while the second line is arranged near a low end of these same panels. To strengthen the connection 64, a longitudinal angle 60 may be associated with each of the two lines, being traversed by pins / bolts and located inside the box 21b. In this first preferred embodiment, the rear portion of the mast caisson 6a reconstitutes the wing structure 21 between the two caissons 21a, 21b, so as to obtain a surface continuity between the upper longitudinal members 35a, 35b, via the longitudinal members. upper 40 of the mast box 6a. A surface continuity is also obtained between the lower longitudinal members 37a, 37b, through the lower longitudinal members 42 of the mast box 6a. Finally, a surface continuity is also ensured between the rear closing ribs 36a, 36b of the wing boxes, by the rear closing rib 48 of the mast box 6a. In other words, the mast box 6a fills the space between the two wing boxes 21a, 21b, so as to obtain a wing structure 21 whose outer geometry is identical or similar to that of a single wing box, as found in the prior art.
    [0018] In a second preferred embodiment shown diagrammatically in FIGS. 6 and 7, only the continuity of the surfaces 36a, 48, 36b behind the boxes 6a, 21a, 21b is retained. On the other hand, the mast casing 6a has a larger cross-sectional area than that of the wing caissons 21a, 21b, implying a break in the surface continuity at the upper longitudinal members 35a, 35b, 40, as well as a rupture. of surface continuity at the lower longitudinal members 37a, 37b, 42. In this regard, it is noted that the portions of the box 6a projecting upwardly and downwardly from the wing structure 21, are preferably equipped with aerodynamic fairings (not shown) forming part of the secondary structures of the mast 4.
    [0019] Referring now to FIGS. 5a to 5e, various successive steps of a method according to the invention are shown, allowing assembly of the assembly 1 described above. Overall, the boxes 21a, 6a and 21b are successively mounted so as to progressively reconstruct the wing structure 21, starting from the inside thereof.
    [0020] First, as shown in Figures 5a and 5b, the mast box 6a is made by assembling the side panels 44, 46, the inner ribs (not shown), and the lower longitudinal members 42. In contrast, upper rails 40 are not yet assembled at this stage, to allow easy access to the interior of the box 5 6a, so as to facilitate the attachment of the latter on the inner wing box 21a as shown schematically in Figure 5c, and to allow the fixing of the outer box 21b on the mast box 6a, as shown schematically in Figure 5d. These two fasteners, made from the inside of the mast box 6a left open, are obtained via the aforementioned first and second links, using bolts and / or shear pins. Finally, the upper longitudinal members 40 are fixed on the transverse inner ribs of the box 6a, to ensure the closure of the latter, as shown schematically in Figure 6e. Of course, various modifications may be made by those skilled in the art to the aircraft assemblies 1 which have just been described, solely by way of non-limiting examples. 20
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Aircraft assembly (1) comprising a wing element (2), a motor (10) with a double flow and an engine attachment pylon (4), said engine comprising a rear part arranged under the wing element (2) which is equipped with a wing structure (21), the mast comprising a primary structure (6) for transmitting the forces of the engine to the wing structure (21), said primary structure comprising a mast box (6a ), and the assembly further comprising hooking means (7) of the primary structure (6) on the engine, characterized in that the wing structure (21) comprises two wing boxes (21a, 21b). successor in a span direction (9) of the wing element (2), and in that the mast box (6a) is arranged between said wing boxes (21a, 21b) and fixed on each of them .
    [0002]
    2. An assembly according to claim 1, characterized in that the two wing boxes (21a, 21b) form an inner box and an outer box, said inner box (21a) being delimited by an outer side panel (38a) and said box outside (21b) being bounded by an inner side panel (38b), said mast box (6a) being delimited by an outer side panel (44) and an inner side panel (46), and in that it comprises a first mechanical link (54) between the outer side panel (38a) of the inner wing box (21a) and the inner side panel (46) of the mast box (6a), and a second mechanical link (64) between the inner side panel (38b) of the outer wing box (21b) and the outer side panel (44) of the mast box (6a).
    [0003]
    3. The assembly of claim 2, characterized in that the outer side panel (38a) of the inner wing box (21a) is pressed against the inner side panel (46) of the mast box (6a), and in that the inner side panel (38b) of the outer wing box (21b) is pressed against the outer side panel (44) of the mast box (6a). 3032421 15
    [0004]
    4. An assembly according to claim 2 or claim 3, characterized in that the first and second mechanical connections (54, 64) are each made by means of bolts and / or shear pins, said bolts and / or pegs. shear preferably having axes (56, 66) substantially parallel to the span direction (9).
    [0005]
    5. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) and the inner and outer wing boxes (21a, 21b) are each delimited by lower rails (37a, 37b) and upper (35a, 35b) lower legs (42) of the mast box (6a) providing surface continuity between the lower longitudinal members (37a, 37b) of the inner and outer wing boxes (21a, 21b), and the longitudinal members upper members (40) of the mast box (6a) ensuring a surface continuity between the upper longitudinal members (35a, 35b) of the inner and outer wing boxes (21a, 21b).
    [0006]
    6. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) has transverse transverse ribs for stiffening the box (52). 20
    [0007]
    7. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) extends forwardly beyond said inner and outer wing box (21a, 21b). 25
    [0008]
    8. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) and the inner and outer wing box (21a, 21b) are each delimited by a rear closing rib (36a, 36b) the rear closing rib (48) of the mast box (6a) providing a surface continuity between the rear closing ribs (36a, 36b) of the inner and outer wing boxes (21a, 21b). 3032421 16
    [0009]
    9. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) has a cross section in overall quadrilateral shape, preferably square or rectangular, said cross section being scalable along the box of mast. 5
    [0010]
    10. An assembly according to any one of the preceding claims, characterized in that said primary structure (6) also comprises an intermediate structure (6b) interposed between the mast box (6a) and said hooking means (7) of the primary structure (6) on the engine, said intermediate structure (6b) taking the form of a fitting, preferably in the general shape of a pyramid.
    [0011]
    11. An assembly according to any one of the preceding claims, characterized in that said mast box (6a) carries, at its front end, a portion of said attachment means (7) of the primary structure (6) on the engine . 15
    [0012]
    12. An assembly according to any one of the preceding claims, characterized in that a front portion of said attachment means (7) of the primary structure (6) on the engine is attached to an outer shell (13b) of a intermediate casing (13a) of the engine, this outer shell (13b) extending in the axial rearward extension of a fan casing (17), or in that this front part of the attachment means (7) of the primary structure (6) on the engine is reported on an inner shell (13c) of said intermediate casing (13a) of the engine.
    [0013]
    13. A method of mounting an assembly (1) according to any one of the preceding claims, characterized in that it comprises the following successive steps; a) fixing at least a portion of the mast box (6a) on the inner wing box (21a); then b) attaching the outer wing box (21b) to said at least a portion of the mast box (6a). 3032421 17
    [0014]
    14. Mounting method according to claim 13, characterized in that said mast box (6a) is delimited by upper longitudinal members (40) mounted on the assembly after step b). 5
    [0015]
    15. Aircraft (100) comprising at least one assembly (1) according to any one of claims 1 to 12. 10
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    同族专利:
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    FR3032421B1|2017-03-10|
    US9889942B2|2018-02-13|
    US20160229545A1|2016-08-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP1910167A1|2005-07-29|2008-04-16|AIRBUS France|Assembly for aircraft comprising a wing system element as well as an attachment mast|
    FR2931133A1|2008-05-14|2009-11-20|Airbus France Sas|MOTOR ATTACHING MACHINE COMPRISING MEANS FOR FIXING LONGERONS AND AGENCY PANELS OUTSIDE OF THE INTERIOR SPACE OF HOUSING|
    FR2993535A1|2012-07-20|2014-01-24|Airbus Operations Sas|Propelling assembly i.e. double flow turbojet assembly, for commercial plane, has force recovery units, where one recovery unit is arranged behind another recovery unit according to longitudinal direction and is integrated into side beams|FR3061149A1|2016-12-27|2018-06-29|Airbus Operations|PRIMARY STRUCTURE OF A MAT FOR AN AIRCRAFT PROPELLER COMPRISING A PYRAMIDAL PART WITH CONVERGENT AMOUNTS|DE19909658A1|1999-03-05|2000-09-07|Bosch Gmbh Robert|Method and device for operating an internal combustion engine with gasoline direct injection|
    US6758439B2|2002-10-22|2004-07-06|The Boeing Company|Apparatuses and methods for attaching engine nacelles to aircraft|
    US7083143B2|2003-10-17|2006-08-01|The Boeing Company|Apparatuses and methods for attaching engines and other structures to aircraft wings|
    GB0919832D0|2009-11-13|2009-12-30|Airbus Operations Ltd|Thermal test apparatus and method|
    US9475579B2|2013-08-13|2016-10-25|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Vertical take-off and landing vehicle with increased cruise efficiency|FR3042010B1|2015-10-05|2018-07-13|Safran Aircraft Engines|AIRCRAFT WITH A MULTI-BLOWING PROPULSIVE ASSEMBLY FIXED UNDER AILE|
    US10604265B2|2016-11-15|2020-03-31|The Boeing Company|Integrated strut support fittings with underwing longerons|
    US10899463B2|2017-05-16|2021-01-26|Rohr, Inc.|Segmented pylon for an aircraft propulsion system|
    CN109455304A|2018-11-30|2019-03-12|中国商用飞机有限责任公司北京民用飞机技术研究中心|A kind of aircraft static indeterminacy hanging structure|
    CN113237661B|2021-05-10|2022-02-25|中国商用飞机有限责任公司|Device and method for measuring dynamic test load of wing-mounted engine|
    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-12| PLSC| Publication of the preliminary search report|Effective date: 20160812 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-23| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550955A|FR3032421B1|2015-02-06|2015-02-06|AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF HITCHING MAT INTEGRATED WITH THE STRUCTURE OF THE VESSEL ELEMENT|FR1550955A| FR3032421B1|2015-02-06|2015-02-06|AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF HITCHING MAT INTEGRATED WITH THE STRUCTURE OF THE VESSEL ELEMENT|
    US15/015,841| US9889942B2|2015-02-06|2016-02-04|Aircraft assembly comprising a mounting pylon primary structure integrated to the structure of the wing element|
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