• 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 the case of a rear part of an aircraft equipped with a structure for supporting engines passing through the fuselage, the assembly of the rear part poses problems due to the displacement of the box of the support structure through lateral openings of the fuselage. To remedy these problems, there is provided a method of assembling an aircraft rear portion (10) in which the box (32) of the engine support structure (24) is inserted into the fuselage (12). through an upper opening (72) extending from one side to the other of the fuselage passing through a vertical median plane (P) of the fuselage so that the upper opening opens upwards and towards the sides of the fuselage, fuselage.
    公开号:FR3020347A1
    申请号:FR1453807
    申请日:2014-04-28
    公开日:2015-10-30
    发明作者:Julien Guillemaut；Esteban Martino-Gonzalez；Cortes Diego Folch；Jerome Colmagro；Jonathan Blanc
    申请人:Airbus Operations SL；Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to the assembly of an aircraft rear part equipped with engines mounted on its fuselage. STATE OF THE PRIOR ART In order to produce such a rear part of an aircraft, it has been proposed in the prior art to interpose an attachment pylon between the fuselage and each engine, as described, for example, by the international application WO 2011/086221. In this configuration, the mast is directly attached to the fuselage. To ensure satisfactorily the transfer of the motor forces towards the fuselage, important structural reinforcements are necessary for both the mast, the part of the fuselage supporting it, as well as for the fastening means interposed between these elements. This results in a significant mass penalty. Another solution consists in providing a support structure for the engines passing through the fuselage, as well as the interior space of the aircraft defined by this fuselage, as for example in the international application WO 2010/031959. This solution makes it possible to reduce the intensity of the forces introduced into the fuselage at each of the two openings of the latter through which the support structure passes, in particular the forces oriented along the main direction of the support structure. to say in a plane orthogonal to a longitudinal direction of the aircraft. However, the assembly of the engine support structure to the fuselage requires that the two half-structures forming said support structure are moved towards each other through the fuselage openings.
    [0002] Such an operation presents risks of damage to the fuselage and the engine support structure, and is difficult to execute and time consuming. DISCLOSURE OF THE INVENTION The invention aims in particular to provide a simple, economical and effective solution to this problem. To this end, it proposes a method of assembling an aircraft rear part, comprising the following steps: on the one hand, assembling an outer skin of fuselage and circumferential frames so as to form a fuselage of said rear part aircraft having an upper opening extending from one side to the other of said fuselage through a vertical median plane of the fuselage so that said upper opening opens upwards and towards the sides of the fuselage, and secondly assembling a support structure comprising a box and having opposite ends provided with attachment means for attaching aircraft engines to said support structure, then - inserting the box of said support structure into said upper opening of the fuselage, then fix the box of said support structure to said fuselage.
    [0003] The "top" and "sides" are naturally defined by reference to an orientation taken by the aft portion of an aircraft when it equips an aircraft parked on a horizontal surface. This orientation is preferably also the orientation taken by the fuselage of the rear part of the aircraft during the assembly process of the latter.
    [0004] The insertion of the support structure box into a fuselage opening that opens upwards and towards the sides of the fuselage makes it easier to mount the support structure on the fuselage and to reduce the risk of damage. of these elements encountered in the use of assembly methods of the prior art, which consist in inserting and moving the box through lateral openings of the fuselage. The method according to the invention also offers the possibility of assembling aerodynamic fairings on side portions of the box before mounting the support structure on the fuselage. Similarly, the method according to the invention also makes it possible to mount aircraft engines on the support structure before the mounting of this support structure on the fuselage. Preferably, said fuselage comprises two circumferential frames, respectively front and rear, which extend forwardly and rearward of said upper opening of the fuselage. Preferably, the method comprises a subsequent step of connecting said front and rear circumferential frames by means of at least one upper cross member extending above said middle portion of said box of the support structure. Preferably, one of said at least one upper cross member, hereinafter referred to as upper central cross member, is centered in the vertical median plane of the rear part of the aircraft, the method comprising fixing said upper central cross member to the said support structure.
    [0005] Preferably, said front and rear circumferential frames are connected to each other by means of two lateral cross members respectively extending on each side of the fuselage, below said upper opening of the fuselage. Preferably, the method comprises, before the insertion of the box of said support structure into said upper opening of the fuselage, a step of assembling a fairing greater than said middle portion of said box of said support structure, so that said upper fairing aerodynamically closes a medial portion of said upper fuselage opening after attachment of said middle portion of said housing to said fuselage. Preferably, said upper fairing is previously secured to an upper fin, said upper fin being positioned so that, when the upper fairing is assembled to the fuselage, said upper fin extends above the upper fairing and in the extension to the upper fairing. before a tail of said rear part of aircraft. Alternatively, the method comprises, after fixing said middle portion of said box to said fuselage, a subsequent step of mounting an upper fairing on said fuselage, over said middle portion of said box of said support structure, so that said upper fairing aerodynamically closes a medial portion of said upper fuselage opening. Preferably, the method comprises a subsequent step of mounting an upper fin on said upper fairing, in the forward extension of a tail of said aircraft aft portion. Preferably, said upper fairing integrates longitudinal stiffeners so that, in normal operation, said upper fairing contributes to the transfer of forces between a part of the fuselage located behind said upper opening of the fuselage and a part of the fuselage situated in front of said upper opening of the fuselage. According to another variant, said median portion of said box of said support structure comprises an aerodynamic upper skin defining said box and shaped so as to extend in the extension of the outer skin of said fuselage, after insertion of said middle portion of said box in said upper opening of the fuselage. In general, the method preferably comprises a displacement of said support structure in a vertical direction resulting in said insertion of the box of the support structure into said upper opening of the fuselage. Furthermore, the method preferably comprises a step of fixing aircraft engines to said support structure, this step taking place before the insertion of the box of said support structure into said upper opening of the fuselage.
    [0006] BRIEF DESCRIPTION OF THE DRAWINGS The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of non-limiting example and with reference to the appended drawings in which: Figure 1 illustrates two steps of a method of assembling an aircraft rear portion according to a first preferred embodiment of the invention; - Figure 2 illustrates the rear part of the aircraft at the end of a subsequent step of the method according to the first preferred embodiment of the invention; FIG. 3 illustrates the rear part of the aircraft at the end of an alternative embodiment of the step of FIG. 2; FIG. 4 illustrates a subsequent step of the method according to the first preferred embodiment of the invention; FIG. 5 illustrates the rear part of the aircraft at the end of the process step illustrated in FIG. 4; FIG. 6 is a schematic perspective view of an engine support structure intended to be used for the implementation of a method of assembling an aircraft rear part according to a second preferred embodiment of FIG. the invention; FIG. 7 is a partial schematic perspective view of an aircraft rear part obtained by means of the method according to the second preferred embodiment of the invention. In all of these figures, identical references may designate identical or similar elements. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS FIG. 1 illustrates a first step of a method of assembling an aircraft rear part according to a first preferred embodiment of the invention, from a fuselage 12 intended to to define an interior space of the aircraft, a rear stabilizer 16 provided with a rudder 18 and a elevator 20, two motors (not shown) which are for example turbofan engines with contra-rotating propellers, type commonly referred to as "open rotor", and a support structure 24 for supporting the motors. The engines can of course be turboprops, or even jet engines with streamlined blower, without departing from the scope of the invention. In the following description, X is called the longitudinal direction of the aircraft, Z is the vertical direction, and Y is the transverse direction, orthogonal to the two preceding directions. These directions are defined by reference to an orientation taken by the rear part of the aircraft when it equips an aircraft parked on a horizontal surface, which also preferably corresponds to an orientation of the fuselage 12 of the rear part of the aircraft 10 during of the assembly process of the latter.
    [0007] The support structure 24 comprises a front spar 26 and a rear spar 28 interconnected by a plurality of ribs extending substantially orthogonal to the spars so as to form a box 32. The box 32 has opposite lateral ends 34 which are provided with attachment means (not shown) for fastening the motors. The box 32 is stiffened and closed by means of an upper skin 37a and a lower skin 37b respectively fixed on the upper edge and on the lower edge of the longitudinal members 26, 28 and ribs of the box 32. In general , the longitudinal members 26, 28 of the box 32 are preferably each made in one piece, or may alternatively each be formed of several beams assembled end-to-end, for example by bolting or by bolting. Similarly, the top 37a and lower 37b skins may each be made in one piece or in several parts assembled to each other. The casing 32 is divided into a median portion 38 intended to be housed inside the fuselage 12, and in two lateral parts 40 intended to extend outside the fuselage 12 and ending respectively in the lateral ends 34. The fuselage 12 generally comprises an outer skin 50, possibly reinforced by means of internal longitudinal stiffeners (the latter not being visible in FIG. 1), and circumferential frames supporting the outer skin 50. FIG. to see five of these circumferential frames, in particular a front circumferential frame 66 and a rear circumferential frame 68, as well as an intermediate circumferential frame 70. The circumferential front frames 66 and 68 rear define front and rear ends of an opening upper 72 of the fuselage 12 for housing the housing 32 of the support structure 24, while the circumferential frame the intermediate ring 70 extends between the circumferential front frames 66 and rear 68, and is truncated, that is to say without an upper portion, so that the circumferential intermediate frame 70 extends completely below the upper opening 72. The front and rear circumferential frames 66 and 66 are connected to each other by two lateral fuselage cross-members 74 extending respectively on each side of the fuselage 12, below the upper opening 72 of the fuselage. The lateral crosspieces extend symmetrically with respect to a vertical median plane P of the rear part of aircraft 10. These lateral crosspieces each extend at least to the circumferential frame 77a consecutive to the circumferential frame before 66 towards the front , and up to the circumferential frame 77b consecutive to the rear circumferential frame 68 towards the rear. The circumferential intermediate frame 70 is truncated by the two lateral fuselage cross members 74, and thus has two opposite circumferential ends respectively connected to the two lateral fuselage cross members 74.
    [0008] Each of the front and rear circumferential frames 68 and 68 further comprises a reinforcing cross member 79 extending in the transverse direction Y, substantially at the same vertical elevation as the lateral cross members 74. The fuselage 12 has two front fasteners 80, two rear fasteners 82, two intermediate fasteners 84, and four recovery rods 86, intended for fixing the support structure 24 to the fuselage 12. The set of these fasteners and connecting rods is arranged symmetrically on either side of the plane vertical median P. The front fasteners 80, rear 82, and intermediate 84 take for example the form of articulated clevises along respective axes substantially parallel to the transverse direction Y so as to allow the transmission of forces along the longitudinal directions X and vertical Z .
    [0009] The front clips 80 are configured to connect the front spar 26 of the box 32 to the front circumferential frame 66, while the rear brackets 82 are configured to connect the rear spar 28 of the box 32 to the rear circumferential frame 68. In the illustrated example, the front 80 and rear 82 fasteners are configured to extend respectively forward and back of the casing 32. Furthermore, the recovery rods 86 are divided into two connecting rods and two rear connecting rods (a connecting rod of each type being visible in Figure 2, as will become clearer in what follows). Each front link has an end intended to be connected to a clevis secured to the front spar 26 and an opposite end intended to be connected to a clevis integral with the circumferential front frame 66. Similarly, each rear link has an end intended to be connected. to a clevis secured to the rear spar 28 and an opposite end intended to be connected to a yoke secured to the rear circumferential frame 68. These load-bearing rods 86 extend substantially in the transverse direction Y so as to mainly transmit the forces oriented in this transverse direction Y. The method of assembling the rear fuselage portion 10 comprises firstly the assembly of the elements making up the fuselage 12, in particular the circumferential frames 66, 68, 70, 77a, 77b, the outer skin 50, the lateral cross-members 74, and the fasteners 80, 82, 84 and load-carrying connecting rods 86, so as to obtain the fuselage as shown in part in Figure 1, with its upper opening 72 extending from one side to the other of the fuselage 12 through the vertical median plane P of the fuselage. The upper opening 72 thus opens upwards and towards the sides of the fuselage. Furthermore, the method comprises assembling the elements that make up the box 32 of the support structure 24 of the motors, in particular the longitudinal members 26 and 28, the ribs, the skins 37a and 37b, and possibly the means for fastening the engines, as well as the engines. The motors and the attachment means of these motors are not shown in FIG. 1 for reasons of clarity.
    [0010] The assembly of the support structure 24 of the motors can be operated before assembly of the fuselage 12, or after assembly of the fuselage, or parallel thereto. Then, the method comprises the insertion of the box 32 of the support structure 24 into the upper opening 72 of the fuselage, as symbolized by the arrow 90 in FIG. 1, then the attachment of the box 32 of the support structure 24 to the fuselage, for example by means of the fasteners 80, 82, 84 and the recovery rods 86 described above. In parallel with these operations of insertion and fixing of the box 32 of the support structure, or before or after these operations, the empennage 16 is also mounted on the fuselage 12 as illustrated by the arrow 92 of FIG. In the first embodiment of the invention, the method then comprises attaching one or more upper cross members 76 to the front and rear circumferential frames 66 and 66 so that each upper cross member connects these two circumferential frames, one to the other, as shown in Figure 2. In the example shown in Figure 2, only one upper cross member 76 is shown and the latter is centered relative to the vertical median plane P. This upper cross is called "central cross superior "in what follows. In addition, the upper central beam 76 extends in the axial extension of two upper longitudinal beams 76a and 76b of the fuselage 12, arranged respectively forward and backward of the upper central beam 76, and also extending in the median plane. P. In the example illustrated in FIG. 2, the upper central beam 76 extends away from the box 32 of the support structure 24.
    [0011] In general, each upper cross member 76 allows a portion of the forces, in particular the forces oriented along the longitudinal direction X, to travel from the portion of the fuselage 12 located behind the opening 72 towards the fuselage portion 12 located at the front of the opening 72.
    [0012] FIG. 3 illustrates an alternative embodiment of the method, in which the method further comprises attaching the upper central bar 76 to the box 32 of the support structure 24. For this purpose, the upper central bar 76 takes, for example the shape of a plate or a beam extending in the vertical median plane P, and having a front end connected to a yoke 132 secured to the front circumferential frame 66 so as to form a connection of pivot or patella type suitable for take up the longitudinal and vertical forces, a rear end connected to a yoke 134 secured to the rear circumferential frame 68 so as to also form a pivot type connection or ball joint adapted to take up the longitudinal and vertical forces, and a lower edge 136 integral a rib 30 of the housing 32. For this purpose, the lower edge 136 may be fixed to the rib of the box by bolting, or the central cross member The upper portion 76 may be made in one piece with the rib. Part of the longitudinal and vertical forces communicated by the support structure 24 to the fuselage 12 can thus pass directly through the upper central beam 76. In the example shown, the upper central beam 76 is secured to the box 32 of the support structure 24 before the assembly of the latter to the fuselage 12. Thus, the method of assembly of the support structure 24 to the fuselage 12 comprises the attachment of the upper central web 76 to the circumferential frames 66 and 68. Figure 4 illustrates a later step of the method according to the first embodiment of the invention, of mounting an upper fairing 102 on the fuselage 12, over the middle portion 38 of the support structure 24 so as to close a middle portion of the upper opening 72 of the fuselage and thus ensure the aerodynamic continuity of the outer skin 50 of the fuselage. The upper fairing 102 is for example fixed on the front circumferential frames 66 and rear 68 and on the upper cross member 76, for example by means of countersunk fasteners.
    [0013] In the example shown, the upper fairing 102 incorporates four longitudinal stiffeners 103 distributed symmetrically on each side of a median plane of the fairing. The assembly of the upper fairing 102 thus also comprises the fixing of the longitudinal stiffeners 103 on the circumferential front and rear frames 68 and 68, for example by means of countersunk fasteners. The circumferential frames have notches open radially outward to receive the longitudinal stiffeners 103. In addition to its aerodynamic function, the upper fairing 102 can thus fulfill a structural role, ie participate in the transfer of forces, including longitudinal, between a part of the fuselage situated behind the upper opening 72 of the fuselage, in particular the rear circumferential frame 68, and a part of the fuselage situated in front of the upper opening 72 of the fuselage, in particular the circumferential front frame 66. Moreover , the upper fairing 102 can participate in the protection of each of the engines in case of incident leading to the projection of a blade or a blade, or a fragment of such a part, torn from the opposite motor. Indeed, the upper fairing 102 is on potential trajectories connecting the respective rotors of the engines to each other. In addition, in the example shown, the upper fairing 102 is previously secured to an upper fin 104, also called "back flap", positioned to extend above the upper fuselage fairing 102 when the latter is mounted on the fuselage 12, as shown in Figure 5. The upper fin 104 thus extends in the forward extension of the empennage 16, and thus forms a lower portion of a leading edge of the empennage 16.
    [0014] Alternatively, the upper fin 104 may be assembled to the upper fairing 102 after the latter has been assembled to the fuselage 12. The upper fin 104 is designed to participate in the protection of each of the engines in case of incident giving rise to the projection of a blade or a blade, or a fragment of such a part, torn from the opposite motor.
    [0015] The method further comprises a step (not shown in the figures) of mounting aerodynamic fairings at the front and rear of the side portions 40 of the support structure 24, so that these aerodynamic fairings are connected to the fuselage 12 and form respective leading edges and trailing edges of the two side portions 40 of the support structure. These aerodynamic fairings can be previously assembled to the support structure 24 before the junction thereof with the fuselage 12. Alternatively, these aerodynamic fairings can be installed on the support structure 24 after the assembly of the latter to the fuselage 12 .
    [0016] On the other hand, in the case where an upper cross member 76 is preassembled to the box 32 of the support structure 24, as described above with reference to Figure 3, the upper fairing 102 may be previously attached to the upper rail 76 , before the insertion of the box 32 of the support structure into the upper opening 72 of the fuselage. The upper cross member 76 thus makes it possible to mechanically support the upper fairing 102 before assembling the upper fairing 102 to the fuselage. FIG. 6 illustrates an engine support structure 24 intended to be used for the implementation of a method of assembling an aircraft rear part according to a second preferred embodiment of the invention. This support structure 24 differs from the support structure of FIGS. 1 to 5 in that the medial portion 38 of the box 32 is covered with an aerodynamic upper skin 140 forming part of the upper skin 37a of the box 32 and conformably shaped. to extend in the extension of the outer skin 50 of the fuselage 12 when the box 32 of the support structure 24 is attached to the fuselage 12, as shown in Figure 7 which shows the rear part of aircraft 10 equipped with this In the example described, the box 32 of the support structure 24 is fixed on the opposite upper ends of three consecutive circumferential truncated frames respectively referred to as the front circumferential frame 142, the circumferential intermediate frame 144, and the rear circumferential frame. 146. The middle part 38 of the box 32 thus connects to each other the upper ends of each of the circumferential frames items 142, 144 and 146.5
    权利要求:
    Claims (13)
    [0001]
    REVENDICATIONS1. A method of assembling an aircraft rear portion (10), characterized in that it comprises the following steps: - on the one hand, to assemble a fuselage outer skin (50) and circumferential frames (66, 68 , 70, 77a, 77b, 142, 144, 146) to form a fuselage (12) of said aircraft rear portion having an upper opening (72) extending from one side to the other of said fuselage passing through a vertical median plane (P) of the fuselage so that said upper opening (72) opens up and to the sides of the fuselage, and secondly, assembling a box (32) of a support structure (24). ) provided with attachment means for attaching aircraft engines to said support structure, and then - inserting a medial portion (38) of said housing (32) of said support structure (24) into said upper opening (72); ) of the fuselage (12), then - fix said middle portion (38) of said housing (32) to said fuselage (12).
    [0002]
    2. The method of claim 1, wherein said fuselage (12) has two circumferential frames, respectively (66) and rear (68), which extend forwardly and rearward of said upper fuselage opening (72).
    [0003]
    The method of claim 2 including a subsequent step of connecting said front and rear circumferential frames by means of at least one upper cross member (76) extending above said middle portion (38) of said housing (32). ) of the support structure (24).
    [0004]
    4. The method of claim 3, wherein one of said at least one upper cross member (76), hereinafter called upper central cross member, is centered in the vertical median plane (P) of the rear part of the aircraft, the method comprising attaching said upper central bar (76) to the box (32) of said support structure.
    [0005]
    A method according to any one of claims 2 to 4, wherein said front (66) and rear (68) circumferential frames are connected to each other by means of two lateral cross members (74) respectively extending on each side of the fuselage (12), below said upper fuselage opening (72).
    [0006]
    6. A method according to any one of claims 1 to 5, comprising, before the insertion of the box (32) of said support structure (24) in said upper opening (72) of the fuselage, an assembly step of an upper fairing (102) at said middle portion (38) of said box (32) of said support structure, whereby said upper fairing (102) aerodynamically closes a middle portion of said upper fuselage opening (72) after fixing said middle portion (38) of said box (32) to said fuselage (12).
    [0007]
    7. The method of claim 6, wherein said upper fairing (102) is previously secured to an upper fin (104), said upper fin being positioned so that when the upper fairing (102) is assembled to the fuselage (12). said upper fin extends over the upper fairing (102) and in the forward extension of a tail (16) of said aircraft aft portion (10).
    [0008]
    The method of any one of claims 1 to 5 including, after attaching said middle portion (38) of said housing (32) to said fuselage (12), a subsequent step of mounting an upper fairing (102) on said fuselage (12), over said middle portion (38) of said box (32) of said support structure (24), so that said upper fairing (102) aerodynamically closes a medial portion of said upper opening ( 72) of the fuselage.
    [0009]
    The method of claim 8 including a subsequent step of mounting an upper fin (104) on said upper fairing (102) in the forward extension of a tail (16) of said aircraft aft portion. (10).
    [0010]
    10. The method of claim 8 or 9, wherein said upper fairing (102) incorporates longitudinal stiffeners (103) so that in normal operation, said upper fairing (102) participates in the transfer of forces between a portion of the fuselage. (12) located behind said upper fuselage opening (72) and a fuselage portion (12) located in front of said fuselage upper opening (72).
    [0011]
    The method according to any one of claims 1 to 5, wherein said middle portion (38) of said box (32) of said support structure (24) comprises an aerodynamic upper skin (140) delimiting said box (32) and shaped to extend in the extension of the outer skin (50) of said fuselage (12), after insertion of said middle portion (38) of said casing (32) into said upper fuselage opening.
    [0012]
    A method according to any one of the preceding claims, comprising moving said support structure (24) in a vertical direction (Z) resulting in said insertion of the box (32) of the support structure into said upper opening (72). ) of the fuselage.
    [0013]
    A method as claimed in any one of the preceding claims, including a step of attaching aircraft engines to said support structure (24), which step occurs prior to inserting the box (32) of said support structure in said upper opening (72) of the fuselage.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3020347A1|2015-10-30|METHOD FOR ASSEMBLING A REAR AIRCRAFT PART
    EP2038176B1|2010-09-15|Engine assembly for aircraft comprising an aerodynamic coupling fairing mounted on two separate elements
    EP2038175B1|2009-11-18|Engine assembly for an aircraft comprising a support cradle for a fan shroud mounted on two separate elements
    EP2500268B1|2013-10-16|Engine pylon for an aircraft
    WO2009147341A2|2009-12-10|Engine mounting pylon including means for attaching spars and panels arranged outside the inner space of the box
    EP2185413B1|2011-02-02|Cradle for holding a fan coil mounted on the attachment pylon and on the nacelle air intake
    FR3014840A1|2015-06-19|AIRCRAFT ASSEMBLY COMPRISING A MOTOR ATTACHING BODY EQUIPPED WITH AT LEAST ONE MANILITY SUPPORT BRACKET PENETRATING IN THE HOUSING OF THE ATTACHING MAT
    EP2426051B1|2014-03-19|Jet engine pylon comprising aligned front attachment points
    EP1896325B1|2012-09-12|Engine mounting structure for an aircraft
    EP2554478B1|2013-10-09|Articulated fairing for nacelle members supported by these nacelle members in a closed position
    FR2887851A1|2007-01-05|ENGINE ATTACHING MAT FOR AN AIRCRAFT
    FR2891244A1|2007-03-30|ENGINE ATTACHING MAT FOR AN AIRCRAFT
    FR2887853A1|2007-01-05|ENGINE ATTACHMENT FOR AN AIRCRAFT INTENDED TO BE INTERPOSED BETWEEN A MOTOR AND A COUPLING MAT
    FR3014841A1|2015-06-19|AIRCRAFT ASSEMBLY COMPRISING A PART ATTACHED ENGINE BODY MADE OF A SINGLE PIECE WITH AN INNER RIB OF A RIGIDIFICATION OF A HOUSING MAT SUBSTATION
    CA2623760A1|2007-03-29|Engine assembly for aircraft comprising an engine as well as a device for locking said engine
    FR3015433A1|2015-06-26|AIRCRAFT ASSEMBLY COMPRISING AN INTEGRATED PLATFORM LOADING MACHINE AND REAR PARTLY FUSELING AGENCY
    FR2891247A1|2007-03-30|Aircraft assembly, has engine mounting structure with rigid structure forming shell with rear closing element, and rigid structure mounted on wing element so that wing element is supported against front longeron
    FR3047973A1|2017-08-25|AIRCRAFT ENGINE ASSEMBLY, COMPRISING A MOTOR ATTACHING DEVICE EQUIPPED WITH STRUCTURAL MOBILE HOOKS CONNECTED TO THE CENTRAL CABIN
    FR2891526A1|2007-04-06|Aicraft jet engine mounting system pylon has one transverse rib of rigid mounting structure made with two lateral extensions fixed to curved housings
    FR3065442A1|2018-10-26|AIRCRAFT ENGINE ASSEMBLY COMPRISING A FRONT ENGINE ATTACHMENT INTEGRATED WITH THE BOX OF THE ATTACHING MAT
    WO2015067891A2|2015-05-14|Assembly for an aircraft including a fitting secured to the upper surface of a wing box, for mounting an engine strut to said wing box
    FR3032421A1|2016-08-12|AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF HITCHING MAT INTEGRATED WITH THE STRUCTURE OF THE VESSEL ELEMENT
    FR3076282A1|2019-07-05|AIRCRAFT ASSEMBLY COMPRISING A PRIMARY STRUCTURE OF A COUPLING MAT FIXED TO A SAILBOX BY ATTACHES WITH A REDUCED SIZE IN THE ATTACK EDGE AREA
    EP3437999B1|2019-10-09|Light primary structure for aircraft engine mounting strut
    FR2963608A1|2012-02-10|Mounting adapter for assembling rigid structure of connecting strut of jet engine of e.g. Airbus A380 type aircraft, on e.g. main wing element, has binding interface cooperating with another binding interface fixed to aircraft element
    同族专利:
    公开号 | 公开日
    CN105035329A|2015-11-11|
    CN105035329B|2019-09-20|
    US9656736B2|2017-05-23|
    FR3020347B1|2016-05-20|
    US20160311515A1|2016-10-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2010031959A1|2008-09-18|2010-03-25|Airbus Operations |Rear part of an aircraft comprising a structure for supporting engines, extending through the fuselage and connected thereto by at least one connecting rod|
    FR2939101A1|2008-12-01|2010-06-04|Airbus France|RIGID STRUCTURE OF AIRCRAFT MAT PLATED AGAINST A LATERAL FUSELAGE EXTENSION FOR ITS FASTENING|
    WO2011086221A2|2010-01-14|2011-07-21|Airbus Operations S.L.|Support pylon for aircraft engines|EP3181454A1|2015-12-15|2017-06-21|Airbus Operations, S.L.|Aircraft pylon assembly|US4821980A|1987-09-29|1989-04-18|The Boeing Company|Vibration isolating engine mount|
    FR2762585B1|1997-04-24|1999-06-04|Snecma|MOTORIZATION SYSTEM OF A PROPELLER TRANSPORT AIRCRAFT|
    DE19834703C1|1998-07-31|1999-12-30|Daimler Chrysler Aerospace|Method of production of aircraft fuselage|
    DE19929471C1|1999-06-26|2001-01-18|Eads Airbus Gmbh|Method and device for producing a three-dimensional large component|
    DE502004002030D1|2003-07-18|2006-12-28|Telair Int Gmbh|FREIGHT DECK AND METHOD OF ASSEMBLY|
    FR2876658B1|2004-10-15|2007-01-19|Airbus France Sas|VERTICAL EMPTYING FOR AIRCRAFT AND AIRCRAFT PROVIDED WITH SUCH A TENSION|
    US20060185143A1|2004-11-22|2006-08-24|Airbus Deutschland Gmbh|Method and device for manufacturing sections for transportation systems|
    FR2891242B1|2005-09-23|2007-10-26|Airbus France Sas|TURBOREACTOR FOR AIRCRAFT, AIRCRAFT PROVIDED WITH SUCH A TURBOJET ENGINE, AND METHOD FOR FITTING SUCH A TURBO AIRBORNE ON AN AIRCRAFT|
    DE102007019692B4|2007-04-26|2011-06-01|Airbus Operations Gmbh|Wing-hull section of an airplane|
    DE102007028918A1|2007-06-22|2009-01-02|Airbus Deutschland Gmbh|Method for producing a fuselage cell of an aircraft and device|
    US20090212156A1|2007-09-06|2009-08-27|Honeywell International, Inc.|Aircraft engine system with gearbox unit|
    ES2342866B1|2007-11-30|2011-05-18|Airbus España, S.L.|IMPACT RESISTANT AIRCRAFT FUSELAGE.|
    US8766138B2|2008-05-13|2014-07-01|Airbus Operations Gmbh|Method for producing large-sized shell segments as well as shell segment|
    FR2931799B1|2008-05-30|2010-12-24|Airbus France|AIRPLANE WITH REAR REACTORS.|
    DE102008038806A1|2008-08-13|2010-02-25|Airbus Deutschland Gmbh|Pre-assembly and integration of aircraft cabins|
    FR2935351B1|2008-08-29|2010-09-17|Airbus France|FUSELAGE AIRCRAFT SUSPENDED UNDER THE WING.|
    FR2936496B1|2008-09-30|2010-09-24|Airbus France|METHOD FOR MANUFACTURING AN AIRCRAFT FUSELAGE TRUNK OF COMPOSITE MATERIAL|
    FR2943039B1|2009-03-12|2012-09-28|Airbus France|PLANE TANK-TAIL AND REVERSE ENGINE.|
    ES2376098B1|2009-07-24|2013-02-04|Airbus Operations S.L.|PROCESS OF ASSEMBLY OF FUSELAGE SECTIONS OF AN AIRCRAFT.|
    ES2398287B1|2010-03-29|2014-01-29|Airbus Operations S.L.|FUSELAGE OF AIRCRAFT RESISTANT TO IMPACT AND TOLERANT TO DAMAGE.|
    EP2655193B1|2010-12-23|2017-05-03|Airbus Operations GmbH|Aircraft system component carrier module and system, and mounting method|
    ES2560896T3|2011-12-28|2016-02-23|Airbus Operations S.L.|Rear of the fuselage with a shield for an aircraft with engines mounted on the fuselage and method for determining the area of the shield|
    CN202508161U|2012-03-31|2012-10-31|重庆至信实业有限公司|Automobile engine bin edge beam rear closing plate|DE102012005352A1|2012-03-16|2013-09-19|Airbus Operations Gmbh|Aircraft fuselage structure|
    US10040534B2|2015-12-07|2018-08-07|Bell Helicopter Textron Inc.|Fuselage to wing attachment|
    ES2841399T3|2016-12-16|2021-07-08|Airbus Operations Sl|Aircraft with a rear section with a continuous skin for the fuselage and vertical tail stabilizer|
    US10752333B2|2017-10-02|2020-08-25|Textron Innovations Inc.|Wing-fuselage integrated airframe beams for tiltrotor aircraft|
    EP3653490A1|2018-11-16|2020-05-20|Airbus Operations, S.L.U.|Frame assembly for a rear section of an aircraft and rear section of an aircraft comprising said frame assembly|
    CN111928092A|2020-07-17|2020-11-13|中国航空工业集团公司沈阳飞机设计研究所|Mounting bracket and have its mounting structure|
    法律状态:
    2015-04-21| PLFP| Fee payment|Year of fee payment: 2 |
    2015-10-30| PLSC| Publication of the preliminary search report|Effective date: 20151030 |
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-18| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453807A|FR3020347B1|2014-04-28|2014-04-28|METHOD FOR ASSEMBLING A REAR AIRCRAFT PART|FR1453807A| FR3020347B1|2014-04-28|2014-04-28|METHOD FOR ASSEMBLING A REAR AIRCRAFT PART|
    US14/695,731| US9656736B2|2014-04-28|2015-04-24|Method for assembling an aircraft aft portion|
    CN201510208189.8A| CN105035329B|2014-04-28|2015-04-28|Method for assembling aircraft aft|
    [返回顶部]