• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method of assembling an aircraft fuselage section characterized in that it comprises a step of positioning and fixing the elements (42) of a secondary structure (32) in a module self-supporting assembly (48) and a step of introducing and fixing the self-supporting assembly module (48) equipped with the elements (42) of the secondary structure (32) in a primary structure (30) of the fuselage section. The invention also relates to an aircraft fuselage section assembled from said assembly process.
    公开号:FR3051177A1
    申请号:FR1658716
    申请日:2016-09-19
    公开日:2017-11-17
    发明作者:Emmanuel Collot
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    METHOD FOR ASSEMBLING A FUSELAGE SECTION OF AN AIRCRAFT USING AN ASSEMBLY MODULE AND AN AIRCRAFT FUSELAGE ASSEMBLY ASSEMBLED THEREBY
    PROCESS
    The present application relates to a method of assembling a fuselage section of an aircraft using an assembly module and to an aircraft fuselage section assembled according to said method.
    In Figure 1, there is shown an aircraft 10 which comprises a fuselage 12 formed of several sections arranged end to end.
    For the rest of the description, the longitudinal axis of the aircraft corresponds to the axis that connects the front tip to the rear tip of the aircraft. A longitudinal direction is a direction parallel to the longitudinal axis. A radial direction is a direction perpendicular to the longitudinal axis. A longitudinal plane is a plane that passes through the longitudinal axis. A transverse plane is a plane perpendicular to the longitudinal axis.
    FIGS. 2A and 2B show a nose 14 of an aircraft corresponding to the most forward section of the aircraft.
    Like all the sections, the front tip 14 comprises a primary structure 16 which comprises transverse stiffeners called frames, longitudinal stiffeners called smooth and a skin which forms the outer casing of the aircraft. The nose 14 comprises a floor 18 connected to the primary structure 16 which divides the nose in two zones, an upper zone corresponding to a cockpit 20 and a lower zone corresponding to an avionics bay 22. The nose 14 also comprises a secondary structure 24 which comprises panels which partition and cover the inside of the primary structure 16 and various equipment, accessories, furniture 26.1 to 26.7 which are connected to the primary structure 16.
    For the remainder of the description, the element of the secondary structure is understood to mean all the elements forming the secondary structure which are positioned inside the primary structure 16 and connected thereto, such as panels, partitions, equipment , accessories, furniture, ...
    According to the prior art, a method of assembling a nose 14 of an aircraft comprises the following steps: a first step of assembling the primary structure 16 of the nose 14, a second step of setting up of the floor 18 in the primary structure 16, a third step of installing and fixing the different elements of the secondary structure 24 in the primary structure 16.
    The different elements of the secondary structure 24 are installed in the primary structure 16 independently of each other. Thus, each of them comprises a system for positioning and attachment to the primary structure 16 which is specific to it and which is distinct from that of the other elements of the secondary structure 24.
    According to this assembly method, the three assembly steps are necessarily performed one after the other. However, the third step of installing and fixing the different elements of the secondary structure 24 in the primary structure 16 is a relatively long step (the elements of the secondary structure being installed one by one) which tends to slow down the production rate. of an aircraft assembly line. This third step is even longer than the elements of the secondary structure 24 must be attached to the primary structure 16 with a relatively high positioning accuracy.
    The present invention aims to overcome the disadvantages of the prior art. To this end, the invention relates to a method of assembling an aircraft fuselage section, said section comprising a primary structure and elements of a secondary structure positioned in the primary structure. According to the invention, the assembly method is characterized in that it comprises a step of positioning and fixing the elements of the secondary structure in a self-supporting assembly module and a step of introducing and fixing the module. self-supporting assembly equipped with the elements of the secondary structure in the primary structure.
    According to the invention, the self-supporting assembly module is assembled and equipped with the different elements of the secondary structure concomitantly with the assembly of the primary structure. Thus, the assembly of the elements of the secondary structure is made in masked time which contributes to improving the rate of assembly of the aircraft. The invention also relates to an aircraft fuselage section comprising a primary structure and elements of a secondary structure positioned in the primary structure, characterized in that the fuselage section comprises a self-supporting assembly module to which are connected the elements of the secondary structure and at least one immobilization system configured to immobilize the self-supporting assembly module with respect to the primary structure.
    Advantageously, the self-supporting assembly module comprises a floor and a stiffened arch-shaped wall, said stiffened wall having external shapes that follow internal shapes of the primary structure.
    According to one embodiment, each immobilization system comprises on the one hand a rod connected by a pivotal connection to the self-supporting assembly module and which comprises a head at one end and a bit at a second end, and other part, a plate connected to the primary structure and which has an orifice comprising a section identical to the operating clearance near the section of the rod and the bit.
    Preferably, each immobilization system comprises a resilient element interposed between the head of the rod and the self-supporting assembly module so as to limit the appearance of stresses.
    According to one configuration, for each immobilization system, the self-supporting assembly module comprises a through hole oriented in a radial direction and which comprises a section identical to the operating clearance near the section of the rod and the bit.
    Advantageously, the aircraft fuselage section comprises a guidance system configured to guide the self-supporting assembly module in the primary structure in a longitudinal direction.
    According to one embodiment, the guiding system comprises on the one hand two rails oriented in the longitudinal direction, connected to the primary structure and arranged on either side of the self-supporting assembly module, and on the other hand, wheels connected to the self-supporting assembly module and configured to ride on the rails.
    In one configuration, each rail has in a transverse plane a U-shaped section that includes a base with an upper surface that forms a rolling surface for the wheels and two wings between which the wheels are guided.
    In the case of a forward nose of an aircraft, the wheels are connected to the self-supporting assembly module by a sliding swivel connection to enable them to follow the curved rails.
    According to one embodiment, the self-supporting assembly module comprises two grooves oriented in the longitudinal direction, arranged on either side of the self-supporting assembly module, configured to accommodate the wheels. Each groove has a C-shaped section with a bottom at which the wheels are located.
    Advantageously, the aircraft fuselage section comprises at least one stop to limit the movement of the self-supporting assembly module relative to the primary structure in the longitudinal direction. The invention also relates to an aircraft comprising at least one fuselage section according to the invention. Other features and advantages will become apparent from the following description of the invention, a description given by way of example only, with reference to the appended drawings in which:
    FIG. 1 is a side view of an aircraft,
    FIG. 2A is a diagrammatic representation of a primary structure of a front tip of an aircraft which illustrates an embodiment of the prior art,
    FIG. 2B is a schematic representation of the front tip visible in FIG. 2A equipped with different elements of a secondary structure,
    FIG. 3 is a schematic representation of an assembly module equipped, ready to be introduced into a primary structure of a front tip of an aircraft which illustrates an embodiment of the invention,
    FIG. 4 is a schematic representation of a primary structure which illustrates an embodiment of the invention,
    FIG. 5 is a schematic representation of an assembly module equipped with different elements of a secondary structure which illustrates an embodiment of the invention,
    FIG. 6A is a schematic representation of the assembly module visible in FIG. 5 when it is introduced into the primary structure visible in FIG. 4,
    FIG. 6B is a schematic representation of the equipped assembly module positioned in the primary structure,
    FIG. 7 is a diagrammatic representation in plan view of an assembly module positioned in a primary structure of a front tip of an aircraft which illustrates a first embodiment of the invention,
    FIG. 8 is a section along the line VIII - VIII of FIG. 7 of a guide system of the assembly module with respect to the primary structure which illustrates the first embodiment of the invention,
    FIG. 9 is a section along the line IX-IX of FIG. 7 of an immobilization system of the assembly module in the primary structure which illustrates the first embodiment of the invention,
    FIG. 10 is a perspective view of the immobilization system visible in FIG. 9,
    FIG. 11 is a perspective view of an assembly module equipped which illustrates a second embodiment,
    FIG. 12 is a diagrammatic representation in plan view of an assembly module positioned in a primary structure of a front tip of an aircraft which illustrates the second embodiment of the invention,
    Figure 13 is a section along the line XIII-XIII of Figure 12 of a guide system of the assembly module relative to the primary structure which illustrates the second embodiment of the invention.
    In the various Figures 3 to 5, 6A, 6B and 7, there is shown at 28 a forward tip of an aircraft.
    As illustrated in FIG. 6B, this front tip 28 comprises a primary structure 30, a secondary structure 32 and a floor 34.
    The primary structure 30 comprises transverse stiffeners called frames 36, longitudinal stiffeners called smooth 38 and a skin 40 which forms the outer envelope of the aircraft. The primary structure 30 is not more detailed because it may be identical to that of the prior art.
    The secondary structure 32 comprises various elements 42 such as panels, partitions, equipment, accessories, furniture, ... which are positioned in the primary structure 30. These various elements are not described because they are identical to those of the prior art.
    The floor 34 separates the nose 28 into two zones, a first upper zone 44 positioned above the floor 34 which corresponds to a cockpit in the case of the nose 38 and a second lower zone 46 positioned below the nose. floor 34 which corresponds to an avionics hold in the case of the front tip 38.
    According to a characteristic of the invention, the front tip 28 comprises a self-supporting assembly module 48, equipped with the elements 42 of the secondary structure 32 and configured to be introduced into the primary structure 30 and connected thereto.
    By self-supporting means that the assembly module comprises a sufficiently rigid structure to be manipulated when the assembly module 48 is equipped with the various elements 42 of the secondary structure 32.
    This self-supporting assembly module 48 comprises the floor 34 and a stiffened wall 52 in the form of an arch. The stiffened wall 52 has two edges 54 which are connected to the floor 34.
    The floor 34 is not more detailed because it can have the same structure as in the prior art.
    According to one embodiment, the stiffened wall 52 is made of composite material and includes reinforcements that give it its rigidity.
    The stiffened wall 52 has outer shapes that conform to the inner shapes of the primary structure 30.
    Preferably, the stiffened wall 52 comprises an inner surface 56 configured to provide the dressing function of the walls of the cockpit, in the manner of the secondary structure of the trim panels according to the prior art.
    The various elements 42 of the secondary structure 24 are connected to the self-supporting assembly module 48 by appropriate fastening systems which may be identical to those used to attach them to the primary structure according to the prior art.
    In the case of a front tip 28, the self-supporting assembly module 48 is equipped with different wiring, flight controls, a central console and different furniture, prior to its introduction into the primary structure 30.
    According to the invention, the primary structure 30 is assembled and the self-supporting assembly module 48 is assembled and equipped with the various elements 42 of the secondary structure 32 concomitantly. Thus, the assembly of the elements 42 of the secondary structure 32 is performed in masked time which contributes to improving the rate of assembly of the aircraft. All the elements 42 of the secondary structure 32 and the floor 34 are introduced and positioned during a single operation in the primary structure 30 which tends to reduce the assembly time.
    The precise positioning of the various elements 42 of the secondary structure 32 is achieved during the assembly of these elements 42 in the self-supporting assembly module 48. Unlike the prior art, this precise positioning has a small impact on the time of the assembly of the aircraft because it is performed in masked time.
    The nose 28 comprises a guide system 58 to facilitate the introduction of the self-supporting assembly module 48 into the primary structure 30. This guide system 58 is also configured to ensure proper positioning of the self-supporting assembly module 48 relative to to the primary structure 30.
    Preferably, the guiding system 58 comprises on the one hand two rails 60, 60 'oriented in the longitudinal direction, connected to the primary structure 30 and disposed on either side of the self-supporting assembly module 48, and on the other hand, wheels 62 connected to the self-supporting assembly module 48 and configured to roll on the rails 60, 60 '. In the case of the nose 28 of an aircraft, the two rails 60, 60 'are curved to follow the curved profile of the interior of the primary structure 30, as illustrated in FIG. 7.
    According to an embodiment visible in FIG. 7, each rail 60, 60 'is connected to the frames 36 of the primary structure 30.
    Each rail 60, 60 'comprises a rolling surface for the wheels 62, the rolling surfaces of the two rails 60, 60' being arranged in the same horizontal plane. According to an embodiment visible in FIG. 8, each rail 60, 60 'has in a transverse plane a U-shaped section which comprises a base 64 whose upper surface forms one of the rolling surfaces and two flanges 66 between which the wheels 62 are guided.
    According to an embodiment illustrated in FIG. 8, each wheel 62 comprises an axis of rotation A62 connected by a pivoting connection 68 to the stiffened surface 52 of the self-supporting assembly module 48. According to one configuration, the assembly module 48 comprises four wheels 62, two for each rail 60, 60 '. In the case of the nose 28 of an aircraft, the pivot link 68 is sliding type, as shown in Figures 7 and 8, to allow the wheels 62 to follow the curvature of the rails 60, 60 '.
    Preferably, the axes of rotation A62 are arranged in the same horizontal plane. Advantageously, the front tip 28 comprises at least one stop 70 to limit the movement of the self-supporting assembly module 48 relative to the primary structure 30 in the longitudinal direction. According to one embodiment, each stopper 70 is fixed to one of the rails 60, 60 'and is suitably positioned on the rail 60, 60' so that at least one of the wheels 62 of the self-supporting assembly module 48 is in contact with said stop 70 when the self-supporting assembly module 48 is positioned correctly in the longitudinal direction relative to the primary structure 30. According to one embodiment, each rail 60, 60 'comprises a stop 70.
    The guide system 58 and the stop (s) 70 are configured to obtain precise positioning of the self-supporting assembly module 48 with respect to the primary structure 30. All the elements 42 of the secondary structure 32 being accurately positioned relative to the self-supporting assembly module 48, they are in fact positioned precisely with respect to the primary structure 30 because of the precise positioning of the self-supporting assembly module 48 with respect to the primary structure 30.
    According to another characteristic, the front tip 28 comprises at least one immobilization system 72 of the self-supporting assembly module 48 with respect to the primary structure 30.
    Advantageously, each immobilization system 72 is a latch quarter turn.
    According to one embodiment, each immobilization system 72 comprises on the one hand a rod 74 connected to the self-supporting assembly module 48 by a pivoting connection 76 and which comprises a bit 78, and on the other hand, a connected plate 80 the primary structure 30 and which has an orifice 82 whose section is identical to the operating clearance near the section of the rod 74 and its bit 78.
    The plate 80 is a bracket with two wings, a first wing 80.1 disposed in a transverse plane and connected to a frame 36 of the primary structure 30 and a second wing 80.2 disposed in a plane perpendicular to the radial direction and which comprises the orifice 82.
    The rod 74 comprises at a first end a head 84 which includes shapes for pivoting the rod 74.
    The self-supporting assembly module 48 comprises a through hole 86 whose section is identical to the operating clearance near the section of the rod 74 and its bit 78. This hole is oriented in an approximately radial direction. Preferably, this through hole 86 comprises a countersink 88 for housing the head 84 of the rod 74.
    The bit 78 is positioned at a second end of the rod 74. In one configuration, the blade 78 has a rectangular section in a plane perpendicular to the axis of the rod 74. In this case, the orifices 82 and the through hole 86 have a circular section with a rectangular protrusion 90 to allow the rod 74 and its bit 78 to pass through.
    To immobilize the self-supporting assembly module 48, the rod 74 is inserted into the orifice 82 of the plate 80 connected to the primary structure 30. When the bit 78 has passed through the plate 80, the rod 74 is rotated by means of its head 84 so that the bit 78 does not cooperate with the protrusion 90 and abuts against the plate 80 as illustrated in FIG.
    The front tip 28 comprises a plurality of immobilization systems 72 distributed on the stiffened wall 52 and which are positioned relative to the frames 36 so as not to increase the complexity of the primary structure 30, the plates 80 being positioned at the frames 36.
    Advantageously, each immobilization system 72 comprises a resilient element 92 such as a compression spring for example, interposed between the head 84 of the rod 74 and the self-supporting assembly module 48 so as to limit the appearance of stresses.
    According to the invention, the assembly method is as follows:
    Simultaneously, the primary structure 30 is assembled on a first assembly station and the self-supporting assembly module 48 is assembled and equipped on a second assembly station.
    By following, the assembled self-supporting assembly module 48 is transported from the second assembly station to the first assembly station by any appropriate means, such as for example using a handling truck. The self-supporting assembly module 48 is positioned in the extension of the primary structure 30 as illustrated in FIG. 3, so that the wheels 62 of the module cooperate with the rails 60, 60 'of the primary structure 30. The module self-supporting assembly 48 is then introduced into the primary structure 30 as illustrated in Figure 6A until it abuts against at least one of the stops 70 as shown in Figures 6B and 7. Finally, the assembly module self-supporting 48, correctly positioned relative to the primary structure 30, is immobilized through the immobilization systems 72. In addition, the floor 34 is connected directly to the primary structure by any suitable means.
    Although described applied to the front tip of an aircraft, the assembly method can be used to assemble the other fuselage sections of the aircraft.
    In Figures 11 to 13, there is shown a second embodiment.
    As before, the self-supporting assembly module 48 is equipped with the various elements 42 of the secondary structure 32. It comprises a floor 34 and a stiffened wall 52 in the form of an arch. The guide system 58 comprises on the one hand two rails 60, 60 'oriented in the longitudinal direction, connected to the primary structure 30 and arranged on either side of the self-supporting assembly module 48, and on the other hand, wheels 62 connected to the self-supporting assembly module 48 and configured to roll on the rails 60, 60 '. The rails 60, 60 'and the wheels 62 are identical to those of the first embodiment illustrated by FIGS. 7 and 8.
    According to the second embodiment, the self-supporting assembly module 48 comprises two grooves 94, 94 'oriented in the longitudinal direction, arranged on either side of the self-supporting assembly module 48, configured to accommodate the wheels 62.
    The grooves 94, 94 'are formed in the stiffened wall 52.
    Each groove 94, 94 'has a C-section in a transverse plane and comprises a bottom 96, an upper wall 98 and a bottom wall 100. The grooves 94, 94' are approximately symmetrical with respect to a vertical longitudinal plane. The upper and lower walls 98, 100 are parallel and arranged in substantially horizontal planes. For each groove 94, 94 ', the distance between the upper and lower walls 98,100 is determined to accommodate the wheels 62 and the rail 60, 60'.
    The wheels 62 are located on the bottom 96 of the grooves 94, 94 '. Each groove 94, 94 'has a depth determined to accommodate the wheels 62.
    Because of the presence of the grooves 94, 94 ', the clearance J2 between the self-supporting assembly module 48 and the primary structure 30 is reduced and less than the clearance J1 of the first embodiment visible in FIGS. 7 and 8. , the second embodiment makes it possible to obtain a larger self-supporting assembly module 48 and therefore a larger useful volume.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    A method of assembling an aircraft fuselage section, said section comprising a primary structure (30) and elements (42) of a secondary structure (32) positioned in the primary structure (30), characterized in that the method comprises a step of positioning and fixing the elements (42) of the secondary structure (32) in a self-supporting assembly module (48) and a step of introducing and fixing the self-supporting assembly module ( 48) provided with the elements (42) of the secondary structure (32) in the primary structure (30).
    [2" id="c-fr-0002]
    Aircraft fuselage section comprising a primary structure (30) and elements (42) of a secondary structure (32) positioned in the primary structure (30), characterized in that the fuselage section comprises a module self-supporting assembly (48) to which are connected the elements (42) of the secondary structure (32) and at least one immobilization system (72) configured to immobilize the self-supporting assembly module (48) with respect to the primary structure (30).
    [3" id="c-fr-0003]
    Aircraft fuselage section according to claim 2, characterized in that the self-supporting assembly module comprises a floor (34) and a stiffened wall (52) in the form of an arch, said stiffened wall (52) having shapes exterior of the inner forms of the primary structure (30).
    [4" id="c-fr-0004]
    Aircraft fuselage section according to claim 2 or 3, characterized in that each immobilization system (72) comprises on the one hand a rod (74) connected by a pivot connection (76) to the assembly module self-supporting member (48) and having a head (84) at one end and a bit (78) at a second end, and a plate (80) connected to the primary structure (30) and having a orifice (82) comprising a section identical to the operating clearance near the section of the rod (74) and the bit (78).
    [5" id="c-fr-0005]
    5. Aircraft fuselage section according to the preceding claim, characterized in that each immobilization system (72) comprises an elastic element (92) interposed between the head (84) of the rod (74) and the module of self-supporting assembly (48) so as to limit the occurrence of constraints.
    [6" id="c-fr-0006]
    Aircraft fuselage section according to claim 4 or 5, characterized in that, for each immobilization system (72), the self-supporting assembly module (48) comprises a through hole (86) oriented in one direction. radial and which includes a section identical to the operating clearance near the section of the rod (74) and the bit (78).
    [7" id="c-fr-0007]
    7. Aircraft fuselage section according to one of claims 2 to 6, characterized in that it comprises a guide system (58) configured to guide in a longitudinal direction the self-supporting assembly module (48) in the primary structure (30).
    [8" id="c-fr-0008]
    Aircraft fuselage section according to the preceding claim, characterized in that the guide system (58) comprises firstly two rails (60, 60 ') oriented in the longitudinal direction, connected to the primary structure (30). ) and arranged on either side of the self-supporting assembly module (48), and on the other hand, wheels (62) connected to the self-supporting assembly module (48) and configured to roll on the rails (60, 60 ').
    [9" id="c-fr-0009]
    Aircraft fuselage section according to claim 8, characterized in that each rail (60, 60 ') has in a transverse plane a U-shaped section which comprises a base (64) with an upper surface which forms a surface of rolling for the wheels (62) and two wings (66) between which the wheels (62) are guided.
    [10" id="c-fr-0010]
    10. Aircraft fuselage section according to claim 8 or 9, characterized in that the wheels (62) are connected to the self-supporting assembly module (48) by a sliding swivel connection (68).
    [11" id="c-fr-0011]
    Aircraft fuselage section according to one of Claims 8 to 10, characterized in that the self-supporting assembly module (48) comprises two grooves (94, 94 ') oriented in the longitudinal direction, arranged on one side and other self-supporting assembly module (48), configured to accommodate the wheels (62).
    [12" id="c-fr-0012]
    Aircraft fuselage section according to claim 11, characterized in that each groove (94, 94 ') has a C-shaped section with a bottom (96) at which the wheels (62) are located.
    [13" id="c-fr-0013]
    13. Section fuselage aircraft according to one of claims 7 to 12, characterized in that it comprises at least one stop (70) to limit the movement of the self-supporting assembly module (48) relative to the structure primary (30) in the longitudinal direction.
    [14" id="c-fr-0014]
    14. Aircraft comprising at least one fuselage section according to one of claims 2 to 13.
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    同族专利:
    公开号 | 公开日
    FR3051176A1|2017-11-17|
    FR3051176B1|2019-05-03|
    FR3051177B1|2019-08-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2263365A|1938-06-01|1941-11-18|Firm Henschel Flugzeug Werke A|Cabin for aircraft|
    US3999630A|1976-03-26|1976-12-28|Mcphee Donald T|Transport and serving device|
    WO2010004172A2|2008-06-30|2010-01-14|AlRBUS OPERATIONS |Method for assembling a floor in a cockpit structure previously constructed from a section of aircraft fuselage|
    US20130009007A1|2011-07-05|2013-01-10|Marc Tomasi|Intermediate support structure for the cockpit of an aircraft|
    US20140175224A1|2012-12-21|2014-06-26|Airbus Operations |Aircraft nose with cockpit and avionics bay modules integrated therein|
    FR3082824A1|2018-06-20|2019-12-27|Airbus Operations|TRANSVERSE CHASSIS FOR AN AVIONIC HOLDER OF AN AIRCRAFT, ASSEMBLY MODULE AND AIRCRAFT COMPRISING SAID TRANSVERSE CHASSIS|
    FR3095423A1|2019-04-26|2020-10-30|Airbus Operations |Poly-articulated aerial workstation|
    FR3096666A1|2019-05-28|2020-12-04|Airbus Operations|INSTALLATION FOR THE POSITIONING OF AN AIRCRAFT MODULE IN AN INTERIOR SPACE DEFINED BY A TIP FRONT FRAME|
    法律状态:
    2017-09-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-17| PLSC| Search report ready|Effective date: 20171117 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-26| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-14| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1654263A|FR3051176B1|2016-05-12|2016-05-12|METHOD FOR ASSEMBLING AN AIRCRAFT FUSELAGE STRING USING AN ASSEMBLY MODULE AND AN AIRCRAFT FUSELAGE TRUNK ASSEMBLED THEREBY|
    FR1654263|2016-05-12|
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