FR2788743A1 - Assembly jig for aircraft fuselage sections has frame with mountings to support fuselage halves and components for assembly - Google Patents

Abstract

The assembly jig for aircraft fuselage section halves to form a complete section has a frame (2) to support all the required components which are attached to retainers. The frame has hoist transfer frames (3) to position the fuselage sections in the assembly frame.

Description

I The invention relates to a device intended for mounting sections

  aircraft fuselage capable of fixing and arranging the constituent parts of said sections in the process of assembling said parts for the formation of the

  corresponding section in each case.

  There are different patents, such as German patents 7 12 525, 7 13 281, 7 25 369 and 10 10 836, US patents 5 560 102, 5 586 391, 5 615 483 and 5 649 888, and patents Europeans 0 142 697 and 0 593 127, which relate to

  devices and installations for mounting fuselage sections of aircraft.

  However, all of these solutions correspond to very rigid installations, since they are used for only one type of part, so that they only make it possible to position parts of a concrete configuration, since it is

  devices must be replaced when the parts to be fixed change.

  On the other hand, the Spanish patent 9100894 and the Spanish utility model 9101588, which belong to M MANUEL TORRES MARTINEZ relate to a fixing means having a variable positioning capacity, in

  allowing to fix pieces of different sizes and different configurations.

  With this means of assembly, we have developed facilities for handling

  large parts in transport and turnaround.

  Starting from this principle, according to the present invention, a device is proposed which offers an essential characteristic of good flexibility, so that it can be used for fixing different types of parts, with a simple modification of the positioning of the elements intended for fixing, this device

  being intended for the construction assembly of fuselage sections for aircraft.

  Said device according to the invention comprises a structure intended for the assembly of half-carcasses constituting each of the sides of the respective section of fuselage to be built; and another structure intended for assembling the two lateral assemblies to the rest of the constituent parts of the fuselage section; each of said structures comprising supports adaptable to the constituent parts of the fuselage for fixing the corresponding parts; while transfer devices, also adaptable to the constituent parts, make it possible to transport the lateral assemblies formed in the first structure to arrange them in the second structure in order to couple them to the other parts of the

fuselage section to build.

  The structure for the shaping of the sides comprises two symmetrically arranged assemblies, each of which comprises a support which can be moved horizontally towards and away from a central position, while on said support there is a frame capable of

  vertical displacement, equipped with adaptable means for fixing a half

  upper lateral carcass, while, in the lower part, is arranged another support capable of horizontal movement jointly with the previous one, this lower support being in turn provided with adaptable means for fixing a

  lower side half-carcass.

  Each of the transfer devices consists of an armature which can be transported by independent means such as, for example by means of an overhead crane, this armature being provided with adaptable means for fixing the assembled assembly of the two half-carcasses upper and lower on each side. The mounting structure of the entire section comprises supports which can be moved towards and away from one another, with respect to which the transfer devices can be incorporated in fixing, said structure comprising in its lower part a mobile support in lifting and lowering, which is provided with adaptable means for fixing a lower closure panel of the section; while, in the upper part is arranged another support capable of horizontal displacement towards a side and movable in turn in descent and in elevation, which is provided on its side with adaptable means for fixing a

  upper closure panel of the section to be built.

  As regards the mounting structure of the aforementioned assembly, there is an additional independent support, which can be transported by external means such as, for example, by means of an overhead crane, the platform corresponding to the floor of the cockpit of the fuselage section which can be incorporated using said support, for fixing this platform in the assembly. A device is thus obtained provided with fixing means for all the constituent parts of the fuselage sections to be constructed, said means being able to be positioned and adapted according to the parts which are to be fixed, so that they allow flexibility which makes the device capable of being used with the same elements for different types of parts, thus making possible the construction of different fuselage sections, such as those which correspond to different

parts of aircraft.

  In this way, the device which is the subject of the invention certainly has very advantageous characteristics, thus acquiring a life of its own and a character

  preferential compared to known means intended for the same function.

  Figure 1 shows a perspective view of the entire structure

  intended for the formation of the sides of the fuselage sections to be built.

  Figure 2 is a perspective view of the same previous structure in

  construction phase of the sides for a fuselage section.

  Figure 3 is a perspective view of the base frame of this previous structure. Figure 4 is a perspective view of the supports carrying the fastening frames of the upper half-carcasses in the construction of the sides of the sections

of fuselage.

  Figure 5 is a perspective view of the mounting brackets of the half

  abovementioned upper carcasses on the sides of the fuselage sections.

  Figure 6 is a perspective view of the mounting brackets of the half

  lower carcasses in the construction of the abovementioned sides for the fuselage sections. Figure 7 is a perspective view of the mounting structure of

  all of the fuselage sections.

  Figure 8 is a perspective view of the same previous structure in

  construction phase of a fuselage section.

  Figure 9 is a perspective view of the base frame of said structure

previous.

  FIG. 10 is a perspective view of the fixing supports for the transfer devices in the aforementioned structure for mounting all of the

fuselage sections.

  Figure 11 is a perspective view of the transfer devices which are used for transporting the sides of the fuselage sections from the formation structure thereof to the mounting structure of all the fuselage sections. FIG. 12 is a perspective view of the transfer devices proper, with the corresponding sides of a fuselage section arranged on

them.

  Figure 13 is a perspective view of the support for fixing the lower closure panel in the construction of the fuselage sections. Figure 14 is a perspective view of the support for fixing and

  positioning of the upper closure panel of the fuselage sections.

  FIG. 15 is an end view of the structure for forming the sides of the fuselage sections, which represents the positioning of the lower half-carcass

corresponding to one of the sides.

  FIG. 16 is a view of the same structure which represents the positioning of the respective upper half-carcass of the same formation

side as the previous figure.

  Figure 17 is a view showing the positioning phase of the half

  constituent carcasses on the side to carry out their mutual assembly.

  Figure 18 is a view showing the coupling of the half-carcasses

  constituting the side to a juxtaposed edge zone, for the corresponding drilling.

  Figure 19 is a view which shows the distance of the half-carcasses after drilling, for cleaning and for sealing, returning to the juxtaposition for

assembly riveting.

  Figure 20 shows the introduction of the respective transfer device for

  receive the side formed by the two previous half-carcasses assembled.

  Figure 21 shows the attachment of the transfer device, by means of its adaptable elements, on the whole of the side formed by the two assembled half-carcasses. Figure 22 represents the extraction of the side formed by the half-carcasses

  assembled, by means of the transfer device.

  FIG. 23 represents the installation of the lower closure panel in the mounting structure, for the formation of construction of a fuselage section. Figure 24 shows the placement of the sides of the section to be constructed, at

  means of respective transfer devices.

  Figure 25 represents the installation of the platform of the floor of

  the cockpit of the fuselage section by means of an accessory conveyor device.

  FIG. 26 shows the closure for assembly by riveting of the entire fuselage section and the subsequent extraction of the device carrying the

floor platform.

  FIG. 27 represents the positioning of the upper closure panel,

  by means of the corresponding support, on the previous assembly assembled.

  Figure 28 shows the extraction of the transfer devices, to leave free the fuselage section built so that it can be transported to the place

  o we proceed to its installation.

  Figures 29.1 to 29.20 show schematically the complete sequence of the construction process of a fuselage section with the device

according to the invention.

  The invention relates to a device for assembling the construction of aircraft fuselage sections, said device comprising a structure (1) intended for making the sides of the fuselage sections and a structure (2) intended for mounting the fuselage sections. of said fuselage sections, using transfer devices (3) for transporting the sides from the formation structure

  (1) to the assembly structure (2).

  The structure (1), the assembly of which is visible in FIG. 1, comprises a base frame (4) shown in FIG. 3, on which two symmetrical assemblies are mounted, each of which comprises a support (5) which can move

  horizontally in approximation and distance from the middle zone.

  On the supports (5), the assembly of which is visible in FIG. 4, armatures (6), shown in FIG. 5, are mounted, which can be set in movement in elevation and in descent, by means of extensible elements. (22) on which they are supported in connection with the supports (5), said frames (6) being equipped with elements (7) adaptable in positioning and orientation, of the type of those of the utility model 9101588, intended for fix the corresponding half-carcasses 8 forming the sides for the fuselage sections as

can see it in figure 2.

  On the base frame (4) are mounted, in the lower part, supports (9) the assembly of which is visible in FIG. 6, which correspond to the respective symmetrical assemblies, said supports (9) being capable of being fixed to the supports (5) and detach from them, to move jointly with them or to remain static independently. The aforementioned lower supports (9) are in turn provided with elements (7) adaptable in positioning and orientation, of the type of those of

  utility model 9101588, by means of which it is also possible to fix the half

  corresponding carcasses (10) intended for forming the sides of the sections of

fuselage.

  The structure (2), the assembly of which is visible in FIG. 7, in turn comprises a base frame (I 1) shown in FIG. 9, on which mount supports (12), the assembly of which is visible in Figure 10, which are arranged in a movable arrangement, with the possibility of reconciliation and mutual separation, being intended to allow to fix on them the transfer devices (3) which carry the sides of the fuselage sections to be constructed, as we can see it on the

figure 8.

  In the lower part of the same base frame (11) is disposed a support (13), shown in Figure 13, which is arranged in the base frame (11) according to an elevation and descent arrangement; said support (13) being in turn provided with adaptable elements (7), of the type of those of utility model 9101588, by means of which the fixing of a panel (14) intended for closure can be carried out

  bottom of the fuselage section.

  In the upper part of the frame (11) is mounted another support (15) which is shown in Figure 14, which is arranged on guides (16) which allow it to be moved between a lateral position located above a tilting support (17) and a central position relative to the structure (2); said support (15) being additionally capable of raising and lowering, and also having adaptable elements (7) of the type of those of utility model 9101588 by means of which it is possible to fix a panel (18) intended to the upper closure of the sections of

  fuselage, which is placed, for reception, on the tilting support (17).

  The transfer devices (3) which can be seen in FIG. 11 are likewise provided with adaptable elements (7), also of the type of those of utility model 9101588, for fixing the lateral assemblies formed by the half carcasses

  corresponding (8) and (10) as seen in Figure 12.

  In this way, the construction of a fuselage section, with the device according to the invention, takes place in accordance with the following method: First, the sides are formed in the structure (1), which is why the respective lower half-carcasses (10) are placed on the corresponding supports (9), as FIG. 15 shows for one of the sides, it being understood

  that the operation is carried out in the same way for the other side.

  Then, as shown in FIG. 16, the upper half-carcass (8) on each side is placed on the respective support frame (6), this operation being carried out with the corresponding frames (6) placed in a

  high position, to facilitate installation.

  Then, the frame (6) is lowered relative to the corresponding support (5) until the edges of the half-carcasses (8) and (10) are face to face as shown in FIG. 17, the support (5) then moving towards the center of the assembly, until the edges of the half-carcasses (8) and (10) are juxtaposed, as shown in FIG. 18, position in which the supports are moored ( 5) and (9) to fix the positioning, by drilling the juxtaposed edges of the

half-carcasses (8) and (10).

  Once the holes have been drilled, we start moving the half-pieces away

  carcasses (8) and (10) to remove burrs from the holes and apply a sealant, then returning once again to the juxtaposed position, as shown in Figure 19, to rivet the assembly through the

  previously drilled holes.

  Then, by means of an independent conveyor, which can be an overhead crane or any other similar means, a transfer device (3) is brought to the lateral assembly formed by the respective half-carcasses (8) and (10 ),

  as shown in figure 20.

  The transfer device (3) is positioned correspondingly on the whole of the side formed by the half-carcasses (8) and (10), the fixing of said assembly being effected by means of the respective adaptable elements (7), as shown in Figure 21; once this has been done, the above-mentioned assembly is released, consisting of the half-carcasses (8) and (10), of the fixing provided by the elements (7) of the support (9) and of the frame (6), the whole side being extracted by means of the

  corresponding transfer (3), as shown in figure 22.

  In the structure (2), a panel (14) is placed on its side on the lower support (13) while the latter is located in the low position, as shown in FIG. 23; the sides carried by the transfer devices (3) are then mounted, as shown in FIG. 24, so that the aforementioned transfer devices (3) are fixed on the supports (12) while remaining located in a

  fixed positioning that said supports (12) determine.

  By means of an accessory support device (19), the corresponding platform (20) is introduced from the floor of the passenger compartment of the fuselage section, as shown in FIG. 25, the aforementioned platform (20) being fixed on a support

  correspondent (21) who establishes his position.

  By moving the support (12) towards the central zone, the lateral assemblies are then assembled relative to the lower panel (14), previously raised to an adequate position and relative to the platform (20) of the floor of the passenger compartment, as shown in Figure 26; the assembly riveting of the assembly taking place in this position; meanwhile, we remove the device

  (19) when the platform (20) has been fixed on the sides.

  Then, by means of the upper support (15), the upper closure panel (18) is received, previously arranged for this on one side on the tilting support (17), bringing said panel (18) to the area median to place it in the upper closed position of the fuselage section, as shown in Figure 27; the assembly riveting of said panel (18) is carried out in this position to the upper half-carcasses (8) on the sides, the result is that the entire fuselage section is structurally assembled, and the transfer devices can be removed (3), as shown in FIG. 28, for the transport of said section of

  fuselage built in the appropriate place.

  In FIGS. 29.1 to 29.20, we can see in schematic form the complete sequence of the construction assembly of a fuselage section by the method described with reference to FIGS. 15 to 28, by representing the following operations:

  Figure 29.1: positioning of the lower half-carcass (10) on one side.

  Figure 29.2: positioning of the upper half-carcass (8) from the side.

  Figure 29.3: corresponding positioning movement of the half

carcasses (8) and (10).

  Figure 29.4: assembly of the supports (5) and (9) and coupling of the half

  carcasses (8) and (10) for drilling.

  Figure 29.5: distance of the half-carcasses (8) and (10) for cleaning

  burrs and the application of the sealant.

  Figure 29.6: positioning of the half-carcasses (8) and (1 0) for riveting.

  Figure 29.7: introduction of the transfer device (3).

  Figure 29.8: approximation of the formed side and adaptation of the

  transfer (3) to the exterior surface of the assembly on said side.

  Figure 29.9: exchange on the formed side and distance from the support (5).

  Figure 29.10: extraction from the formed side, using the transfer device (3).

  Figure 29.11: loading the lower closure panel (14).

  Figure 29.12: positioning of the aforementioned lower panel (14).

  Figure 29.13: loading of the previously formed sides, using the

  respective transfer devices (3).

  Figure 29.14: loading the floor platform (20).

  Figure 29.15: positioning of the sides and riveting on the platform of the

  floor (20) and on the lower panel (14).

  Figure 29.16: extraction of the device (19) carrying the platform of the

floor (20).

  Figure 29.17: positioning of the upper panel (18) for closing

of the fuselage section.

  Figure 29.18 installation of leveling fittings.

  Figure 29.19 extracting the transfer devices (3).

  Figure 29.20 extraction of the fuselage section constructed.

  The adaptability of the fixing elements (7) in the different supports of the component parts of the fuselage sections makes it possible to use the device for the formation of fuselage sections of different dimensions and of different shapes without the need to change the fixing elements of the parts as a function of the latter but by simply adapting all of the elements (7) of each

  support depending on the part it has to support.

  In the frames (6) and in the supports (9), (13) and (15), the installation of the respective adaptable elements (7) in the working position is carried out prior to the reception of the parts to be fixed, it being provided that said positioning is carried out manually without excluding the possibility of automatic positioning,

  by means of motorizations controlled by a numerical control.

  Since the parts to be fixed may have geometry deviations from the nominal geometry, which affect the positioning of the adaptable elements (7), these are provided with a micrometric mechanism which makes it possible to manually adjust said elements ( 7), one by one, independently, to the part to be fixed, provided that the variations relative to the nominal geometry do not affect the interchangeability of the parts, since it is a question of ensuring the supply of the number

maximum possible number of pieces.

  Said manual adjustment process must therefore necessarily be carried out on the structure (1) for the half-carcasses (8) and (10) on the sides and on the structure (2) for the closure panels (14) and (18). lower and upper section of

fuselage.

  In the transfer devices (3), the corresponding adaptable elements (7) automatically reproduce the exterior surface of all of the respective half-carcasses (8) and (10) assembled, admitting possible deviations from the actual geometry that said outer surface can have

  with respect to the nominal geometry.

  Therefore, when said transfer devices (3) are positioned on the structure (1) and the movement of the corresponding supports (5) and (9) assembled is carried out, bringing the assembly formed on the respective side, until that it has been positioned to carry out the exchange of the support, the adjustment of the mentioned assembly from the side with respect to the corresponding transfer device (3) does not have to be carried out manually, since it is carried out automatically by the reproduction of the external surface on the side executed by the transfer device (3), thanks to the fact that it has adaptable elements (7) which are actuated pneumatically, because they have a pneumatic locking brake which is activated automatically when the element detects the surface of the part to be fixed, at the same time as a vacuum is produced in the adaptable element (7) to ensure the fixing. This does not however exclude the possibility that the elements (7) mentioned may be actuated by another type of

any motorization.

  Said reproduction makes it possible to automatically compensate for any possible deviations in the geometry of the outer surface of the sides of the fuselage section relative to the nominal geometry; said reproduction being able to be made thanks to the fact that the constituent half-carcasses (8) and (10) are positioned in their supports (6) and (9), on which a manual adjustment has been made so that each transfer device ( 3), when it is positioned on the structure (1), is referenced with respect to the supports (6) and (9) above which support the lateral assemblies formed. Thanks to the reproduction process carried out by the transfer devices (3), the adjustment of the adaptable elements (7) to the geometry of the sides intended for the fuselage section, has to be carried out manually only once, during of the reception of the half-carcasses (8) and

(10) on the structure (1).

he

Claims (9)

  1. Device for mounting sections of the fuselage of aircraft, characterized in that it consists of a structure (1) intended for forming the sides of the fuselage sections to be constructed, and by a structure (2) intended for mounting of the assembly of all the constituent parts of the fuselage sections, each of said structures comprising adaptable supports for fixing the various constituent parts of the fuselage sections; while by means of transfer devices (3), also adaptable to the corresponding parts, the sides formed in the structure (1) can be transported to place them in the mounting position correlatively with the other parts inside of the structure (2).   2. Device for mounting sections of the fuselage of aircraft according to claim 1, characterized in that the structure (1) comprises supports (5) movable in the horizontal direction in the direction of approaching or moving away, on which are mounted in the upper position, respective frames (6) arranged with the possibility of raising and lowering, which are provided with adaptable elements (7) for the fixing of half-carcasses (8) constituting   sides of the fuselage sections to be built.   3. Device for mounting sections of the fuselage of aircraft, according to   Claims 1 and 2, characterized in that the structure (1) comprises supports   lower (9) which can be made integral and detached from the supports (5), to be moved jointly with them or to be independently static, while said supports (9) are in turn provided with adaptable elements (7) intended to the fixing of semi-carcasses (10) constituting the sides of the sections of fuselage to build.   4. Device for mounting sections of the aircraft fuselage according to claim 1, characterized in that the structure (2) comprises supports (12) movable in the horizontal direction in the direction of approaching or moving away, on which can be mounted in fixed fixing the   transfer (3) which carry the sides of the fuselage sections to be built.   5. Device for mounting sections of the aircraft fuselage according to claim 1, characterized in that the structure (2) comprises, in the lower position, a support (13) arranged with the possibility of raising and lowering, which is provided with adaptable elements (7) for fixing a closure panel (14)   lower sections of the fuselage to be built.   6. Device for mounting sections of the aircraft fuselage according to claim 1, characterized in that the structure (2) comprises, in the upper position, a support (15) disposed in mounting on guides (16) for movement between a lateral position above a tilting support (17) and a central positioning in the structure (2), said support (15) being additionally movable in descent and in elevation, and in turn having adaptable elements (7 ) for fixing a panel (18) for closing the upper sections of fuselage to build.   7. Device for mounting sections of the fuselage of aircraft, according to the   Claims I to 4, characterized in that the transfer devices (3) are provided   adaptable elements (7) for fixing the lateral assemblies of the sections of   fuselage to be built, formed by an upper half-carcass (8) and a half lower casing (10).   8. Device for mounting sections of the fuselage of aircraft according to the   Claims 1 to 6, characterized in that in the reinforcements (6) and in the   supports (9), (13) and (15), the respective adaptable elements (7) are put into place in the working position before receiving the parts to be fixed,   said positioning preferably being carried out manually.   9. Device for mounting sections of the fuselage of aircraft   according to claims 1 and 7, characterized in that in the transfer devices   (3), the corresponding adaptable elements (7) automatically reproduce the external surface of the lateral assembly formed by the respective half-carcasses (8) and (10) assembled by admitting any possible deviations from the actual geometry   that said outer surface can have relative to the nominal geometry.