FR3105168A1 - Stabilizer for flexibly assembling a frame member and stiffener for an aircraft fuselage. - Google Patents

Abstract

- Stabilizer intended to flexibly assemble a frame element and a stiffener for an aircraft fuselage. - The stabilizer (1) comprises a part (11A) intended to be fixed to a core (6) of a frame member (2), a part (11B) intended to be fixed to a surface (17) of a stiffener (4) and an intermediate part (11C) connecting the part (11A) and the part (11B), the intermediate part (11C) being included in a plane (P1) inclined by a nominal angle of inclination (A) non-zero with respect to a plane (P2) perpendicular to part (11A). The stabilizer (1) allows a tolerance as to the height of the stiffener (4). Figure for the abstract: Fig. 3

Description

Stabilizer intended to flexibly assemble a frame element and a stiffener for an aircraft fuselage.

The present invention relates to a stabilizer for an aircraft fuselage, as well as a structural fuselage part comprising at least one such stabilizer.

It is known that the fuselage of an aircraft, in particular of a transport aircraft, is designed in particular to resist loads induced by pressurization and merchant loads (passengers and freight).

To do this, the fuselage of the aircraft generally comprises a structural part comprising frame elements extending circumferentially, and an aerodynamic skin to which these frame elements are fixed, as well as stiffeners extending longitudinally , which are arranged on an inner face of the skin.

Document EP2832634 discloses a frame element for such a structural part. This frame element comprises a web provided with a through opening intended for the passage of a fuselage stiffener. The opening is made in such a way as to emerge outside the frame element, via a mouthpiece. In addition, this frame element comprises a tongue which is made in one piece with the core and which is connected to the latter by a fold delimiting the opening. This tab is intended for fixing the frame element to the stiffener.

When assembling the structural part, the frame elements are brought inside the structural part and placed on the stiffeners previously fixed to the skin. During this installation, the openings of the frame elements surround the stiffeners via their external mouth. The installation of the frame elements on the stiffeners does not allow any tolerance as to the height of the stiffeners.

The object of the present invention is to remedy this drawback. To do this, it relates to a stabilizer intended to assemble a frame element and a stiffener for an aircraft fuselage, the frame element comprising a core and a sole, the core having an open contour opening extending onto the sole , the opening being configured to be traversed by the stiffener.

According to the invention, the stabilizer comprises:
- a first part intended to be fixed to the web of the frame element,
- a second part intended to be fixed to a fixing surface of the stiffener and
- an intermediate part connecting the first part and the second part, the intermediate part being included in an inclined plane with a non-zero nominal angle of inclination with respect to a plane perpendicular to the first part.

Thus, the intermediate part thus makes it possible to obtain a tolerance as to the height of the stiffener. Indeed, when the second part rests on the fixing surface of the stiffener, the intermediate part allows the movement of the second part inwards or outwards when the height of the stiffener is greater or less than that provided. .

Without limitation, the nominal angle of inclination is less than 45°.

Advantageously, the nominal angle of inclination is between 5° and 30°.

Furthermore, the intermediate part and the first part are connected together by a first connection corresponding to a fold and in that the second part and the intermediate part are connected together by a second connection corresponding to a fold.

In addition, the first link and/or the second link have flexibility, said flexibility making it possible to vary the nominal angle of inclination by an angle of variation when the second part bears on the fixing surface of the stiffener before the attachment of the second part to the attachment surface of the stiffener.

In addition, the stabilizer comprises at least one side part intended to form a gusset between the web of the frame element and the sole of the frame element.

In addition, the stabilizer comprises at least a third part intended to be fixed to the sole of the frame element, the side part(s) forming a gusset between the first part and the third part.

According to one embodiment, the third part or parts extend the side part or parts, the or each of the third parts being configured to be fixed to a tongue made in one piece with the sole of the frame element, the tongue being connected to the sole by a fold defining the opening at the level of the sole.

The present invention also relates to a structural part of an aircraft fuselage.

According to the invention, said structural part comprises at least one frame element and one stabilizer as well as at least one stiffener as described above, said stiffener passing through the opening of the frame element and being fixed to the latter. through the stabilizer.

Further, the structural part comprises a plurality of spaced apart frame members along a longitudinal direction of the structural part, a plurality of stiffeners arranged parallel to the longitudinal direction, each of which passes through the openings of a plurality of frame members, and stabilizers securing the stiffeners to the frame members at the openings.

The present invention further relates to an aircraft, in particular a transport airplane, which comprises at least one structural part of the fuselage, such as that described above.

The present invention also relates to a method of assembling a structural part of the fuselage.

According to the invention, said method comprises:
- a step for fixing the stiffeners consisting in fixing the stiffeners to the skin;
- a sequence of steps comprising at least the fixing of the first part of the stabilizers to the web of the frame elements and the fixing of the second part of the stabilizers to the fixing surface of the stiffeners.

According to a first embodiment, the sequence of steps comprises:
- a step of fixing the stabilizers to the core of the frame elements consisting in fixing the first part of the stabilizers to the core of the frame elements;
- a step of approach consisting in approaching the stiffeners and the skin of the frame elements and the stabilizers;
- A step of fixing the stabilizers to the stiffeners consisting in fixing the second part of the stabilizers to the fixing surface of the stiffeners.

According to a second embodiment, the sequence of steps comprises:
- a step of positioning the frame elements on the skin;
- a step for positioning the stabilizers on the stiffeners and the frame elements;
- a step of fixing the frame elements, the stiffeners and the stabilizers consisting in fixing the frame elements to the skin, in fixing the first part of the stabilizers to the core of the frame elements and in fixing the second part of the stabilizers to the stiffener attachment surface.

The appended figures will make it clear how the invention can be implemented. In these figures, identical references designate similar elements.

Figure 1 is a side view of an aircraft, to which the present invention can be applied.

FIG. 2 is a schematic view, in perspective, of a structural part of an aircraft fuselage.

FIG. 3 is a partial view, in perspective, of a stabilizer, of a stiffener and of a frame element mounted on a skin according to a first embodiment.

FIG. 4 is a partial view, in perspective, of a stabilizer, of a stiffener and of a frame element mounted by rivets on a skin according to the first embodiment.

Figure 5 is a partial view, in perspective, of a stabilizer, a stiffener and a frame element mounted by welding or gluing on a skin according to the first embodiment.

FIG. 6 is a partial view, in perspective, of a stabilizer, of a stiffener and of a frame element mounted on a skin according to a second embodiment.

Figure 7 is a partial view, in perspective, of a stabilizer, a stiffener and a frame element mounted by rivets on a skin according to the second embodiment.

Figure 8 is a partial view, in perspective, of a stabilizer, a stiffener and a frame element mounted by welding or gluing on a skin according to the second embodiment.

Figure 9 is a longitudinal sectional view of a stabilizer attached to a frame member and a stiffener.

Figure 10 is a sectional view of a stabilizer attached to a frame member whose flexible connection is biased by a stiffener inserted in the opening of the frame member.

Figure 11 illustrates the assembly of a structural part according to one embodiment.

FIG. 12A schematically illustrates successive steps of an embodiment of a method for assembling a structural part of an aircraft fuselage. FIG. 12B schematically illustrates successive steps of another embodiment of a method for assembling a structural part of an aircraft fuselage.

In Figure 1, there is shown an aircraft AC, for example a transport aircraft, which comprises, in particular, a fuselage F.

This fuselage F is provided with a structural part 20, for example a fuselage section, as shown schematically, by way of illustration, in FIG. 2.

The structural part 20 has a longitudinal axis L, corresponding to the longitudinal axis of the aircraft AC. Along this longitudinal axis L are arranged a plurality of frame elements 2.

Each frame element 2 extends over the entire periphery 3 of the structural part 20 of the fuselage F, in a transverse plane P, that is to say in a plane which is orthogonal to the longitudinal direction L. The shape of each frame element 2 can be circular or have another shape. The shape of each frame element 2 depends on the section of the aircraft AC.

Alternatively (not shown), the frame elements 2 can also extend over only part of the periphery of the structural part 20. In the example shown in Figure 2, the frame elements 2 have a circular shape. It is also conceivable to provide a frame element 2 having the shape of an arc of a circle or an arc shape having any curve, depending on the section of the aircraft AC.

Each frame element 2 can be made in one piece or be formed from several frame arcs assembled together, each frame arc forming in this case an angular sector of the frame element 2.

To facilitate the description, an arrow L1 has been shown in FIG. 2 which indicates a direction defining a so-called "forward" direction (directed along the longitudinal axis L), namely towards the front of the aircraft AC in the direction of flight (or movement) of the aircraft AC. The direction opposite to that of the arrow L1 defines a so-called “rear” direction.

Furthermore, the adjectives “internal”, “interior”, “external” and “exterior” are also defined with reference to the longitudinal axis L, and with respect to the direction of arrows R1 (figure 2) which are directed radially in s 'deviating from the longitudinal axis L. Double arrows R illustrate radial directions. The terms “external” and “exterior” are defined according to the direction of the arrows R1, that is to say deviating from the longitudinal axis L, and the terms “internal” and “interior” are defined according to the direction opposite to that of the arrows R1, i.e. approaching the longitudinal axis L.

There has also been shown in FIG. 2, by a double arrow C, a circumferential direction which is defined according to a curved shape evolving around the longitudinal axis L. In FIG. 2, the curved shape corresponds to, for example, an arc of a circle evolving around the longitudinal axis L.

The structural part 20 further comprises a plurality of stiffeners 4. These stiffeners 4 are arranged longitudinally, parallel to the longitudinal axis L, preferably crossing the frame elements 2, as specified below.

The structural part 20 further comprises a skin 5 (partially and schematically shown in Figure 2) which covers, towards the outside, the assembly formed by the frame elements 2 and the stiffeners 4.

In a preferred embodiment shown in Figure 2, the structural part 20 comprises a plurality of frame elements 2 spaced from each other along the longitudinal direction L and a plurality of stiffeners 4 arranged parallel to the longitudinal direction L , each of which passes through openings of a plurality of frames. In addition, stabilizers (not shown in Figure 2), specified below, fix the stiffeners 4 to the frame elements 2.

Each frame element 2 can comprise, as represented in FIG. 3 and FIG. 6, a core 6 which is arranged transversely, parallel to the plane P. The core 6 has a rounded elongated shape (for example in an arc of a circle as represented in Figure 11) extending around the circumferential direction C. The core 6 is provided, at its outer end 6A, with a curved part forming a sole 7, and at its inner end 6B, with a curved part forming a wing 8. These parts are curved in different directions. The sole 7 can be curved backwards and the wing 8 forwards (in the direction of the arrow L1 in FIG. 3), or vice versa. Thus, each frame element 2 can have a Z shape. However, each frame element 2 can have a C shape in which the sole 7 and the wing 8 are curved in the same direction. Each frame element 2 can also have an I-shape or any other suitable shape.

In the example shown in Figure 3, sole 7 and wing 8 are arranged substantially orthogonally to web 6.

In addition, the core 6 comprises at least one through opening 9 (FIGS. 6 and 9), which extends to the sole 7. The opening 9 thus emerges at the level of the sole 7. Preferably, the core 6 comprises a plurality of openings 9, as shown for example in Figure 11.

Said opening 9 has an open contour 10 (FIG. 11), that is to say with a mouth which is located at the level of the sole 7. In addition, the size of the opening 9 is greater than the cross section d a stiffener 4 intended to pass through said opening 9, as specified below and shown for example in Figure 6.

By size, we mean the dimensions of the opening 9.

In the example of Figure 11, the opening 9 has a general trapezium shape adapted to the shape of each frame element 2.

In the example of Figure 3 and Figure 6, the stiffener 4 has a general shape of Z. The stiffener 4 comprises an intermediate wall 19. The intermediate wall 19 is provided at an outer end with a curved part corresponding to an outer wall 14 of the stiffener 4 and an inner end of a curved part corresponding to an inner wall 18 of the stiffener 4. These parts are curved in different directions. The internal wall 18 comprises the fixing surface 17 of the stiffener 4, in particular the internal surface of the stiffener 4. The external wall 14 comprises the external surface of the stiffener 4. The fixing surface 17 of the stiffener 4 corresponds to the surface of the stiffener 4 directed towards the inside of the structural part 20. The external surface of the stiffener 4 corresponds to the surface of the stiffener 4 directed towards the outside of the structural part 20.

The stabilizer 1 is intended to assemble a frame element 2 and a stiffener 4. As represented in FIGS. 3 to 10, the stabilizer 1 comprises a part 11A intended to be fixed to the core 6 of the frame element 2 and a part 11B intended to be fixed to the fixing surface 17 of the stiffener 4. The parts 11A and 11B can correspond to plates which are fixed respectively to the web 6 of the frame element 2 and to the fixing surface 17 of the stiffener 4.

Stabilizer 1 further comprises an intermediate part 11C connecting part 11A and part 11B. The intermediate part 11C is included in an inclined plane P1 forming a non-zero nominal angle of inclination A with respect to a plane P2 perpendicular to the part 11A (FIG. 9). Parts 11B and 11C form a tongue which has flexibility.

The intermediate part 11C, which can be flexible, thus makes it possible to obtain a tolerance as to the height H of the stiffener 4. Indeed, when the part 11B is based on the fixing surface 17 of the stiffener 4, the intermediate part 11C allows the movement of the part 11B inwards (in the direction of R1) or outwards (in the opposite direction to R1) according to the height H of the stiffener 4.

The intermediate part 11C also makes it possible to stabilize the frame element 2 with respect to the stiffener 4.

The nominal angle of inclination A is determined according to needs for stabilization and anti-tilting of the frame element 2. In particular, the greater the nominal angle of inclination A, the less the resistance to overturning of frame element 2 is effective. On the other hand, the smaller the nominal angle of inclination A, the less the stabilization of the frame element 2 is effective.

In a non-limiting manner, the nominal angle of inclination A is substantially less than 45°.

By way of non-limiting example, the nominal angle of inclination A is between 5° and 30°.

For example, part 11A, part 11B and intermediate part 11C are integral. Part 11A is linked to intermediate part 11C by a link 12A corresponding to a bend and part 11B is linked to intermediate part 11C by a link 12B also corresponding to a bend.

Advantageously, the connection 12A and/or the connection 12B connecting the intermediate part 11C to the part 11A and the part 11B respectively has flexibility. This flexibility makes it possible to vary the nominal angle of inclination A by a variation angle B so that the part 11B rests on the fixing surface 17 of the stiffener 4 before the fixing of the part 11B to the fixing surface 17 of the stiffener 4. The variation angle B corresponds to a variation in one direction or the other of the nominal angle of inclination A. This variation of angle makes it possible to obtain a variation D of the height of the part 11B so that the stabilizer 1 adapts to the height H of the stiffener 4. The height H of the stiffener 4 corresponds to a distance between the external surface of the stiffener 4 and the internal surface of the stiffener. For example, the internal surface corresponds to the fixing surface 17 of the stiffener 4 and the external surface corresponds to the surface fixed to the skin 5. FIG. 10 illustrates this flexibility by the representation of several positions of the intermediate part 11C and of the part 11B caused by the support of a stiffener 4 on part 11B.

In a non-limiting way, the flexibility of the link 12A and/or the link 12B allows the angle of variation B to be between 0.5° and 1°. In this case, the height of part 11B can be increased by approximately 1mm.

When the height H of the stiffener 4 is equal to the distance between the part 11B and the skin 5, the angle of variation B is zero. When the height H of the stiffener 4 is greater or less than the distance between the part 11B and the skin 5, the variation angle B is not zero.

Furthermore, the stabilizer 1 may comprise at least one side part 13 intended to form a gusset between the web 6 of the frame element 2 and the sole 7 of the frame element 2. This or these side parts 13 make it possible to stabilize the frame element 2 by acting against compression loads.

In the example of Figure 3, the side part 13 is integral with the part 11A. The side part 13 and the part 11A are connected by a fold 12C.

As shown in Figures 3 and 6, the stabilizer 1 comprises at least one part 11D intended to be fixed to the sole 7 of the frame element 2. The side part or parts 13 thus form a gusset between the part 11A and the third part 11D.

In a first embodiment of Figures 3 to 5, the part or parts 11D are included in a plane substantially perpendicular to the part 11A. The plane substantially perpendicular to part 11A is configured to be substantially parallel to sole 7 of frame element 2. Side part(s) 13 are integral with part(s) 11D. Part 11A is connected to part or parts 11D by a fold 12D. The stabilizer 1 according to the first embodiment can be mounted on a common fuselage panel, for example cylindrical, and on nose cone or tail cone panels.

In a second embodiment of Figures 6 to 9, the part or parts 11D extend the side part or parts 13. The or each of the parts 11D are configured to be fixed to a tongue 23 made in one piece with the sole 7 of the frame element 2. The tongue 23 is connected to the sole 7 by a fold 12E delimiting the opening 9 at the level of the sole 7. The side parts or parts 13 thus rest directly on the tongues 23. The stabilizer 1 can then accommodate an opening angle gradient between sole 7 and web 6 of frame element 2. Stabilizer 1 according to this second embodiment can therefore be used for elements frame 2 having a range of opening angles. The range is defined by the flexibility provided by the tongue formed by the parts 11B and 11C and the overlapping surface between the side part(s) 13 and the tongues 23. This allows the use of fewer types of stabilizer 1 according to this mode of realization, for example on front nose panels of AC aircraft. Indeed, the frame elements 2 have different opening angles on this type of panels. Preferably, the opening 9 is made outwards and in particular in the outer half of the core 6 by extending to the sole 7.

Furthermore, the core 6 of elongated shape and evolving in the circumferential direction C (in a circle or arc of a circle or other curved shape) is provided with a plurality of openings 9 spaced apart from each other along the web length 6.

In addition, a stabilizer 1 is fixed both to the web 6 of the frame element 2 and to the stiffener 4 to hold these two parts together.

The stabilizer 1 can be made of composite material or of metallic material.

For example, the composite material corresponds to a thermoplastic such as a polymer reinforced with carbon fibers.

The stabilizer 1 can be fixed to the core 6 and to the fixing surface 17 of the stiffener 4 by rivets 21 (FIGS. 4 and 7).

By way of example, the stabilizer 1 is fixed to the core 6 and to the fixing surface 17 of the stiffener 4 by rivets 21 when these elements are made of metallic material.

The stabilizer 1 can also be fixed to the core 6 and to the fixing surface 17 of the stiffener 4 by gluing or by welding 22 (FIGS. 5 and 8).

By way of example, the stabilizer 1 is fixed to the core 6 and to the fixing surface 17 of the stiffener 4 by gluing or by welding 22 when these elements are made of composite material.

This stabilizer 1 makes it possible to stabilize both the stiffener 4 and the frame element 2.

The structural part 20 therefore comprises a skin 5 and structural elements attached to the skin 5 to give it its rigidity. These structural elements typically comprise longitudinal stiffeners 4, also called stringers, extending substantially in planes parallel to the longitudinal axis L of the fuselage F, and circumferential frame elements 2, which extend globally along a transverse plane P , that is to say orthogonal to the longitudinal axis L, all around this longitudinal axis L. The stabilizers 1 thus make it possible to assemble the stiffeners 4 and the frame elements 2 together.

The structural part 20, as described above, can be assembled according to an assembly method, as specified below and in Figure 12.

Said assembly method comprises:
- A step A1 for fixing the stiffeners consisting in fixing the stiffeners 4 to the skin 5;
- a sequence of steps comprising at least the fixing of part 11A of the stabilizers 1 to the web 6 of the frame elements 2 and the fixing of the part 11B of the stabilizers 1 to the fixing surface 17 of the stiffeners 4.

For a stabilizer 1 configured according to the first embodiment, the sequence of steps includes:
- A step A2 of fixing the stabilizers to the core of the frame elements consisting in fixing the part 11A of the stabilizers 1 to the core 6 of the frame elements 2;
- A step A3 of bringing together consisting of bringing the stiffeners 4 and the skin 5 closer to the frame elements 2 and the stabilizers 1;
- a step A4 of fixing the stabilizers to the stiffeners consisting in fixing the part 11B of the stabilizers 1 to the fixing surface 17 of the stiffeners 4.

Steps A1 and A2 can be carried out simultaneously. They can also be carried out successively in any order.

For a stabilizer 1 configured according to the second embodiment, the sequence of steps includes:
- a step A5 for positioning the frame elements 2 on the skin 5;
- A step A6 for positioning the stabilizers 1 on the stiffeners 4 and the frame elements 2;
- a step A7 for fixing the frame elements, the stiffeners and the stabilizers consisting in fixing the frame elements 2 to the skin 5, in fixing the part 11A of the stabilizers 1 to the web 6 of the frame elements 2 and in fixing the part 11B of the stabilizers 1 to the fixing surface 17 of the stiffeners 4.

In step A3 and step A7, the flexibility of the links 12 of the stabilizers 1 allows the stabilizers 1 to adapt to the heights H of each of the stiffeners 4.

For step A3, the arrow 100 represents the preferred direction of bringing together the stiffeners and the skin 5 of the frame elements 2 and the stabilizers 1.

The structural part 20, as described above, has many advantages:
- Easier assembly of the structural part 20 by the reduced number of structural elements (stiffener 4, frame element 2, stabilizer 1) and by the simple configuration of each of the structural elements. Access to tools for assembly is also facilitated.
- assembly and fixing of structural elements carried out by robots,
- reduction in weight of the structural part 20 by the reduced number of structural elements and improved structural efficiency due to their configuration,
- less elements are needed to link the structural elements by better integrated structural elements,
- possibility of forming single or double curvature fuselages.

Claims (15)

Stabilizer intended to assemble a frame element (2) and a stiffener (4) for an aircraft fuselage (F) (AC), the frame element (2) comprising a web (6) and a sole (7), the core (6) having an opening (9) with an open contour extending onto the flange (7), the opening (9) being configured to be crossed by the stiffener (4),
characterized in that the stabilizer (1) comprises:
- a first part (11A) intended to be fixed to the core (6) of the frame element (2),
- a second part (11B) intended to be fixed to a fixing surface (17) of the stiffener (4) and
- an intermediate part (11C) connecting the first part (11A) and the second part (11B), the intermediate part (11C) being included in a plane (P1) inclined at a non-zero nominal angle of inclination (A) with respect to a plane (P2) perpendicular to the first part (11A). Stabilizer according to claim 1,
characterized in that the nominal angle of inclination (A) is less than 45°. Stabilizer according to any one of claims 1 or 2,
characterized in that the nominal angle of inclination (A) is between 5° and 30°. Stabilizer according to any one of claims 1 to 3,
characterized in that the intermediate part (11C) and the first part (11A) are interconnected by a first connection (12A) corresponding to a bend and in that the second part (11B) and the intermediate part (11C) are interconnected by a second link (12B) corresponding to a bend. Stabilizer according to claim 4,
characterized in that the first link (12A) and/or the second link (12B) have flexibility, said flexibility making it possible to vary the nominal angle of inclination (A) by a variation angle (B) so that the second part (11B) rests on the fixing surface (17) of the stiffener (4) before fixing the second part (11B) to the fixing surface (17) of the stiffener (4). Stabilizer according to any one of claims 1 to 5,
characterized in that it further comprises at least one lateral part (13) intended to form a gusset between the core (6) of the frame element (2) and the sole (7) of the frame element ( 2). Stabilizer according to claim 6,
characterized in that it comprises at least a third part (11D) intended to be fixed to the sole (7) of the frame element (2), the lateral part(s) (13) forming a gusset between the first part ( 11A) and the third part (11D). Stabilizer according to claim 7,
characterized in that the third part or parts (11D) extend the side part or parts (13), the or each of the third parts (11D) being configured to be fixed to a tab (23) made in one piece with the sole (7) of the frame element (2), the tongue (23) being connected to the sole (7) by a fold (12E) delimiting the opening (9) at the level of the sole (7). Aircraft fuselage structural part,
characterized in that it comprises at least one frame element (2), as well as at least one stiffener (4) and a stabilizer (1) according to any one of Claims 1 to 8, the said stiffener (4) passing through the opening (9) of the frame element (2) and being fixed to the latter via the stabilizer (1). Structural part according to claim 9,
characterized in that it further comprises at least one outer skin (5) which is fixed to the frame element (2) and to the stiffener (4). Structural part according to one of claims 9 or 10,
characterized in that it comprises a plurality of frame elements (2) spaced from each other along a longitudinal direction (L) of the structural part (20), a plurality of stiffeners (4) arranged parallel to the longitudinal direction (L), each of which passes through the openings (9) of a plurality of frame elements (2), and stabilizers (1) fixing the stiffeners (4) to the frame elements (2) at the openings (9). Aircraft,
characterized in that it comprises at least one structural part (20) of the fuselage (F) according to any one of claims 9 to 11. Method of assembling a structural part of the fuselage according to any one of Claims 9 to 11,
characterized in that it comprises:
- a step (A1) for fixing the stiffeners (4) consisting in fixing the stiffeners (4) to the skin (5);
- a sequence of steps comprising at least the fixing of the first part (11A) of the stabilizers (1) to the core (6) of the frame elements (2) and the fixing of the second part (11B) of the stabilizers ( 1) to the fixing surface (17) of the stiffeners (4). Method according to claim 13,
characterized in that the sequence of steps comprises:
- a step (A2) of fixing the stabilizers (1) to the core (6) of the frame elements (2) consisting in fixing the first part (11A) of the stabilizers (1) to the core (6) of the frame (2);
- a step (A3) of bringing together consisting of bringing the stiffeners (4) and the skin (5) close to the frame elements (2) and the stabilizers (1);
- a step (A4) of fixing the stabilizers (1) to the stiffeners (4) consisting in fixing the second part (11B) of the stabilizers (1) to the fixing surface (17) of the stiffeners (4). Method according to claim 13,
characterized in that the sequence of steps comprises:
- a step (A5) of positioning the frame elements (2) on the skin (5);
- a step (A6) for positioning the stabilizers (1) on the stiffeners (4) and the frame elements (2);
- a step (A7) of fixing the frame elements (2), the stiffeners (4) and the stabilizers (1) consisting in fixing the frame elements (2) to the skin (5), in fixing the first part ( 11A) of the stabilizers (1) to the core (6) of the frame elements (2) and to fix the second part (11B) of the stabilizers (1) to the fixing surface (17) of the stiffeners (4).