Adjustable floor module for a fuselage portion of an aircraft and method of integrating such a floor module.

Abstract

Adjustable floor module for a fuselage portion of an aircraft, in particular a nose cone, and method of integrating such a floor module.The floor module (2) comprises a so-called front sub-module (3) and a so-called rear sub-module (4) arranged relative to each other in a longitudinal direction of the floor module (2), said sub-modules (3, 4) being linked together by a plurality of connecting elements (5) configured to allow relative movement between said sub-modules (3, 4) at least in the longitudinal direction and to allow the transmission of forces between said sub-modules (3, 4) in a vertical direction substantially orthogonal to the floor module (2) without generating relative movement, the sub-modules (3, 4) thus linked by the connecting elements 5 being structurally decoupled, namely that they can be slightly moved relative to each other, which makes it possible to adjust the geometry of the floor module (2), for example to compensate for tolerance defects in the fuselage part on which it is intended to be installed. Figure for abstract: Figure 3.

Description

Title of the invention: Adjustable floor module for a fuselage part of an aircraft and method of integrating such a floor module. Technical field

[0001] The present invention relates to an adjustable floor module for a fuselage portion of an aircraft, in particular for a nose cone, and a method of integrating such a floor module. State of the art

[0002] For the manufacture of certain parts of an aircraft, in particular a transport aircraft, it is known to use modular type assembly processes. These are processes comprising the assembly of several parts to form modules (preferably in a limited number) which are themselves subsequently assembled together to obtain the desired aircraft part. This can make it possible to optimize certain assembly steps, in particular by setting up dedicated workstations which can operate in parallel.

[0003] For example, the manufacture of a nose cone of an aircraft may correspond to a method providing, first of all, to assemble a plurality of parts to independently manufacture several modules, such as fuselage parts and a floor module. The fuselage parts are then assembled together to form a fuselage body into which the floor module is inserted and fixed. It is thus possible to achieve a saving of time and efficiency.

[0004] However, in the manufacturing method considered, the floor module is fixed on two different fuselage parts, which can pose a problem of tolerancing. Indeed, the fuselage body can have alignment defects (inherent in the assembly steps in general) involving slight offsets between the fuselage parts. Consequently, the step of fixing the floor module in the fuselage body can be complicated.

[0005] There is therefore a need to find a solution to improve the assembly processes as mentioned above. Statement of the invention

[0006] The present invention aims to remedy the aforementioned drawbacks. It relates to a floor module for a fuselage part of an aircraft, in particular a nose cone, said floor module having a longitudinal direction.

[0007] According to the invention, the floor module comprises at least one sub-module called front and a so-called rear sub-module arranged longitudinally relative to each other, front and rear being defined in opposite directions along the longitudinal direction of the floor module, said sub-modules being linked together by a plurality of connecting elements configured to allow relative movement between said sub-modules at least along the longitudinal direction and to allow the transmission of forces between said sub-modules along a vertical direction substantially orthogonal to the floor module, without generating relative movement between said sub-modules.

[0008] Thus, thanks to the present invention, it is possible to obtain, simply and at low cost, a floor module formed by sub-modules which are structurally decoupled, namely which are linked together by the connecting elements so as to be able to be slightly displaced relative to each other at least longitudinally, which makes it possible to adjust the geometry of the floor module, for example to compensate for tolerance defects in the fuselage part in which it is intended to be installed.

[0009] In a particular embodiment, each of said connecting elements comprises at least two fixing lugs arranged, respectively, at a front end of the rear sub-module and at a rear end of the front sub-module, and a connecting rod provided with two articulations, said connecting rod being arranged between said fixing lugs while being linked to each of them by one of its articulations.

[0010] Advantageously, for each of said connecting elements, one of said fixing lugs is fixed integrally to one end of a rail of the rear sub-module and the other fixing lug is fixed integrally along a rear cross member of the front sub-module.

[0011] Furthermore, advantageously, each of said articulations of the connecting rod of each of said connecting elements comprises at least one articulation axis arranged in the corresponding fixing lug and on which the connecting rod is mounted so as to form at least one simple pivot type connection between said connecting rod and the corresponding fixing lug.

[0012] In another particular embodiment, the connecting elements are configured to also allow relative movement between the sub-modules in a transverse direction substantially orthogonal to the longitudinal direction and substantially parallel to the floor module.

[0013] Furthermore, advantageously, each of said articulations of the connecting rod of each of said connecting elements comprises at least one ball joint mounted on an articulation axis arranged through the corresponding fixing lug, said ball joint being sandwiched between two spacers having a shape adapted so as to form a ball joint type connection between said connecting rod and the corresponding fixing lug.

[0014] The present invention also relates to a fuselage part of an aircraft comprising at least one fuselage body formed by a plurality of fuselage parts.

[0015] According to the invention, the fuselage part comprises at least one floor module as described above, arranged inside the fuselage body, the front sub-module and the rear sub-module of the floor module each being fixed to different fuselage parts.

[0016] In a preferred embodiment, the fuselage portion corresponds to a nose cone of the aircraft.

[0017] The present invention also relates to a method of integrating a floor module as described above, into a fuselage part.

[0018] According to the invention, the method comprises at least the following series of steps: - a preliminary assembly step for connecting together the front sub-module and the rear sub-module using a plurality of connecting elements so as to obtain said floor module; - an assembly step for introducing the floor module obtained in the preliminary assembly step into the fuselage body of the fuselage part; and - a fixing step for fixing the floor module to said fuselage body, the front sub-module and the rear sub-module each being fixed to different fuselage parts.

[0019] The present invention further relates to a method of assembling a fuselage part of an aircraft, in particular a nose cone, comprising at least the following series of steps: - a succession of assembly steps for assembling a plurality of fuselage parts of the fuselage portion so as to obtain a fuselage body; and - an integration step for integrating at least one floor module into the fuselage body obtained in the succession of assembly steps, said integration step corresponding to the integration method described above. Brief description of the figures

[0020] The attached figures will make it clear how the invention can be implemented. In these figures, identical references designate similar elements.

[0021] [Fig.l] is a schematic view, in perspective and in partial section, of a nose cone of an aircraft comprising a particular embodiment of a floor module.

[0022] [Fig.2] is a schematic perspective view of the front tip of [Fig.l], seen from the rear.

[0023] [Fig. 3] is a partial schematic perspective view of the floor module showing an interface between a front submodule and a rear submodule linked together by a plurality of linking elements.

[0024] [Fig. 4] is a detailed perspective view of a particular embodiment of one of the connecting elements of [Fig.3].

[0025] [Fig.5] is a detailed perspective view of an articulation of the element of connection of [Fig.4].

[0026] [Fig. 6] is a schematic view of a particular embodiment of a method assembly of an aircraft nose cone.

[0027] [Fig.7] is a schematic view of a particular embodiment of a method of integrating a floor module into a nose cone of an aircraft.

[0028] [Fig.8] is a block diagram of a method of assembling a part of fuselage of an aircraft including a method of integrating a floor module. Detailed description

[0029] A nose cone 1 of an aircraft comprising a floor module 2 and making it possible to illustrate the invention, is shown in [Fig. 1] and [Fig. 2] in a particular embodiment. The floor module 2 is adjustable, that is to say that it can be slightly adjusted, as explained below, so as to adapt, if necessary, to potential tolerance defects of the nose cone 1.

[0030] The nose cone 1 corresponds to the front part of the aircraft comprising at least the cockpit and, in general, also a fuselage part provided with the front side access doors of the aircraft.

[0031] The floor module 2 corresponds to a part of the floor of the aircraft intended to be fixed inside the nose cone 1. It comprises at least one frame formed, in particular, by rails and crosspieces on which floor panels and equipment such as seats or monuments (not shown in [Fig.l] and [Fig.2]) are intended to be fixed.

[0032] In the context of the present invention, the floor module 2 is particularly suitable for being installed in an aircraft nose cone, as described above. However, in other embodiments, the floor module 2 may be intended to be installed in another part of the aircraft fuselage, for example in a part of the fuselage located longitudinally more towards the middle of the aircraft, and more particularly above the wing box, or, according to another example, in a tail cone. By "fuselage part" is meant one or more consecutive sections forming a portion of the aircraft fuselage.

[0033] As shown in [Fig.l], we consider a plane PI formed by: - a longitudinal direction oriented along a longitudinal axis XX of the front tip 1 (and of the aircraft); and - a transverse direction oriented along a transverse axis YY orthogonal to the longitudinal axis XX.

[0034] The floor module 2 has a generally planar shape and is arranged in the front tip 1 so as to be substantially parallel to the plane PL. In [Fig.l], a vertical direction oriented along a vertical axis ZZ which is orthogonal to said plane PL has also been shown. The direction Z corresponds to a vertical direction when the aircraft is on the ground.

[0035] In a particular embodiment, shown from [Fig.l] to [Fig.3], the floor module 2 comprises a front sub-module 3 and a rear sub-module 4 arranged longitudinally relative to each other.

[0036] In the context of the present invention, the terms "front" and "rear" designate opposite directions in the longitudinal direction. The front direction, represented by an arrow A ([Fig.l]), is defined towards the front of the front tip 1, and the rear direction, represented by an arrow B ([Fig.l]), is defined towards the rear of the front tip 1.

[0037] Sub-module 3 corresponds to the front part of floor module 2, intended to be arranged towards the front end of nose cone 1. Sub-module 3 represents the part on which elements of the cockpit are intended to be installed.

[0038] Sub-module 4, for its part, corresponds to the rear part of floor module 2, which is arranged longitudinally at the rear of sub-module 3. Sub-module 4 represents the part on which equipment, such as seats or monuments, are intended to be installed.

[0039] The sub-modules 3 and 4 are arranged end to end and attached to each other to form the floor module 2. More specifically, as detailed in [Fig.2] and [Fig.3], the floor module 2 comprises a plurality of connecting elements 5 arranged between a rear end 6 of the sub-module 3 and a front end 7 of the sub-module 4 so as to connect said sub-modules 3 and 4 together.

[0040] The sub-module 3 comprises a grid-shaped structure comprising crosspieces, and in particular a rear crosspiece 8 arranged transversely to the rear end 6 of the sub-module 3. The rear crosspiece 8 is configured to allow the attachment of the connecting elements 5 to the sub-module 3 on the one hand and to carry out, in the usual manner, part of the attachment of the sub-module 3 to the fuselage body of the front tip 1 (by usual attachment means not shown) on the other hand.

[0041] The sub-module 4 also comprises a grid-shaped structure comprising rails 9 and crosspieces 10. The crosspieces 10 extend transversely across the sub-module 4. Each crosspiece 10 has at its ends fixing holes 11 configured to allow the sub-module 4 to be fixed to the fuselage body of the nose cone 1. The rails 9, for their part, are arranged on the crosspieces 10 and extend longitudinally relative to the sub-module 4 so that each rail 9 has an end 12 (circled in [Fig.2]) extending towards the front end 7 of the sub-module 4. The ends 12 are configured to allow the attachment of the connecting elements 5 to the sub-module 4.

[0042] In the particular embodiment, shown in [Fig. 2], the rails 9 do not all have the same length; some extend over the entire length of the sub-module 4 and others only over a part. Furthermore, in this particular embodiment, the structure of the sub-module 4 comprises other rails, similar to the rails 9, but which do not participate in the connection of the sub-modules 3 and 4.

[0043] As shown in [Fig. 3], the sub-modules 3 and 4 are arranged so that the end 12 of each rail 9 faces the crosspiece 8, substantially perpendicular to the latter. Each connecting element 5 provides the connection between the sub-modules 3 and 4, by being fixed to the crosspiece 8 on the one hand, and to one of the rails 9 on the other hand.

[0044] In the particular embodiment, shown in [Fig.3] and [Fig.4], each connecting element 5 comprises a first fixing lug 13 configured to be fixed integrally to the crosspiece 8. The fixing lug 13 comprises a support 14, in the form of a plate, arranged against a rear face 15 of the rear crosspiece 8. The support 14 is provided with holes 16 for the passage of usual fixing elements (not shown) such as bolts or rivets, through the support 14 and the crosspiece 8.

[0045] In addition, each connecting element 5 comprises a second fixing lug 17 configured to be fixedly fixed to one of the rails 9. The fixing lug 17 is formed of two symmetrical tabs 17A and 17B, which are arranged on either side of the corresponding rail 9 in the extension of said rail 9. In the particular embodiment considered, the rails 9 have an “I”-shaped section (IPN beam type) comprising a central wall 18. The tabs 17A and 17B are arranged on each side of the rail 9 against the central wall 18. The tabs 17A and 17B each comprise holes 19 for the passage of usual fixing elements (not shown) such as bolts or rivets, through said tabs 17A and 17B and the central wall 18.

[0046] Furthermore, each connecting element 5 comprises a connecting rod 20 configured to provide a connection between the fixing lugs 13 and 17. To do this, the connecting rod 20 is connected to each of the fixing lugs 13 and 17 by means of a joint. Thus, as described in detail below, the connecting elements 5 make it possible to connect the sub-modules 3 and 4 together, while allowing relative movement between said sub-modules 3 and 4.

[0047] In the particular embodiment, shown in [Fig.4], for each connecting element 5, a first end 21 of the connecting rod 20 is connected to the lug of fixing 13 by means of a first articulation 27 and a second end 24 of the connecting rod 20 is linked to the fixing lug 17 by means of a second articulation 28.

[0048] For the articulation 27, the fixing lug 13 comprises two walls 22 and 23 extending perpendicularly to the plate of the support 14 so as to form a projecting fork. The end 21 is mounted between the walls 22 and 23 so as to allow the arrangement of the articulation 27, as described below. In [Fig. 4], the walls 22 and 23 of the fixing lug 13 are shown in transparency for a better understanding of the arrangement of the articulation 27.

[0049] For the articulation 28, the fixing lug 17 comprises two walls 25 and 26 extending longitudinally in the extension, respectively, of the tabs 17A and 17B at the end 12 of the corresponding rail 9 so as to form a projecting fork. The end 24 of the connecting rod 20 is mounted between the walls 25 and 26 so as to allow the arrangement of the articulation 28.

[0050] In the particular embodiment of [Fig. 4], the articulation 27 is provided with an axis 29 arranged in a through manner between the walls 22 and 23 of the fixing lug 13 and the end 21 of the connecting rod 20. As shown in detail in [Fig. 5], the axis 29 comprises a head 30 arranged on the side of the wall 23 and configured to make a translational stop against said wall 23. Opposite the head 30, the axis 29 comprises a threaded end 31 projecting on the side of the wall 22.

[0051] Furthermore, the articulation 27 comprises a ball joint 32 sandwiched between two spacers 33 and 34, the assembly being mounted on the axis 29. The ball joint 32 is provided with a central bore for the passage of the axis 29. In addition, the ball joint 32 is mounted, at its periphery 39, in the connecting rod 20. To do this, the periphery 39 of the ball joint has a cylindrical shape set in a bore 40 ([Fig.4]) made in the end 21 of the connecting rod 20.

[0052] The spacers 33 and 34 are arranged on the axis 29 on each side of the ball joint 32. As shown in transparency in [Fig. 4], openings are provided in the walls 22 and 23 for the passage of the axis 29 and for receiving the spacers 33 and 34. Furthermore, the spacer 33 has, in particular, a shoulder 43 configured to come to bear against the wall 23.

[0053] The articulation 27 also comprises washers 35 and 36 and a nut 37 screwed to the threaded end 31 of the axis 29 to achieve the fixing of said articulation 27 between the walls 22 and 23 of the fixing lug 13. The washer 35 is interposed between the head 30 of the axis 29 and the wall 23, and the washer 36 is interposed between the nut 37 and the wall 22. In the particular embodiment of [Fig. 5], the nut 37 corresponds to a castellated nut which is locked, in the usual manner, by a split pin 38 when said nut 37 is screwed onto the axis 29 to fix the articulation 27.

[0054] The ball joint 32 and the spacers 33 and 34, thus mounted on the axis 29 between the walls 22 and 23, are configured to obtain a ball joint type connection between the connecting rod 20 and the fixing lug 13. Indeed, the ball joint 32 has, on either side, two hemispherical parts 41 and 42 facing, respectively, the spacer 33 and the spacer 34. In addition, the spacers 33 and 34 have shapes adapted to cooperate with these hemispherical parts 41 and 42 so as to allow rotations of the ball joint 32 according to three degrees of freedom.

[0055] In the particular embodiment considered in the present description, the articulation 28 is identical to the articulation 27 and it is arranged in a similar manner between the end 24 of the connecting rod 20 and the fixing lug 17. However, in other embodiments, the articulations 27 and 28 may be different from each other.

[0056] Thus, thanks to the connecting elements 5 described above, a floor module 2 is obtained formed by two sub-modules 3 and 4 which are structurally decoupled. By "structurally decoupled" is meant that the sub-modules 3 and 4, when connected together by the connecting elements 5, can be slightly displaced relative to each other, at least longitudinally and / or transversely.

[0057] In the embodiment described above, in which the joints 27 and 28 form ball-and-socket type connections, the connecting elements 5 allow relative movement in the longitudinal direction (XX) and relative movement in the transverse direction (YY). Consequently, it is possible to move the sub-modules 3 and 4 relative to each other back and forth and also laterally (i.e. transversely).

[0058] In addition, the connecting elements 5 also allow a transmission of forces between said sub-modules 3 and 4 in the vertical direction (ZZ) without generating relative movement. Thus, it is possible to carry out certain operations requiring the application of mechanical stresses to the floor module 2, such as for example the installation of monuments, without moving the sub-modules 3 and 4 relative to each other.

[0059] It will be noted that the configuration of the connecting elements 5, as described above, assumes a kinematics in which a longitudinal or transverse movement of one of the sub-modules 3 or 4 relative to the other implies a slight vertical relative movement. However, this vertical relative movement is negligible compared to the longitudinal and / or transverse movement. Consequently, it is considered that the connecting elements 5 do indeed prevent a relative movement in the vertical direction (ZZ) between the sub-modules 3 and 4.

[0060] The amplitude of the movements between the sub-modules 3 and 4, authorized by the connecting elements 5, depends on their dimensioning and in particular that of the connecting rods 20 and ball joints 32. In the preferred application considered, namely a floor module for a nose cone of an aircraft, the connecting elements 5 are configured to obtain a relative movement between the sub-modules 3 and 4 of the order of a few millimeters, for example up to 10 mm. In other embodiments, this amplitude may be greater than 10 mm.

[0061] The structural decoupling of the sub-modules 3 and 4 allows their relative positions to be adjusted longitudinally and transversely. This may allow slight adjustment to the overall geometry of the floor module 2 to adapt it to the fuselage portion on which it is intended to be installed. For example, in the context of the integration of the floor module 2 into a fuselage portion such as the nose cone 1, this may make it possible to overcome assembly difficulties related to alignment problems caused, for example, by tolerancing defects, as described in more detail below.

[0062] An additional advantage of the structural decoupling of the sub-modules 3 and 4 is to avoid transmitting unwanted forces between the front and rear parts of the floor module 2. Indeed, the connecting elements 5 are configured so that, when one of the sub-modules 3 or 4 is subjected to forces in the longitudinal direction (XX) and / or the transverse direction (YY), for example inertial forces, these forces are redirected entirely towards the fuselage of the aircraft, via the fixings of said sub-module 3 or 4, rather than being transmitted to the other sub-module.

[0063] In the embodiment described above, the articulations 27 and 28 are produced in a particular way in order to obtain ball-and-socket type connections. This configuration is not limiting and the articulations 27 and 28 can be produced in different ways. For example, in an alternative embodiment (not shown), the articulations 27 and 28 can be configured to obtain pivot-type connections, namely a rotational connection with a single degree of freedom, instead of ball joints.

[0064] The floor module 2, as described above, can be integrated into a fuselage portion of an aircraft, such as the nose cone 1, by implementing an integration method M shown schematically in [Fig.7] and [Fig.8]. The method M comprises a preliminary assembly step E1, a mounting step E2 and a fixing step E3.

[0065] In the context of the present invention, a fuselage part corresponds to a longitudinal portion of an aircraft (for example one or more fuselage sections), obtained by assembling several fuselage parts to form a fuselage body. In a preferred embodiment, shown in [Fig.6] and [Fig.7], the fuselage part corresponds to the front tip 1. This front tip 1 comprises a fuselage body 50 formed by assembling parts 51, 52 and 53 manufactured and assembled prior to the implementation of the method M.

[0066] Step E1 comprises the manufacture of the floor module 2. The sub-modules 3 and 4 are manufactured independently of each other. Then, they are assembled by being linked together by a plurality of connecting elements 5 so as to obtain the floor module 2.

[0067] Step E2 comprises the introduction of the floor module 2, obtained in step E1, into the fuselage body 50 of the nose cone 1. The introduction is carried out by inserting the floor module 2 from the rear of the nose cone 1, as illustrated by an arrow F in [Fig.7]. During step E2, fixing points of the floor module 2 are placed opposite fixing points of the fuselage body 50, provided for fixing the floor module 2. The fixing points of the fuselage body 50 are distributed over several of the parts 51, 52 and 53.

[0068] Step E3 comprises the fixing of the floor module 2 to the fuselage body 50. The sub-modules 3 and 4 of the floor module 2 are each fixed to one of the different parts 51, 52, 53.

[0069] This method M of integrating a floor module 2 into a fuselage part, such as the nose cone 1, is particularly suitable for being implemented in a method P of assembling said fuselage part. The method P, shown schematically in [Fig.7] and [Fig.8], comprises a succession E4 of steps E41, E42 and E43 of assembling fuselage parts and a step E5 of integrating the floor module 2.

[0070] The steps E41, E42 and E43, illustrated in [Fig.7], correspond to steps of assembling the parts 51, 52 and 53 to form the fuselage body 50. The number N of steps E41, ..., E4N of the sequence E4 depends, in particular, on the number of parts necessary to form the fuselage body 50. Also, in embodiments other than that of [Fig.7], the sequence E4 may comprise more than three steps.

[0071] Step E5 comprises the integration of the floor module 2 into the fuselage body 50 formed by the succession E4 of steps. This step E5 corresponds to the implementation of the method M as described above.

[0072] As in any assembly process, particularly for parts as large as fuselage parts, it is possible for tolerance defects to appear during the assembly of the parts 51, 52 and 53. Indeed, there may be slight deformations or slight offsets between the parts 51, 52 and 53, when they are assembled, which result in an approximate coincidence between the fixing points provided on the parts 51, 52 and 53 and the fixing points of said floor module 2. The assembly of the floor module 2 can then be complex and waste labor time.

[0073] Thanks to the floor module 2 and the method M of integrating said floor module 2, it is possible to overcome these difficulties. Indeed, the floor module 2 being adjustable, the sub-modules 3 and 4 can adapt to defects such as misalignments of the attachment points. Once one of the sub-modules, for example the sub-module 3, is attached to the fuselage part on which it is intended to be attached, the sub-module 4 can be adjusted by being slightly moved longitudinally and / or transversely as required. In this way, it is easy to adjust the position of the sub-module 4 so as to align the attachment points of the latter with the attachment points of the fuselage part on which it is to be attached, even if the fuselage body 50 has tolerance defects.

[0074] The floor module 2 as described above, allowing the implementation of method M and method P, has numerous advantages. In particular: - it allows sub-modules 3 and 4 to be structurally decoupled so as to allow relative movement between them, longitudinally and transversely; - it helps to overcome assembly difficulties linked to defects appearing during the assembly stages; - it allows the transmission of forces between sub-modules 3 and 4 vertically without generating relative movement between said sub-modules 3 and 4; - it allows the transmission of forces between sub-modules 3 and 4 to be decoupled longitudinally and transversely; - it simplifies the integration of floor module 2 into a fuselage section and thus reduces costs, particularly by saving labor time; and - it is simple to implement and inexpensive since it does not require significant modifications compared to a standard floor module.

Claims

Claims

1. Floor module for a fuselage section of an aircraft, in particular for a nose cone (1), said floor module (2) having a longitudinal direction (XX), characterized in that it comprises at least one sub-module (3) called front and one sub-module (4) called rear arranged longitudinally with respect to each other, front and rear being defined in opposite directions along the longitudinal direction (XX) of the floor module (2), said sub-modules (3, 4) being linked together by a plurality of linking elements (5) configured to allow relative movement between said sub-modules (3, 4) at least along the longitudinal direction (XX) and to allow the transmission of forces between said sub-modules (3, 4) along a vertical direction (ZZ) substantially orthogonal to the floor module (2), without generating relative movement between said sub-modules (3, 4).

2. Floor module according to claim 1, characterized in that each of said connecting elements (5) comprises at least two fixing lugs (13, 17) arranged, respectively, at a front end (7) of the rear sub-module (4) and at a rear end (6) of the front sub-module (3), and a connecting rod (20) provided with two articulations (27, 28), said connecting rod (20) being arranged between said fixing lugs (13, 17) being linked to each of them by one of its articulations (27, 28).

3. Floor module according to claim 2, characterized in that, for each of said connecting elements (5), one of said fixing lugs (17) is fixed integrally to one end (12) of a rail (9) of the rear sub-module (4) and the other fixing lug (13) is fixed integrally along a rear cross member (8) of the front sub-module (3).

4. Floor module according to one of claims 2 and 3, characterized in that each of said articulations (27, 28) of the connecting rod (20) of each of said connecting elements (5) comprises at least one articulation axis (29) arranged in the corresponding fixing lug (13, 17) and on which the connecting rod (20) is mounted so as to form at least one simple pivot type connection between said connecting rod (20) and the corresponding fixing lug (13, 17).

5. Floor module according to claim 4, characterized in that the connecting elements (5) are configured to also allow relative movement between the sub-modules (3, 4) in a transverse direction (YY) substantially orthogonal to the longitudinal direction (XX) and substantially parallel to the floor module (2).

6. Floor module according to claim 5, characterized in that each of said articulations (27, 28) of the connecting rod (20) of each of said connecting elements (5) comprises at least one ball joint (32) mounted on the articulation axis (29) and sandwiched between two spacers (33, 34) having a shape adapted so as to form a ball joint type connection between said connecting rod (20) and the corresponding fixing lug (13, 17).

7. Fuselage part of an aircraft comprising at least one fuselage body (50) formed by a plurality of fuselage parts (51, 52, 53), characterized in that it comprises at least one floor module (2) according to any one of claims 1 to 6, arranged inside the fuselage body (50), the front sub-module (3) and the rear sub-module (4) of the floor module (2) each being fixed to different fuselage parts (51, 52, 53).

8. Fuselage part according to claim 7, characterized in that it corresponds to a front tip (1) of the aircraft.

9. Method for integrating a floor module according to any one of claims 1 to 6 into a fuselage part of an aircraft according to one of claims 7 and 8, characterized in that it comprises at least the following series of steps: - a preliminary assembly step (El) for connecting together the front sub-module (3) and the rear sub-module (4) using a plurality of connecting elements (5) so as to obtain said floor module (2); - a mounting step (E2) for introducing the floor module (2) obtained in the preliminary assembly step (El) into the fuselage body (50) of the fuselage part; and - a fixing step (E3) for fixing the floor module (2) to said fuselage body (50), the front sub-module (3) and the rear sub-module (4) each being fixed to different fuselage parts (51, 52, 53).

10. Method for assembling a fuselage part of an aircraft, in particular a nose cone (1), comprising at least the following sequence of steps: - a succession (E4) of assembly steps (E41, E42, E43) for assembling a plurality of fuselage parts (51, 52, 53) of the fuselage portion so as to obtain a fuselage body (50); and - an integration step (E5) for integrating at least one floor module (2) into the fuselage body obtained in the succession (E4) of assembly steps (E41, E42, E43), characterized in that the integration step (E5) corresponds to the integration method (M) according to claim 9.

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