Aerodynamic profile comprising at least one nested trailing edge, aircraft comprising at least one such aerodynamic profile

Abstract

Aerodynamic profile comprising at least one nested trailing edge, aircraft comprising at least one such aerodynamic profile The invention relates to an aerodynamic profile comprising upper and lower walls (40, 42) as well as at least one profile (48) forming a trailing edge which comprises upper and lower wings (50, 52) cooperating respectively with the upper and lower walls (40, 42) and having front edges (50.1, 52.1) positioned between the upper and lower walls (40, 42), each upper or lower wing (50, 52) comprising at least one shape (54, 58) which cooperates with at least one complementary shape (56, 60) secured to the corresponding upper or lower wall (40, 42). According to the invention, the profile (48) is configured to deform elastically to allow insertion of the front edges (50.1, 52.1) upper and lower wings (50, 52) between the upper and lower walls (40, 42) and obtain a connection by interlocking. The invention also relates to an aircraft comprising at least one such aerodynamic profile. Figure 5.

Description

Title of the invention: Aerodynamic profile comprising at least one nested trailing edge, aircraft comprising at least one such aerodynamic profile

[0001] The present application relates to an aerodynamic profile comprising at least one nested trailing edge as well as to an aircraft comprising at least one such aerodynamic profile.

[0002] As illustrated in [Fig.l], an aircraft 10 comprises a fuselage 12, wings 14 positioned on either side of the fuselage 12 and a tailplane 16 positioned at the rear end of the fuselage 12. The wings 14 and the tailplane 16 comprise movable ailerons 18 at the rear. According to an embodiment visible in [Fig.2], a fin 18 comprises an upper wall 20, also called the extrados, having a first rear edge 20.1, a lower wall 22, also called the intrados, having a second rear edge 22.1 and a trailing edge 24 connecting the first and second rear edges 20.1, 22.1 of the upper and lower walls 20, 22.

[0003] For the present application, an aerodynamic profile means a wing, a fin or any other element of the aircraft having a trailing edge.

[0004] According to a first embodiment visible in [Fig. 3], an aerodynamic profile 26 comprises an upper wall 20 having a first rear edge 20.1, a lower wall 22 having a second rear edge 22.1 as well as a trailing edge 24 in the form of a U-shaped profile 28 having first and second wings 28.1, 28.2 between which the first and second rear edges 20.1, 22.1 are positioned close to the upper and lower walls 20, 22. The aerodynamic profile 26 comprises a large number of fixing elements 30 for connecting the U-shaped profile 28 to the upper and lower walls 20, 22.

[0005] To obtain aerodynamic continuity, the upper and lower walls 20, 22 each comprise a groove 20.2, 22.2 so that the external faces F28.1, F28.2 of the first and second wings 28.1, 28.2 are flush with the external faces F20, F22 of the upper and lower walls 20, 22. In other words, the ends of the upper and lower walls 20, 22 move closer to each other so that the ends of the upper and lower walls 20, 22 are positioned between the first and second wings 28.1, 28.2 and the external faces F28.1, F28.2 of the first and second wings 28.1, 28.2 are flush with the external faces F20, F22 of the upper and lower walls 20, 22 beyond said ends. The distance between the ends of the upper and lower walls 20, 22 decreases so that the first and second wings 28.1, 28.2 surround said ends and the external faces F28.1, F28.2 of the first and second wings 28.1, 28.2 are flush with the external faces F20, F22 of the upper and lower walls 20, 22 beyond said ends.

[0006] The presence of a large number of fixing elements 30 leads to an increase in the mass of the aerodynamic profile 26, its cost and the duration of its assembly. The presence of grooves 20.2, 22.2 at the level of the upper and lower walls 20, 22 tends to complicate the manufacturing process of said walls 20, 22 and to increase their production cost.

[0007] According to a second embodiment visible in [Fig.4], an aerodynamic profile 26' comprises a trailing edge 24 in the form of a profile 28' having first and second wings 28.1', 28.2' inserted between the upper and lower walls 20, 22.

[0008] According to this second embodiment, the profile 28' has a reinforcement 28.3', connecting the first and second wings 28.1', 28.2', to stiffen it.

[0009] As for the first embodiment, the aerodynamic profile 26' comprises a large number of fixing elements 30 for connecting the profile 28' to the upper and lower walls 20, 22. The presence of a large number of fixing elements 30 leads to an increase in the mass of the aerodynamic profile 26', its cost and the duration of its assembly.

[0010] In these first and second embodiments, in the event of damage to the aircraft at a profile, repairs to the profile are lengthy since it is necessary to remove the fasteners and then make cuts around the profile. These repairs are not optimized either from an aerodynamic point of view or in terms of associated time and cost.

[0011] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0012] To this end, the invention relates to an aerodynamic profile comprising upper and lower walls each having a rear edge, an external face and an internal face as well as at least one profile having an upper wing cooperating with the upper wall and a lower wing cooperating with the lower wall, each of the upper and lower wings extending between front and rear edges and having an external face oriented towards the corresponding upper or lower wall, the front edges of the upper and lower wings being positioned between the upper and lower walls.

[0013] According to the invention, the upper wing comprises at least one first shape cooperating with at least one second shape, of a shape complementary to the first shape, secured to the upper wall. In addition, the lower wing comprises at least one third shape cooperating with at least one fourth shape, of a shape complementary to the third shape, secured to the lower wall.

[0014] According to the invention, the profile is configured to deform elastically between an undeformed state in which the front edges of the upper and lower wings are spaced apart by a first gap and a deformed state in which the front edges of the upper and lower wings are spaced apart by a second gap less than the first gap.

[0015] In the deformed state of the profile, the second gap is configured to allow insertion of the front edges of the upper and lower flanges between the upper and lower walls.

[0016] This solution makes it possible to maintain the assembled profile by interlocking thanks to the complementary shapes of the walls and the upper and lower wings. Thus, it is possible to significantly reduce the number of fixing elements necessary to maintain the assembled profile or even to eliminate them, which results in a reduction in the mass of the aerodynamic profile, costs and the duration of its assembly. This solution also makes it possible to reduce the repair time of the profile, in the event of damage to it, by simplifying the assembly / disassembly of said profile.

[0017] According to another characteristic, the front edges of the upper and lower wings are spaced apart by a third gap less than or equal to the first gap and greater than the second gap.

[0018] According to another characteristic, each first or third shape is a hollow shape relative to the external face of the upper or lower wing. In addition, each second or fourth shape is a protruding shape relative to the internal face of the upper or lower wall.

[0019] According to another characteristic, the upper or lower wing comprises at least one first or third hollow shape which extends over the entire length of the profile. For example, the upper or lower wing comprises a single first or third hollow shape which extends over the entire length of the profile.

[0020] According to another characteristic, the upper or lower wall comprises at least one second or fourth projecting shape which extends over the entire length of the airfoil. For example, the upper or lower wall comprises a single second or fourth projecting shape which extends over the entire length of the airfoil or several second or third projecting shapes distributed over the length of the airfoil.

[0021] According to another characteristic, the profile is made of a material capable of deforming elastically.

[0022] According to another characteristic, the upper and lower wings each have at least one reduction in thickness to allow at least a portion of each of the upper and lower wings to deform elastically.

[0023] According to another characteristic, the internal faces of the upper and lower walls converge towards the rear edges and form between them an angle greater than or equal to 3°.

[0024] According to another characteristic, each profile is obtained by extrusion or from an extruded profile, for example cut from a very long extruded profile.

[0025] The invention also relates to an aircraft comprising at least one aerodynamic profile according to one of the preceding characteristics.

[0026] The invention also relates to a method of assembling an aerodynamic profile according to one of the preceding characteristics. The method comprises: a. a step of elastically deforming the profile so as to obtain the profile in a deformed state, in which the front edges of the upper and lower flanges are spaced apart by a second gap less than the first gap, b. a step of inserting the front edges of the upper and lower wings between the upper and lower walls so that the first and third shapes are arranged facing the second and fourth shapes respectively, c. a step of releasing the elastic deformation of the profile so that the first and third shapes cooperate respectively with the second and fourth shapes, the profile being in a deformed state in which the front edges of the upper and lower flanges are spaced apart by a third gap less than or equal to the first gap and greater than the second gap.

[0027] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which:

[0028] [Fig-1] is a perspective view of an aircraft,

[0029] [Fig.2] is a perspective view of an aerodynamic profile illustrating a mode of implementation of the prior art,

[0030] [Fig.3] is a cross-section of a rear portion of an aerodynamic profile illustrating a first embodiment of the prior art,

[0031] [Fig.4] is a cross-section of a rear portion of an aerodynamic profile illustrating a second embodiment of the prior art,

[0032] [Fig.5] is a schematic representation of the different stages of assembly of a aerodynamic profile illustrating an embodiment of the invention.

[0033] According to one embodiment, an aircraft comprises at least one aerodynamic profile 38 which comprises an upper wall 40 having a first rear edge 40.1 as well as a lower wall 42 having a second rear edge. 42.1. According to one configuration, the first and second rear edges 40.1, 42.1 are substantially parallel to each other and extend in a longitudinal direction.

[0034] The upper and lower walls 40, 42 respectively comprise external faces F40, F42 as well as internal faces F40', F42'.

[0035] According to a configuration given by way of example, the aerodynamic profile 38 comprises a reinforcement 44, connecting the upper and lower walls 40, 42, which extends in the longitudinal direction while being distant from the first and second rear edges 40.1, 42.1.

[0036] According to one application, the aerodynamic profile 38 is an aircraft fin positioned at the rear of a wing or empennage.

[0037] Of course, the invention is not limited to this application.

[0038] The aerodynamic profile 38 comprises a trailing edge 46 connecting the first and second rear edges 40.1, 42.1 of the upper and lower walls 40, 42. This trailing edge 46 comprises at least one profile 48 which has a U-shaped or V-shaped cross-section (perpendicular to the longitudinal direction) which is substantially constant in the longitudinal direction. According to one configuration, the trailing edge 46 comprises a single profile 48 which extends over the entire length of the aerodynamic profile 38 or several profiles 48 positioned end to end in the longitudinal direction, with substantially identical cross-sections.

[0039] When assembled, the profile 48 comprises an upper wing 50 cooperating with the upper wall 40 as well as a lower wing 52 cooperating with the lower wall 42. Each of the upper and lower wings 50, 52 extends between a front edge 50.1, 52.1 and a rear edge 50.2, 52.2, the rear edges 50.2, 52.2 of the upper and lower wings 50, 52 being directly or indirectly connected to each other.

[0040] The upper wing 50 comprises a first overlapping portion 50.3, which extends from the front edge 50.1 of the upper wing 50, positioned opposite a first rear zone 40.2 of the upper wall 40 which extends from the first rear edge 40.1 of the upper wall 40.

[0041] In parallel, the lower wing 52 comprises a second overlapping part 52.3, which extends from the front edge 52.1 of the lower wing 52, positioned opposite a second rear zone 42.2 of the lower wall 42 which extends from the second rear edge 42.1 of the lower wall 42.

[0042] The profile 48 is configured to occupy a disassembled state visible in part (A) of [Fig.5] and an assembled state visible in part (D) of [Fig.5] in which the front edges 50.1, 52.1 and the overlapping portions 50.3, 52.3 of the upper and lower wings 50, 52 are positioned between the upper and lower walls 40, 42. Each of the upper and lower wings 50, 52 comprises an external face F50, F52 oriented towards the corresponding upper or lower wall 40, 42 when the profile 48 is in the assembled state.

[0043] According to one characteristic, the upper wing 50 comprises at least one first shape 54, among hollow and projecting shapes, configured to cooperate with at least one second shape 56, different from the first shape 54, among hollow and projecting shapes, secured to the upper wall 40. The lower wing 52 comprises at least one third shape 58, among hollow and projecting shapes, configured to cooperate with at least one fourth shape 60, different from the third shape 58, among hollow and projecting shapes, secured to the lower wall 42. The first and second shapes 54, 56 are complementary. The same is true of the third and fourth shapes 58, 60.

[0044] This configuration of the wings and the upper and lower walls 40, 42, 50, 52 makes it possible to obtain a connection by interlocking between the profile 48 and the upper and lower walls 40, 42.

[0045] According to one configuration, each first or third shape 54, 58 is a hollow shape relative to the external face F50 of the upper or lower wing 50, 52, located at the overlapping portion 50.3, 52.3 of the upper or lower wing 50, 52. In addition, each second or fourth shape 56, 60 is a protruding shape relative to the internal face F40', F42' of the upper or lower wall 40, 42, located at the rear zone 40.2, 42.2 of the upper or lower wall 40, 42.

[0046] According to one embodiment, the upper wing 50 comprises a single first hollow shape 54 which extends over the entire length of the profile 48 (dimension taken in a direction parallel to the first and second front edges 50.1, 52.1 of the profile 48). In addition, the upper wall 40 comprises a single second protruding shape 56 which extends over the entire length of the aerodynamic profile 38 (dimension taken in a direction parallel to the first and second rear edges 40.1, 42.1 of the aerodynamic profile 38) or several second protruding shapes 56 distributed over the length of the aerodynamic profile 38.

[0047] The lower wing 52 comprises a single third hollow shape 58 which extends over the entire length of the profile 48. In addition, the lower wall 42 comprises a single fourth projecting shape 60 which extends over the entire length of the aerodynamic profile 38 or several fourth projecting shapes 60 distributed over the length of the aerodynamic profile 38.

[0048] According to a feature of the invention, the profile 48 is configured to deform elastically between an undeformed state, visible in part (A) of [Fig. 5], in which the front edges 50.1, 52.1 of the upper and lower wings 50, 52 are spaced apart by a first gap, and a deformed state, visible in parts (B) and (C), in in which the front edges 50.1, 52.1 of the upper and lower wings 50, 52 are spaced apart by a second gap less than the first gap allowing insertion of the front edges 50.1, 52.1 of the upper and lower wings 50, 52 between the upper and lower walls 40, 42. When the profile 48 is in the assembled state, the front edges 50.1, 52.1 of the upper and lower wings 50, 52 are spaced apart by a gap less than or equal to the first gap.

[0049] According to one embodiment, the profile 48 is made of a metallic material capable of deforming elastically and / or the upper and lower wings 50, 52 each have at least one reduction in thickness 50.4, 52.4 to allow at least a portion of each of the upper and lower wings 50, 52 to deform elastically.

[0050] Alternatively, the profile 48 could be made of composite material or any other material.

[0051] According to one production method, each profile 48 is obtained by extrusion or cut from a very long extruded profile.

[0052] According to one configuration, when the profile 48 is in the assembled state and the first, second, third and fourth shapes 54, 56, 58, 60 cooperate with each other, the profile 48 is in the deformed state, the front edges 50.1, 52.1 of the upper and lower wings 50, 52 being spaced apart by a third gap less than the first gap and greater than the second gap. According to this configuration, the upper and lower wings 50, 52 are compressed between the upper and lower walls 40, 42 when the profile 48 is in the assembled state. This configuration makes it possible to reinforce the retention of the upper and lower wings 50, 52 between the upper and lower walls 40, 42.

[0053] According to one embodiment, the internal faces F40', F42' of the upper and lower walls 40, 42 converge towards the first and second rear edges 40.1, 42.1, at the rear zones 40.2, 42.2 of the upper and lower walls 40, 42, and form between them an angle greater than or equal to 3°. This embodiment makes it possible to reinforce the retention of the upper and lower wings 50, 52 between the upper and lower walls 40, 42.

[0054] As illustrated in part (B) of [Fig. 5], the upper and lower wings 50, 52 are deformed so as to bring the front edges 50.1, 52.1 of said upper and lower wings 50, 52 closer together. Therefore, as illustrated in part (C) of [Fig. 5], the upper and lower wings 50, 52 being maintained in the deformed state, it is possible to introduce them between the upper and lower walls 40, 42 until the first and third shapes 54, 58 can cooperate with the second and fourth shapes 56, 60. When the first and third shapes 54, 58 are correctly positioned relative to the second and fourth shapes 56, 60, the upper wings and lower 50, 52 are released, as illustrated in part (D) of [Fig.5]. The first, second, third and fourth forms 54, 56, 58, 60 cooperate with each other and make it possible to keep the aerodynamic profile 38 and the profile 48 assembled.

[0055] According to one embodiment, the aerodynamic profile 38 comprises, in the extension of at least one of the first and second rear edges 40.1, 42.1, at least one filling material 62, such as mastic for example, to ensure continuity of the external faces F40, F42, F50, F52 of the walls and of the upper and lower wings 40, 42, 50, 52 in order to limit aerodynamic disturbances.

[0056] According to one operating mode, a method of assembling a profile 48 comprises: a. a step of elastic deformation of the profile 48 so as to obtain the profile 48 in a deformed state, in which the front edges 50.1, 52.1 of the upper and lower wings 50, 52 are spaced apart by a second gap less than the first gap, b. a step of inserting the front edges 50.1, 52.1 of the upper and lower wings 50, 52 between the upper and lower walls 40, 42 so that the first and third shapes 54, 58 are arranged facing respectively the second and fourth shapes 56, 60, c. a step of releasing the elastic deformation of the profile 48 so that the first and third shapes 54, 58 cooperate respectively with the second and fourth shapes 56, 60, the profile 48 being in a deformed state in which the front edges 50.1, 52.1 of the upper and lower wings 50, 52 are spaced apart by a third gap less than or equal to the first gap and greater than the second gap.

[0057] Whatever the embodiment, the geometry and / or the shapes of the upper and lower wings 50, 52 make it possible to keep the latter nested between the upper or lower walls 40, 42 so that it is possible to greatly reduce the number of fixing elements necessary to connect the profile 48 to the upper and lower walls 40, 42 of the aerodynamic profile 38, or even to eliminate them. Thus, it is possible to simplify the method of assembling the aerodynamic profiles 38, to reduce the assembly costs and their mass.

[0058] According to another advantage, this solution makes it possible to simplify the disassembly of each profile 48 since a small number of fixing elements must be disassembled.

Claims

Claims

1. Aerodynamic profile comprising upper and lower walls (40, 42) each having a rear edge (40.1, 42.1), an outer face (F40, F42) and an inner face (F40', F42') as well as at least one profile (48) having an upper wing (50) cooperating with the upper wall (40) and a lower wing (52) cooperating with the lower wall (42), each of the upper and lower wings (50, 52) extending between front and rear edges (50.1, 50.2, 52.1, 52.2) and having an outer face (F50, F52) oriented towards the corresponding upper or lower wall (40, 42), the front edges (50.1, 52.1) upper and lower wings (50, 52) being positioned between the upper and lower walls (40, 42); characterized in that the upper wing (50) comprises at least one first shape (54) cooperating with at least one second shape (56), of complementary shape to the first shape (54), integral with the upper wall (40), in that the lower wing (52) comprises at least one third shape (58) cooperating with at least one fourth shape (60), of complementary shape to the third shape (58), integral with the lower wall (42) and in that the profile (48) is configured to deform elastically between an undeformed state in which the front edges (50.1, 52.1) of the upper and lower wings (50, 52) are spaced apart by a first gap and a deformed state in which the front edges (50.1, 52.1) of the upper and lower wings (50, 52) are spaced apart by a second gap less than the first gap.

2. Aerodynamic profile according to the preceding claim, characterized in that the front edges (50.1, 52.1) of the upper and lower wings (50, 52) are spaced apart by a third gap less than or equal to the first gap and greater than the second gap.

3. Aerodynamic profile according to one of the preceding claims, characterized in that each first or third shape (54, 58) is a hollow shape relative to the external face (F50) of the upper or lower wing (50, 52) and in that each second or fourth shape (56, 60) is a protruding shape relative to the internal face (F40') of the upper or lower wall (40, 42).

4. Aerodynamic profile according to the preceding claim, characterized in that the profile (48) has a length corresponding to a dimension taken in a direction parallel to the front edges (50.1, 52.1) of the upper and lower wings (50, 52) and in that the upper or lower wing (50, 52) comprises at least a first or third hollow shape (54, 58) which extends over the entire length of the profile (48).

5. Aerodynamic profile according to the preceding claim, characterized in that the aerodynamic profile (38) has a length corresponding to a dimension taken in a direction parallel to the rear edges (40.1, 42.1) of the upper and lower walls (40, 42) and in that the upper or lower wall (40, 42) comprises at least one second or fourth projecting shape (56) which extends over the entire length of the aerodynamic profile (38).

6. Aerodynamic profile according to one of the preceding claims, characterized in that the profile (48) is made of a material capable of deforming elastically.

7. Aerodynamic profile according to one of the preceding claims, characterized in that the upper and lower wings (50, 52) each have at least one reduction in thickness (50.4, 52.4) to allow at least a portion of each of the upper and lower wings (50, 52) to deform elastically.

8. Aerodynamic profile according to one of the preceding claims, characterized in that the internal faces (F40', F42') of the upper and lower walls (40, 42) converge in the direction of the rear edges (40.1, 42.1) and form between them an angle greater than or equal to o°

9. J. Aircraft comprising at least one aerodynamic profile according to one of the preceding claims.

10. A method of assembling an aerodynamic profile according to one of claims 1 to 8, characterized in that the method comprises: a. a step of elastically deforming the profile (48) so as to obtain the profile (48) in a deformed state in which the front edges (50.1, 52.1) of the upper and lower wings (50, 52) are spaced apart by a second gap less than the first gap, b. a step of inserting the front edges (50.1, 52.1) of the upper and lower wings (50, 52) between the upper and lower walls (40, 42) so that the first and third shapes (54, 58) are arranged facing respectively the second and fourth shapes (56, 60), c. a step of releasing the elastic deformation of the profile (48) so that the first and third shapes (54, 58) cooperate respectively with the second and fourth shapes (56, 60), the profile (48) being in a deformed state in which the front edges (50.1, 52.1) of the upper and lower wings (50, 52) are spaced apart by a third gap less than or equal to the first gap and greater than the second gap.

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