Aircraft wing comprising at least one flap controlled by at least one kinematic chain passing through a spar

Abstract

Aircraft wing comprising at least one flap controlled by at least one kinematic chain passing through a spar The invention relates to an aircraft wing comprising: an aerodynamic envelope (34), at least one structure (32) which comprises at least one spar (32.2) delimiting with the aerodynamic envelope (34) first and second zones (Z30, Z30') respectively located on either side of the spar (32.2), the latter comprising at least one opening (46) communicating the first and second zones (Z30, Z30'), at least one flap (40) connected to the structure (32) by at least one main pivot axis (42) located in the second zone (Z30'), at least one kinematic chain (44), configured to pivot the flap (40) around the main pivot axis (A42), which extends in the first and second zones (Z30, Z30') and passes through the spar (32.2) via opening (46). Figure 4

Description

Title of the invention: Aircraft wing comprising at least one flap controlled by at least one kinematic chain passing through a spar

[0001] The present application relates to an aircraft wing comprising at least one flap controlled by at least one kinematic chain passing through a spar as well as to an aircraft comprising at least one such wing.

[0002] According to an embodiment visible in [Fig.l], an aircraft 10 comprises a fuselage 12, wings 14 positioned on either side of the fuselage 12 as well as a tailplane 16 comprising a vertical stabilizer 16.1 (also called a tail fin) and horizontal stabilizers 16.2, 16.2 positioned on either side of the vertical stabilizer 16.1.

[0003] As illustrated in [Fig.2], each wing 14 comprises a first end 14.1 connected to the fuselage 12, a second end 14.2 distant from the fuselage 12 as well as leading and trailing edges 14.3, 14.4, connecting the first and second ends 14.1 and 14.2, positioned respectively at the front and rear of the wing 14. The wing 14 also has upper and lower faces F14, F14' (also called extrados and intrados) connecting the leading and trailing edges 14.3, 14.4.

[0004] Structurally, each wing 14 comprises a structure 18 which has front and rear spars 18.1, 18.2, transverse reinforcements which connect the front and rear spars 18.1, 18.2 as well as upper and lower walls 20.1, 20.2, supported by the structure 18, which form an aerodynamic envelope of the wing 14.

[0005] According to one configuration, the wing 14 comprises a central zone Z14, delimited by the front and rear spars 18.1, 18.2 as well as by the upper and lower walls 20.1, 20.2, adapted to contain or form a fuel tank.

[0006] The wing 14 comprises at least one flap 22 connected to the structure 18 by a pivoting connection 24 which has a pivot axis A24 substantially parallel to the rear spar 18.2. According to one configuration, the flap 22 is positioned at the rear of the rear spar 18.2 and extends to the trailing edge 14.4. In addition, the wing 14 comprises actuators 26 for controlling the pivoting movement of the flap 22 about the pivot axis A24, these actuators being positioned in a rear zone Z14' delimited by the rear spar 18.2, the pivot axis A24 as well as the upper and lower walls 20.1, 20.2.

[0007] Given the tapered aerodynamic profile of the wing 14, this rear zone Z14' has a reduced cross-section (perpendicular to the rear spar 18.2). Consequently, it is generally necessary to provide several actuators 26 compact to control the same shutter. Even if each actuator 26 is compact, providing several for each shutter 22 leads to a significant mass for all the actuators 26.

[0008] According to another problem, to improve the aerodynamic performance of the aircraft, the wings 14 tend to have a profile that is as tapered as possible, which tends to complicate the integration of the actuators 26 in a rear zone Z14' of increasingly reduced cross sections. Furthermore, even if this rear zone Z14' has a reduced cross section compared to the central zone Z14, insofar as it extends over the entire length of the wing 14, it has a significant volume that could be used for other functions such as fuel storage for example.

[0009] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0010] To this end, the invention relates to an aircraft wing comprising: a. an aerodynamic envelope, b. at least one structure which comprises at least one spar delimiting with the aerodynamic envelope first and second zones respectively located on either side of the spar, c. at least one flap, d. at least one pivoting connection, located in the second zone, which connects the flap and the structure and has a main pivot axis, e. at least one drive train configured to pivot the flap about the main pivot axis.

[0011] According to the invention, the spar comprises at least one opening acting as communicate the first and second zones. In addition, the drive train extends into the first and second zones and passes through the side member via the opening.

[0012] The first zone corresponding to the central zone of a wing, it has a greater thickness than that of the second zone. Consequently, the kinematic chain can include larger and therefore more powerful actuators. Thus, it is possible to reduce the number of actuators and therefore the mass of the actuators present in a wing. Furthermore, the available volume being larger, it is possible to house electromechanical type linear actuators there. Finally, this solution makes it possible to declutter the second zone.

[0013] According to another characteristic, the kinematic chain comprises at least one linear actuator positioned in the first zone and connected to the structure as well as at least one first connecting rod positioned in the first and second zones, connected to the flap and passing through the spar via the opening.

[0014] According to another characteristic, the linear actuator comprises first and second ends, the first end being connected by a first articulation to the structure and / or to the aerodynamic envelope. In addition, the first link extends between first and second ends, the first end being connected by a second articulation to the flap, the second end of the first link being connected to the second end of the linear actuator, the first and second articulations respectively having first and second secondary pivot axes parallel to the main pivot axis.

[0015] According to another characteristic, the kinematic chain comprises at least one second connecting rod, a third articulation connecting the second connecting rod to the structure and / or the aerodynamic envelope as well as at least one fourth articulation connecting the second connecting rod; the linear actuator and the first connecting rod, the third and fourth articulations respectively having third and fourth secondary pivot axes parallel to the main pivot axis.

[0016] According to another characteristic, the second connecting rod comprises first and second branches which each have first and second ends, the first ends of the first and second branches being rigidly connected to each other, the third articulation being located at the first ends of the first and second branches, the fourth articulation being located at the second end of the first branch and connecting the second end of the linear actuator and the second end of the first branch. In addition, the kinematic chain comprises a fifth articulation located at the second end of the second branch and connecting the second end of the first connecting rod and the second end of the second branch, the fifth articulation having a fifth secondary pivot axis parallel to the main pivot axis.

[0017] According to another characteristic, the first and second branches form an angle of between 15 and 45°.

[0018] According to another characteristic, the first and second branches have equal lengths.

[0019] According to another characteristic, the main pivot axis and the second secondary pivot axis are separated by a distance substantially equal to the lengths of the first and second branches.

[0020] According to another characteristic, the aerodynamic envelope comprises at least one opening opening into the first or second zone and closed by a removable cover.

[0021] According to another characteristic, the wing comprises at least one partition in at least the first zone separating a first compartment configured to store fuel and a second dry compartment configured to house a part of the drive train.

[0022] The invention also relates to an aircraft comprising at least one wing according to one of the preceding characteristics.

[0023] 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:

[0024] [Fig-1] is a perspective view of an aircraft,

[0025] [Fig.2] is a schematic cross-section of a wing illustrating a mode of rea prior art,

[0026] [Fig.3] is a schematic top view of a wing illustrating an embodiment of the invention,

[0027] [Fig.4] is a schematic cross-section of a wing and a chain here nematic illustrating an embodiment of the invention,

[0028] [Fig.5] is a section along the broken line VV of [Fig.4] of a part of a kinematic chain illustrating an embodiment of the invention,

[0029] [Fig.6] is a schematic representation of the different positions occupied by characteristic points of the kinematic chain visible in Figures 4 and 5, illustrating an embodiment of the invention,

[0030] [Fig.7] is a schematic cross-section of a wing illustrating a mode of rea lization of the invention,

[0031] [Fig.8] is a section along line VIII-VIII visible in [Fig.4] of a three-point connecting rod illustrating an embodiment of the invention,

[0032] [Fig.9] is a perspective view of a three-point link illustrating a mode of realization of the invention,

[0033] [Fig. 10] is a perspective view of a yoke supporting a three-point link illustrating one embodiment of the invention.

[0034] According to an embodiment visible in Figures 3 and 4, a wing 30 of an aircraft comprises a first end 30.1 connected to the fuselage of the aircraft, a second end 30.2 distant from the fuselage as well as leading and trailing edges 30.3, 30.4, connecting the first and second ends 30.1 and 30.2, positioned respectively at the front and rear of the wing 30. The wing 30 also comprises upper and lower faces F30, F30' (also called extrados and intrados) connecting the leading and trailing edges 30.3, 30.4.

[0035] For the remainder of the description, a longitudinal direction is a direction which extends between the first and second ends 30.1, 30.2, approximately parallel to the leading and trailing edges 30.3, 30.4. A transverse plane is a plane perpendicular to the longitudinal direction.

[0036] Structurally, each wing 30 comprises a structure 32 comprising front and rear side members 32.1, 32.2 and transverse reinforcements which connect the front and rear side members 32.1, 32.2 as well as an aerodynamic envelope 34, supported by the structure 32, comprising first and second walls 34.1, 34.2 whose outer surfaces correspond respectively to the upper and lower faces F30, F30', called extrados and intrados.

[0037] According to one embodiment, each front or rear spar 32.1, 32.2 comprises a core 36 which extends between first and second wings 38.1, 38.2 connected respectively to the first and second walls 34.1, 34.2.

[0038] The wing 30 comprises a central zone Z30 delimited by the front and rear spars 32.1, 32.2 as well as the first and second walls 34.1, 34.2, the central zone Z30 being configured to contain or form a fuel tank.

[0039] The wing 30 comprises at least one flap 40 connected to the structure 32 by a pivoting connection 42 which has a main pivot axis A42 substantially parallel to the rear spar 32.2. According to one configuration, the flap 40 is positioned at the rear of the rear spar 32.2 and extends to the trailing edge 30.4. In addition, the wing 30 comprises at least one kinematic chain 44 for controlling the pivoting movement of the flap 40 about the main pivot axis A42, this kinematic chain 44 being positioned in a rear zone Z30' of the wing 30 delimited by the rear spar 32.2, the main pivot axis A42 as well as the first and second walls 34.1, 34.2.

[0040] With the exception of the kinematic chain 44, the other elements of the wing 30 are not further described because they may be identical to those of the prior art.

[0041] According to a particular feature, the rear spar 32.2 comprises at least one opening 46 which passes through the rear spar 32.2 and connects the central and rear zones Z30, Z30'. In addition, the kinematic chain 44 extends in the central and rear zones Z30, Z30' and passes through the rear spar 32.2 via the opening 46.

[0042] The kinematic chain 44 extends between a first anchoring point 44.1 secured to the structure 32 and a second anchoring point 44.2 secured to the flap 40 and offset from the main pivot axis A42.

[0043] According to one embodiment, the kinematic chain 44 comprises at least one linear actuator 48 positioned in the central zone Z30 and connected to the structure 32 as well as at least one first connecting rod 50 connected to the flap 40, positioned in the central and rear zones Z30, Z30' and passing through the rear spar 32.2 via the opening 46.

[0044] According to one arrangement, the linear actuator 48 comprises a body 52 which has a first end 52.1 connected by a first articulation 54 to the structure 32 and / or to the aerodynamic envelope 34, more particularly to the front spar 32.1, as well as a rod 56, movable relative to the body 52, which has a second end 56.1.

[0045] At the central zone Z30, the wing 30 has a greater thickness (distance between the first and second walls 34.1, 34.2) than at the rear zone Z30'. Consequently, it is possible to provide a linear actuator 48 of larger cross-section and therefore to reduce the number of linear actuators 48, namely to provide at most two for each flap 40, which makes it possible to reduce the on-board mass. Furthermore, it is possible to use electromechanical linear actuators 48 which have larger cross-sections than hydraulic linear actuators. Arranging the kinematic chain 44 partly in the central zone Z30 and reducing the number of kinematic chains makes it possible to free up the rear zone Z30', which makes it possible to have other elements there such as a fuel storage tank.Furthermore, the linear actuators 48 being positioned in the central zone Z30, it is possible to reduce the thickness of the wing 30 at the level of the rear zone Z30'.

[0046] According to one embodiment, the first articulation 54 has a first secondary pivot axis A54, parallel to the main pivot axis A42. According to one configuration, the first articulation 54 comprises a ball joint. According to an arrangement visible in [Fig. 5], the first articulation 54 comprises a yoke 54.1 secured to a first element among the structure 32 and the linear actuator 48, a tab 54.2 secured to a second element different from the first element among the structure 32 and the linear actuator 48 as well as a cylindrical rod 54.3 which passes through and connects the yoke 54.1 and the tab 54.2 so as to form the first secondary pivot axis A54. According to one arrangement, the body 52 of the linear actuator 48 is connected by the first articulation 54 to the structure 32, in particular to its front spar 32.1. The 54.1 yoke and the 32.1 front side member can form a single piece. Alternatively, the 54.1 may be separate from the front spar 32.1 and connected to the front spar 32.1 by fastening elements. For example, the cylindrical rod 54.3 is a rod of a bolt. .

[0047] According to one embodiment, the kinematic chain 44 comprises a second articulation 58 connecting the flap 40 and the first link 50. The second articulation 58 has a second secondary pivot axis A58, parallel to the main pivot axis A42. According to one configuration, the second articulation 58 comprises a ball joint. According to an arrangement visible in [Fig. 5], the second articulation 58 comprises a yoke 58.1 secured to a first element among the flap 40 and the first link 50, a lug 58.2 secured to a second element different from the first element among the flap 40 and the first link 50 as well as a cylindrical rod 58.3 which passes through and connects the yoke 58.1 and the lug 58.2 so as to form the second secondary pivot axis A58. According to one arrangement, the first connecting rod 50 extends between first and second ends 50.1, 50.2, the first end 50.1 being connected by the second articulation 58 to the flap 40. For example, the cylindrical rod 58.3 is a rod of a bolt.

[0048] According to a first arrangement, the kinematic chain 44 comprises a third articulation directly connecting the second end 56.1 of the linear actuator 48 and the second end 50.2 of the first connecting rod 50.

[0049] According to a second arrangement, the kinematic chain 44 comprises a second three-point link 60, a third articulation 62 connecting the second three-point link 60 and the structure 32 and / or the aerodynamic envelope 34, a fourth articulation 64 connecting the linear actuator 48 and the second three-point link 60 as well as a fifth articulation 66 connecting the first and second links 50, 60.

[0050] According to an embodiment visible in [Fig.9], the second three-point connecting rod 60 comprises first and second branches 68, 70 which each have first and second ends 68.1, 70.1, 68.2, 70.2, the first ends 68.1, 70.1 of the first and second branches 68, 70 being rigidly connected to each other, the third articulation 62 being located at the first ends 68.1, 70.1 of the first and second branches 68, 70, the fourth articulation 64 being located at the second end 68.2 of the first branch 68, the fifth articulation 66 being located at the second end 70.2 of the second branch 70.

[0051] According to one embodiment, the third articulation 62 has a third secondary pivot axis A62, parallel to the main pivot axis A42. According to one configuration, the third articulation 62 comprises a ball joint. According to an arrangement visible in FIGS. 8 to 10, the third articulation 62 comprises a yoke 62.1 secured to the aerodynamic envelope 34, a tab 62.2 secured to the second three-point link 60 as well as a cylindrical rod 62.3 which passes through and connects the yoke 62.1 and the tab 62.2 so as to form the third secondary pivot axis A62. Alternatively, the yoke could be secured to the second three-legged link 60. In addition, the tab could be integral with the aerodynamic envelope 34. According to one configuration, the yoke 62.1 is a separate element from the aerodynamic envelope 34. According to this configuration, the yoke 62.1 is connected by fixing elements 62.4 to the second wall 34.2 of the aerodynamic envelope 34. For example, the cylindrical rod 62.3 is a rod of a bolt.

[0052] According to one embodiment, the fourth articulation 64 has a fourth secondary pivot axis A64, parallel to the main pivot axis A42. According to one configuration, the fourth articulation 64 comprises a ball joint. According to one arrangement, the fourth articulation 64 comprises a yoke 64.1 secured to a first element among the linear actuator 48, more particularly the second end 56.1 of the rod 56, and the second three-point link 60, more particularly the second end 68.2 of its first branch 68, a tab 64.2 secured to a second element different from the first element among the linear actuator 48, more particularly the second end 56.1 of the rod 56, and the second three-point link 60, more particularly the second end 68.2 of its first branch 68, as well as a cylindrical rod 64.3 which passes through and connects the yoke 64.1 and the tab 64.2 so as to form the fourth secondary pivot axis A64. For example, the cylindrical rod 64.3 is a rod of a bolt.

[0053] According to one embodiment, the fifth articulation 66 has a fifth secondary pivot axis A66, parallel to the main pivot axis A42. According to one configuration, the fifth articulation 66 comprises a ball joint. According to one arrangement, the fifth articulation 66 comprises a yoke 66.1 secured to a first element among the first link 50, more particularly its second end 50.2, and the second three-point link 60, more particularly the second end 70.2 of its second branch 70, a lug 66.2 secured to a second element different from the first element among the first link 50, more particularly its second end 50.2, and the second three-point link 60, more particularly the second end 70.2 of its second branch 70, as well as a cylindrical rod 66.3 which passes through and connects the yoke 66.1 and the lug 66.2 so as to form the fifth secondary pivot axis A66. For example, the cylindrical rod 66.3 is a rod of a bolt. .

[0054] According to one embodiment, the first and second branches 68, 70 form, in a plane perpendicular to the third secondary pivot axis A62, an angle α of between 15 and 45°. The angle α is as small as possible.

[0055] According to a third arrangement, the second connecting rod comprises only two points. According to this arrangement, the angle α is equal to 0 and the fourth and fifth pivot axes A64, A66 are coincident. According to this third arrangement, the second connecting rod comprises a first end articulated relative to the structure and / or the aerodynamic envelope as well as a second end articulated relative to the linear actuator 48 and the first connecting rod 50.

[0056] In operation, the rod 56 translates relative to the body 52 and the linear actuator 48 has a length L48 (corresponding to the distance between the first and second ends 52.1, 56.1) which varies between minimum and maximum values. The length L48 may have a median value between the minimum and maximum values.

[0057] As illustrated in [Fig.6], when the length L48 is equal to the minimum value, the fourth secondary pivot axis A64 occupies a first extreme position Bl(-), the fifth secondary pivot axis A66 occupies a first position extreme B2(-) and the second secondary pivot axis A54 occupies a first extreme position B3(-) corresponding to a position of the flap 40 P(-) inclined downwards.

[0058] When the linear actuator 48 is actuated and the length L48 reaches the median value, the second link 60 pivots clockwise. The fourth secondary pivot axis A64 occupies a median position B1(0), the fifth secondary pivot axis A66 occupies a median position B2(0) and the second secondary pivot axis A54 occupies a median position B3(0) corresponding to a substantially horizontal position of the flap 40.

[0059] When the linear actuator 48 is actuated and the length L48 reaches the maximum value, the fourth secondary pivot axis A64 occupies a second extreme position Bl(+), the fifth secondary pivot axis A66 occupies a second extreme position B2(+) and the second secondary pivot axis A54 occupies a second extreme position B3(+) corresponding to a position of the flap 40 P(+) inclined upwards.

[0060] According to one embodiment, the first branch 68 has a length L68 corresponding, in a plane perpendicular to the main pivot axis A42, to a distance separating the third and fourth secondary pivot axes A62, A64. The second branch 70 has a length L70 corresponding, in a plane perpendicular to the main pivot axis A42, to a distance separating the third and fifth secondary pivot axes A62, A66. According to a preferred configuration, the length L68 of the first branch 68 is substantially equal to the length L70 of the second branch 70.

[0061] The flap 40 has a flap dimension D40 corresponding, in a plane perpendicular to the main pivot axis A42, to a distance separating the main pivot axis A42 and the second secondary pivot axis A54. According to a preferred configuration, the flap dimension D40 is substantially equal to the lengths L68, L70 of the first and second branches 68, 70.

[0062] In order to reduce the power of the linear actuator 48 required to pivot the flap 40, the dimension of the flap 40 as well as the lengths of the first and second branches 68, 70 are as large as possible.

[0063] According to one embodiment, the aerodynamic envelope 34 comprises at least one opening 72 closed by a removable cover 72.1. According to a preferred configuration, the aerodynamic envelope 34 comprises a first opening 72, at the central zone Z30, positioned in line with the linear actuator 48 and closed by a first removable cover 72.1 as well as a second opening 72', at the rear zone Z30', closed by a second removable cover 72.1'. The presence of the covers 72.1, 72.1' allows access to the central and rear zones Z30, Z30' for maintenance, inspection or repair operations.

[0064] According to an embodiment visible in [Fig. 3], the wing 30 comprises at least one partition 74 in at least the central zone Z30 separating a first compartment 74.1 configured to store fuel and a second compartment 74.2 configured to house a part of the kinematic chain 44. The wing 30 may comprise several partitions 74, 74', 74” to compartmentalize the central and rear zones Z30, Z30' into different compartments, some being configured to store fuel and others to house one or more kinematic chain(s) 44 configured to control the pivoting of a flap 40.

[0065] Although described as applied to an aircraft wing 30, the invention is not limited to this application.

[0066] For the present application, the term wing covers all parts of the aircraft which have a wing-shaped profile such as a wing 30 of the airfoil, a vertical stabilizer, a horizontal stabilizer or others.

[0067] The term flap covers all the moving parts of a wing such as a control surface, a flap, an airbrake or others.

[0068] According to the invention, the wing 30 comprises: a. an aerodynamic envelope 34 which extends between leading and trailing edges 30.3, 30.4 and comprises first and second walls 34.1, 34.2, b. at least one structure 32 comprising at least one spar 32.2 interposed between the first and second walls 34.1, 34.2, connected to the latter and delimiting with the aerodynamic envelope 34 first and second zones Z30, Z30' respectively positioned on either side of the spar 32.2, the first zone Z30 (corresponding to the central zone) being located at the front of the spar 32.2 and the second zone Z30' (corresponding to the rear zone) being located at the rear of the spar 32.2, c. at least one flap 40, d. at least one pivoting connection 42, located in the second zone Z30', which connects the shutter 40 and the structure 32 and has a main pivot axis A42, e. at least one kinematic chain 44 configured to pivot the flap 40 around the main pivot axis A42.

Claims

Claims

1. Aircraft wing (30) comprising: a. an aerodynamic envelope (34), b. at least one structure (32) which comprises at least one spar (32.2) delimiting with the aerodynamic envelope (34) first and second zones (Z30, Z30') respectively located on either side of the spar (32.2), c. at least one shutter (40), d. at least one pivoting connection (42), located in the second zone (Z30'), which connects the shutter (40) and the structure (32) and has a main pivot axis (A42), e. at least one kinematic chain (44) configured to pivot the flap (40) about the main pivot axis (A42); f. characterized in that the spar (32.2) comprises at least one opening (46) connecting the first and second zones (Z30, Z30') and in that the kinematic chain (44) extends in the first and second zones (Z30, Z30') and passes through the spar (32.2) via the opening (46).

2. Aircraft wing (30) according to the preceding claim, characterized in that the kinematic chain (44) comprises at least one linear actuator (48) positioned in the first zone (Z30) and connected to the structure (32) as well as at least one first link (50) positioned in the first and second zones (Z30, Z30'), connected to the flap (40) and passing through the spar (32.2) via the opening (46).

3. Aircraft wing (30) according to the preceding claim, characterized in that the linear actuator (48) comprises first and second ends (52.1, 56.1), the first end (52.1) being connected by a first articulation (54) to the structure (32) and / or to the aerodynamic envelope (34), and in that the first link (50) extends between first and second ends (50.1, 50.2), the first end (50.1) being connected by a second articulation (58) to the flap (40), the second end (50.2) of the first link (50) being connected to the second end (56.1) of the linear actuator (48), the first and second articulations (54, 58) respectively having first and second secondary pivot axes (A54, A58) parallel to the main pivot axis (A42).

4. Aircraft wing (30) according to the preceding claim, characterized in that the kinematic chain (44) comprises at least one second link (60), a third articulation (62) connecting the second link (60) to the structure (32) and / or the aerodynamic envelope (34) as well as at least one fourth articulation (64) connecting the second link (60), the linear actuator (48) and the first link (50), the third and fourth articulations (62, 64) respectively having third and fourth secondary pivot axes (A62, A64) parallel to the main pivot axis (A42).

5. Aircraft wing (30) according to the preceding claim, characterized in that the second link (60) comprises first and second branches (68, 70) which each have first and second ends (68.1, 70.1, 68.2, 70.2), the first ends (68.1, 70.1) of the first and second branches (68, 70) being rigidly connected to each other, the third articulation (62) being located at the first ends (68.1, 70.1) of the first and second branches (68, 70), the fourth articulation (64) being located at the second end (68.2) of the first branch (68) and connecting the second end (56.1) of the linear actuator (48) and the second end (68.2) of the first branch (68) and in that the kinematic chain (44) comprises a fifth articulation (66) located at the second end (70.2) of the second branch (70) and connecting the second end (50.2) of the first connecting rod (50) and the second end (70.2) of the second branch (70), the fifth articulation (66) having a fifth secondary pivot axis (A66) parallel to the main pivot axis (A42).

6. Aircraft wing (30) according to the preceding claim, characterized in that the first and second branches (68, 70) form an angle (a) of between 15 and 45°.

7. Aircraft wing (30) according to one of claims 5 to 6, characterized in that the first and second branches (68, 70) have equal lengths (L68, L70).

8. Aircraft wing (30) according to the preceding claim, characterized in that the main pivot axis (A42) and the second secondary pivot axis (A54) are separated by a distance substantially equal to the lengths (L68, L70) of the first and second branches (68, 70).

9. Aircraft wing (30) according to one of the preceding claims, characterized in that the aerodynamic envelope (34) comprises at least one opening (72) opening into the first or second zone (Z30, Z30') and closed by a removable cover (72.1).

10. Aircraft wing (30) according to one of the preceding claims, characterized in that the wing (30) comprises at least one partition (74) in at least the first zone (Z30) separating a first compartment (74.1) configured to store fuel and a second dry compartment (74.2) configured to house a part of the kinematic chain (44).

11. Aircraft comprising at least one wing according to one of the preceding claims.

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