Airplane wing and airplane comprising such an airplane wing

Abstract

The invention relates to an aircraft wing and to an aircraft comprising such an aircraft wing. The aircraft wing comprises a wing structure supporting a wing cover having an outer aerodynamic surface forming part of an airfoil profile of the wing and a recess stepped back from the wing airfoil profile, and a spoiler device comprising a spoiler coupled to the wing structure by a spoiler actuation mechanism for moving the spoiler between a retracted position and a deployed position, the spoiler having a surface following the outer profile of the wing airfoil profile and the spoiler being fully accommodated in the recess when the spoiler is in the retracted position, and wherein the spoiler surface extends away from the wing cover when the spoiler is in the deployed position.

Description

Technical Field

[0001] This invention relates to aircraft wings and aircraft. Background Technology

[0002] Spoiler devices are known to be installed on aircraft wings to disrupt lift generated by the wing, reduce load, and control roll. Such spoiler devices are typically movable between a deployed position that disrupts lift generated by the wing and a retracted position that does not disrupt lift generated by the wing. In the deployed position, gaps or cuts are typically present around the wing profile. These cuts may affect the local structural integrity of the wing that needs reinforcement, leading to increased weight, or may allow airflow to enter the wing's internal structure. These factors can affect the performance of the spoiler device and / or the aircraft wing. Summary of the Invention

[0003] A first aspect of the invention provides an aircraft wing comprising: a wing structure supporting a wing cover having an outer aerodynamic surface forming a portion of an airfoil profile and a recessed portion recessed rearward from the airfoil profile; and a spoiler assembly comprising a spoiler coupled to the wing structure via a spoiler actuation mechanism for moving the spoiler between a retracted position and an deployed position, the spoiler having a surface conforming to the airfoil profile, and the spoiler being fully received in the recess when in the retracted position, wherein the spoiler surface extends away from the wing cover when in the deployed position.

[0004] Optionally, the wing cover has a substantially constant thickness in a first portion having an outer aerodynamic surface and a second portion having a recess.

[0005] Optionally, the spoiler includes a spoiler seal arranged to engage with the wing cover when the spoiler is in a retracted position to form a sealing joint between the spoiler surface and the outer aerodynamic surface of the wing cover.

[0006] Optionally, the spoiler actuation mechanism extends through at least one orifice located in a recessed portion of the wing cover. Optionally, the orifice has an area less than 20% of the spoiler's surface area. Minimizing the orifice's surface area can reduce its impact on the wing's load-bearing structure.

[0007] Optionally, each orifice includes an orifice seal.

[0008] Optionally, the wing structure includes a front spar, wherein a recess in the wing cover is positioned adjacent to the front spar, and preferably immediately behind the front spar.

[0009] Alternatively, the wing cover is an upper wing cover.

[0010] Optionally, the spoiler is positioned in the outer portion of the wing, preferably at a spanwise position of at least 60% of the wing span.

[0011] Optionally, the aircraft wing includes a fixed wing portion and a folding wingtip portion that can rotate relative to the fixed wing portion, wherein a spoiler device is disposed in the folding wingtip portion of the aircraft wing.

[0012] Optionally, the aircraft wing may also include a leading-edge movable high-lift device positioned in front of the spoiler.

[0013] Alternatively, the spoiler is positioned on the portion of the wing furthest from the volume containing the liquid fuel.

[0014] Alternatively, the spoiler is positioned at the spanwise position of the wing where there is no trailing-edge high-lift device.

[0015] Optionally, the spoiler actuation mechanism is configured to move the spoiler from a retracted position to an deployed position in a rotational and / or translational manner.

[0016] Optionally, the actuation mechanism includes at least one link arranged to rotate relative to the wing structure, the link being connected to the front portion of the spoiler.

[0017] Optionally, the link includes a bent portion and an extension portion to form a gooseneck structure, the bent portion having a constant radius of curvature relative to the point where it is rotatably connected to the wing structure, and the extension portion extending between the bent position and the rotation point.

[0018] Optionally, the aircraft wing further includes a plurality of spoiler devices arranged along the spanwise direction of the aircraft wing, wherein the plurality of spoiler devices are received in a common recess of the wing cover when they are in their respective retracted positions.

[0019] Another aspect of the present invention provides an aircraft including the aircraft wings of the first aspect of the present invention. Attached Figure Description

[0020] Embodiments of the present invention will now be described with reference to the accompanying drawings, in which:

[0021] Figure 1 A schematic diagram of the aircraft is shown;

[0022] Figure 2 A schematic diagram of a portion of an aircraft wing is shown;

[0023] Figure 3A schematic diagram of the aircraft wing structure is shown;

[0024] Figure 4 A cross-sectional view of the aircraft wing is shown;

[0025] Figure 5 A cross-sectional view of an aircraft wing including a first spoiler device is shown;

[0026] Figure 6 It shows Figure 5 Another cross-sectional view of the aircraft wing;

[0027] Figure 7 It shows Figure 5 An enlarged schematic diagram of a portion of the wing of an aircraft;

[0028] Figure 8 A schematic top view of a portion of the aircraft's wing is shown;

[0029] Figure 9 A cross-sectional view of the aircraft wing is shown;

[0030] Figure 10 A cross-sectional view of an aircraft wing including a second spoiler device is shown;

[0031] Figure 11 It shows Figure 10 Another cross-sectional view of the aircraft wing;

[0032] Figure 12 A cross-sectional view of the aircraft wing including the third spoiler device is shown;

[0033] Figure 13 It shows Figure 12 Another cross-sectional view of the aircraft wing;

[0034] Figure 14 It shows Figure 13 A three-dimensional view of the aircraft's wings;

[0035] Figure 15 A schematic diagram of the aircraft's wings is shown;

[0036] Figure 16 A schematic diagram of a portion of an aircraft wing is shown; and

[0037] Figure 17 A schematic diagram of another aircraft wing is shown. Detailed Implementation

[0038] Figure 1Aircraft 10 is shown. Aircraft 10 has a fuselage 12, a starboard fixed wing 13, and a port fixed wing 14. Each wing 13, 14 is equipped with an engine 15. Aircraft 10 is a typical jet passenger aircraft, but the present invention is applicable to a variety of fixed-wing aircraft types, including commercial, military, passenger, cargo, jet, propeller, and general aviation aircraft, which have any number of engines attached to the wings or fuselage. This aircraft is a fixed-wing aircraft with cantilevered wings.

[0039] Each wing has a cantilever wing structure extending spanwise from a root 18 to a tip 19, wherein the root 18 is connected to the fuselage 12. Wings 13 and 14 are similar in construction, and therefore only the starboard wing 13 will be described in detail. Wing 13 has a leading edge 16 and a trailing edge 17. The leading edge 16 is located at the leading tip of the wing, and the trailing edge 17 is located at the trailing tip of the wing.

[0040] The wing has an upper wing cover 22, a lower wing cover 24, and leading-edge and trailing-edge cover panels. These covers can be collectively referred to as wing cover 20. Wing cover 20 has an outer aerodynamic surface that forms the outer aerodynamic surface of wing 13. Wing 13 has an upper aerodynamic surface between its leading edge 16 and trailing edge 17, and a lower aerodynamic surface between its leading and trailing edges.

[0041] The wing 13 has a spanwise axis S extending from the wing root 18 to the wing tip 19, and a chordwise axis extending from the leading edge 16 to the trailing edge 17. The wing 13 has an airfoil cross-section. The wing 13 has a thickness direction perpendicular to both the chordwise and spanwise directions.

[0042] Figure 2A simplified diagram of a wing 13 including a leading-edge spoiler assembly 40, hereinafter referred to as spoiler assembly 40, is shown. Spoiler assemblies are known to be provided to disrupt airflow over the wings of an aircraft to impair or reduce lift generated by the wing. Although the spoiler assembly 40 is shown positioned adjacent to the leading edge 16 of the wing 13, it will be understood that in some cases, the spoiler assembly 40 may extend to the leading edge 16 of the wing 13. Preferably, the spoiler assembly 40 is positioned closer to the leading edge 16 of the wing 13 than to the trailing edge 17 of the wing 13, as this improves the lift reduction effect and reduces the torsional load applied to the wing 13 due to the deployment of the spoiler assembly 40. A leading-edge spoiler assembly can provide improved load mitigation compared to a trailing-edge spoiler assembly sized in a similar manner. The closer the spoiler is to the leading edge 16, the greater the proportion of lift generated by the wing is disrupted along the wing chord. Therefore, unlike a spoiler that only disrupts lift at the trailing edge of the wing, away from the wing's neutral axis, a leading-edge spoiler disrupts lift over a large portion of the wing, thus reducing the torsional effect around the neutral axis caused by spoiler deployment. In the case of a trailing-edge spoiler, the pitching moment (upward torsion of the wing's leading edge) generated by spoiler deployment offsets the load-reducing effect of spoiler deployment. In the case of a leading-edge spoiler, this pitching moment is reduced compared to a trailing-edge spoiler sized in a similar manner, and therefore the load-reducing effect of spoiler deployment is improved.

[0043] Figure 3 A schematic diagram of the wing box 30 of the wing 13 of the aircraft 1 is shown. The wing box 30 is arranged to bear most of the load applied to the wing 13. Figure 1 As shown, the wing 13 tapers from its inner root end to its outer tip end, such that the chord length of the wing 13 decreases from the inner end to the outer end, and the thickness of the wing 13 also decreases from the inner end to the outer end. Accordingly, the wing box 30 also tapers in both directions.

[0044] The wing box 30 includes an upper cover 22 and a lower cover 24, which are formed as at least a portion of the outer aerodynamic surface of the wing 13. It will be understood that... Figure 3 The wing box 30 is schematic, and the upper cover 22 and lower cover 24 are each non-planar. In particular, the upper cover 22 and lower cover 24 have external aerodynamic surfaces, each forming part of the airfoil profile of the wing 13. The wing box 30 also includes a wing structure 32 for supporting the wing cover 20. Figure 3The wing structure 32 shown includes a front spar 32a and a rear spar 32b, with the front spar 32a positioned toward the leading edge 16 of the wing 13 and the rear spar 32b positioned toward the trailing edge 17 of the wing 13. It will be understood that although shown in a generally C-shaped form, each spar can take any profile. The upper cover 22 and the lower cover 24 can be connected to the front spar 32a and the rear spar 32b using any suitable method, such as by fasteners and / or by coupling.

[0045] Figure 4 It shows including Figure 3 A schematic diagram of the cross-section of the wing 13 of the wing box 30. It will be understood that although the wing cover 20 is shown as a single body, the wing cover 20 can be as described above regarding... Figure 1 and Figure 3 The described wing cover 20 is formed by multiple wing coverings. The wing covering 20 has an outer aerodynamic surface that forms the airfoil profile of the wing 13 for generating lift. The wing covering 20 also defines a recess 26 that is stepped backward from the airfoil profile. That is, the recess 26 is formed in the outer aerodynamic surface of the wing covering 20. The recess 26 extends along the spanwise direction S of the wing 13. In some cases, the recess 26 can increase the area moment of inertia of the wing covering 20, thereby increasing the stiffness of the wing 13.

[0046] Therefore, the wing cover 20 includes a first portion 20a and a second portion 20b, the first portion 20a having an outer aerodynamic surface exposed to the airflow, and the second portion 20b defining a recess 26. Although the first portion 20a is in Figure 4 The portion shown as the wing cover 20 immediately in front of the recess 26 is actually the first portion 20a; however, it will be understood that the first portion 20a can be considered any portion of the wing cover 20 that does not have the recess 26. Preferably, the wing cover 20 is configured to have a constant thickness t at all points around the wing airfoil profile to reduce the likelihood of forming areas of increased local stress around the wing cover 20. Therefore, the wing cover 20 can have a substantially constant thickness t at both the first portion 20a and the second portion 20b. Such a cover with a constant thickness but stepped recess to provide the recess can be referred to as a "joggle". It will be understood that... Figure 4 This is a schematic diagram, and the thickness of the wing cover 20 shown may not be drawn accurately.

[0047] Figure 5 Another example of a wing 13 further including a spoiler assembly 40 is shown. For clarity, only the outer surface of the wing cover 20 is shown, although... Figure 5 The wing cover 20 can be with Figure 4The wing cover 20 is substantially the same. The spoiler assembly 40 includes a spoiler 42, which is connected to the wing 13, and specifically to the wing structure 32, via a spoiler actuation mechanism 44. The spoiler actuation mechanism 44 is arranged such that the spoiler 42 is in a retracted position ( Figure 5 (as shown) and unfolded position ( Figure 6 It can move between the deployed and retracted positions (as shown in the diagram). Therefore, it can be said that the spoiler device 40 is capable of moving between the deployed and retracted positions.

[0048] In the retracted position, the spoiler 42 is fully received within the recess 26. Alternatively, the spoiler 42 may be described as being received or included in the recess 26 when retracted. Therefore, the spoiler 42 includes a spoiler surface 43 that follows the shape profile of the airfoil profile when the spoiler assembly 40 is retracted. The spoiler surface 43 may form a substantially continuous profile with the first portion 20a of the wing cover 20 to minimize the aerodynamic effects of the spoiler assembly 40 when the spoiler 42 is retracted. In the deployed position, the spoiler surface 43 extends away from the wing cover 20, thereby disrupting the airflow above the wing 13 and impairing the lift generated by the wing 13. In the deployed position, the spoiler 42 extends a maximum height H1 above the outer aerodynamic surface of the wing cover 20. The height H1 may be between 5% and 10% of the local chord of the airfoil profile, for example, approximately 6% of the local chord of the airfoil profile.

[0049] In the retracted position, it is advantageous to minimize the impact of the spoiler assembly 40 on the aerodynamic performance of the wing 13. Therefore, the spoiler 42 may include a spoiler seal 46 arranged to form a sealing joint between the spoiler 42 and the wing cover 20 when the spoiler assembly 40 is retracted. This sealing joint is defined herein as a joint that does not allow airflow. This is particularly important for leading-edge spoiler assemblies, as any gaps when the spoiler is retracted can interfere with airflow, thereby increasing drag and reducing lift. Figure 7 It shows Figure 5 A schematic diagram of a portion of the wing 13, wherein the spoiler actuation mechanism 44 is omitted for clarity. The spoiler 42 includes spoiler seals 46 at its leading and trailing edges; however, it will be understood that the spoiler seals 46 may extend around the entire periphery of the spoiler 42. Figure 7 In the retracted position shown, the spoiler seal 46 engages with the outer surface of the recess 26 to form a sealing engagement. By way of a non-limiting example, the spoiler seal 46 may include an elastically deformable member coupled to the spoiler 42 and arranged to deform upon contact with the wing cover 30 to form a sealing engagement. It will be understood that... Figure 7The outline of the spoiler seal 46 shown is only schematic, and the spoiler seal 46 can take any suitable form.

[0050] As previously stated, it is preferable to position the spoiler assembly 40 toward the leading edge 16 of the wing 13. Therefore, the spoiler assembly 40 and thus the recess 26 for receiving the spoiler 42 can be positioned toward the leading edge 16 of the wing 13. In the case where the wing 13 includes a front spar 32a, the recess 26 can be positioned adjacent to the front spar 32a. This configuration provides, as Figure 5 and Figure 6 The diagram illustrates a convenient arrangement for connecting the spoiler 42 to the wing structure 32 by connecting the spoiler actuation mechanism 44 to the front wing spars 32a. More preferably, the recess 26 is located immediately behind the front wing spars 32a. The airfoil profile of the wing 13 typically has its maximum height at this chordal position, which allows the spoiler actuation mechanism 44 to be more easily accommodated within the wing cover 20.

[0051] Preferably, the spoiler device 40 is positioned at a spanwise location on the wing 13, away from any liquid contained within the wing 13, such as a volume of liquid fuel stored in a fuel tank. That is, the portion of the spoiler device 40, particularly the spoiler mechanism 44, located within the wing cover 20 is positioned not adjacent to any liquid stored in the wing 13. This increases the space within the wing 13 available to accommodate the spoiler actuation mechanism 44. Positioning the spoiler device 40 adjacent to a volume of stored liquid may also require a sealed volume or similar sealing structure around the actuation mechanism 44, thus increasing the number of components and weight of the spoiler device 40.

[0052] Because the spoiler 42 is positioned adjacent to the outer aerodynamic surface of the wing 13, and the spoiler actuation mechanism 44 is coupled to the inner wing structure 32, the spoiler actuation mechanism 44 needs to extend through the wing cover 20. It will be understood that the spoiler actuation mechanism 44 extends through the wing cover 20 in both the retracted and deployed positions of the spoiler assembly. Therefore, the second portion 20b of the wing cover 20 having the recess 26 may include at least one aperture 27 through which the spoiler actuation mechanism 44 extends, such as... Figure 3 and Figure 7 As is most clearly shown. By configuring only the spoiler actuation mechanism 44 to extend through the wing cover 20 (compared to, for example, configuring the spoiler 42 to extend through the wing cover 20), the size of the aperture 27 can be minimized.

[0053] Minimizing the size of the orifice 27 reduces the negative impact on the structural stiffness of the wing torsion box caused by the orifice. Minimizing the size of the orifice 27 also reduces the impact of the spoiler assembly 40 on the aerodynamic performance of the wing 13 as the spoiler assembly 40 extends. To reduce airflow into the wing 13, each orifice may also include an orifice seal 28 arranged to form a sealing engagement with a spoiler actuation mechanism 44 extending therethrough. By way of a non-limiting example, the orifice seal may include a resiliently deformable member coupled to the wing cover 20 and contacting the spoiler actuation mechanism 44 to form a sealing engagement therebetween.

[0054] Figure 8 A schematic top view of a portion of the upper panel 22, including the recess 26, is shown. The spoiler assembly 40 has been omitted, making the orifices 27 visible. In the example shown, the spoiler actuation mechanism 44 extends through the wing cover 20 via the first orifice 27a and the second orifice 27b. Arranging the spoiler actuation mechanism 44 to extend through a plurality of spaced-apart orifices 27 can improve the stability and / or rigidity of the spoiler assembly 40 in the deployed position. The total surface area of ​​the first orifice 27a and the second orifice 27b can be less than 20% of the surface area of ​​the spoiler surface 23 and / or less than 20% of the outer surface area of ​​the recess 26. Each orifice 27 is also provided with a first orifice seal 28a and a second orifice seal 28b, respectively. It will be understood that, although in Figure 8 The rectangular recess shown is a rectangular recess with a circular opening 27, but both the recess 26 and the opening 27 can take any suitable shape.

[0055] The spoiler device 40 can be positioned adjacent to the high-lift device 50. Figure 9 An example of a wing 13 is shown, which includes a high-lift device 50 positioned in front of the spoiler assembly 40 and at the leading edge 16 of the wing 13. Positioning both the spoiler assembly 40 and the high-lift device 50 at a common spanwise location along the wing 13 provides more efficient use of space along the wing span, as this arrangement provides both a lift-enhancing device and a lift-disrupting device at the common spanwise location. It will be understood that the high-lift device 50 can include any known leading-edge high-lift device, such as a deployable leading-edge slat or a Kruger flap, and therefore the high-lift device 50 can form part of the leading edge 16 of the wing 13.

[0056] When the spoiler 42 is moved from the retracted position to the deployed position, it is preferable to rotate and translate the spoiler 42. This can, for example, cause the spoiler surface 43 to move forward toward the leading edge 16 of the wing 13 when the spoiler 42 is deployed, which can reduce the torsional load on the wing 13 due to the lift generated by the spoiler along most of the chord of the wing. Figure 5 and Figure 6 An example of a spoiler actuation mechanism 44 configured to deploy a spoiler 42 in this manner is shown. The spoiler actuation mechanism 44 includes a link 45 rotatably connected at its first end to a wing structure 32. The point at which the first end of the link 45 is connected to the wing structure 32 can be referred to as the rotation point. A second end of the link 45, away from the first end, is rigidly connected to the spoiler 42 at a forward position. Therefore, rotating the link 45 relative to the wing structure 32 causes rotation and translation of the spoiler 42, thereby moving the spoiler assembly 40 between a retracted position and a deployed position. Although the link 45... Figure 5 and 6 The linkage 45 is shown to be rotated by two linear actuators 48, but it will be understood that any number (including one) of linear actuators or rotary actuators or any other suitable arrangement can be used to rotate the linkage 45.

[0057] To minimize the required size of the opening 27 through the wing cover 20, it is preferable to configure the link 45 to have a constant radius of curvature relative to the point where the link 45 is rotatably coupled to the wing structure 32. That is, the link 45 is shaped such that when the link 45 rotates relative to the wing structure 32, the point where the link 45 extends through the wing cover 20 does not move. This allows the opening 27 to be sized to match the width or thickness of the link 45 without needing to accommodate the chordal movement of the link 45 as it passes through the wing cover 20. In the example shown, this is achieved by providing a gooseneck link 45 comprising a curved portion 45a coupled to the spoiler 42 and an extension portion 45b extending between the curved portion 45a and the point of rotation. It will be understood that while the curved portion 45a and the extension portion 45b of the gooseneck link 45 are rotatably coupled to the wing structure 32, the point where the link 45 extends through the wing cover 20 does not move. Figure 5 and Figure 6 The two parts are shown as rigidly connected, but the curved portion 45a and the extended portion 45b of the gooseneck link 45 can be formed integrally.

[0058] Figure 10 and Figure 11 Alternative spoiler assembly 140 is shown. Spoiler components similar to those of spoiler assembly 40 are numbered using similar reference numerals in the 100 series. The remaining features of wing 13 are substantially the same as those already discussed and are therefore labeled accordingly.

[0059] Figure 10 and Figure 11 The spoiler 142 is only in the retracted position by rotation. Figure 10 (as shown) and unfolded position ( Figure 11 The spoiler assembly 140 includes a spoiler 142 that is pivotally connected to the wing structure, preferably at the foremost point of the spoiler 142.

[0060] The spoiler actuation mechanism 144 includes a linear actuator 148 pivotally coupled to the wing structure 32 at a first end of the linear actuator 148. The linear actuator 148 is also pivotally coupled to the spoiler 142 at a second end of the linear actuator 148, the second end being located away from the first end. This arrangement allows for operation of the spoiler assembly 140 using a single actuator 148, or for operation of the spoiler assembly 140 using multiple actuators.

[0061] Figures 12 to 14 Another alternative spoiler assembly 240 is shown. Spoiler components similar to those of spoiler assembly 40 are numbered using similar reference numerals in the 200 series. The remaining features of wing 13 are substantially the same as those already discussed and are therefore labeled accordingly.

[0062] Figures 12 to 14 The spoiler 242 is in the retracted position only by translation. Figure 12 (as shown) and unfolded position ( Figure 13 The spoiler assembly 240 includes a spoiler 247, which is formed as a retractable barrier between the spoiler panel 242 and the wing structure. The spoiler panel 242 is coupled to a linear actuator 248, which is arranged to extend the spoiler panel 242 above the outer aerodynamic surface of the wing 13 when moving from a retracted position to an extended position. The spoiler panel generally extends along the chord and spanwise directions of the wing.

[0063] When the spoiler device 240 is deployed, the retractable barrier 247 blocks the airflow between the spoiler panel 242 and the outer aerodynamic surface of the wing 13. The retractable barrier 247 is connected to the front portion of the spoiler panel 242 and the wing structure adjacent to the wing cover 20. Figure 14A perspective view of a portion of wing 13 is shown, illustrating the spoiler assembly 240 in its deployed position. In the illustrated example, the retractable barrier 247 comprises a series of pivotally linked barrier panels 247a spaced apart along the spanwise length of the spoiler assembly 240. Each barrier panel 247a is pivotally coupled to an adjacent barrier panel 247a and to either the wing cover 20 or the spoiler panel 242. The retractable barrier spoiler 247 is fully housed in the recess 26 when the spoiler assembly 240 is retracted, such that only the spoiler actuation mechanism 244 extends through the wing cover 20.

[0064] It will be understood that any references to spoiler device 40 mentioned below may also be applied to alternative spoiler device 140 or another alternative spoiler device 240.

[0065] Although the recess 26 is shown in all figures as being located in the upper cover 22 of the wing 13, it will be understood that in some embodiments (not shown), the recess 26, and therefore the spoiler assembly 40, may be located in the lower cover 24 of the wing 13. Arranging the spoiler assembly to extend from the lower surface of the wing may be beneficial in mitigating negative gust loads and loads under wing camber conditions. In other arrangements, spoiler assemblies in both the upper and lower covers may be desirable.

[0066] Preferably, the spoiler device 40 is positioned on the outer portion of the wing 13, because this improves load reduction (prevents wing bending) when the spoiler 42 is deployed compared to a spoiler device located more inward in the spanwise direction. The outer portion of the wing is defined herein as the portion of the wing 13 positioned toward the wingtip 19. Figure 15 Another simplified diagram of a wing 13 including a spoiler assembly 40 is shown. The wing 13 has a total wing span length S1 measured from the root 18 to the tip 19, and the spoiler assembly 40 is located at a spanwise position one spanwise length S2 from the root 18. The length S2 can be at least 60%, preferably at least 70%, and more preferably at least 75% of the wing span S1.

[0067] The spoiler device disclosed herein can also be applied to foldable aircraft wings. This allows the spoiler device 40 to be positioned close to the wingtip 19. Figure 16An example of an alternative wing 113 is shown, comprising a fixed wing portion 113a and a folding wingtip portion 113b rotatable relative to the fixed wing portion 113a. A spoiler assembly 40 is disposed in the folding wingtip portion 113b. The previously discussed spoiler assemblies 40, 140, and 240 may be particularly advantageous for use in the folding wingtip portion 113b because they can comprise simple spoiler actuation mechanisms 44, 144, and 244, which are lighter in weight compared to more complex actuation methods. The folding portion of the wing can also be “fuel-free,” i.e., without a fuel volume, making it more suitable to position the spoiler towards the leading edge than at a location on the wing with a fuel volume.

[0068] The recess 26 can extend over most of the wingspan of the wing 13, such as, for example Figure 17 As shown in the diagram. Therefore, the wing 13 may include a plurality of spoiler devices 40, each of which is received in a common recess 26 when retracted. Although Figure 17 A wing 13 comprising four spoiler devices 40 is shown, but it will be understood that the wing 13 may include any number of spoiler devices 40. Each spoiler device 40 may operate independently relative to the others. The edges of the plurality of spoiler devices 40 may abut against each other along the spanwise direction of the wing 13. Providing a single common recess 26 in which the plurality of spoiler devices 40 are received can improve the structural integrity of the wing cover 20, because the single recess 26 can be formed as an integral feature, for example, of the upper cover 22, such that the wing cover 20 has a constant thickness at all points around the airfoil. In an alternative example (not shown), the wing includes a plurality of discrete recesses spaced apart from each other, and a plurality of spoiler devices each received in a respective discrete recess.

[0069] Preferably, the spoiler device 40 is positioned along the spanwise direction of the wing 13, with no high-lift device at the trailing edge 17 of the wing 13. This is because if the wing structure needs to accommodate the pitching effect of the trailing-edge high-lift device anyway, the beneficial effect of reducing wing twist from having a leading-edge spoiler (compared to a trailing-edge spoiler) will be reduced.

[0070] Preferably, the leading-edge spoiler is positioned along the spanwise direction of the wing 13 without ailerons / flaps. Although it is possible to arrange these devices together, it is preferable to position the spoiler devices away from the ailerons to ensure roll control authority.

[0071] When the word "or" appears, it will be interpreted as meaning "and / or", meaning that the items referred to are not necessarily mutually exclusive and can be used in any appropriate combination.

[0072] Although the invention has been described above with reference to one or more preferred embodiments, it will be understood that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.

Claims

1. An aircraft wing, comprising: A wing structure supporting a wing cover, the wing cover having an outer aerodynamic surface forming part of the airfoil profile of the wing and a recessed portion that is stepped backward from the airfoil profile of the wing. as well as A spoiler assembly comprising a spoiler connected to the wing structure via a spoiler actuation mechanism for moving the spoiler between a retracted position and an deployed position, the spoiler having a surface profile conforming to the airfoil profile, and the spoiler being fully received in a recess when in the retracted position, wherein the spoiler surface extends away from the wing cover when in the deployed position.

2. The aircraft wing according to claim 1, wherein, The wing cover has a substantially constant thickness at the first portion having the outer aerodynamic surface and the second portion having the recess.

3. The aircraft wing according to any of the preceding claims, wherein, The spoiler includes a spoiler seal arranged to engage with the wing cover when the spoiler is in the retracted position to form a sealing joint between the surface of the spoiler and the outer aerodynamic surface of the wing cover.

4. The aircraft wing according to any of the preceding claims, wherein, The spoiler actuation mechanism extends through at least one orifice located in the portion of the wing cover having the recess, optionally wherein the orifice has an area less than 20% of the surface area of ​​the spoiler.

5. The aircraft wing according to claim 4, wherein, Each orifice includes an orifice seal.

6. The aircraft wing according to any of the preceding claims, wherein, The wing structure includes a front wing spars, and wherein the recess in the wing cover is positioned adjacent to the front wing spars, and preferably positioned immediately behind the front wing spars.

7. The aircraft wing according to any of the preceding claims, wherein, The wing cover is the upper wing cover.

8. The aircraft wing according to any of the preceding claims, wherein, The spoiler is positioned on the outer portion of the wing, preferably at a spanwise position of at least 60% of the wing's span.

9. The aircraft wing according to any of the preceding claims, wherein, The aircraft wing includes a fixed wing portion and a folding wingtip portion that can rotate relative to the fixed wing portion, wherein the spoiler device is disposed in the folding wingtip portion of the aircraft wing.

10. The aircraft wing according to any of the preceding claims further includes a leading-edge movable high-lift device positioned in front of the spoiler assembly.

11. The aircraft wing according to any of the preceding claims, wherein, The spoiler device is positioned on the portion of the wing furthest from the volume containing the liquid fuel.

12. The aircraft wing according to any of the preceding claims, wherein, The spoiler device is positioned at the spanwise position of the wing where there is no trailing edge high-lift device.

13. The aircraft wing according to any of the preceding claims, wherein, The spoiler actuation mechanism is configured to move the spoiler from the retracted position to the deployed position in a rotational and / or translational manner.

14. The aircraft wing according to claim 13, wherein, The actuation mechanism includes at least one link arranged to rotate relative to the wing structure, the link being connected to the front portion of the spoiler.

15. The aircraft wing according to claim 14, wherein, The link includes a bent portion and an extension portion to form a gooseneck structure. The bent portion has a constant radius of curvature relative to the point where it is rotatably connected to the wing structure. The extension portion extends between the bent position and the rotation point.

16. The aircraft wing according to any of the preceding claims further includes a plurality of spoiler devices arranged along the spanwise direction of the aircraft wing, wherein, The plurality of spoiler devices are received within a common recess in the wing cover when they are in their respective retracted positions.

17. An aircraft comprising the wings of any of the preceding claims.

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