Limiting device and airplane

Abstract

The invention provides a limiting device which can fully utilize a space between a slat and a fixed leading edge to limit relative deformation of the slat and the fixed leading edge when the slat is folded and can adapt to a narrow space and an airplane. The limiting device is used for limiting relative deformation of a slat and a fixed front edge, and is provided with a first limiting piece which is installed on the slat and is provided with a clamping part, and a second limiting piece which is installed on the fixed front edge, the second limiting piece is installed on the convex surface of the fixed front edge and provided with a protruding part, the first limiting piece and the second limiting piece move relative to the fixed front edge through the slat so as to be close to or away from each other, and when the slat is located at the folding position, the clamping part makes surface contact with the protruding part from the lower portion so that the slat can be folded. And the contact surface of the clamping part and the protruding part is crossed with the deformation direction of the slat.

Description

Technical Field

[0001] The present invention relates to a limiting device for restricting relative deformation between a slat and a fixed leading edge, and an aircraft equipped with the limiting device. Background Art

[0002] For the slat structure at the leading edge of the wing of a large airliner, a two-track method is mostly adopted to support and move the slat. For example, in the cruise state, the slat is in the retracted position. Under the action of aerodynamic lift, the deformation of the slat structure will affect the aerodynamic efficiency. Therefore, it is necessary to carry out the stiffness design of the slat to reduce the slat deformation so as to improve the aerodynamic efficiency.

[0003] In the prior art, some adopt a three-track support method to limit the slat deformation; some adopt a two-track method, open a notch C inside the fixed leading edge at the middle position between the two tracks, and extend a long stop D on the slat. When the slat is retracted, the stop D contacts the leading edge notch C, thereby restricting the slat deformation (refer to Figure 10 ).

[0004] In the first method above, since an additional track is added, the structure will increase in weight and is less used in large aircraft. The second method can effectively solve the slat deformation problem. However, in the second method, since a notch is opened inside the leading edge of the box section, there is still an outer shape notch that is not closed after the slat is retracted, which will reduce the aerodynamic efficiency to a certain extent and will increase additional noise. At the same time, the leading edge needs to be strengthened around the notch, increasing some weight. And the stop D on the slat has to extend into the fixed leading edge of the wing box, resulting in a longer force arm L of the slat stop D, poor load-bearing performance, and a heavier structure. Summary of the Invention

[0005] The present invention is completed in view of the above problems. One of the purposes is to provide a limiting device and an aircraft equipped with the limiting device that can make full use of the space between the slat and the fixed leading edge to restrict the relative deformation between the slat and the fixed leading edge when the slat is retracted and can adapt to narrow spaces.

[0006] To achieve the above object, a first aspect of the present invention provides a limiting device for restricting relative deformation between a slat and a fixed leading edge, comprising: a first limiting member, the first limiting member is installed on the slat and has an engaging portion; and a second limiting member, the second limiting member is installed on the convex surface of the fixed leading edge and has a protruding portion, the first limiting member and the second limiting member approach or move away from each other as the slat moves relative to the fixed leading edge. When the slat is in the retracted position, the engaging portion contacts the protruding portion in a surface-to-surface manner from below, and the contact surface between the engaging portion and the protruding portion intersects the direction in which the slat is to be deformed.

[0007] The limiting device according to the first aspect of the present invention utilizes the space between the slat and the fixed leading edge to arrange a limiting device composed of a pair of first limiting members and a second limiting member. It can make full use of the space between the slat and the fixed leading edge to limit the relative deformation between the slat and the fixed leading edge when the slat is retracted, and can adapt to narrow spaces. Moreover, the first limiting member installed on the slat does not exceed the slat envelope contour, which can avoid increasing the windward area of the slat; the force arms of the pair of first limiting members and the second limiting member are short, and the load-bearing effect is good, which is beneficial to weight reduction; there is no need to additionally provide an opening on the fixed leading edge, and the box section structure at the corresponding position does not need to be designed with an additional strengthening structure, which is beneficial to weight reduction; when the slat is in the retracted position, the fixed leading edge has a complete shape and does not lose aerodynamic efficiency.

[0008] In addition, in the limiting device of the present invention, it may also be that the first limiting member has: a first base, the first base having a bottom plate and a front plate bent and erected from the front end of the bottom plate; and a engaging portion installed on the bottom plate in a height-adjustable manner. According to the above structure, by adjusting the height, the engaging portion can properly contact the protruding portion, and it can be applied to various wing structures.

[0009] In addition, in the limiting device of the present invention, it may also be that the second limiting member has: a second base; and the protruding portion, the protruding portion protruding from the second base toward the first limiting member side when viewed in side view, and a notch is formed at a position of the front plate opposite to the protruding portion, the notch extending from the top to the bottom of the front plate, and the width of the notch is greater than the width of the protruding portion. According to the above structure, it can be avoided that the protruding portion and the front plate interfere with each other, for example, due to external force, which helps the limiting device to adapt to a narrow installation space.

[0010] In addition, in the limiting device of the present invention, it may also be that the top surface of the engaging portion is convex-curved, the protruding portion has a relative surface opposite to the bottom plate, and a groove in contact with the top surface is provided on the relative surface. By setting the part in contact with the engaging portion as a concave groove, it is possible to easily avoid interference between the slat moving relative to the fixed leading edge and the first limiting member and the like installed thereon and the protruding portion (second limiting member) while having a larger contact surface.

[0011] Preferably, the contact surface is a curved surface. Thus, it is possible to further suppress or avoid the deviation of the engaging portion and the protruding portion from each other due to external force or the like. In addition, in the limiting device of the present invention, it may also be that the deviation between the normal vector of the tangent plane of at least one point of the contact surface and the deformation direction of the slat is less than 45°. According to the above structure, an excellent deformation suppression effect can be achieved. For example, the normal vector of the tangent plane of at least one point of the contact surface is parallel to the deformation direction of the slat.

[0012] A second aspect of the present invention provides an aircraft, comprising: the slat; the fixed leading edge; and any one of the above-mentioned limiting devices.

[0013] In addition, in the aircraft of the present invention, it may also be that the first limiting member has a first base, and the first base has: a bottom plate fixed to the lower wingspan edge of the front skin of the slat; and a front plate bent and erected from the front end of the bottom plate and fixed to the rear skin of the slat. According to the above structure, the space between the rear skin and the lower wingspan edge can be fully utilized to stably and reliably install the first limiting member.

[0014] In addition, in the aircraft of the present invention, it may also be that the bottom plate is provided with a first through hole, and the engaging portion includes: a bushing in interference fit with the first through hole; and a first bolt having an external thread screwed with the internal thread of the bushing. A hexagonal hollow hole is opened at the bottom of the first bolt, and a second through hole is provided at the lower wingspan edge at a position aligned with the hexagonal hollow hole, and the inner diameter of the second through hole is larger than the inner diameter of the hexagonal hollow hole. According to the above structure, the height of the first bolt (engaging portion) can be adjusted via the second through hole without removing the first limiting member.

[0015] In addition, in the aircraft of the present invention, it may also be that at least one third through hole is opened on the outer peripheral portion of the head of the first bolt, and at least one fourth through hole is opened on the bottom plate. The limiting device further includes a wire, and the wire passes through the third through hole and the fourth through hole to maintain the screwing position of the first bolt. According to the above structure, after adjusting the height of the first bolt (engaging portion), the rotation of the bolt can be prevented by a simple anti-rotation structure, achieving the effect of fixing the height, and the loosening of the first bolt due to vibration or the like can be avoided.

[0016] In addition, in the aircraft of the present invention, it may also be that two slide rails are provided on the slat to move the slat relative to the fixed leading edge, and the limiting device is located at the middle part between the two slide rails in the wingspan direction. According to the above structure, the deformation suppression effect of the limiting device can be improved. Description of the Drawings

[0017] Figure 1 It is a partial cross-sectional view schematically showing an aircraft wing equipped with the limiting device of an embodiment of the present invention, with the slat in the retracted state.

[0018] Figure 2 It is a side view schematically showing the limiting device of an embodiment of the present invention and its surroundings.

[0019] Figure 3 It is a perspective view schematically showing the first limiting member of the limiting device of an embodiment of the present invention.

[0020] Figure 4 It is a perspective view schematically showing a second limiting member of a limiting device according to an embodiment of the present invention.

[0021] Figure 5 It is a cross-sectional view schematically showing a limiting device according to an embodiment of the present invention and its periphery.

[0022] Figure 6 It is a partial cross-sectional view schematically showing a limiting device according to an embodiment of the present invention and its periphery.

[0023] Figure 7 It is a perspective view schematically showing a slat of an aircraft installed with a limiting device according to an embodiment of the present invention.

[0024] Figure 8 It is a perspective view schematically showing a first limiting member according to an embodiment of the present invention and its periphery.

[0025] Figure 9 It is a view showing an example of the direction in which the slat is to be deformed.

[0026] Figure 10 It is a cross-sectional schematic view showing a limiting structure between an existing slat and a fixed leading edge.

[0027] Symbol Explanation

[0028] 10 First limiting member

[0029] 11 First base

[0030] 12 Engaging portion

[0031] 20 Second limiting member

[0032] 21 Second base

[0033] 22 Protruding portion

[0034] 100 Limiting device

[0035] 111 Bottom plate

[0036] 112 Front plate

[0037] 113 Reinforcing rib

[0038] 114 Notch

[0039] 121 Bushing

[0040] 122 First bolt

[0041] 200 Slat

[0042] 201 Front skin

[0043] 202 Rear skin

[0044] 221 Front surface

[0045] 221a First part

[0046] 221b Second part

[0047] 221c Third part

[0048] 222 One side surface

[0049] 223 The other side surface

[0050] 300 Fixed leading edge

[0051] 400 Slide rail

[0052] 1211 Cylindrical part

[0053] 1212 Flange part

[0054] 1221 Head

[0055] 1222 Rod part

[0056] 2011 Lower wingspan edge

[0057] 2211 Groove

[0058] H1 First through hole

[0059] H2 Hexagonal hole

[0060] H3 Second through hole

[0061] H4 Third through hole

[0062] H5 Fourth through hole

[0063] W Wire Detailed implementation mode

[0064] Hereinafter, with reference to the drawings, the technical solutions of the embodiments and modification examples of the present invention will be described. In addition, the scope of the present invention is not limited to the following embodiments and modification examples, and can be arbitrarily changed within the scope of the technical idea of the present invention. In addition, in the following drawings, in order to facilitate the understanding of each structure, sometimes the actual structure is different from the scale, quantity, etc. in each structure.

[0065] The present invention provides a limiting device 100 composed of a pair of limiting members 10 and 20, which can make full use of the space between the slat 200 and the fixed leading edge 300 in the aircraft to limit the relative deformation between the slat and the fixed leading edge when the slat is retracted, and can adapt to narrow spaces.

[0066] <First Embodiment>

[0067] Figure 1FIG. 0 is a partial cross-sectional view schematically showing an aircraft wing equipped with the position-limiting device 100 of the first embodiment of the present invention, with the slat in the retracted state. Figure 2 FIG. 1 is a side view schematically showing the position-limiting device 100 and its surroundings. Figure 3 FIG. 2 is a perspective view schematically showing the first position-limiting member 10 of the position-limiting device 100. Figure 4 FIG. 3 is a perspective view schematically showing the second position-limiting member 20 of the position-limiting device 100. Figure 5 FIG. 4 is a cross-sectional view schematically showing the position-limiting device 100 and its surroundings. Figure 6 FIG. 5 is a partial cross-sectional view schematically showing the position-limiting device 100. Figure 7 FIG. 6 is a perspective view schematically showing the slat of an aircraft equipped with the position-limiting device 100. Figure 8 FIG. 7 is a perspective view schematically showing the first position-limiting member 10 and its surroundings.

[0068] The aircraft is provided with a plurality of slats 200, a fixed leading edge 300, and a position-limiting device 100. The position-limiting device 100 can be provided separately for each slat 200. The aircraft is also provided with a slide rail 400 (which can also be referred to Figure 7 ), and this slide rail 400 is fixed to the slat 200 and cooperates with a gear (not shown) on the fixed leading edge 300 to move the slat 200 relative to the fixed leading edge 300 to be in the deployed state or the retracted state.

[0069] Each slat is provided with a plurality of ( Figure 7 In the example of FIG., two) slide rails 400. Preferably, the position-limiting device 100 is located at an intermediate position between at least any two adjacent slide rails among the plurality of slide rails in the wingspan direction. Thus, the effect of suppressing deformation of the position-limiting device 100 can be improved. When each slat is provided with two slide rails 400, preferably, the position-limiting device 100 is located at an intermediate position between these two slide rails 400.

[0070] (Position-limiting device)

[0071] The position-limiting device 100 of the present invention arranges a position-limiting device 100 composed of a pair of position-limiting members 10 and 20 in the space between the slat 200 and the fixed leading edge 300.

[0072] The position-limiting device 100 is used to limit the relative deformation between the slat 200 and the fixed leading edge 300 when the slat is retracted, and includes a first position-limiting member 10 and a second position-limiting member 20. The first position-limiting member 10 and the second position-limiting member 20 can approach or move away from each other as the slat 200 moves relative to the fixed leading edge 300.

[0073] The first limiting member 10 is installed on the slat 200. The first limiting member 10 has a first base 11 and an engaging portion 12. The material of the first base 11 is not particularly limited, for example, it is made of metal. The first base 11 has a bottom plate 111 and a front plate 112. The front plate 112 is bent and erected from the front end of the bottom plate 111.

[0074] The slat 200 includes a front skin 201 and a rear skin 202. The front skin 201 has a lower wingspan edge 2011 at its lower end (bottom end), and the lower wingspan edge 2011 extends to a position further rearward than the lower edge of the rear skin 202. A receiving space is formed at the corner between the lower edge of the rear skin 202 and the lower wingspan edge 2011. In the present embodiment, the bottom plate 111 is fixed to the lower wingspan edge 2011, and the front plate 112 is fixed to the rear skin 202 (specifically, the lower edge portion of the rear skin 202). The first limiting member 10 can be fixed to the slat 200 by fasteners such as bolts or other fixing means such as welding. In the present embodiment, the first base 11 is fixed to the slat 200 by bolts. For example, a plurality of holes 112a are formed in the front plate 112, and bolts are passed through the holes 112a and fastened to the rear skin 202; a plurality of holes 111a are formed in the bottom plate 111, and bolts are passed through the holes 111a and fastened to the lower wingspan edge 2011.

[0075] The engaging portion 12 is provided on the first base 11. In the present embodiment, the engaging portion 12 is installed on the bottom plate 111 inside the corner formed by the bottom plate 111 and the front plate 112. Preferably, the engaging portion 12 is installed on the bottom plate 111 in a height-adjustable manner. In the present embodiment, a first through hole H1 (refer to Figure 6 ) is formed through the bottom plate 111. The engaging portion 12 includes a bushing 121 and a first bolt 122. The bushing 121 is interposed between the first bolt 122 and the first through hole H1. The bushing 121 has a cylindrical portion 1211 that is in interference fit with the first through hole H1 and a flange portion 1212 that extends outward from the top end of the cylindrical portion 1211. The bushing 121 has an internal thread provided on the inner surface of the cylindrical portion 1211. The first bolt 122 has an external thread that is screwed with the internal thread of the bushing 121.

[0076] The first bolt 122 has a head 1221 and a rod portion 1222. The top surface 1221a of the head 1221 is convexly curved. That is, the top surface of the engaging portion 12 is convexly curved. Preferably, a hexagonal hollow hole H2 is formed in the middle of the bottom of the first bolt 122, so that the installation height of the first bolt 122 can be adjusted with a hexagonal screwdriver at the bottom, so that when the slat 200 is in the retracted position, the first bolt 122 (the head 1221) of the first limiting member 10 just contacts the protruding portion 22 of the second limiting member 20 described later. The hexagonal hollow hole H2 is formed recessed from the bottom surface of the rod portion 1222.

[0077] Preferably, a second through hole H3 is provided through the lower wingspan edge 2011 of the front skin 201 at a position aligned with the hexagonal empty hole H2. The inner diameter of the second through hole H3 is larger than that of the hexagonal empty hole H2. Thus, without removing the first limiting member 10, the height of the first bolt 122 (engaging portion 12) can be adjusted via the second through hole H3.

[0078] In the present embodiment, at least one third through hole H4 is formed in the outer peripheral portion of the head 1221, as Figure 3 shown. For example, two openings of the third through hole H4 are respectively formed on the outer peripheral surface of the head 1221. When there are a plurality of third through holes H4, the plurality of third through holes H4 are located at different positions in the circumferential direction around the central axis of the first bolt 122. At least one fourth through hole H5 is formed in the rear edge portion of the bottom plate 111. For example, two openings of the fourth through hole H5 are respectively formed on the surface of the bottom plate 111 facing the protruding portion 22 and the surface facing the rear side.

[0079] The limiting device 100 further has a wire W. The wire W passes through the third through hole H4 and the fourth through hole H5 to hold the screwing position of the first bolt 122 after the first bolt 122 is screwed to the required height, so as to fix the height of the first bolt 122. For example, one end of the wire W is fastened to the third through hole H4 by knotting, welding, bonding, etc., and the other end is fastened to the fourth through hole H5. Thereby, it is possible to prevent the first bolt 122 from loosening due to vibration or the like. The material of the wire W is not particularly limited, and for example, it can be a wire.

[0080] In addition, the first base 11 may include a reinforcing rib 113 that connects the bottom plate 111 and the front plate 112 to improve the strength of the first base 11 (first limiting member 10). For example, the reinforcing rib 113 connects the end portions of the bottom plate 111 and the front plate 112 in the wingspan direction.

[0081] The second limiting member 20 is correspondingly mounted on the convex surface of the fixed leading edge 300 with respect to the first limiting member 10. The second limiting member 20 has a second base 21 and a protruding portion 22. The material of the second limiting member 20 is not particularly limited, and for example, it is made of metal. In the present embodiment, the protruding portion 22 protrudes from the middle portion of the second base 21 in the wingspan direction. The second limiting member 20 is fixedly mounted on the convex surface of the fixed leading edge 300 at the second base 21 by fasteners such as bolts or other fixing means such as welding. The back surface of the second base 21 has a shape matching the convex surface of the fixed leading edge 300. For example, a plurality of holes 21a are respectively provided at positions on both sides of the second base 21 in the wingspan direction of the protruding portion 22, and bolts are passed through the holes 21a and fastened to the skin of the fixed leading edge 300 or the fixed leading edge rib plate.

[0082] When viewed from the front side (front side), the protruding portion 22 has a substantially rectangular outer shape. Preferably, when viewed in side view, the protruding portion 22 protrudes in a tapered shape from the second base 21 toward the first limiting member 10 side. The protruding portion 22 has a front surface 221, one side surface 222, and the other side surface 223. The front surface 221 includes a first portion 221a and a second portion 221b. The first portion 221a is in a substantially steep downhill shape toward the first limiting member 10 side when viewed in side view. When the slat 200 is in the stowed position, the first portion 221a is spaced apart from the front plate 112 and faces it, and the space between the first portion 221a and the front plate 112 increases as the direction away from the bottom plate 111 is approached. The top end of the second portion 221b is connected to the bottom end of the first portion 221a. The second portion 221b bends from the bottom end of the first portion 221a toward the second base 21 side and is in a flat shape substantially parallel to the surface of the bottom plate 111 facing the protruding portion 22. The second portion 221b constitutes a facing surface opposite to the bottom plate 111. That is, the protruding portion 22 has a facing surface opposite to the bottom plate 111. A groove 2211 in contact with the top surface 1221a is provided in the second portion 221b. Preferably, the groove 2211 is located at a position in the second portion 221b far from the second base 21, whereby the force arm of the limiting device can be made larger. In addition, the front surface 221 may further include a third portion 221c connecting the second portion 221b and the second base 21. The third portion 221c bends and extends from the bottom end of the second portion 221b in a direction away from the bottom plate 111, whereby it is possible to make the force arm of the limiting device larger in a limited space while easily avoiding interference between the lower wingspan edge 2011, etc. and the second limiting member 20.

[0083] Preferably, a notch 114 is formed in the front plate 112 of the first base 11 at a position opposite to the protruding portion 22. The notch 114 extends from the top to the bottom of the front plate 112, and the width of the notch 114 (in the wingspan direction in this embodiment) is greater than the width of the protruding portion 22. Thereby, it is possible to avoid interference between the protruding portion 22 and the front plate 112 due to external force, for example, and it helps the limiting device 100 to adapt to a narrow installation space.

[0084] When the slat 200 is in the stowed position, the engaging portion 12 is in surface contact with the protruding portion 22 from below. More specifically, the top surface 1221a of the engaging portion 12 is in contact with the groove 2211 of the protruding portion 22. By providing the portion in contact with the engaging portion 12 as the groove 2211 recessed from the second portion 221b (facing surface), a larger contact surface can be obtained. At the same time, compared with the case where the portion in contact with the engaging portion 12 is provided in a protruding shape, it is easy to avoid interference between the lower wingspan edge 2011 of the slat 200 moving relative to the fixed leading edge 300 and the first limiting member 10 installed on the slat 200, etc. and the protruding portion 22 (second limiting member 20).

[0085] The contact surface M between the engaging portion 12 and the protruding portion 22 intersects with the direction in which the slat is to be deformed. When the slat 200 is subjected to aerodynamic loads, the limiting device 100 formed by a pair of limiting members 10 and 20 restricts the slat 200 from moving relative to the fixed leading edge 300 in the direction in which it is to be deformed. The "direction in which the slat is to be deformed" can be determined according to the acting direction of the slat aerodynamic force and the wing surface structure of a specific aircraft model. For example, it can be a direction along a direction perpendicular to the wing chord plane. In one example, the direction in which the slat is to be deformed is a direction having a vertical component.

[0086] In the present embodiment, the contact surface M is a curved surface. By making the contact surface M a curved surface, compared with the case where the contact surface M is a plane, it is possible to further suppress or avoid the engaging portion 12 and the protruding portion 22 from deviating from each other due to external forces or the like. In addition, the present invention does not exclude the case where the contact surface M is a plane.

[0087] Preferably, the deviation between the normal vector of the tangent plane of at least one point of the contact surface M and the direction in which the slat is to be deformed is less than 45°. More preferably, the normal vector of the tangent plane of at least one point of the contact surface M is parallel to the direction in which the slat is to be deformed. In a preferred solution, the normal vector of the tangent plane at the center point of the contact surface M is parallel to the direction in which the slat is to be deformed. Here, the "parallel" direction also includes a substantially parallel direction.

[0088] Hereinafter, an example of the installation steps of the limiting device 100 of the present invention will be described.

[0089] The installation of the limiting device 100 includes:

[0090] Install the first limiting member 10 on the slat 200;

[0091] Install the second limiting member 20 on the fixed leading edge 300;

[0092] Place the slat 200 in the stowed position, and adjust the first bolt 122 on the first limiting member 10 so that it just contacts the protruding portion 22 of the second limiting member 20.

[0093] According to the limiting device 100 of the present invention, the limiting device 100 formed by a pair of limiting members 10 and 20 is arranged in the space between the slat 200 and the fixed leading edge 300. The first limiting member 10 installed on the slat 200 does not exceed the slat envelope profile, which can avoid increasing the slat windward area; the acting arms of the pair of limiting members 10 and 20 are short, and the load-bearing effect is good, which is beneficial to weight reduction; there is no need to additionally provide an opening on the fixed leading edge 300, and the corresponding box section structure does not need to be designed with an additional strengthening structure, which is beneficial to weight reduction; when the slat 200 is in the stowed position, the fixed leading edge 300 has a complete profile and does not lose aerodynamic efficiency.

[0094] The specific embodiments of the present invention have been specifically described above in conjunction with the accompanying drawings. However, it is understood that the above description does not limit the present invention in any way, and the technical features in each embodiment can be combined with each other in any manner to form new embodiments. In addition, after understanding the above specific embodiments, those skilled in the art can make various other modifications and changes to the present invention as needed. None of these deviate from the essence of the present invention.

Claims

1. A limiting device for limiting the relative deformation between a slat and a fixed leading edge, characterized in that Comprising: A first limiting member, which is installed on the slat and has an engaging portion; and A second limiting member, which is installed on the convex surface of the fixed leading edge and has a protruding portion, The first limiting member and the second limiting member approach or move away from each other as the slat moves relative to the fixed leading edge, When the slat is in the retracted position, the engaging portion is in surface contact with the protruding portion from below, The contact surface between the engaging portion and the protruding portion intersects the direction in which the slat is to be deformed.

2. The limiting device according to claim 1, wherein The first limiting member has: a first base, the first base having a bottom plate and a front plate bent and erected from the front end of the bottom plate; and the engaging portion installed on the bottom plate in a height-adjustable manner.

3. The limiting device according to claim 2, wherein The second limiting member has: a second base; and the protruding portion, which protrudes from the second base toward the first limiting member side when viewed in side view, A notch is formed at a position of the front plate opposite to the protruding portion, the notch extends from the top to the bottom of the front plate, and the width of the notch is greater than the width of the protruding portion.

4. The limiting device according to claim 2, wherein The top surface of the engaging portion is in a convex curved shape, The protruding portion has a relative surface opposite to the bottom plate, and a groove in contact with the top surface is provided on the relative surface.

5. The limiting device according to claim 1, wherein The contact surface is a curved surface, The normal vector of the tangent plane at at least one point of the contact surface is parallel to the direction in which the slat is to be deformed.

6. An aircraft, characterized in that, Comprising: The slat; The fixed leading edge; and The limiting device according to any one of claims 1 to 5.

7. The aircraft according to claim 6, wherein The first limiting member has a first base, The first base has: a bottom plate, the bottom plate being fixed to the lower wingspan edge of the front skin of the slat; And a front plate bent and erected from the front end of the bottom plate, the front plate being fixed to the rear skin of the slat.

8. The aircraft according to claim 7, wherein The bottom plate is provided with a first through hole, The engaging portion includes: a bushing in interference fit with the first through hole; and a first bolt having an external thread screwed into the internal thread of the bushing, A hexagonal hollow hole is formed at the bottom of the first bolt, A second through hole is provided at the lower wingspan edge at a position aligned with the hexagonal hollow hole, and the inner diameter of the second through hole is larger than the inner diameter of the hexagonal hollow hole.

9. The aircraft according to claim 8, wherein At least one third through hole is formed in the outer peripheral portion of the head of the first bolt, At least one fourth through hole is formed in the bottom plate, The limiting device further includes a wire, and the wire passes through the third through hole and the fourth through hole to maintain the screwing position of the first bolt.

10. The aircraft according to claim 6, wherein Two slide rails are provided on the slat to enable the slat to move relative to the fixed leading edge, The limiting device is located at the middle part between the two slide rails in the wingspan direction.

Images