Slat mechanism and aircraft

Abstract

The embodiment of the utility model discloses a slat mechanism and an aircraft, and belongs to the technical field of aircrafts, the slat mechanism comprises a driving part, a mounting assembly and a sliding rail, the driving part comprises an actuator and a telescopic section, the actuator is arranged on the inner side of a wing, the end, away from the actuator, of the telescopic section extends out of the wing and is connected with a slat, and the mounting assembly comprises two rib plates; the rib plates are arranged on the face, facing the slat, of the wing in a protruding mode, the sliding rail is arranged in a containing cavity defined by the two rib plates in the advancing direction, one end of the sliding rail is connected with the slat, the other end of the sliding rail is suspended, the actuator can drive the telescopic section to drive the slat to move in the advancing direction, and the slat can drive the sliding rail to move between the two rib plates in the advancing direction. The actuators are arranged on the inner sides of the wings, the space utilization rate is increased, it is guaranteed that the slats can smoothly stretch out and retract, and therefore the stability and safety of the aircraft are guaranteed.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a slat mechanism and an aircraft. Background Technology

[0002] Supercritical airfoils are widely used in aircraft, with slats located at the leading edge of the wing. Most existing aircraft use a rack and pinion actuator to drive the slats to retract and extend. However, since the airfoil height on the outer side of a supercritical airfoil is relatively low, the actuator required to meet the load requirements for slat retraction and extension is too large. An excessively large actuator will protrude from the shape of the wing, which will have a significant impact on the lift of the aircraft. Utility Model Content

[0003] Embodiments of this application provide a slat mechanism and an aircraft to solve the problem that existing gear and rack drive methods affect the lift of aircraft.

[0004] To address the aforementioned technical problems, embodiments of this application disclose the following technical solutions:

[0005] A first aspect of this application provides a slat mechanism for connecting the wing and a slat of an aircraft. The slat mechanism includes: a drive element comprising an actuator and a telescopic section connected along the direction of travel of the aircraft; the actuator being disposed on the inner side of the wing; the telescopic section extending from one end away from the actuator and connected to the slat; a mounting assembly comprising two ribs spaced apart along the wingspan direction of the wing to define a receiving cavity; the ribs protruding from the side of the wing facing the slat along the direction of travel; and a slide rail disposed in the receiving cavity along the direction of travel, one end of the slide rail being connected to the slat and the other end being suspended; the actuator being capable of driving the telescopic section to move the slat along the direction of travel, and the slat being capable of driving the slide rail to move between the two ribs along the direction of travel.

[0006] In addition to one or more of the features disclosed above, or alternatively, the mounting assembly further includes at least two limiting wheels spaced apart in the receiving cavity along the travel direction; the slide rail includes a first surface and a second surface disposed opposite to each other along the thickness direction of the wing; along the thickness direction, the first surface abuts against at least one of the limiting wheels, and the second surface abuts against at least one of the limiting wheels; the slide rail moves along the travel direction, and the slide rail is capable of driving the limiting wheels to rotate.

[0007] In addition to one or more of the features disclosed above, or as an alternative, the first surface has a protrusion extending from one end of the slat along the direction of travel; and / or, the second surface has a protrusion extending from one end of the slat along the direction of travel; along the direction of travel, the slat drives the slide rail closer to the wing, and the protrusion can abut against the limiting wheel of the adjacent slat to prevent the slat from continuing to approach the wing.

[0008] In addition to one or more of the features disclosed above, or alternatively, the mounting assembly further includes at least two support wheels spaced apart in the receiving cavity along the travel direction; the slide rail includes a first surface and a second surface disposed opposite to each other along the thickness direction of the wing; along the thickness direction, at least one support wheel is disposed on the side of the first surface opposite to the second surface, and at least one support wheel is disposed on the side of the second surface opposite to the first surface; along the thickness direction, there is a gap between the support wheel and the slide rail, and the support wheel is capable of abutting against the slide rail.

[0009] In addition to one or more of the features disclosed above, or as an alternative, there is a first distance L1 mm between the support wheel disposed on one side of the first surface and the opposite surface of the first surface, satisfying: 0.1mm≤L1≤0.3mm; and / or, there is a second distance L2 mm between the support wheel disposed on one side of the second surface and the opposite surface of the second surface, satisfying: 0.1mm≤L2≤0.3mm.

[0010] In addition to one or more of the features disclosed above, or alternatively, the mounting assembly further includes a stop inserted into the rib; the slide rail includes a third and a fourth surface disposed opposite to each other along the wingspan direction of the wing; at least one of the third and fourth surfaces has a groove, the groove including a first groove wall and a second groove wall disposed opposite to each other along the travel direction, the first groove wall being adjacent to the slat and the second groove wall being away from the slat; the stop is inserted into the groove, the slat drives the slide rail away from the wing along the travel direction, and the stop can abut against the second groove wall to prevent the slat from continuing to move away from the wing.

[0011] In addition to one or more of the features disclosed above, or as an alternative, the mounting assembly further includes at least two clamping members inserted into the ribs, with one rib corresponding to at least one clamping member; the slide rail includes a third surface and a fourth surface disposed opposite to each other along the wingspan direction of the wing; the clamping member inserted into one of the ribs abuts against the third surface, and the clamping member inserted into the other rib abuts against the fourth surface to form a clamping of the slide rail.

[0012] In addition to one or more of the features disclosed above, or alternatively, the clamping member makes rolling contact with the slide rail.

[0013] In addition to one or more of the features disclosed above, or as an alternative, the slide rail includes a first surface and a second surface disposed opposite to each other along the thickness direction of the wing; the first surface protrudes in the thickness direction away from the second surface to form a convex arc surface; and / or, the second surface is recessed in the thickness direction towards the first surface to form a concave arc surface.

[0014] In addition to one or more of the features disclosed above, or as an alternative, the wing includes a wing box, the actuator is disposed in the wing box, the wing box includes a first beam and a second beam disposed opposite to each other along the direction of travel; the slat has a first connecting portion protruding from the side of the wing along the direction of travel; the end of the actuator opposite to the telescopic section is detachably connected to the first beam; the end of the telescopic section opposite to the actuator extends out of the second beam and is detachably connected to the first connecting portion; along the direction of travel, the rib protrudes from the side of the second beam opposite to the first beam.

[0015] In addition to one or more of the features disclosed above, or as an alternative, the number of mounting components is two, spaced apart along the wingspan direction; one mounting component is provided on each side of the drive member along the wingspan direction.

[0016] In addition to one or more of the features disclosed above, or as an alternative, the slat has a second connecting portion protruding from the side facing the wing along the direction of travel; the slide rail is detachably connected to the second connecting portion at one end adjacent to the slat along the direction of travel.

[0017] A second aspect of this application provides an aircraft including the slat mechanism as described above.

[0018] One of the above technical solutions has the following advantages or beneficial effects: It provides a slat mechanism and an aircraft having the slat mechanism. The slat mechanism includes a drive component, a mounting assembly, and a slide rail. The drive component includes an actuator and a telescopic section connected along the aircraft's direction of travel. The actuator is located on the inner side of the wing. The telescopic section extends out of the wing from the actuator and connects to the slat. The mounting assembly includes two ribs spaced apart along the wing's span direction. The ribs protrude from the side of the wing facing the slat along the direction of travel. The slide rail is located in a receiving cavity defined by the two ribs along the direction of travel. One end of the slide rail is connected to the slat, and the other end... With the end suspended in the air, the actuator can drive the telescopic section to move the slat along the direction of travel. The slat can drive the slide rail to move between the two ribs along the direction of travel. The actuator is set on the inner side of the wing, which improves space utilization and avoids occupying the space between the wing and the slat. It also prevents the wing shape from becoming too large due to the actuator size being too large. The output power of the actuator meets the load requirements for the slat to extend and retract, reducing the impact on the lift of the aircraft. This makes the slat mechanism suitable for the extension and retraction of slats on supercritical wings. Moreover, the combination design of the ribs and slide rails can ensure that the slat can extend and retract smoothly, thereby ensuring the stability and safety of the aircraft. Attached Figure Description

[0019] The technical solution and other beneficial effects of this application will become apparent from the following detailed description of specific embodiments in conjunction with the accompanying drawings.

[0020] Figure 1 This is a schematic diagram of the combined structure of the slat mechanism and the slat provided in the embodiments of this application;

[0021] Figure 2 A schematic diagram showing the relative positions of the ribs and clamping members in the mounting assembly of the slat mechanism provided in the embodiments of this application;

[0022] Figure 3 This is a schematic diagram of the mounting components in the slat mechanism provided in the embodiments of this application;

[0023] Figure 4 This is a schematic diagram of the slide rail structure in the slat mechanism provided in the embodiments of this application;

[0024] Figure 5 A schematic diagram of the combined structure of the slide rail and the slat in the slat mechanism provided in the embodiments of this application;

[0025] Figure 6 This is a schematic diagram of the combined structure of the mounting components and the slide rail in the slat mechanism provided in the embodiments of this application;

[0026] Figure 7 for Figure 6 A partial decomposition diagram;

[0027] Figure 8 A schematic diagram of the combined structure of the slat, mounting components, and slide rail in the slat mechanism provided in the embodiments of this application;

[0028] Figure 9 A schematic diagram of the combined structure of the slat, mounting components and slide rail in the slat retracted state of the slat mechanism provided in the embodiments of this application;

[0029] Figure 10 A schematic diagram of the combined structure of the slat, mounting components, and slide rail in the slat extended state in the slat mechanism provided in the embodiments of this application;

[0030] Figure 11 A schematic diagram of the combined structure of the slat and the drive component in the slat retracted state in the slat mechanism provided in the embodiments of this application;

[0031] Figure 12 This is a schematic diagram of the combined structure of the slat and the drive component in the extended state of the slat mechanism provided in the embodiments of this application.

[0032] Figure 13 A schematic diagram of the combined structure of the slat, slide rail and drive component in the slat extended state in the slat mechanism provided in the embodiments of this application;

[0033] Figure 14 A schematic diagram of the combined structure of the slat, mounting components, and slide rail in the slat mechanism provided in the embodiments of this application;

[0034] Figure 15 for Figure 14 Sectional view along axis AA;

[0035] Figure 16 for Figure 14 BB-direction sectional view;

[0036] Figure 17 A schematic diagram of the combined structure of the actuator and the wing box in the drive component of the slat mechanism provided in the embodiments of this application;

[0037] Figure 18 A schematic diagram of the combined structure of the telescopic section and the first connecting part in the drive component of the slat mechanism provided in the embodiments of this application;

[0038] Figure 19 This is a schematic diagram of the aircraft provided in the embodiments of this application.

[0039] The components in the attached diagram are labeled as follows:

[0040] 100. Slat mechanism;

[0041] 10. Driving component; 11. Actuator; 12. Telescopic section;

[0042] 20. Mounting component; 21. Rib plate; 21a. First rib plate; 21b. Second rib plate; 2100. Receiving cavity; 22. Limiting wheel; 22a. First limiting wheel; 22b. Second limiting wheel; 23. Support wheel; 23a. First support wheel; 23b. Second support wheel; 230. Clearance; 24. Stop; 25. Clamping component; 26. Bolt; 27. Nut.

[0043] 30. Slide rail; 301. First surface; 302. Second surface; 303. Third surface; 304. Fourth surface; 31. Protrusion; 32. Groove; 321. First groove wall; 322. Second groove wall; 33. Ear.

[0044] 200. Aircraft;

[0045] 210. Wing; 211. Wing box; 2111. First beam; 2112. Second beam; 2113. Third connecting part;

[0046] 220, slat; 2201, inner skin; 2202, outer skin; 221, first connecting part; 222, second connecting part;

[0047] X, direction of travel; Y, wingspan; Z, thickness. Detailed Implementation

[0048] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0049] In some embodiments of this application, an aircraft 200 is provided, with reference to... Figure 19The aircraft 200 includes wings 210 and slats 220, and also includes a slat mechanism 100 for connecting the wings 210 and slats 220. The aircraft 200 can be any fixed-wing aircraft, commercial aircraft, military aircraft, passenger aircraft, autonomous aircraft, rotorcraft, etc.

[0050] In some embodiments of this application, a slat mechanism 100 is provided, which is used to connect the wing 210 and the slat 220 of the aircraft 200, see reference. Figures 1 to 18 The slat mechanism 100 includes: a drive component 10, a mounting component 20, and a slide rail 30.

[0051] Reference Figure 1 , Figures 11-13 as well as Figures 17-18 The drive unit 10 includes an actuator 11 and a telescopic section 12 connected along the travel direction X of the aircraft 200. The actuator 11 is disposed on the inner side of the wing 210, as shown in the figure. Figure 1 as well as Figures 11-12 The end of the telescopic section 12 opposite to the actuator 11 is connected to the slat 220. The actuator 11 can drive the telescopic section 12 to extend or retract along the travel direction X of the aircraft 200.

[0052] Reference Figures 1-3 , Figures 6-10 as well as Figures 15-16 The mounting assembly 20 includes two ribs 21, which are spaced apart along the wingspan direction Y of the wing 210, as shown in the figure. Figure 3 as well as Figures 6-7 The two ribs 21 define a receiving cavity 2100, as shown in the figure. Figure 13 Rib 21 protrudes from the side of wing 210 facing slat 220 along the direction of travel X.

[0053] Reference Figure 1 , Figures 6-10 as well as Figures 14-16 The slide rail 30 is disposed in the receiving cavity 2100 along the traveling direction X, as shown in the reference. Figure 1 , Figures 4 to 10 as well as Figures 14-15 The slide rail 30 extends along the travel direction X, with one end of the slide rail 30 connected to the slat 220 and the other end of the slide rail 30 suspended in the air.

[0054] Reference Figure 11 and Figure 12 The actuator 11 can drive the telescopic section 12 to move the slat 220 along the travel direction X, as shown in the reference. Figure 9 and Figure 10The slat 220 can drive the slide rail 30 to move between the two ribs 21 along the travel direction X. Specifically, the actuator 11 drives the telescopic section 12 to extend the slat 220 along the travel direction X, and the slat 220 drives the slide rail 30 to extend from between the two ribs 21 along the travel direction X; the actuator 11 drives the telescopic section 12 to retract the slat 220 along the travel direction X, and the slat 220 drives the slide rail 30 to retract to between the two ribs 21 along the travel direction X, thereby realizing the extension and retraction of the slat 220.

[0055] To improve aerodynamic performance in the transonic range, reduce drag, and enhance attitude controllability, the aircraft employs a supercritical wing. The deployment and retraction of slats on supercritical wings typically utilize a rack and pinion drive. However, due to the relatively low airfoil height on the outer side of supercritical wings, a rack and pinion actuator to meet the slat deployment and retraction load requirements would be excessively large. Such an oversized actuator would protrude from the wing's shape, resulting in a large wing volume and significantly impacting the aircraft's lift. Conversely, small-sized rack and pinion actuators present manufacturing difficulties, leading to increased costs.

[0056] The slat mechanism 100 provided in this application embodiment has the actuator 11 in the drive member 10 located inside the wing 210, and the telescopic section 12 extending out of the wing 210 and connecting to the slat 220 at one end away from the actuator 11. This improves space utilization and avoids occupying the space between the wing 210 and the slat 220, preventing the wing 210 from becoming too large due to the actuator 11 being too large. It also ensures that the output power of the actuator 11 meets the load requirements for slat retraction and extension, making the slat mechanism 100 suitable for the retraction and extension of slats on supercritical wings, reducing the impact on the lift of the aircraft 200. Two ribs 21 are provided on the side of the wing 210 facing the slat 220 along the travel direction X, and the slide rail 30 is provided on the two ribs. In the cavity 2100 defined by 21, one end of the slide rail 30 is connected to the slat 220, and the other end is suspended. The actuator 11 can drive the telescopic section 12 to extend or retract along the travel direction X, thereby driving the slat 220 to extend or retract along the travel direction X through the telescopic section 12. This causes the slat 220 to drive the slide rail 30 to move between the two ribs 21 along the travel direction X. The combined design of the ribs 21 and the slide rail 30 limits the slide rail 30 through the two ribs 21, allowing the slide rail 30 to move stably and smoothly along the travel direction X. In turn, the slide rail 30 restricts the extension or retraction of the slat 220 along the travel direction X, ensuring the stability of the slat 220's extension and retraction, and ensuring the stability and safety of the aircraft 200.

[0057] In some embodiments, the actuator 11 is a linear actuator, such as a linear motor. In other implementations, the actuator 11 can be a hydraulic cylinder or a pneumatic cylinder, depending on the specific application requirements.

[0058] In some embodiments, refer to Figures 8-10 as well as Figures 14-15 The mounting assembly 20 also includes at least two limiting wheels 22, which are spaced apart in the receiving cavity 2100 along the travel direction X, as shown in the figure. Figures 8-10 The slide rail 30 includes a first surface 301 and a second surface 302 arranged opposite each other along the thickness direction Z of the wing 210. Along the thickness direction Z, the first surface 301 abuts against at least one limiting wheel 22, and the second surface 302 abuts against at least one limiting wheel 22. The slide rail 30 moves along the travel direction X, and the slide rail 30 can drive the limiting wheel 22 to rotate. The design of the limiting wheel 22, and the fact that the first surface 301 and the second surface 302 of the slide rail 30 abut against the limiting wheel 22 respectively, allows the limiting wheel 22 to guide the movement of the slide rail 30 along the travel direction X and to limit the slide rail 30 along the thickness direction Z, thereby bearing the aerodynamic load and vertical heading load of the slat 220 along the thickness direction Z, ensuring the stability of the slat 220's deployment and retraction.

[0059] In some embodiments, refer to Figures 8-10 as well as Figures 14-15 There are two limiting wheels 22, including a first limiting wheel 22a and a second limiting wheel 22b. The first limiting wheel 22a and the second limiting wheel 22b are spaced apart in the receiving cavity 2100 along the traveling direction X. Specifically, the first limiting wheel 22a is adjacent to the slat 220 along the traveling direction X, and the second limiting wheel 22b is away from the slat 220 along the traveling direction X. Along the thickness direction Z, the first limiting wheel 22a abuts against the first surface 301 of the slide rail 30, and the second limiting wheel 22b abuts against the second surface 302 of the slide rail 30. Specifically, the first limiting wheel 22a rolls in contact with the first surface 301, and the second limiting wheel 22b rolls in contact with the second surface 302. The slat 220 drives the slide rail 30 to move in the receiving cavity 2100 along the traveling direction X, and the slide rail 30 can drive the first limiting wheel 22a and the second limiting wheel 22b to rotate. The first limiting wheel 22a and the second limiting wheel 22b cooperate to limit the slide rail 30 along the thickness direction Z, thereby bearing the aerodynamic load and vertical yaw load of the slat 220 along the thickness direction Z and ensuring the stability of the slat 220's retraction and extension. Moreover, the first limiting wheel 22a and the second limiting wheel 22b are spaced apart along the travel direction X, which can improve the space utilization rate within the receiving cavity 2100.

[0060] In some embodiments, the number of limiting wheels 22 can be selected according to actual usage requirements. Specifically, the first surface 301 of the slide rail 30 can abut against two or more first limiting wheels 22a, and the second surface 302 can abut against two or more second limiting wheels 22b.

[0061] In some embodiments, refer to Figures 2-3 as well as Figures 6-7 The two ribs 21 include a first rib 21a and a second rib 21b, which are spaced apart along the spanwise direction Y, as shown in the figure. Figure 15 The limiting wheel 22 is sleeved on the bolt 26, and the bolt 26 is inserted into the first rib 21a and the second rib 21b along the span direction Y. The bolt 26 is fitted with a nut 27 to ensure the installation stability of the first limiting wheel 22a and the second limiting wheel 22b in the receiving cavity 2100.

[0062] In some embodiments, refer to Figures 4-5 as well as Figures 8-10 The first surface 301 of the slide rail 30 has a protrusion 31 extending from the end adjacent to the slat 220 along the travel direction X. Along the travel direction X, as the slat 220 moves the slide rail 30 closer to the wing 210, the protrusion 31 can abut against the limiting wheel 22 of the adjacent slat 220 to prevent the slat 220 from continuing to approach the wing 210. Specifically, as follows... Figures 8-10 In the embodiment shown, the protrusion 31 is adjacent to the first limiting wheel 22a along the travel direction X, referring to... Figure 9 During the process of the actuator 11 driving the telescopic section 12 to retract the slat 220, the slat 220 drives the slide rail 30 to approach the wing 210 along the travel direction X until the protrusion 31 abuts against the first limiting wheel 22a, thereby forming a blockage to the slide rail 30 moving along the travel direction X, preventing the slat 220 from continuing to approach the wing 210, thus preventing the slat 220 from colliding with the wing 210 during the retraction process, ensuring the safety and service life of the slat 220 and the wing 210.

[0063] In some embodiments, a protrusion 31 protrudes from the second surface 302 of the slide rail 30, near one end of the slat 220 along the travel direction X. At least one limiting wheel 22 abuts against the second surface 302, and is disposed in the receiving cavity 2100 near one end of the slat 220. The slat 220 drives the slide rail 30 closer to the wing 210 along the travel direction X. The protrusion 31 abuts against the limiting wheel 22 along the travel direction X to prevent the slat 220 from continuing to approach the wing 210.

[0064] In some embodiments, refer to Figure 3 , Figures 6-10 as well as Figures 14-15 The mounting assembly 20 also includes at least two support wheels 23, which are spaced apart in the receiving cavity 2100 along the travel direction X. Along the thickness direction Z, at least one support wheel 23 is provided on the side of the first surface 301 opposite to the second surface 302, and at least one support wheel 23 is provided on the side of the second surface 302 opposite to the first surface 301. (Refer to...) Figures 8-10 as well as Figure 15Along the thickness direction Z, there is a gap 230 between the support wheel 23 and the slide rail 30, allowing the support wheel 23 to abut against the slide rail 30. The design of the support wheel 23 in the mounting assembly 20, and the gap 230 between the support wheel 23 and the slide rail 30 in the thickness direction Z, enables the slat 220 to smoothly move the slide rail 30 along the travel direction X, thus ensuring the stability of the slat 220's deployment and retraction. When the slat 220 is retracted or extended, and the actuator 11 is stopped, or when the aircraft 200 is stopped, the support wheel 23 abuts against the slide rail 30 along the thickness direction Z to support the slide rail 30, thereby bearing the aerodynamic load and vertical yaw load of the slat 220 along the thickness direction Z, ensuring the stability and safety of the slat 220's deployment and retraction, and guaranteeing the service life of the slat 220.

[0065] In some embodiments, refer to Figures 8-10 as well as Figures 14-15 There are two support wheels 23, including a first support wheel 23a and a second support wheel 23b. The first support wheel 23a and the second support wheel 23b are spaced apart in the receiving cavity 2100 along the traveling direction X. Specifically, the first support wheel 23a is away from the slat 220 along the traveling direction X, and the second support wheel 23b is adjacent to the slat 220 along the traveling direction X. The first support wheel 23a and the first limiting wheel 22a are located on the same side of the first surface 301, and the second support wheel 23b and the second limiting wheel 22b are located on the same side of the second surface 302. (Refer to...) Figures 8-9 The first support wheel 23a and the first surface 301 have a gap 230 along the thickness direction Z, as shown in the figure. Figures 8-9 as well as Figure 15 A gap 230 exists between the second support wheel 23b and the second surface 302 along the thickness direction Z. This gap 230 ensures that during the movement of the slat 220 along the travel direction X, at least one of the first support wheel 23a and the second support wheel 23b will not contact the slide rail 30, thus guaranteeing the smooth movement of the slide rail 30 along the travel direction X and ensuring the smoothness and stability of the slat 220's retraction and extension. When the slat 220 is retracted or extended, the actuator 11 is stopped, or the aircraft 200 is stopped, the first support wheel 23a can abut against the first surface 301 along the thickness direction Z, and / or the second support wheel 23b can abut against the second surface 302 along the thickness direction Z, forming support for the slide rail 30. This supports the aerodynamic load and vertical yaw load of the slat 220 along the thickness direction Z, ensuring the stability and safety of the slat 220's retraction and extension, and guaranteeing the service life of the slat 220.

[0066] In some embodiments, the number of support wheels 23 can be selected according to actual usage requirements. Specifically, two or more first support wheels 23a can be provided on the side of the first surface 301 of the slide rail 30 that is away from the second surface 302, and two or more second support wheels 23b can be provided on the side of the second surface 302 that is away from the first surface 301.

[0067] In some embodiments, the support wheel 23 can roll contact with the slide rail 30. Specifically, the first support wheel 23a can roll contact with the first surface 301 of the slide rail 30, and the second support wheel 23b can roll contact with the second surface 302 of the slide rail 30.

[0068] In some embodiments, refer to Figure 15 The support wheel 23 is sleeved on the bolt 26, and the bolt 26 is inserted into the first rib 21a and the second rib 21b along the span direction Y. The bolt 26 is fitted with a nut 27 to ensure the installation stability of the first support wheel 23a and the second support wheel 23b in the receiving cavity 2100.

[0069] In some embodiments, refer to Figure 8 A first distance L1 mm exists between the support wheel 23 located on one side of the first surface 301 and the opposite surface of the first surface 301, satisfying: 0.1 mm ≤ L1 ≤ 0.3 mm, specifically as follows: Figure 8 In the illustrated embodiment, a first distance L1mm exists between the first support wheel 23a and the opposite surface of the first surface 301, satisfying: 0.1mm≤L1≤0.3mm. The value of L1 can be any value among 0.1mm, 0.15mm, 0.2mm, 0.25mm, and 0.3mm, or any value within a range of any two values. When the value of the first distance L1 is within the above range, it ensures that the distance between the first support wheel 23a and the first surface 301 can guarantee the smoothness and stability of the slide rail 30 moving along the travel direction X. It also ensures support for the slide rail 30 along the thickness direction Z when the actuator 11 or the aircraft 200 is stopped, thereby bearing the aerodynamic load and vertical heading load of the slat 220 along the thickness direction Z, ensuring the stability and safety of the slat 220's deployment and retraction, and guaranteeing the service life of the slat 220.

[0070] In some embodiments, refer to Figure 8 A second distance L2 mm exists between the support wheel 23 located on one side of the second surface 302 and the opposite surface of the second surface 302, satisfying: 0.1 mm ≤ L2 ≤ 0.3 mm, specifically as follows: Figure 8In the illustrated embodiment, a second distance L2mm exists between the second support wheel 23b and the opposite surface of the second surface 302, satisfying: 0.1mm≤L2≤0.3mm. The value of L2 can be any value among 0.1mm, 0.15mm, 0.2mm, 0.25mm, and 0.3mm, or any value within a range of any two values. When the value of the second distance L2 is within the above range, it ensures that the distance between the second support wheel 23b and the second surface 302 can guarantee the smoothness and stability of the slide rail 30 moving along the travel direction X. It also ensures support for the slide rail 30 along the thickness direction Z when the actuator 11 or the aircraft 200 is stopped, thereby bearing the aerodynamic load and vertical heading load of the slat 220 along the thickness direction Z, ensuring the stability and safety of the slat 220's deployment and retraction, and guaranteeing the service life of the slat 220.

[0071] In some embodiments, refer to Figures 6-10 as well as Figure 14 The mounting component 20 also includes a stop 24, see reference. Figures 6-7 The stop 24 is inserted into the rib 21, as shown in the reference. Figure 4 , Figure 8 as well as Figure 16 The slide rail 30 includes a third surface 303 and a fourth surface 304 arranged opposite each other along the wingspan direction Y of the wing 210, as shown in the figure. Figures 4 to 10 as well as Figures 14-16 At least one of the third surface 303 and the fourth surface 304 has a groove 32, as shown in the figure. Figure 8 and Figure 10 The groove 32 includes a first groove wall 321 and a second groove wall 322 disposed opposite to each other along the travel direction X. The first groove wall 321 is adjacent to the slat 220, and the second groove wall 322 is away from the slat 220. (Refer to...) Figures 8-10 The stop 24 is inserted into the groove 32, as shown in the reference. Figure 10 The slat 220 drives the slide rail 30 away from the wing 210 along the travel direction X. The stop 24 can abut against the second groove wall 322 to prevent the slat 220 from continuing to move away from the wing 210. During the process of the actuator 11 driving the telescopic section 12 to extend and drive the slat 220 to extend, the slat 220 drives the slide rail 30 away from the wing 210 along the travel direction X. The design of the stop 24 and the groove 32 on the slide rail 30 allows the stop 24 to abut against the second groove wall 322 of the groove 32 to prevent the slat 220 from continuing to drive the slide rail 30 away from the wing 210. This limits the extension stroke and extension range of the slat 220, avoids damage due to excessive extension stroke and extension range of the slat 220, and ensures the stability and service life of the slat 220, slide rail 30, and wing 210.

[0072] In some embodiments, refer to Figure 15The slide rail 30 has grooves 32 on its third surface 303 and fourth surface 304 respectively. A stop 24 is inserted on the first rib 21a and the second rib 21b respectively. The two stop 24 are respectively inserted into the grooves 32 adjacent to each other along the wingspan direction Y. The two stop 24 are arranged opposite to each other and coaxial along the wingspan direction Y, so that the two stop 24 cooperate to form a synchronous stop on the slide rail 30 moving along the travel direction X, thereby forming a stability that limits the extension stroke and extension range of the slat 220.

[0073] In some embodiments, the stop 24 is a bolt, specifically, the stop 24 is a stop bolt.

[0074] In some embodiments, refer to Figures 2-3 , Figures 6-10 , Figure 14 as well as Figure 16 The mounting assembly 20 also includes at least two clamping members 25, which are inserted into ribs 21. Each rib 21 corresponds to at least one clamping member 25. The clamping member 25 inserted into one rib 21 abuts against the third surface 303 of the slide rail 30, and the clamping member 25 inserted into the other rib 21 abuts against the fourth surface 304 of the slide rail 30, thereby clamping the slide rail 30. The clamping members 25 can clamp the slide rail 30 along the spanwise direction Y, thereby bearing the lateral load of the slide rail 30 along the spanwise direction Y, ensuring the installation stability of the slide rail 30 in the receiving cavity 2100, and thus ensuring the stability of the slat 220's retraction and extension.

[0075] In some embodiments, refer to Figures 2-3 , Figures 6-10 , Figure 14 as well as Figure 16 The mounting assembly 20 includes four clamping members 25 along the wingspan direction Y. The four clamping members 25 are arranged in pairs facing each other. Two clamping members 25 inserted on the same rib plate 21 are arranged at intervals along the travel direction X, thereby ensuring the stability of clamping the slide rail 30 along the wingspan direction Y, ensuring the stability of the clamping members 25 bearing the lateral load of the slide rail 30 along the wingspan direction Y, and ensuring the stability of the slat 220 in retraction and extension.

[0076] In some embodiments, refer to Figure 16The clamping member 25 rolls in contact with the slide rail 30. Specifically, the clamping member 25 inserted on the first rib 21a rolls in contact with the third surface 303 of the slide rail 30, and the clamping member 25 inserted on the second rib 21b rolls in contact with the fourth surface 304 of the slide rail 30. This ensures the smoothness and stability of the slide rail 30's movement along the travel direction X, reduces wear between the clamping member 25 and the slide rail 30, and extends their service life. In some implementations, a bearing is provided at one end of the clamping member 25 adjacent to the slide rail 30 along the span direction Y, thereby achieving rolling contact between the clamping member 25 and the slide rail 30.

[0077] In some embodiments, refer to Figure 4 The first surface 301 protrudes along the thickness direction Z in a direction away from the second surface 302 to form a convex arc surface.

[0078] In some embodiments, refer to Figure 4 The second surface 302 protrudes along the thickness direction Z away from the first surface 301 to form a concave arc surface.

[0079] The structural design of the first surface 301 (convex arc surface) and / or the structural design of the second surface 302 (concave arc surface) makes the slide rail 30 form an arc structure as a whole, thereby achieving a 0° to 24° extension angle of the slat wing, ensuring the smoothness and stability of the slat wing 220 in retraction and extension.

[0080] In some embodiments, refer to Figures 11-13 as well as Figure 17 The wing 210 includes a wing box 211, and an actuator 11 is disposed in the wing box 211. The wing box 211 includes a first beam 2111 and a second beam 2112 disposed opposite to each other along the travel direction X. (Refer to...) Figure 1 as well as Figures 11-13 The slat 220 has a first connecting portion 221 protruding from the side facing the wing 210 along the travel direction X, as shown in the reference. Figures 11-13 as well as Figure 17 The actuator 11 is detachably connected to the first beam 2111 at one end opposite to the telescopic section 12 along the travel direction X, as shown in the reference. Figures 11-13 as well as Figure 18 The telescopic section 12 extends from the end opposite to the actuator 11 along the travel direction X, extending out of the second beam 2112 and detachably connected to the first connecting part 221. (Refer to...) Figure 13Rib 21 protrudes along the travel direction X and is disposed on the side of the second beam 2112 opposite to the first beam 2111. The arrangement of the wing box 211 allows the actuator 11 in the drive component 10 to be disposed in the wing 210, thereby improving the space utilization rate inside the wing 210 and avoiding occupying the space between the wing 210 and the slat 220. This prevents the wing 210 from becoming too large due to the excessive size of the actuator 11, and ensures that the output power of the actuator 11 meets the load requirements for the slat retraction and extension. This allows the slat mechanism 100 to be applicable to the retraction and extension of slats on supercritical wings, reducing the impact on the lift of the aircraft 200. Moreover, the second beam 2112 can provide a mounting base for the rib 21 in the mounting assembly 20, ensuring the installation stability of the mounting assembly 20, and thus ensuring the installation stability of the slide rail 30.

[0081] Among them, reference Figure 1 and Figure 5 The slat 220 includes an inner skin 2201 and an outer skin 2202 arranged along the travel direction X. The outer skin 2202 is arc-shaped. The two opposite ends of the inner skin 2201 along the thickness direction Z are respectively connected to the outer skin 2202. The first connecting part 221 protrudes from the inner skin 2201 along the travel direction X.

[0082] In the following embodiments, reference is made to Figure 1 , Figures 11-13 as well as Figure 17 The first beam 2111 has a third connecting part 2113 protruding from the side of the first beam 2111 facing the second beam 2112 along the travel direction X. The end of the actuator 11 away from the telescopic section 12 is detachably connected to the third connecting part 2113, thereby ensuring the installation stability of the actuator 11 in the wing box 211, and thus ensuring the stability of the slat 220 in retraction and extension.

[0083] In some embodiments, refer to Figure 1 and Figure 13 There are two mounting components 20, spaced apart along the wingspan direction Y. One mounting component 20 is provided on each side of the drive component 10 along the wingspan direction Y. This arrangement of the mounting components 20 and the drive component 10 along the wingspan direction Y improves the space utilization between the wing 210 and the slat 220, and ensures the stability of the slat 220 during retraction and extension.

[0084] In some embodiments, refer to Figure 5 , Figures 8-10 The slat 220 has a second connecting part 222 protruding from the side facing the wing 210 along the travel direction X. The end of the slide rail 30 adjacent to the slat 220 along the travel direction X is detachably connected to the second connecting part 222. Specifically... Figure 5 In the embodiment shown, the second connecting portion 222 protrudes from the inner skin 2201 of the slat 220, specifically as follows: Figure 5 as well as Figures 8-10 In the embodiment shown, the slide rail 30 has an ear 33 protruding from one end adjacent to the slit 220 along the travel direction X. The slide rail 30 is detachably connected to the second connecting part 222 through the ear 33, thereby ensuring the connection stability between the slide rail 30 and the slit 220 and ensuring the opening and closing stability of the slit 220.

[0085] The above provides a detailed description of a slat mechanism and aircraft provided in the embodiments of this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The description of the above embodiments is only for the purpose of helping to understand the technical solutions and core ideas of this application. Those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A slat mechanism for connecting a wing (210) of an aircraft (200) with a slat (220), characterized by The slat mechanism (100) includes: The drive unit (10) includes an actuator (11) and a telescopic section (12) connected along the travel direction (X) of the aircraft (200). The actuator (11) is disposed on the inner side of the wing (210), and the telescopic section (12) extends out of the wing (210) from one end away from the actuator (11) and is connected to the slat (220). Mounting assembly (20) includes two ribs (21) spaced apart along the wingspan direction (Y) of the wing (210) to define a receiving cavity (2100), the ribs (21) protruding from the side of the wing (210) facing the slat (220) along the travel direction (X); A slide rail (30) is disposed in the receiving cavity (2100) along the travel direction (X), one end of the slide rail (30) is connected to the slat (220), and the other end is suspended. The actuator (11) can drive the telescopic section (12) to move the slat (220) along the direction of travel (X), and the slat (220) can drive the slide rail (30) to move between the two ribs (21) along the direction of travel (X).

2. The slat mechanism of claim 1, wherein, The mounting assembly (20) further includes at least two limiting wheels (22), which are spaced apart in the receiving cavity (2100) along the travel direction (X); The slide rail (30) includes a first surface (301) and a second surface (302) disposed opposite to each other along the thickness direction (Z) of the wing (210); Along the thickness direction (Z), the first surface (301) abuts against at least one of the limiting wheels (22), and the second surface (302) abuts against at least one of the limiting wheels (22); The slide rail (30) moves along the travel direction (X), and the slide rail (30) can drive the limiting wheel (22) to rotate.

3. The slat mechanism of claim 2, wherein, The first surface (301) has a protrusion (31) protruding from one end of the first surface (301) adjacent to the slat (220) along the travel direction (X); And / or, the second surface (302) is provided with a protrusion (31) protruding from one end of the slat (220) along the travel direction (X); Along the travel direction (X), the slat (220) drives the slide rail (30) to approach the wing (210), and the protrusion (31) can abut against the limiting wheel (22) of the adjacent slat (220) to prevent the slat (220) from continuing to approach the wing (210).

4. The slat mechanism of claim 1, wherein, The mounting assembly (20) further includes at least two support wheels (23), which are spaced apart in the receiving cavity (2100) along the travel direction (X); The slide rail (30) includes a first surface (301) and a second surface (302) disposed opposite to each other along the thickness direction (Z) of the wing (210); Along the thickness direction (Z), at least one of the support wheels (23) is provided on the side of the first surface (301) opposite to the second surface (302), and at least one of the support wheels (23) is provided on the side of the second surface (302) opposite to the first surface (301); Along the thickness direction (Z), there is a gap (230) between the support wheel (23) and the slide rail (30), and the support wheel (23) can abut against the slide rail (30).

5. The slat mechanism of claim 4, wherein, The support wheel (23) disposed on one side of the first surface (301) has a first distance L1 mm between it and the opposite surface of the first surface (301), satisfying: 0.1 mm ≤ L1 ≤ 0.3 mm; And / or, there is a second distance L2 mm between the support wheel (23) disposed on one side of the second surface (302) and the opposite surface of the second surface (302), satisfying: 0.1mm≤L2≤0.3mm.

6. The slat mechanism of claim 1, wherein, The mounting assembly (20) further includes a stop (24) inserted into the rib (21); The slide rail (30) includes a third surface (303) and a fourth surface (304) arranged opposite each other along the wingspan direction (Y) of the wing (210); At least one of the third surface (303) and the fourth surface (304) is provided with a groove (32), the groove (32) including a first groove wall (321) and a second groove wall (322) disposed opposite to each other along the travel direction (X), the first groove wall (321) being adjacent to the slat (220) and the second groove wall (322) being away from the slat (220); The stop (24) is inserted into the groove (32), and the slat (220) drives the slide rail (30) away from the wing (210) along the travel direction (X). The stop (24) can abut against the second groove wall (322) to prevent the slat (220) from continuing to move away from the wing (210).

7. The slat mechanism of claim 1, wherein, The mounting assembly (20) further includes at least two clamping members (25), which are inserted into the rib (21), with one rib (21) corresponding to at least one clamping member (25); The slide rail (30) includes a third surface (303) and a fourth surface (304) arranged opposite each other along the wingspan direction (Y) of the wing (210); The clamping member (25) inserted on one of the ribs (21) abuts against the third surface (303), and the clamping member (25) inserted on the other rib (21) abuts against the fourth surface (304) to form a clamping of the slide rail (30).

8. The slat mechanism of claim 7, wherein, The clamping member (25) makes rolling contact with the slide rail (30).

9. The slat mechanism of claim 1, wherein, The slide rail (30) includes a first surface (301) and a second surface (302) disposed opposite to each other along the thickness direction (Z) of the wing (210); The first surface (301) protrudes in the direction away from the second surface (302) along the thickness direction (Z) to form a convex arc surface; And / or, the second surface (302) is recessed along the thickness direction (Z) toward the first surface (301) to form a concave arc surface.

10. The slat mechanism of claim 1, wherein, The wing (210) includes a wing box (211), and the actuator (11) is disposed in the wing box (211). The wing box (211) includes a first beam (2111) and a second beam (2112) disposed opposite to each other along the travel direction (X). The slat (220) has a first connecting portion (221) protruding from the side facing the wing (210) along the direction of travel (X); The actuator (11) is detachably connected to the first beam (2111) at one end away from the telescopic section (12); The telescopic section (12) extends out of the second beam (2112) from the end opposite to the actuator (11) and is detachably connected to the first connecting part (221); Along the direction of travel (X), the rib (21) protrudes from the side of the second beam (2112) opposite to the first beam (2111).

11. The slat mechanism of claim 1, wherein, The number of the mounting components (20) is two, and they are spaced apart along the wingspan direction (Y); Along the wingspan direction (Y), a mounting assembly (20) is provided on each side of the drive member (10).

12. The slat mechanism of claim 1, wherein, The slat (220) has a second connecting part (222) protruding from the side facing the wing (210) along the direction of travel (X); The slide rail (30) is detachably connected to the second connecting part (222) at one end of the slide rail (30) adjacent to the slat (220) along the travel direction (X).

13. An aircraft characterized by, Includes the slat mechanism (100) as described in any one of claims 1 to 12.

Images