Flap support assembly for a wing including a flap and a wing including a flap

Abstract

The present invention relates to a flap support assembly for a wing comprising a flap and a wing comprising a flap. The flap support assembly comprises a flap support body having a guide rail on a first side of the flap support body for a flap to be slidably connected to the flap support body, a first support member having a first end rotatably connected to a first end of the flap support body and a second end rotatably connected to a first location of a frame of the wing, and a second support member having a first end rotatably connected to a second end of the flap support body and a second end rotatably connected to a second location of the frame, wherein the flap support body, the first support member, the second support member and the frame are formed as a four-bar linkage such that the guide rail on the flap support body is movable relative to the frame under constraint of the first support member and the second support member.

Description

Technical Field

[0001] This invention relates to a flap support assembly for an aircraft wing including flaps, which provides support for the flaps throughout their entire extension and retraction stroke and limits their displacement or vibration in non-motion directions. The invention also relates to an aircraft wing including flaps. This invention belongs to the field of aircraft wing structure design. Background Technology

[0002] Aircraft flaps are movable flaps attached to the trailing edge of the wing. Normally integrated with the wing, they can be deployed to adjust the aircraft's attitude. Flaps increase the wing's surface area, alter its airfoil curvature, and increase lift, and are most commonly used during low-speed takeoff and landing. The flaps are connected to the wing by two sets of motion mechanisms, each positioned at a specific location on either side of the flap's spanwise direction.

[0003] Flaps are typically mounted on the trailing edge of the wings of fixed-wing aircraft and can deflect downwards and slide backwards when in use. When the flaps are deployed, their ends are suspended in the air, and significant vibrations occur at the ends as airflow passes over them, especially on large aircraft. If the ends are not restrained, the vibration effect caused by airflow is even more pronounced, which can cause discomfort to passengers and crew, and may even lead to structural damage and induce other vibration problems.

[0004] In the prior art, the patent "Auxiliary Support System for Flaps of Aircraft Wings" describes a flap rail sealing device. This device uses rollers and I-beam rails, with the rails connected to the flaps via spherical bearings. The rail surface is S-shaped and non-parallel, and the tail has a stop function. However, the flap support system using rollers and I-beam rails is suitable for flaps with two-dimensional motion. When the flaps undergo three-dimensional motion, this design is no longer applicable.

[0005] Therefore, there is an urgent need to develop a support device that can suppress flap tip vibration without affecting flap movement, so as to provide technical reserves for model development. Summary of the Invention

[0006] To address the aforementioned problems in the prior art, the present invention aims to provide a flap support mechanism that is simple in form, provides support for the flap throughout its entire extension and retraction stroke, limits its displacement or vibration in non-movement directions, and has high motion reliability.

[0007] In a first example of the flap support assembly, the flap support assembly includes: a flap support body having a guide rail on a first side for slidably connecting a flap to the flap support body; a first support member having a first end rotatably connected to a first end of the flap support body and a second end rotatably connected to a first position of the wing frame; and a second support member having a first end rotatably connected to a second end of the flap support body and a second end rotatably connected to a second position of the frame; wherein the flap support body, the first support member, the second support member, and the frame form a four-bar linkage, such that the guide rail on the flap support body can move relative to the frame under the constraint of the first and second support members.

[0008] In a second example of the flap support assembly, a first example may be included, wherein a first end of a first support member is connected to a first end of a flap support body via two lugs and a pin, and the first support member is allowed to rotate relative to the flap support body only in a first rotational direction; and a second end of the first support member is connected to the wing frame via two lugs and a pin, and the first support member is allowed to rotate relative to the frame only in the first rotational direction, so that the flap support body can provide support for the flap in the non-movement direction and thus withstand torques in other directions.

[0009] In a third example of the flap support assembly, one or more of the first and second examples may be included, wherein the first end of the second support is connected to the second end of the flap support body via a spherical bearing, and the second end of the second support is connected to the wing frame via a spherical bearing.

[0010] In the fourth example of this flap support assembly, one or more of the first to third examples may be included. The second support member is in the form of a sleeve rod and its overall length can be adjusted and maintained. Therefore, the overall movement of the flap support assembly 1 can be adjusted during ground installation to meet the actual needs of the flap 3 during aircraft operation.

[0011] In the fifth example of the flap support assembly, one or more of the first to fourth examples may be included, wherein the flap support body and / or the first support member and / or the second support member are provided with a body weight-reducing part or a support member weight-reducing part that does not affect the overall structural strength. The shape and position of these body weight-reducing parts and support member weight-reducing parts are designed not to affect their overall structural strength.

[0012] In the sixth example of this flap support assembly, one or more of the first to fifth examples may be included, with the first support and / or the second support connected to the second side of the flap support body opposite the first side. The appropriate dimensions of the quadrilateral in the form of a four-bar linkage, allowing the flap's travel distance, can be achieved while ensuring that the length of the flap support body 20 meets the length of the guide rail 21.

[0013] In the seventh example of this flap support assembly, one or more of the first to sixth examples may be included, with the frame comprising a wing bulkhead and a wing rear spars. Due to its proximity to the bulkhead, the lengths of the first and second supports can be shorter when fixed to the bulkhead, resulting in an overall weight reduction.

[0014] The present invention also provides a wing including flaps, wherein the wing includes the flap support assembly described in any of the foregoing examples.

[0015] The flap support assembly of the present invention has the characteristics of simple form, providing support for the flap throughout the entire stroke of the flap and limiting its displacement or vibration in non-movement directions, and having high motion reliability. Attached Figure Description

[0016] To describe embodiments of the above and other features of the present invention, a more detailed description of the invention will be presented with reference to exemplary embodiments of the invention shown in the accompanying drawings. It is to be understood that these drawings depict only exemplary embodiments of the invention and should not be considered as limiting its scope; the invention will be described and explained using the drawings and with the aid of additional features and details. In the drawings:

[0017] Figure 1 This is a perspective view of the flap support assembly in its installed state according to an embodiment of the present invention;

[0018] Figure 2 This is a perspective view of the flap support body of the flap support assembly according to an embodiment of the present invention;

[0019] Figure 3 This is a perspective view of the flap support assembly according to an embodiment of the present invention, viewed from another direction; and

[0020] Figure 4 This is an exploded view of the flap support assembly according to an embodiment of the present invention.

[0021] Figures 1 to 4 The figures are drawn roughly to scale; however, the dimensions in the accompanying drawings are merely illustrative and not necessarily to scale, but are intended to make the illustration clearer. Other relative dimensions may be used in other embodiments.

[0022] Throughout this and all subsequent content, the same features appearing in different figures are indicated by the same or similar reference numerals.

[0023] List of reference numerals in the attached diagram:

[0024] 1. Flap support assembly

[0025] 2 Framework

[0026] 3. Flaps

[0027] 20. Flaps support the main body.

[0028] 20a First end of the flap support body

[0029] 20b The second end of the flap support body

[0030] 21 guide rails

[0031] 22. Main body weight reduction section

[0032] 30 First support component

[0033] 31 Weight Reduction Section of Support Components

[0034] 40 Second support component Detailed Implementation

[0035] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0036] In this invention, directional terms such as “vertical,” “horizontal,” “top,” “bottom,” “upper,” “lower,” “inner,” “inward,” “outer,” and “outward” are used to assist in describing the direction of the invention according to the embodiments shown in the figures. Directional terms are not absolute terms such as up, down, horizontal, vertical, etc., and should not be construed as limiting the invention to any particular direction.

[0037] In this invention, unless explicitly stated otherwise, the terms “first,” “second,” etc., are not intended to indicate any order, position, quantity, or importance, but are merely used as labels to distinguish one element from another.

[0038] In this invention, the term "spherical bearing" refers to a joint that can rotate in all directions within a certain range. It is not limited to a bearing, but rather any joint structure that can provide rotation in all directions to prevent the connected mechanism from jamming during movement.

[0039] In existing technology, most flap support components are directly fixed to the rear spars of the wing. Because the support point is far from the rear spars, the flap support component needs to be made long enough, thus requiring more weight.

[0040] The flap support assembly of this application may not be fixed to the rear beam, but may instead be fixed to the adjacent bulkhead. Due to its proximity to the bulkhead, the length of the connector is shorter; specifically, the lengths of the first support 30 and the second support 40 can be shorter, resulting in an overall reduction in weight.

[0041] Figure 1 A perspective view of the flap support assembly 1 of a preferred embodiment of the present invention in its installed state is shown schematically. The flap support assembly 1 mainly includes a flap support body 20 and a first support member 30 and a second support member 40 that connect the flap support body 20 to the wing frame 2.

[0042] Figure 2 This is a schematic perspective view of the flap support body 20 of the flap support assembly 1 according to a preferred embodiment of the present invention, showing a guide rail 21 on a first side of the flap support body 20. The guide rail 21 is shaped to accommodate the flap 3 (in... Figure 1 (As shown in the figure) The flap 3 is slidably connected to the flap support body 20 throughout its entire retraction and extension stroke, and thus the flap 3 is slidably connected to the flap support body 20, and further connected to the wing frame 2.

[0043] When the flap 3 tends to vibrate or deform in a direction other than motion, it will be restricted by the side wall of the guide rail 21 on the flap support body 20, thereby avoiding the vibration or deformation of the flap.

[0044] The specific guiding direction and shape of the guide rail 21 are not limited, and are determined according to the specific movement requirements of the flap 3. During the entire stroke of the flap 3, the movement of the flap 3 will generate relative movement with the flap support body 20. Its relative movement trajectory is consistent with the shape of the guide rail 21 of the flap support body 20, so as to help prevent the movement of the flap 3 from getting stuck.

[0045] The flap 3 has support rods on both sides, and the support rods contact the guide rail 21. Therefore, the guide rail 21 provides guidance and support for the flap 3 throughout its entire extension and retraction.

[0046] Preferably, the flap support body 20 may be provided with a main body weight reduction part 22, the shape and position of which are designed not to affect the overall structural strength. In order to reduce the weight of the parts, weight reduction through holes or weight reduction blind holes may be provided according to the actual situation.

[0047] Now go to Figure 3The figure shows a perspective view of the flap support assembly 1 of a preferred embodiment of the present invention viewed from another direction.

[0048] The first end of the first support member 30 is rotatably connected to the first end 20a of the flap support body 20, and the second end of the first support member 30 is rotatably connected to a first position of the wing frame 2. Furthermore, the first end of the second support member 40 is rotatably connected to the second end 20b of the flap support body 20, and the second end of the second support member 40 is rotatably connected to a second position of the frame 2.

[0049] The flap support body 20, the first support member 30, the second support member 40, and the frame 2 are as follows: Figure 1 The structure shown is a four-bar linkage. This four-bar linkage can be a parallelogram mechanism, but its shape is not limited to this. It can also be an irregular quadrilateral mechanism, as long as the flap support body 20 can move within a certain range, so that the guide rail 21 on the flap support body 20 can move relative to the frame 2 under the constraint of the first support member 30 and the second support member 40.

[0050] The movement trajectory of flap 3 is spatial motion rather than planar motion. The flap support assembly 1, through the four-bar linkage formed by it and the frame 2, moves in the spanwise direction of the aircraft along with the flap 3, thus matching the spatial motion requirements of flap 3 throughout its entire extension and retraction stroke. With the help of this four-bar linkage, the spanwise motion constraint of flap 3 can be released, matching the movement of flap 3 without causing the entire mechanism to jam.

[0051] Figure 4 An exploded view of the flap support assembly 1 according to an embodiment of the present invention is shown schematically.

[0052] refer to Figure 3 and Figure 4 In a preferred embodiment, the first end of the first support member 30 is connected to the first end 20a of the flap support body 20 via a pair of lugs with a predetermined span and a pin, and the first support member 30 is only allowed to rotate relative to the flap support body 20 in the first rotational direction. Furthermore, the second end of the first support member 30 is connected to the wing frame 2 via a pair of lugs and a pin, and the first support member 30 is only allowed to rotate relative to the frame 2 in the first rotational direction.

[0053] Since the first support member 30 is connected by double ears with a predetermined span, the movement of the first support member 30 is constrained, so that the first support member 30 can only rotate relative to the frame 2 or the flap support body 20. Specifically, this structure ensures that the flap support body 20 can only rotate relative to the first support member 30 around the double ears and the pin, so that the flap support body 20 can provide support for the flap 3 in the non-movement direction and thus withstand torque in other directions.

[0054] Therefore, when the flap 3 tends to vibrate or deform in the vertical direction, it will be restricted by the side wall of the guide rail 21 of the flap support body 20, thereby avoiding the vibration or deformation of the flap.

[0055] In contrast, the second support member 40 is designed to provide a predetermined length and is not intended to withstand moments in other directions. The second support member 40 will be described in detail below.

[0056] It is understandable that the structural form of the first support member 30 is not limited to the frame rocker arm form shown in the figure, but can also be a beam with ribs.

[0057] Preferably, the first support member 30 may be provided with a support member weight reduction part 31, the shape and position of which are designed not to affect the overall structural strength. In order to reduce the weight of the part, weight reduction holes or weight reduction blind holes may be provided according to the actual situation.

[0058] Preferably, a connecting lug can be provided on the second side of the flap support body 20 opposite to the first side, and the first support member 30 can be connected to the connecting lug. Compared with the connecting structure being provided at both ends of the flap support body 20, providing it on the second side can satisfy the appropriate size of a quadrilateral in the form of a four-bar linkage that allows the flap's movement stroke, while allowing the length dimension of the flap support body 20 to meet the length dimension of the guide rail 21.

[0059] refer to Figure 3 and Figure 4 The first end of the second support member 40 is connected to the second end 20b of the flap support body 20 via a spherical bearing. Furthermore, the second end of the second support member 40 is connected to the wing frame 2 via a spherical bearing. The "spherical bearing" described herein provides sufficient rotational freedom to prevent the rotary joint from jamming.

[0060] The spherical bearings at both ends of the second support member 40 are used to reduce the friction of the mechanism and ensure the smooth movement of the flap support assembly 1. In addition, the use of spherical bearings also reduces the requirements for the machining accuracy of the mechanism parts, which can reduce costs.

[0061] If the machining accuracy of the parts is sufficient and the rigidity of the connecting components is sufficient, bushings can also be used to replace spherical bearings.

[0062] Using bushings or spherical bearings here not only reduces friction in the mechanism but also protects the main components from wear.

[0063] The second support member 40 is designed in the form of a sleeve, which allows for adjustment of the overall length of the second support member 40 and maintains that overall length during aircraft operation. Therefore, the overall movement of the flap support assembly 1 can be adjusted during ground installation to meet the actual needs of the flap 3 during aircraft operation.

[0064] Preferably, the second support member 40 can be disposed on the second side of the flap support body 20.

[0065] The flap support assembly of the present invention has the characteristics of simple form, providing support for the flap throughout the entire flap extension and retraction stroke and limiting its displacement or vibration in non-movement directions, and having high motion reliability.

[0066] In order to make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention have been clearly and completely described above in conjunction with the specific embodiments and accompanying drawings.

[0067] Although various embodiments have been described above, it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of them, and are presented by way of example rather than limitation. It will be apparent to those skilled in the art that the disclosed subject matter may be implemented in other specific forms without departing from its spirit and essential characteristics.

[0068] Therefore, the embodiments described above are to be considered exemplary and not restrictive in all respects, and are not intended to limit the invention in any way.

[0069] Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. This disclosure also includes various modifications and equivalent variations. In addition, various combinations and methods, further including only one element, one or more or less other combinations and methods, also fall within the scope and concept of this disclosure.

Claims

1. A flap support assembly for a wing including a flap, characterized by, The flap support assembly (1) comprises: a flap support body (20) having a guide rail (21) on a first side of the flap support body (20) for a flap (3) to be slidably connected to the flap support body (20); a first support member (30) having a first end rotatably connected to a first end of the flap support body (20) and a second end rotatably connected to a first location of a frame of the wing; and a second support member (40) having a first end rotatably connected to a second end of the flap support body (20) and a second end rotatably connected to a second location of the frame; wherein the flap support body (20), the first support member (30), the second support member (40) and the frame (2) are formed as a four-bar linkage such that the guide rail (21) on the flap support body (20) is movable relative to the frame (2) under constraint of the first support member (30) and the second support member (40).

2. The flap support assembly according to claim 1, wherein the first end of the first support member (30) is connected to the first end of the flap support body (20) by means of a double ear and a pin shaft and only allows the first support member (30) to rotate relative to the flap support body (20) in a first rotational direction, and the second end of the first support member (30) is connected to the frame (2) of the wing by means of a double ear and a pin shaft and only allows the first support member (30) to rotate relative to the frame (2) in the first rotational direction.

3. The flap support assembly according to claim 1, wherein the first end of the second support member (40) is connected to the second end of the flap support body (20) by means of a joint bearing, and the second end of the second support member (40) is connected to the frame (2) of the wing by means of a joint bearing.

4. The flap support assembly according to claim 1, wherein the second support member (40) is in the form of a set of bars and the overall length of the second support member (40) is adjustable and maintainable.

5. The flap support assembly according to claim 1, wherein a body weight reduction is provided on the flap support body (20), and / or a support member weight reduction is provided on the first support member (30) and / or the second support member (40).

6. The flap support assembly according to claim 1, wherein the first support member (30) and / or the second support member (40) is connected to a second side of the flap support body (20) opposite the first side.

7. The flap support assembly according to claim 1, wherein the frame (2) comprises a bulkhead of the wing and comprises a rear spar of the wing.

8. A wing comprising a flap, characterized in that The wing comprises a flap support assembly according to any one of claims 1-7.

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