An aircraft wing folding mechanism

Abstract

The utility model discloses an aircraft wing folding mechanism, including bottom plate, mounting frame, be located bottom plate's upper end surface's rear side, drive part, be located mounting frame's rear side, sliding block, be located mounting frame's front side and middle part connection drive part's output, two connecting rods, set up along the front and back direction, connect in two sides of sliding block respectively, rocker arm, set up along left and right direction, first end articulate connecting rod's rear end, wing, through the movable seat activity be located bottom plate, the second end of rocker arm connects rotating seat, elastic locking subassembly, be located bottom plate, be used for limiting sliding block moves to the back. Drive part drive sliding block moves forward, and connecting rod moves forward to drive the forward rotation of rocker arm, and drive wing rotates to the unfolded position, and elastic locking subassembly restricts the movement of sliding block to the back, makes wing keep in the unfolded state, through the structure of sliding block, connecting rod and rocker arm converts the linear motion of sliding block into the unfolding motion of wing, and the whole structure is simple, and makes full use of the space on bottom plate, and the structure is compact.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to an aircraft wing folding mechanism. Background Technology

[0002] High-speed unmanned aerial vehicles (UAVs), such as attack loitering munitions, typically take off via box-launch or high-altitude drop. To adapt to rapid relocation and deployment, and to store more UAVs in a limited space, a mechanism is needed that can fold wings for ground storage to minimize space requirements, while also enabling rapid takeoff and in-flight wing deployment. Currently, traditional wing-folding mechanisms are complex, difficult to manufacture and assemble, and mostly consist of disparate structural pieces, lacking modular design and making later maintenance difficult. Utility Model Content

[0003] This utility model provides an aircraft wing folding mechanism, which aims to solve at least one of the technical problems existing in the prior art.

[0004] The technical solution of this utility model relates to an aircraft wing folding mechanism, including... Base plate; The mounting bracket is located on the rear side of the upper end face of the base plate; A drive component is located on the rear side of the mounting bracket; A slider is located on the front side of the mounting bracket and connected in the middle to the output end of the drive component; Two connecting rods are arranged in the front-back direction, and the front ends of the two connecting rods are respectively connected to the two sides of the slider; A rocker arm is provided in the left-right direction, with its first end hinged to the rear end of the connecting rod; The wing is movably mounted on the base plate via a rotating seat, and the second end of the rocker arm is connected to the rotating seat. The number of the rocker arm and the wing matches the number of the connecting rods. An elastic locking component, located on the base plate, is used to restrict the slider from moving backward so that the wing remains in the deployed state.

[0005] According to some embodiments of the present invention, the elastic locking assembly includes a locking block and a spring. The rear side of the locking block is hinged to the base plate. The two ends of the spring are respectively connected to the lower end of the front side of the locking block and the base plate. When the wing rotates to the unfolded state, the spring drives the front side of the locking block to rotate upward and abut against the rear side of the slider.

[0006] According to some embodiments of the present invention, the upper surface of the locking block includes a guide slope and a horizontal surface, the guide slope is inclined from front to top, and the horizontal surface is located on the front side of the guide slope.

[0007] According to some embodiments of the present invention, the output end of the driving component is connected to a push rod, and the front end of the push rod is connected to the slider.

[0008] According to some embodiments of this utility model, there are two locking blocks, which are distributed on both sides of the push rod.

[0009] According to some embodiments of this utility model, it also includes two guide rods, the rear end of which is connected to the mounting bracket, and the other end is connected to the base plate through a mounting seat. The slider is provided with a through hole, and the guide rod is movably inserted into the through hole.

[0010] According to some embodiments of this utility model, a copper sleeve is provided in the through hole, and the guide rod is movably inserted through the copper sleeve.

[0011] According to some embodiments of this utility model, the two guide rods are respectively disposed on the left and right sides of the push rod.

[0012] According to some embodiments of the present invention, a shock-absorbing block is also included. The shock-absorbing block is disposed on the base plate and located on the front side of the rocker arm. The shock-absorbing block is used to provide a buffering effect when the rocker arm rotates to the unfolded state.

[0013] According to some embodiments of the present invention, the rotating seat includes a flange and a rotating shaft. The flange is used to connect the wing, and the rotating shaft is connected to the lower end of the flange. The middle section of the rotating shaft is provided with two limiting planes and limiting holes that cooperate with the rocker arm. The rocker arm and the rotating shaft are connected by a pin or a connecting rod passing through the limiting holes.

[0014] The beneficial effects of this utility model are as follows: 1. The slider is driven forward by the drive component, which in turn moves the connecting rod forward, thereby driving the rocker arm to rotate forward. The rocker arm drives the rotating seat and the wing to rotate to the unfolded position. The backward movement of the slider is restricted by the elastic locking component, keeping the wing in the unfolded state. The linear motion of the slider is converted into the unfolding motion of the wing through the structure of the slider, connecting rod and rocker arm. The overall structure is simple, makes full use of the space on the base plate, is compact, and is easy to process and assemble. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of the aircraft wing folding mechanism according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the bottom plate of the aircraft wing folding mechanism according to an embodiment of the present invention (hiding the wing and part of the panel). Figure 3 This is a schematic diagram of the structure of the bottom plate of the aircraft wing folding mechanism according to an embodiment of the present invention (with hidden guide rods). Figure 4 This is a schematic diagram of the rocker arm in an embodiment of the present invention; Figure 5 This is a schematic diagram of the rotating seat according to an embodiment of the present invention.

[0016] Icon labels: Base plate 100, shock absorber 110, mounting base 120; Mounting bracket 200; Drive component 300, push rod 310, guide rod 320; Slider 400, copper sleeve 410; Linkage 500, front end 510, rear end 520; Rocker arm 600, first end 610, second end 620, connecting rod 630; Wing 700, rotating seat 710, flange 711, rotating shaft 712, limiting plane 713, limiting hole 714; Locking block 800, guide ramp 801, horizontal plane 802, spring 810. Detailed Implementation

[0017] The following will describe several embodiments of the present invention, including embodiments corresponding to the accompanying drawings. It should be understood that the drawings are used to assist in understanding the technical features and technical solutions of the present invention, and should not be construed as limiting the scope of protection of the present invention.

[0018] The following will provide a clear and complete description of the concept, specific structure, and technical effects of this utility model in conjunction with the embodiments and accompanying drawings, so as to fully understand the purpose, solution, and effects of this utility model. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other.

[0019] It should be noted that, unless otherwise explicitly defined, when a feature is referred to as "fixed," "connected," "installed," or "set" on another feature, it can be "fixed," "connected," "installed," or "set" directly on the other feature, or it can be "fixed," "connected," "installed," or "set" on the other feature indirectly. The terms "fixed," "connected," "installed," and "set" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0020] It should be noted that the descriptions of orientations or positional relationships indicated by terms such as up, down, left, right, top, bottom, front, back, inside, and outside used in this utility model are based on the orientations or positional relationships indicated by the accompanying drawings or embodiments. They are only for the purpose of facilitating the description of this utility model and simplifying the description, and are not intended to 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 utility model.

[0021] It should be noted that the term "and / or" used in this utility model includes any combination of one or more related listed items, "several" means one or more, "multiple" means at least two, "greater than", "less than", "exceeding" are understood to exclude the number itself, and "above", "below", "within" are understood to include the number itself.

[0022] It should be noted that the use of "first" and "second" in this utility model is only for the purpose of distinguishing technical features, and should not be construed as indicating or implying relative importance, or implicitly indicating the number of technical features indicated, or implicitly indicating the order of the technical features indicated.

[0023] It should be noted that, unless otherwise expressly defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in this specification is for the purpose of describing particular embodiments only and not for limiting the scope of the invention.

[0024] like Figures 1 to 5 As shown, this embodiment proposes an aircraft wing folding mechanism, including a base plate 100; a mounting frame 200 located on the rear side of the upper end surface of the base plate 100; a drive member 300 located on the rear side of the mounting frame 200; a slider 400 located on the front side of the mounting frame 200 and connected in the middle to the output end of the drive member 300; two connecting rods 500 arranged in the front-rear direction, with the front ends 510 of the two connecting rods 500 respectively connected to the two sides of the slider 400; a rocker arm 600 arranged in the left-right direction, with its first end 610 hinged to the rear end 520 of the connecting rod 500; a wing 700 movably mounted on the base plate 100 via a rotating seat 710, with the second end 620 of the rocker arm 600 connected to the rotating seat 710, the number of rocker arms 600 and wings 700 matching the number of connecting rods 500; and an elastic locking assembly located on the base plate 100, used to restrict the slider 400 from moving backward so that the wing 700 remains in an unfolded state.

[0025] In this embodiment, the drive component 300 is configured as a cylinder, which operates when the wing 700 unfolds to the desired position. Figure 1 The state shown is the unfolded state. At this time, the positions of the connecting rod 500, rocker arm 600, and slider 400 are as follows: Figure 2 As shown.

[0026] The above-mentioned aircraft wing folding mechanism has at least the following beneficial effects: the drive component 300 drives the slider 400 to move forward, causing the connecting rod 500 to move forward, thereby driving the rocker arm 600 to rotate forward. The rocker arm 600 drives the rotating seat 710 and the wing 700 to rotate to the unfolded position. The elastic locking component restricts the backward movement of the slider 400, keeping the wing 700 in the unfolded state. The linear motion of the slider 400 is converted into the unfolding motion of the wing 700 through the structure of the slider 400, the connecting rod 500 and the rocker arm 600. The overall structure is simple, makes full use of the space on the base plate 100, is compact, and is easy to process and assemble.

[0027] According to some embodiments of the present invention, the elastic locking assembly includes a locking block 800 and a spring 810. The rear side of the locking block 800 is hinged to the base plate 100. The two ends of the spring 810 are respectively connected to the lower end of the front side of the locking block 800 and the base plate 100. When the wing 700 rotates to the deployed state, the spring 810 drives the front side of the locking block 800 to rotate upward and abut against the rear side of the slider 400. The upper end surface of the locking block 800 includes a guide slope 801 and a horizontal surface 802. The guide slope 801 extends from the front to the... With the horizontal surface 802 positioned in front of the guide slope 801, it can be understood that the spring 810 always keeps the front side of the locking block 800 in an upward rotational tendency, that is, the spring 810 always provides an upward elastic force to the front side of the locking block 800. When the wing 700 is unfolded from its folded state, the drive component 300 drives the slider 400 to slide forward. The slider 400 moves forward along with the connecting rod 500. The rear end of the connecting rod 500 drives the first end of the rocker arm 600 to rotate forward. The wing 700 rotates along the rocker arm. Driven by 600 and the rotating seat 710, the wing rotates backward to the deployed state. During this rotation, the slider 400 first contacts the guide ramp 801 of the locking block 800, simultaneously pressing down on the locking block 800. The front side of the locking block 800 compresses the spring 810 downward, accumulating elastic potential energy. When the slider 400 continues to move forward to the horizontal surface 802, the compression of the spring 810 reaches its maximum. When the wing 700 rotates to the deployed state, the slider 400 moves forward to disengage from the horizontal surface 802, and the spring 810 releases its elastic potential energy. Pushing the front of the locking block 800 upwards causes the front of the locking block 800 to rotate upwards and abut against the rear of the slider 400, thereby restricting the slider 400 from moving backwards and locking the wing 700 in the deployed state. When the wing 700 needs to be folded and stored, the slider 400 needs to be moved backwards by the drive component 300 while the front of the locking block 800 is pressed down, causing its horizontal surface 802 to rotate below the slider 400. The slider 400 can then move backwards, thereby folding the wing 700.

[0028] According to some embodiments of this utility model, the output end of the drive member 300 is connected to a push rod 310, the front end 510 of the push rod 310 is connected to a slider 400, and two locking blocks 800 are provided. The two locking blocks 800 are distributed on both sides of the push rod 310. By providing locking blocks 800 on both sides of the push rod 310, the locking force on the slider 400 is more uniform, and the slider 400 is prevented from tilting, which would cause the rotation angle of the wings 700 on both sides to deviate.

[0029] According to some embodiments of this utility model, it also includes two guide rods 320. The rear end 520 of the guide rod 320 is connected to the mounting bracket 200, and the other end is connected to the base plate 100 through the mounting seat 120. The slider 400 is provided with a through hole, and the guide rod 320 is movably inserted into the through hole. A copper sleeve 410 is provided in the through hole, and the guide rod 320 is movably inserted into the copper sleeve 410. The guide rod 320 is used to orient and guide the slider 400 for its forward and backward movement, so as to avoid the slider 400 from becoming skewed during its forward and backward movement, which would cause interference or damage to the output shaft of the drive component 300. At the same time, the copper sleeve 410 in the through hole can reduce the coefficient of friction between the slider 400 and the guide rod 320, so that the forward and backward movement of the slider 400 is smoother.

[0030] According to some embodiments of this utility model, two guide rods 320 are respectively disposed on the left and right sides of the push rod 310.

[0031] According to some embodiments of the present invention, a shock-absorbing block 110 is also included. The shock-absorbing block 110 is disposed on the base plate 100 and located on the front side of the rocker arm 600. The shock-absorbing block 110 is used to provide a buffering effect when the rocker arm 600 rotates to the unfolded state. In this embodiment, the shock-absorbing block 110 can be made of flexible materials such as silicone, rubber, or sponge. Since the wing 700 unfolds at a relatively fast speed, the shock-absorbing block 110 can reduce the impact force generated by the wing 700 on the rocker arm 600 during the unfolding process, thereby improving the service life of the rocker arm 600.

[0032] According to some embodiments of the present invention, the rotating seat 710 includes a flange 711 and a rotating shaft 712. The flange 711 is used to connect the wing 700, and the rotating shaft 712 is connected to the lower end of the flange 711. The middle section of the rotating shaft 712 is provided with two limiting planes 713 and limiting holes 714 that cooperate with the rocker arm 600. The rocker arm 600 and the rotating shaft 712 are connected by a pin or a connecting rod 630 passing through the limiting holes 714. The setting of the two limiting planes 713 and the limiting holes 714 makes the rocker arm 600 and the rotating shaft 712 fixedly connected, preventing the rotating shaft 712 and the rocker arm 600 from rotating and misaligning during the deployment of the wing 700.

[0033] It should be noted that in this specification, terms such as "one embodiment", "some embodiments", "basic embodiment", and "extended embodiment" may be used to describe several embodiments of the present invention, and the specific features, structures, materials or characteristics of the several embodiments may be combined in accordance with the principles and spirit of the present invention.

[0034] Although some embodiments of the present invention have been shown and described in this specification, the present invention should not be limited to the above embodiments. As long as they achieve the technical effects of the present invention by the same or equivalent means, any changes, modifications, equivalent substitutions and equivalent variations of these embodiments within the spirit and principles of this disclosure, without departing from the principles and purpose of the present invention, should be included within the scope of protection of this disclosure and should be considered to fall within the protection scope of the present invention.

Claims

1. A wing folding mechanism for an aircraft, characterized in that, include: Base plate; The mounting bracket is located on the rear side of the upper end face of the base plate; A drive component is located on the rear side of the mounting bracket; A slider is located on the front side of the mounting bracket and connected in the middle to the output end of the drive component; Two connecting rods are arranged in the front-back direction, and the front ends of the two connecting rods are respectively connected to the two sides of the slider; A rocker arm is provided in the left-right direction, with its first end hinged to the rear end of the connecting rod; The wing is movably mounted on the base plate via a rotating seat, and the second end of the rocker arm is connected to the rotating seat. The number of the rocker arm and the wing matches the number of the connecting rods. An elastic locking component, located on the base plate, is used to restrict the slider from moving backward so that the wing remains in the deployed state.

2. The aircraft wing folding mechanism according to claim 1, characterized in that, The elastic locking assembly includes a locking block and a spring. The rear side of the locking block is hinged to the base plate. The two ends of the spring are respectively connected to the lower end of the front side of the locking block and the base plate. When the wing rotates to the deployed state, the spring drives the front side of the locking block to rotate upward and abut against the rear side of the slider.

3. The aircraft wing folding mechanism according to claim 2, characterized in that, The upper surface of the locking block includes a guide slope and a horizontal surface. The guide slope slopes upward from front to back, and the horizontal surface is located on the front side of the guide slope.

4. The aircraft wing folding mechanism according to claim 2, characterized in that, The output end of the drive unit is connected to a push rod, and the front end of the push rod is connected to the slider.

5. The aircraft wing folding mechanism according to claim 4, characterized in that, There are two locking blocks, which are distributed on both sides of the push rod.

6. The aircraft wing folding mechanism according to claim 4, characterized in that, It also includes two guide rods, the rear end of which is connected to the mounting bracket, and the other end is connected to the base plate through a mounting seat. The slider is provided with a through hole, and the guide rod is movably inserted into the through hole.

7. The aircraft wing folding mechanism according to claim 6, characterized in that, A copper sleeve is provided in the through hole, and the guide rod is movably inserted through the copper sleeve.

8. The aircraft wing folding mechanism according to claim 6, characterized in that, The two guide rods are respectively located on the left and right sides of the push rod.

9. The aircraft wing folding mechanism according to claim 1, characterized in that, It also includes a shock-absorbing block, which is disposed on the base plate and located on the front side of the rocker arm. The shock-absorbing block is used to provide a buffering effect when the rocker arm rotates to the extended state.

10. The aircraft wing folding mechanism according to claim 1, characterized in that, The rotating base includes a flange and a rotating shaft. The flange is used to connect the wing, and the rotating shaft is connected to the lower end of the flange. The middle section of the rotating shaft is provided with two limiting planes and limiting holes that cooperate with the rocker arm. The rocker arm and the rotating shaft are connected by a pin or a connecting rod passing through the limiting holes.

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