Variable wing sweepback angle mechanism and unmanned aerial vehicle

Abstract

The utility model provides a variable wing sweepback angle mechanism and an unmanned aerial vehicle, and relates to the technical field of fuselage and wing connecting structures of unmanned aerial vehicles. The variable wing sweepback angle mechanism comprises a mounting seat, a driving assembly and a mounting assembly; the mounting seat is configured to be fixed on a fuselage of the unmanned aerial vehicle; the driving assembly comprises a worm, a driving piece and two worm wheels. The worm is rotationally arranged on the mounting seat; the driving piece is connected with the worm so as to drive the worm to rotate; the two worm gears are symmetrically arranged on the two sides of the worm, the worm gears are meshed with the worm, and the worm gears are configured to be fixed to wings of the unmanned aerial vehicle; the installation assembly is configured to install the worm gear on the installation base and comprises a rotating shaft, and the rotating shaft is rotationally connected with the installation base and / or the worm gear so that the worm gear can rotate around the rotating shaft and the installation base. The wings on the two sides are symmetrically adjusted through the driving piece, and the flight safety and stability are effectively guaranteed. The mounting assembly and the driving assembly are independently arranged, and the system stability is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of fuselage and wing connection structure of unmanned aerial vehicles (UAVs), specifically to a variable wing sweep angle mechanism and a UAV. Background Technology

[0002] With the widespread application of drones in agriculture, surveying, logistics, security, power, environmental protection, film and television, scientific research, education and other fields, improving operational efficiency is the main development direction. Therefore, variable sweep angle or folding wings are required when used in certain fields. For example, at lower speeds during take-off and landing, a larger wing area is required; at higher speeds during cruising, a smaller wing area is required to reduce drag. Therefore, variable sweep angle wings are needed to meet the needs of different scenarios. Utility Model Content

[0003] In view of the problems existing in the prior art, the present invention provides a variable wing sweep angle mechanism and a drone to improve the situation where the wing sweep angle cannot be changed and to meet the needs of changing the wing sweep angle in different situations.

[0004] To achieve the above and other related objectives, the first aspect of this utility model provides a variable wing sweep angle mechanism for an unmanned aerial vehicle (UAV). The variable wing sweep angle mechanism includes a mounting base, a drive assembly, and a mounting component. The mounting base is configured to be fixed to the fuselage of the UAV. The drive assembly includes a worm, a drive member, and two worm wheels. The worm is rotatably mounted on the mounting base. The drive member is connected to the worm to drive the worm to rotate. The two worm wheels are symmetrically arranged on both sides of the worm and mesh with it. The worm wheels are configured to be fixed to the wing of the UAV. The mounting component is configured to mount the worm wheels to the mounting base. The mounting component includes a rotating shaft, which is rotatably connected to the mounting base and / or the worm wheels, such that the worm wheels rotate about the rotating shaft relative to the mounting base.

[0005] In an exemplary embodiment of this application, the mounting base is provided with mounting holes, the mounting assembly includes at least two first bearings, the first bearings are disposed in the mounting holes, and the rotating shaft is fixed to the first bearings.

[0006] In an exemplary embodiment of this application, the end of the mounting hole includes a countersunk hole, and the first bearing is mounted in the countersunk hole.

[0007] In an exemplary embodiment of this application, the mounting assembly includes a planar bearing, which is fixed to the rotating shaft and the mounting base, respectively.

[0008] In an exemplary embodiment of this application, the planar bearing is disposed at the end of the mounting hole near the worm gear, and / or the planar bearing is disposed between the two first bearings.

[0009] In an exemplary embodiment of this application, the drive assembly includes: a fixed base, fixedly disposed on the mounting base; and a second bearing, fixedly disposed on the fixed base, wherein the second bearing is fixed to the worm gear.

[0010] In an exemplary embodiment of this application, the top of the rotating shaft is provided with an overlapping portion protruding outward from the outer periphery of the rotating shaft, the overlapping portion abutting against the worm gear and being fixed to the worm gear.

[0011] In an exemplary embodiment of this application, the mounting base has upward protrusions on both sides, and the worm gear is disposed on the protrusions.

[0012] In an exemplary embodiment of this application, the driving component includes a motor, which is directly connected to the worm gear or connected via a coupling.

[0013] A second aspect of this utility model provides an unmanned aerial vehicle (UAV) including a fuselage, a wing, and a variable wing sweep angle mechanism as described above, wherein the variable wing sweep angle mechanism connects the fuselage and the wing.

[0014] In combination with existing technologies, the beneficial effects of this application are as follows:

[0015] Existing drone wings typically have a fixed sweep angle, which fails to meet the usage requirements of different scenarios. The variable wing sweep angle mechanism of this application includes a mounting base, a drive assembly, and a mounting component. The mounting base is fixed to the fuselage, the mounting component is used for mounting the wing to the mounting base, and the drive assembly is used to drive the wing to rotate. This mechanism allows for relative rotation between the wing and the fuselage, thereby adjusting the wing sweep angle to meet the usage requirements of different scenarios.

[0016] The drive assembly of this application includes a worm gear, worm wheels, and a drive component. The drive component drives the worm gear to rotate, which in turn drives the worm wheels on both sides of the worm gear, thereby achieving synchronous rotation of both wings. A single drive component enables symmetrical adjustment of both wings, resulting in a simple structure and ensuring the stability of wing sweep angle adjustment, thus guaranteeing flight stability.

[0017] The worm gear and worm shaft utilize a self-locking mechanism to prevent accidental wing rotation during flight, effectively ensuring flight safety and stability. The worm gear and wing can self-lock at any sweep angle at any time, offering high practicality. Furthermore, they remain folded even when the drive is powered off in a stopped state. The worm gear and worm shaft have a high reduction ratio and high transmission efficiency, thus reducing limitations on drive component selection and lowering drive component costs.

[0018] The mounting component and the drive component of this application are set independently. The worm gear rotates around the rotation axis and is relative to the mounting base. In other words, the wing rotates around the rotation axis and is relative to the fuselage. The lift of the wing is transmitted to the fuselage through the mounting component, which reduces the impact of the wing lift on the drive component, protects the drive component, reduces the probability of damage to the drive component, and improves the stability of the system. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other embodiments can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of an exemplary UAV wing sweep angle adjustment according to the present invention;

[0021] Figure 2 This is a schematic diagram of an exemplary variable wing sweep angle mechanism of the present invention;

[0022] Figure 3 This is a cross-sectional schematic diagram of an exemplary variable wing sweep angle mechanism of this utility model;

[0023] Figure 4 This is a cross-sectional view of an exemplary variable wing sweep angle mechanism of this utility model from another angle.

[0024] Component designation explanation:

[0025] 100, Mounting base; 110, Mounting hole; 120, Protrusion; 200, Drive assembly; 210, Worm gear; 220, Drive component; 230, Worm wheel; 240, Fixed base; 250, Second bearing; 300, Mounting assembly; 310, Rotating shaft; 311, Overlapping part; 320, First bearing; 330, Surface bearing; 400, Fuselage; 500, Wing. Detailed Implementation

[0026] The following specific examples illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. This utility model can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this utility model. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. It should also be understood that the terminology used in the embodiments of this utility model is for describing specific implementation schemes and not for limiting the scope of protection of this utility model. Test methods in the following embodiments that do not specify specific conditions are generally performed under conventional conditions or according to the conditions recommended by the respective manufacturers.

[0027] When numerical ranges are given in the embodiments, it should be understood that, unless otherwise specified in this invention, both endpoints of each numerical range and any value between the two endpoints may be selected. Unless otherwise defined, all technical and scientific terms used in this invention, as well as the prior art known to those skilled in the art and the description of this invention, may be implemented using any prior art methods, equipment, and materials similar to or equivalent to those in the embodiments of this invention.

[0028] It should be noted that the terms such as "upper," "lower," "left," "right," "middle," and "one" used in this specification are merely for clarity of description and are not intended to limit the scope of implementation of this utility model. Any changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of implementation of this utility model.

[0029] With the development of technology, drones are widely used. In some fields, variable sweep angles or folding wings are required. For example, a larger wing area is needed during takeoff and landing, while a smaller wing area is needed during cruise to reduce drag. When parked in a hangar, drones are arranged in a "cross" shape and occupy a large space. Therefore, the wings need to be folded to the side of the fuselage. Compared with an unfolded wing, a folded wing can accommodate two or more drones in the same area.

[0030] In view of this, this application provides a variable wing 500 sweep angle mechanism and a drone, which drives the wing 500 to rotate around the mounting component 300 through the drive component 200, thereby realizing the relative rotation between the wing 500 and the fuselage 400, and thus adjusting the sweep angle of the wing 500 to meet the usage requirements in different scenarios.

[0031] Please see Figures 1 to 4The first aspect of this application provides a variable wing sweep angle mechanism for an unmanned aerial vehicle (UAV) to achieve relative rotation between the wing 500 and the fuselage 400. The variable wing 500 sweep angle mechanism includes a mounting base 100, a drive assembly 200, and a mounting assembly 300.

[0032] The mounting base 100 is fixed to the fuselage 400 of the UAV. The mounting base 100 can be fixed to the fuselage 400 in various ways, such as bolt connection, adhesive connection, welding connection, or integral molding, to achieve relative fixation between the mounting base 100 and the fuselage 400. The mounting base 100 achieves relative fixation between the variable wing 500 sweep angle mechanism and the fuselage 400, and provides installation space for other components of the variable wing 500 sweep angle mechanism.

[0033] Please see Figure 2 The drive assembly 200 is used to drive the wing 500 to rotate relative to the fuselage 400, thereby changing the sweep angle of the wing 500 or retracting the wing 500 to the sides of the fuselage 400. The drive assembly 200 includes a worm 210, a drive member 220, and two worm wheels 230. The worm 210 is rotatably mounted on the mounting base 100, and the drive member 220 is connected to the worm 210 to drive the worm 210 to rotate. The two worm wheels 230 are symmetrically arranged on both sides of the worm 210, and the worm wheels 230 mesh with the worm 210. The worm wheels 230 are fixed to the wing 500 of the UAV. The worm wheels 230 are symmetrically arranged along the axis of the worm 210, and the two worm wheels 230 rotate synchronously with the worm 210.

[0034] Preferably, when the variable wing sweep angle mechanism is installed on the UAV, the worm gear 230 is symmetrically arranged along the axis of the fuselage 400, and the worm gear 230 is symmetrically arranged on both sides of the fuselage 400, thereby synchronously driving the wings 500 on both sides to rotate synchronously.

[0035] As an option, there may be multiple worm gears 230, the number of which is selected according to the number of wings 500.

[0036] Please see Figure 2The mounting assembly 300 is used to mount the worm gear 230 to the mounting base 100. The mounting assembly 300 includes a rotating shaft 310, which is rotatably connected to the mounting base 100 and / or the worm gear 230, so that the worm gear 230 rotates about the rotating shaft 310 relative to the mounting base 100. The rotating shaft 310 can be rotatably connected to the mounting base 100 and fixedly connected to the worm gear 230; the rotating shaft 310 can also be fixedly connected to the mounting base 100 and rotatably connected to the worm gear 230; or the rotating shaft 310 can also be rotatably connected to the mounting base 100 and rotatably connected to the worm gear 230, thereby achieving relative rotation between the worm gear 230 and the mounting base 100.

[0037] In this application, the worm gear 210 is driven to rotate by the drive component 220. The worm gear 210 meshes with the worm wheels 230 on both sides, and the worm gear 210 drives the worm wheels 230 to rotate, thereby achieving synchronous rotation of the two wings 500. The symmetrical adjustment of the two wings 500 is achieved through a single drive component 220, which is simple in structure and ensures the stability of the wing sweep angle adjustment, thereby ensuring flight stability.

[0038] The worm gear 230 and worm 210 utilize a self-locking mechanism to prevent the wing 500 from rotating during flight, effectively ensuring flight safety and stability. The worm gear 230 and wing 500 can self-lock at any sweep angle at any time, offering high practicality. Furthermore, they remain folded even when the drive is powered off in a stopped state. The worm gear 230 and worm 210 have a large reduction ratio and high transmission efficiency, thus reducing the limitations on the selection of the drive component 220 and lowering its cost.

[0039] The mounting component 300 and the drive component 200 are independently configured. The worm gear 230 rotates around the rotation axis 310 relative to the mounting base 100. In other words, the wing 500 rotates relative to the fuselage 400 around the rotation axis 310. The lift, torque, and bending moment of the wing 500 are directly transmitted to the fuselage 400 through the mechanism. Since the bending moment is balanced left and right, it cannot be transmitted to the drive component 220, thus protecting the drive component 220. This results in higher system reliability and significantly reduces the selection limitations of the drive component 220. The lift of the wing 500 is transmitted to the fuselage 400 through the mounting component 300, reducing the impact of the wing 500's lift on the drive component 220, protecting the drive component 220, reducing the probability of damage to the drive component 220, and improving system stability.

[0040] Please see Figure 4In one embodiment, the mounting base 100 is provided with a mounting hole 110, and the mounting assembly 300 includes at least two first bearings 320. The first bearings 320 are disposed in the mounting hole 110, and the two first bearings 320 are arranged vertically along the axial direction of the mounting hole 110. The rotating shaft 310 is fixed to the first bearings 320. When the wing 500 is subjected to lift, the torque of the lift acting on the connection of the wing 500 causes the wing 500 to tend to rotate upward. By providing two first bearings 320, the upward rotation of the wing 500 is prevented. Because the worm gear 230 is relatively fixed to the wing 500, the force exerted by the worm gear 230 on the worm 210 is reduced. On the one hand, this maintains the stability of the sweep angle of the wing 500 and prevents changes in the sweep angle of the wing 500. On the other hand, it can protect the drive component 220, reduce the stress on the drive component 220, reduce the probability of damage to the drive component 220, and improve the service life of the drive component 220.

[0041] The first bearing 320 can be fixed to the mounting hole 110 by an interference fit, or by a bearing retainer, nut, etc. The first bearing 320 and the rotating shaft 310 can be fixed to each other by an interference fit, thereby making the first bearing 320 and the rotating shaft 310 relatively fixed.

[0042] Please see Figure 4 In one embodiment, the end of the mounting hole 110 includes a countersunk hole, and the first bearing 320 is installed in the countersunk hole. The countersunk holes are provided at both ends of the mounting hole 110, thereby facilitating the installation of the first bearing 320 at both ends of the mounting hole 110. By providing countersunk holes, it is convenient to position and fix the first bearing 320, while preventing the first bearing 320 from protruding from the mounting hole 110.

[0043] Please see Figure 4 In one embodiment, the mounting assembly 300 includes a planar bearing 330, which is fixed to both the rotating shaft 310 and the mounting base 100. The planar bearing 330 can share some of the axial force on the rotating shaft 310, thereby further reducing the force exerted by the worm gear 230 on the worm 210 and providing further protection for the drive component 220.

[0044] In one embodiment, the planar bearing 330 is disposed at the end of the mounting hole 110 near the worm gear 230 to share the axial force on the rotating shaft 310.

[0045] In another embodiment, a planar bearing 330 is disposed between the two first bearings 320 to share the axial force on the rotating shaft 310.

[0046] Of course, as some optional methods, multiple planar bearings 330 can also be provided, such as two or three. The planar bearings 330 can be provided at the end of the mounting hole 110 or between two first bearings 320.

[0047] Please see Figure 4 In one embodiment, the top of the rotating shaft 310 is provided with an overlapping portion 311 protruding outward from the outer periphery of the rotating shaft 310. The overlapping portion 311 abuts against the worm gear 230 and is fixed to the worm gear 230. The overlapping portion 311 increases the contact area between the rotating shaft 310 and the worm gear 230, thereby facilitating the relative fixation of the rotating shaft 310 and the worm gear 230.

[0048] The overlapping part 311 can be fixed relative to the worm gear 230 in various ways, such as fixing the overlapping part 311 relative to the worm gear 230 by bolts or other connecting parts; welding the overlapping part 311 to the worm gear 230; or gluing the overlapping part 311 to the worm gear 230.

[0049] Please see Figure 4 In one embodiment, the mounting base 100 has upward protrusions 120 on both sides, and the worm gear 230 is disposed at the protrusions 120. By providing the protrusions 120, on the one hand, the height of the mounting hole 110 is increased, thereby increasing the distance between the two first bearings 320, thereby reducing the radial swing of the rotating shaft 310 and improving the stability of the wing 500; on the other hand, the height of the worm gear 230 can be increased, thereby providing space for the installation of the worm 210 and facilitating the installation of the drive assembly 200.

[0050] Please see Figure 4 In one embodiment, the drive assembly 200 includes a fixed base 240 and a second bearing 250, which are fixedly disposed on the mounting base 100. The fixed base 240 is used to mount the worm gear 210. The second bearing 250 is fixedly disposed on the fixed base 240 and is fixed to the worm gear 210. The worm gear 210 is mounted on the mounting base 100 through the second bearing 250, thereby enabling the drive component 220 to drive the worm gear 210 to rotate.

[0051] The second bearing 250 can be selected as needed, such as a deep groove ball bearing, an angular contact ball bearing, a cylindrical roller bearing, etc., or it can be a combination of multiple bearings to achieve the function of driving the worm gear 210 to rotate.

[0052] In one embodiment, the drive component 220 includes a motor, which is directly connected to the worm gear 210 or connected via a coupling. Driving the worm gear 210 to rotate via the motor provides convenient and controllable control. The motor-driven rotation of the worm gear 210, in turn, drives the worm wheel 230 to rotate, thereby enabling the wing 500 to rotate relative to the fuselage 400, achieving adjustments to the sweep angle or retraction of the wing 500, etc.

[0053] A second aspect of this utility model provides an unmanned aerial vehicle (UAV) including a fuselage 400, a wing 500, and a variable wing sweep angle mechanism as described above, wherein the variable wing sweep angle mechanism connects the fuselage 400 and the wing 500. The UAV also includes power components, etc. Please refer to existing UAVs; details are not provided here.

[0054] The UAV of this application drives the worm gear 210 to rotate via the drive component 220. The worm gear 210 meshes with the worm wheels 230 on both sides, and the worm gear 210 drives the worm wheels 230 to rotate, thereby achieving synchronous rotation of the wings 500 on both sides, and thus changing the sweep angle of the wings 500. The worm wheels 230 and worm gear 210 use a self-locking mechanism to prevent the wings 500 from rotating accidentally during flight, effectively ensuring flight safety and stability. The mounting component 300 and the drive component 200 are set independently. The worm wheel 230 rotates around the rotation axis 310 and is relative to the mounting base 100. In other words, the wings 500 rotate relative to the fuselage 400 around the rotation axis 310. The lift, torque, bending moment and other forces of the wings 500 are directly transmitted to the fuselage 400 through the mechanism, and the bending moment is balanced on both sides, so it cannot be transmitted to the drive component 220, thus protecting the drive component 220. This makes the whole system more reliable and greatly reduces the selection restrictions of the drive component 220. The lift of the low wing 500 is transferred to the fuselage 400 through the mounting component 300, which reduces the impact of the lift of the wing 500 on the drive component 220, protects the drive component 220, reduces the probability of damage to the drive component 220, and improves system stability.

[0055] The variable wing sweep angle mechanism and UAV of this application enable hovering of the wing 500 at any sweep angle, facilitating the adjustment of the wing 500 sweep angle. The mounting component 300 and the drive component 200 are independently configured. The lift, torque, and bending moment of the wing 500 are directly transmitted to the fuselage 400 through the mechanism, and the bending moment is balanced left and right, thus preventing it from being transmitted to the drive component 220, thereby protecting the drive component 220. This results in higher reliability for the entire system and significantly reduces the selection limitations of the drive component 220. Therefore, this utility model effectively overcomes some practical problems in the prior art, thus possessing high utilization value and practical significance.

[0056] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A variable wing sweep angle mechanism for an unmanned aerial vehicle (UAV), characterized in that, Includes mounting base, driver components, and mounting components; The mounting base is configured to be fixed to the fuselage of the drone; The driving component includes: The worm gear is rotatably mounted on the mounting base; A driving component is connected to the worm gear to drive the worm gear to rotate; Two worm gears are symmetrically arranged on both sides of the worm, and the worm gears mesh with the worm. The worm gears are configured to be fixed to the wings of the UAV. The mounting assembly is configured to mount the worm gear to the mounting base, the mounting assembly comprising: A rotating shaft is rotatably connected to the mounting base and / or the worm gear, such that the worm gear rotates about the rotating shaft and the mounting base.

2. The variable wing sweep angle mechanism according to claim 1, characterized in that, The mounting base is provided with mounting holes, and the mounting assembly includes: At least two first bearings are provided, the first bearings are disposed in the mounting holes, and the rotating shaft is fixed to the first bearings.

3. The variable wing sweep angle mechanism according to claim 2, characterized in that, The end of the mounting hole includes a countersunk hole, and the first bearing is installed in the countersunk hole.

4. The variable wing sweep angle mechanism according to claim 2, characterized in that, The installation components include: A planar bearing is fixed to both the rotating shaft and the mounting base.

5. The variable wing sweep angle mechanism according to claim 4, characterized in that, The planar bearing is disposed at the end of the mounting hole near the worm gear, and / or the planar bearing is disposed between the two first bearings.

6. The variable wing sweep angle mechanism according to claim 1, characterized in that, The driving component includes: A fixed base is fixedly mounted on the mounting base; The second bearing is fixedly mounted on the fixed seat, and the second bearing is fixed to the worm gear.

7. The variable wing sweep angle mechanism according to claim 1, characterized in that, The top of the rotating shaft is provided with an overlapping portion protruding outward from the outer periphery of the rotating shaft, the overlapping portion abutting against the worm gear and being fixed to the worm gear.

8. The variable wing sweep angle mechanism according to claim 1, characterized in that, The mounting base has upward protrusions on both sides, and the worm gear is located on the protrusions.

9. The variable wing sweep angle mechanism according to claim 1, characterized in that, The driving component includes a motor, which is directly connected to the worm gear or connected via a coupling.

10. A drone, characterized in that, include: body; Wings; The variable wing sweep angle mechanism according to any one of claims 1 to 9, wherein the variable wing sweep angle mechanism connects the fuselage and the wing.

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