Flap structure of unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle flap structure which comprises a wing, one side of the wing is rotationally connected with at least one flap, and a mounting cavity is formed in the wing; a driving mechanism corresponding to the flap is arranged in the mounting cavity, one end of the driving mechanism extends out of the mounting cavity to be connected with the flap and is used for driving the flap to rotate around the rotating axis, so that an included angle is formed between the flap and the wing; the flap is driven by the driving mechanism to rotate around the rotating axis, so that the flap is turned over and forms an included angle with the wing, the aerodynamic configuration of the unmanned aerial vehicle is further changed, and the flight of the unmanned aerial vehicle is better controlled; and the whole structure does not protrude out of the surface of the wing in the height direction of the wing, so that the influence on the aerodynamic configuration of the unmanned aerial vehicle is effectively reduced, and the unmanned aerial vehicle has better flight performance.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV flap structure. Background Technology

[0002] The development of flaps can be traced back to the early stages of aircraft design. They are a type of movable wing-shaped device, typically mounted on the trailing edge of the wing, parallel to the wing surface. By controlling the rotation of the flaps, the aircraft's lift can be increased or the takeoff and landing distance can be reduced. With the development of unmanned aerial vehicle (UAV) technology, flaps have gradually been applied to UAVs to improve their flight performance and operational flexibility. To obtain greater lift, achieve the predetermined flight distance, and better control the UAV's flight, most current UAV flap structures use servos to drive a rotating rod, which in turn rotates the flaps. Because the servos and linkage mechanisms of the linkage-type flap structure are located on the wing, they affect the wing's aerodynamic shape, thus generating drag during UAV flight and reducing its flight performance. Utility Model Content

[0003] The purpose of this application is to address the above problems by providing a drone flap structure, including:

[0004] The wing has an internal mounting cavity;

[0005] Flaps, at least one of the flaps being rotatably connected to one side of the wing;

[0006] A drive mechanism, at least one of which is disposed in the mounting cavity and is correspondingly disposed to the flap. One end of the drive mechanism extends out of the mounting cavity and connects to the flap, for driving the flap to rotate around the rotation axis so that an angle is formed between the flap and the wing.

[0007] According to the technical solutions provided in certain embodiments of this application, the driving mechanism includes a driving member, the driving member is fixed in the mounting cavity, the driving member is fixedly connected to a first transmission shaft, the first transmission shaft extends along a first direction, a first bevel gear is sleeved on its free end, the first bevel gear meshes with a second bevel gear, a second transmission shaft is fixedly mounted on the second bevel gear, the second transmission shaft extends along a second direction and is rotatably connected to the wing, one end of the second transmission shaft extends out of the mounting cavity and is connected to the flap, the second direction is perpendicular to the first direction.

[0008] According to the technical solutions provided in certain embodiments of this application, the drive mechanism further includes a connecting crank arm, the first end of which is fixed to the second drive shaft, and the second end of which is rotatably and slidably connected to the end of the flap away from the wing.

[0009] According to the technical solutions provided in certain embodiments of this application, the vertical distance between the axis of the first end and the axis of the second end is a first distance, the vertical distance between the axis of the first end and the axis of rotation is a second distance, the vertical distance between the axis of the second end and the axis of rotation is a third distance, and the sum of the first distance and the second distance is greater than or equal to the third distance.

[0010] According to the technical solutions provided in certain embodiments of this application, a plurality of first mounting seats are fixed on one side of the wing along the second direction, and a second mounting seat is rotatably connected to the first mounting seat. The plurality of second mounting seats rotate around the rotation axis and are fixed along the second direction on the side of the flap close to the wing.

[0011] According to the technical solutions provided in certain embodiments of this application, a support lug is fixed on the first mounting base, and a rotating groove is provided on the second mounting base. The support lug is inserted into the rotating groove and rotatably connected to the second mounting base.

[0012] According to the technical solutions provided in certain embodiments of this application, the wing includes a wing skeleton, the wing skeleton is covered with a wing skin, and the mounting cavity is formed inside the wing skin; the wing skeleton is provided with a mounting frame, the driving component is fixed on the mounting frame, and the mounting frame is also provided with a connecting frame; the first drive shaft passes through the mounting frame and the connecting frame in sequence and is rotatably connected to both; the second drive shaft is rotatably connected to the connecting frame.

[0013] According to the technical solutions provided in certain embodiments of this application, the driving component is fixedly connected to the first transmission shaft via a coupling.

[0014] Compared with the prior art, the beneficial effects of this application are as follows: This application provides a UAV flap structure, including a wing, at least one flap is rotatably connected to one side of the wing, and the wing has an internal mounting cavity; the mounting cavity is provided with a drive mechanism corresponding to the flap, one end of the drive mechanism extends out of the mounting cavity and connects to the flap, for driving the flap to rotate around the rotation axis so that an angle is formed between the flap and the wing; by driving the flap to rotate around the rotation axis through the drive mechanism, the flap flips and forms an angle with the wing, thereby changing the aerodynamic shape of the UAV and better controlling the flight of the UAV. At the same time, since the main structure of the drive mechanism is located in the mounting cavity inside the wing, and the overall structure does not protrude from the wing surface in the height direction of the wing, the impact on the aerodynamic shape of the UAV is effectively reduced, giving it better flight performance.

[0015] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of a UAV flap structure provided in an embodiment of this application;

[0018] Figure 2 A schematic diagram of the flap and drive mechanism of a UAV flap structure provided in this application embodiment;

[0019] Figure 3 Another schematic diagram of the flap and drive mechanism of a UAV flap structure provided in this application embodiment;

[0020] Figure 4 for Figure 3 Enlarged view of section A.

[0021] The text labels in the image represent:

[0022] 1. Wing; 2. Flap; 3. Drive unit; 4. First drive shaft; 5. First bevel gear; 6. Second drive shaft; 7. Second bevel gear; 8. Connecting crank arm; 9. First mounting base; 10. Second mounting base; 11. Mounting bracket; 12. Connecting bracket; 13. Lug; 14. Rotating groove; 15. Coupling; 16. Slide groove. Detailed Implementation

[0023] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this invention.

[0024] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0025] As mentioned in the background section, in order to solve the problems existing in the prior art, this embodiment provides a UAV flap structure, including:

[0026] Wing 1, with an internal mounting cavity;

[0027] Flaps 2, at least one flap 2 is rotatably connected to one side of wing 1;

[0028] A drive mechanism, at least one drive mechanism is provided in the mounting cavity and is correspondingly provided with the flap 2. One end of the drive mechanism extends out of the mounting cavity and connects to the flap 2, and is used to drive the flap 2 to rotate around the rotation axis so that the flap 2 and the wing 1 form an angle.

[0029] like Figure 1 and Figure 2 As shown, the first direction is Figure 2 The vertical direction in the middle, the second direction is Figure 2In the horizontal direction, wing 1 is fixed to the UAV body, and flap 2 is located at the trailing edge of wing 1 and can be rotated relative to wing 1. Wing 1 has an internal mounting cavity, and a drive mechanism is located in the mounting cavity. Part of the drive mechanism extends out of the mounting cavity and is connected to the flap 2, which can drive the flap 2 to rotate around the rotation axis. The rotation axis extends along the second direction. The projection of the drive mechanism in the direction from the leading edge of wing 1 to the trailing edge of wing 1 can be completely covered by the projection of wing 1, thereby reducing the impact of the drive mechanism on the aerodynamic shape of the UAV. In this embodiment, three flaps 2 are rotatably connected to wing 1, and the number of drive mechanisms corresponds to the number of flaps 2, also three. The drive mechanism corresponding to the flap 2 is located on the side of the flap 2 closer to the body. In other embodiments of this application, the number of flaps 2 can be adjusted according to actual needs, and no specific limitation is made here.

[0030] The drive mechanism drives the flap 2 to rotate around the axis of rotation, so that the flap 2 and the wing 1 form an angle, thereby changing the aerodynamic shape of the UAV and improving the flight control of the UAV. At the same time, since the main structure of the drive mechanism is located in the mounting cavity inside the wing 1, and the overall structure does not protrude from the surface of the wing 1 in the height direction, the impact on the aerodynamic shape of the UAV is effectively reduced, giving it better flight performance.

[0031] In a preferred embodiment, the drive mechanism includes a drive member 3, which is fixed in the mounting cavity. The drive member 3 is fixedly connected to a first drive shaft 4, which extends along a first direction. A first bevel gear 5 is sleeved on its free end. The first bevel gear 5 meshes with a second bevel gear 7. A second drive shaft 6 is fixedly mounted on the second bevel gear 7. The second drive shaft 6 extends along a second direction and is rotatably connected to the wing 1. One end of the second drive shaft 6 extends out of the mounting cavity and is connected to the flap 2. The second direction is perpendicular to the first direction.

[0032] In a preferred embodiment, the drive mechanism further includes a connecting crank arm 8, the first end of which is fixed to the second drive shaft 6, and the second end of which is rotatably and slidably connected to the end of the flap 2 away from the wing 1.

[0033] like Figure 2-4As shown, the drive unit 3 adopts a servo motor as in the prior art. The servo motor is installed in the mounting cavity, and its drive end is fixedly connected to a first drive shaft 4 extending in a first direction. A second drive shaft 6 extending in a second direction is rotatably connected to the wing 1. A first bevel gear 5 is sleeved on the free end of the first drive shaft 4, and a second bevel gear 7 is sleeved on the second drive shaft 6. The first bevel gear 5 and the second bevel gear 7 mesh with each other. The rotation axis is located on the side of the flap 2 near the wing 1. When the second drive shaft 6 is coaxial with the rotation axis, the second drive shaft 6 is directly fixed to the flap 2. When the servo motor is activated, the servo motor drives the first drive shaft 4 to rotate, which in turn drives the first bevel gear 5. The rotation, through the meshing of the first bevel gear 5 and the second bevel gear 7, changes the transmission direction, causing the second transmission shaft 6 to drive the flap 2 to rotate around the rotation axis. By using the meshing of the first bevel gear 5 and the second bevel gear 7 for transmission, compared with the traditional method of using linkage mechanism transmission, the jamming situation that occurs in the transmission of multiple linkages can be avoided. At the same time, the identical structure of the first bevel gear 5 and the second bevel gear 7 can reduce the speed loss between the first transmission shaft 4 and the second transmission shaft 6, improve the efficiency of energy transmission, and the simple and direct transmission structure reduces the number of failure points, further increasing the stability and maintenance convenience of the drive mechanism.

[0034] Furthermore, when the second drive shaft 6 is not coaxial with the rotation axis, the second drive shaft 6 can be connected to the flap 2 via a connecting crank arm 8; a groove 16 is provided on the end face of the flap 2 near the drive mechanism, the connecting crank arm 8 has a first end and a second end, the first end is fixedly connected to the second drive shaft 6, and the second end is placed in the groove 16, which can slide along the groove 16 while rotating relative to the flap 2; the groove 16 extends along the first direction to the end of the flap 2 near the wing 1 and has a notch, the second end can be inserted into the groove 16 through the notch, when the second drive shaft 6 rotates, the connecting crank arm rotates around the axis of the second drive shaft 6, thereby driving the flap 2 to rotate around the rotation axis, while the connecting crank arm rotates relative to the flap 2, its second end slides along the groove 16 towards the notch. By setting the connecting crank arm, the torque required to drive the flap 2 to flip can be reduced, and a less powerful servo motor can be selected to save costs.

[0035] In a preferred embodiment, the vertical distance between the axis of the first end and the axis of the second end is a first distance, the vertical distance between the axis of the first end and the axis of rotation is a second distance, and the vertical distance between the axis of the second end and the axis of rotation is a third distance, and the sum of the first distance and the second distance is greater than or equal to the third distance.

[0036] like Figure 3 and Figure 4As shown, the axis of the second drive shaft 6 is located on the side of the rotation axis away from the wing 1. Initially, the sum of the first distance and the second distance is equal to the third distance. When the flap 2 rotates around the rotation axis, the first distance and the second distance remain unchanged. Since the second end slides along the groove 16 towards the notch at this time, the distance between it and the rotation axis gradually shortens, that is, the third distance becomes smaller, and the sum of the first distance and the second distance is greater than the third distance.

[0037] In a preferred embodiment, a plurality of first mounting seats 9 are fixed on one side of the wing 1 along the second direction, and second mounting seats 10 are rotatably connected to the first mounting seats 9. The plurality of second mounting seats 10 rotate around the rotation axis and are fixed along the second direction on the side of the flap 2 near the wing 1.

[0038] In a preferred embodiment, a lug 13 is fixed on the first mounting base 9, and a rotating groove 14 is provided on the second mounting base 10. The lug 13 is inserted into the rotating groove 14 and rotatably connected to the second mounting base 10.

[0039] like Figure 3 As shown, multiple first mounting seats 9 are fixed at equal intervals along the second direction at the trailing edge of the wing 1. The first mounting seat 9 has a lug 13 at the end away from the wing 1. A rotating groove 14 is opened on the second mounting seat 10, and both ends pass through the second mounting seat 10. The lug 13 is located in the rotating groove 14 and is rotatably connected to the second mounting seat 10 by a pin. It can rotate 180° relative to the second mounting seat 10 around the pin axis. Multiple second mounting seats 10 are also fixed at equal intervals along the second direction at the end of the flap 2 near the wing 1. In this embodiment, there are three first mounting seats 9 and three second mounting seats 10. In other embodiments of this application, the number of the two can be adjusted according to actual needs, and no specific limitation is made here. By using the first connecting seat and the second connecting seat to connect the wing 1 and the flap 2 respectively, a rotatable connection between the two can be achieved. Compared with the traditional method of directly machining the rotating structure on the flap 2 and the wing 1, the machining cost can be further saved.

[0040] In a preferred embodiment, the wing 1 includes a wing 1 skeleton, a wing 1 skin covering the wing 1 skeleton, and a mounting cavity formed inside the wing 1 skin; a mounting frame 11 is provided on the wing 1 skeleton, a drive component 3 is fixed on the mounting frame 11, and a connecting frame 12 is also provided on the mounting frame 11; a first drive shaft 4 passes through the mounting frame 11 and the connecting frame 12 in sequence and is rotatably connected to both; and a second drive shaft 6 is rotatably connected to the connecting frame 12.

[0041] like Figure 1As shown, the wing 1 frame is the main frame of the wing 1. The wing 1 skin covers the wing 1 frame and forms an internal mounting cavity. The mounting bracket 11 is fixed to the wing 1 frame. One end of the mounting bracket 11 is also fixed to the connecting bracket 12 by bolts. The servo is mounted on the mounting bracket 11. The free end of the first drive shaft 4 passes through the mounting bracket 11 and the connecting bracket 12 in sequence and is fitted with the first bevel gear 5. The two ends of the second rotating shaft are rotatably connected to the connecting bracket 12 respectively. The second bevel gear 7 is fitted between the two ends of the second drive shaft 6 and is located inside the connecting bracket 12. The end of the second drive shaft 6 near the flap 2 passes through the connecting bracket 12 and is fixed to the connecting crank arm 8.

[0042] In a preferred embodiment, the drive component 3 is fixedly connected to the first transmission shaft 4 via a coupling 15.

[0043] like Figure 2 As shown, the drive shaft of the servo motor is coaxially fixed to the first transmission shaft 4 via a coupling 15, so that the servo motor can drive the first transmission shaft 4 to rotate around its drive axis.

[0044] Working principle: When the servo is started, the servo drives the first bevel gear 5 to rotate through the first drive shaft 4. The first bevel gear 5 drives the second drive shaft 6 to rotate through the second bevel gear 7 that meshes with it. When the second drive shaft 6 rotates, the connecting swing arm rotates around the axis of the second drive shaft 6. The second end of the connecting swing arm drives the flap 2 to lift the side away from the wing 1 and rotate around the rotation axis, so that the flap 2 flips relative to the wing 1, thereby adjusting the aerodynamic shape of the UAV.

[0045] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this invention, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A drone flap structure, characterized by, The utility model relates to a kind of wing drive mechanism, including: Wing (1), the wing (1) inside has installation cavity; Flap (2), at least one the flap (2) is rotatably connected in one side of the wing (1); Driving mechanism, at least one the driving mechanism is located in the installation cavity, and it is correspondingly arranged with the flap (2), one end of the driving mechanism is connected the flap (2) and is stretched out from the installation cavity, for driving the flap (2) rotates around rotation axis, to make the flap (2) and the wing (1) between the included angle.

2. The drone flap structure of claim 1, wherein, The driving mechanism includes driving piece (3), the driving piece (3) is fixed in the installation cavity, the driving piece (3) is fixedly connected with first transmission shaft (4), the first transmission shaft (4) extends along first direction, its free end is sleeved with first bevel gear (4), the first bevel gear (4) is engaged with second bevel gear (7), second transmission shaft (6) is fixedly provided on the second bevel gear (7), the second transmission shaft (6) extends along second direction and is rotatably connected on the wing (1), one end of the second transmission shaft (6) is connected the flap (2) after extending out from the installation cavity, the second direction is perpendicular to the first direction.

3. The drone flap structure of claim 2, wherein, The driving mechanism further includes connecting crank arm (8), the first end of the connecting crank arm (8) is fixed with the second transmission shaft (6), and the second end is rotatably and slidingly connected on the flap (2) side end away from the wing (1).

4. The drone flap structure of claim 3, wherein, The vertical distance between the axis of the first end and the axis of the second end is a first distance, the vertical distance between the axis of the first end and the rotation axis is a second distance, and the vertical distance between the axis of the second end and the rotation axis is a third distance. The sum of the first distance and the second distance is greater than or equal to the third distance.

5. The drone flap structure of claim 1, wherein, A plurality of first mounting seats (9) are fixed on one side of the wing (1) along the second direction, and a second mounting seat (10) is rotatably connected on the first mounting seat (9). The plurality of second mounting seats (10) are rotatable around the rotation axis and fixed on one side of the flap (2) close to the wing (1) along the second direction.

6. The drone flap structure of claim 5, wherein, A lug (13) is fixed on the first mounting seat (9), and a rotating groove (14) is formed on the second mounting seat (10). The lug (13) is inserted into the rotating groove (14) and rotatably connected with the second mounting seat (10).

7. The drone flap structure of claim 2, wherein, The wing (1) includes a wing framework, and a wing skin covers the wing framework. The wing skin forms the installation cavity inside. The wing framework is provided with a mounting frame (11), and the driving piece (3) is fixed on the mounting frame (11). The mounting frame (11) is further provided with a connecting frame (12), and the first transmission shaft (4) penetrates the mounting frame (11) and the connecting frame (12) in sequence and is rotatably connected with them. The second transmission shaft (6) is rotatably connected on the connecting frame (12).

8. The drone flap structure of claim 2, wherein, The driving piece (3) is fixedly connected with the first transmission shaft (4) through a shaft coupling (15).

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