Unmanned aerial vehicle aileron structural component and unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle ailerons, and discloses an unmanned aerial vehicle aileron structural component and an unmanned aerial vehicle. The unmanned aerial vehicle aileron structural part comprises an empennage, an aileron and a control assembly used for controlling the aileron, a mounting opening is formed in the empennage, the aileron is rotationally connected into the mounting opening through a connecting assembly, and a protection assembly used for separating the aileron and the control assembly from the empennage for protection is arranged outside the empennage. Under the condition that the unmanned aerial vehicle cannot be controlled to fall, the aileron and the control assembly are separated from the unmanned aerial vehicle, then the box body, the control assembly and the aileron are driven by the parachute to descend, and finally the unmanned aerial vehicle slowly falls on the ground, so that the aileron and the control assembly can be protected, loss is reduced, and after the aileron and the control assembly are separated, the unmanned aerial vehicle is protected. Sound waves are emitted by the sound wave equipment, and birds can be repelled by the sound waves emitted by the sound wave equipment, so that the birds are prevented from interfering with descending of the ailerons.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle ailerons, and in particular relates to an unmanned aerial vehicle aileron structure and a unmanned aerial vehicle. Background Art

[0002] A drone is an unmanned aircraft controlled by a radio remote control device or its own program control device. When in use, the drone can adjust its flight attitude by relying on the swing of the aileron structure.

[0003] When the existing UAV ailerons are in use, when the UAV fails to control, the UAV will fall downward, causing the UAV and the aileron structure to be damaged after landing. When the UAV is confirmed to be damaged, the aileron cannot be protected, thereby failing to reduce the loss.

[0004] Therefore, it is necessary to invent a UAV aileron structure and a UAV to solve the above problems. Summary of the invention

[0005] In view of the above problems, the present invention provides a UAV aileron structure and a UAV to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] An aileron structure of a drone, comprising a tail wing, an aileron and a control assembly for controlling the aileron, wherein the tail wing is provided with a mounting opening, the aileron is rotatably connected in the mounting opening through a connecting assembly, and a protection assembly is provided outside the tail wing for separating the aileron and the control assembly from the tail wing for protection;

[0008] The protection assembly includes: a pair of side plates, a box body, a carrier plate, a first spring, a parachute, a limit film, a puncture assembly for puncturing the limit film, a rotation assembly for rotatably connecting the box body to the pair of side plates, and a limiting assembly for limiting the rotation of the box body;

[0009] A pair of side panels are fixed at the bottom of the tail wing, the box body is fixed at one side of the operating assembly, the carrier plate is slidably arranged in the box body, the first spring connects the carrier plate to the inner wall of the box body, the parachute is arranged on the carrier plate, and the two ends of the limiting membrane are respectively connected to the two sides of the opening of the box body.

[0010] Further, the connecting assembly includes: a pair of slide plates, a rotating shaft, a second spring, a first electromagnet, a controller, and a power supply;

[0011] Both ends of the aileron are provided with a cavity, the skateboard is slidably arranged in the cavity, the inner wall of the cavity is symmetrically provided with vertical grooves, the two ends of the skateboard are located in adjacent vertical grooves, the second spring connects the skateboard to the inner wall of the vertical groove, the inner wall of the mounting port is provided with a rotating groove corresponding to the rotating shaft, the rotating shaft is fixed to a side of the skateboard close to the rotating groove and extends into the rotating groove, the first electromagnet is fixedly connected to the inner wall of the cavity away from the rotating groove, the controller and the power supply are fixed at the bottom of the operating component, the controller can control the power supply to supply power to the first electromagnet, and the material of the skateboard is iron.

[0012] Further, a pair of mounting cylinders, an iron plate, a limit rod, a second electromagnet, and a third spring;

[0013] A pair of mounting tubes are respectively fixed at two ends of the box body, the iron plate is slidably arranged inside the mounting tube, the inner wall of the mounting tube is symmetrically provided with movable grooves, the two ends of the iron plate are arranged in the movable grooves, the third spring connects the inner wall of the movable groove with the iron plate, the second electromagnet is fixed on the inner wall of the mounting tube close to the box body, the limit rod is fixedly connected to the side of the iron plate close to the side plate, the inner side of the side plate is provided with a limit hole cooperating with the limit rod, one end of the limit rod extends into the limit hole, and the controller can control the power supply to supply power to the second electromagnet.

[0014] Furthermore, the rotating assembly includes: a pair of shells, a circular plate, a rotating column, a third electromagnet, and a fourth spring; the pair of shells are respectively fixedly mounted at both ends of the box body, the circular plate is slidably arranged in the shell, the inner wall of the shell is symmetrically provided with sliding grooves, the two sides of the circular plate are located in the sliding grooves, the fourth spring connects the circular plate to the inner wall of the sliding groove, the rotating column is fixedly mounted on a side of the circular plate close to the side plate, the inner side of the side plate is provided with a circular groove matching the rotating column, one end of the rotating column extends into the circular groove, the circular plate is made of iron, the third electromagnet is fixedly mounted on the inner wall of the shell close to the box body, and the controller can control the power supply to supply power to the third electromagnet.

[0015] Further, a blade, a push rod, a fifth spring, an inclined surface arranged at one end of the push rod, and a squeeze rod;

[0016] Both sides of the box body are provided with movable openings, the push rod is located in the movable opening, the fifth spring connects the push rod to the inner wall of the movable opening, the blade is fixedly connected to the two push rods and the blade is arranged in the box body, the extrusion rod is fixedly connected to the side of the circular plate close to the push rod, and the shell is provided with an extension hole corresponding to the push rod.

[0017] Furthermore, the inner wall of the box body is fixedly connected to the sound wave device, and the outer side of the box body is provided with multiple circular holes connected to the interior thereof, one of the circular holes is provided with a push switch cooperating with the sound wave device, and one end of the push switch extending into the box body is set as an arc end.

[0018] Furthermore, the weight of the aileron is greater than the total weight of the control assembly, the box body, the control assembly and all components installed and connected to the box body, and the box body can be rotated by a rotating column.

[0019] The present invention also provides a UAV, comprising the UAV aileron structure as described above.

[0020] Technical effects and advantages of the present invention:

[0021] 1. The present invention can separate the aileron and the control assembly from the drone when the drone cannot be controlled and falls, and then the box body, the control assembly and the aileron are lowered by a parachute, and finally slowly land on the ground, so that the aileron and the control assembly can be protected, thereby reducing losses;

[0022] 2. After the aileron and the control assembly are separated, the present invention can emit sound waves through the sound wave device, and the sound waves emitted by the sound wave device can drive away birds and prevent the birds from interfering with the descent of the aileron. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A schematic diagram of the structure of a UAV aileron structure and a UAV according to an embodiment of the present invention is shown;

[0024] Figure 2 The structure diagram of the aileron structure of the UAV according to the embodiment of the present invention is shown. Figure 1 ;

[0025] Figure 3 The cross-sectional structure diagram of the aileron structure of the UAV according to the embodiment of the present invention is shown. Figure 1 ;

[0026] Figure 4 The structure diagram of the aileron structure of the UAV according to the embodiment of the present invention is shown. Figure 2 ;

[0027] Figure 5 The embodiment of the present invention is shown Figure 4 The enlarged structural diagram at A in the middle;

[0028] Figure 6 The cross-sectional structure diagram of the aileron structure of the UAV according to the embodiment of the present invention is shown. Figure 2 ;

[0029] Figure 7 The embodiment of the present invention is shown Figure 6 The enlarged structural diagram at B in the middle;

[0030] In the figure: 1. tail wing; 2. aileron; 3. side panel; 4. box body; 5. control assembly; 6. carrier plate; 7. first spring; 8. parachute; 9. limit film; 10. slide plate; 11. rotating shaft; 12. second spring; 13. first electromagnet; 14. controller; 15. power supply; 16. mounting tube; 17. iron plate; 18. limit rod; 19. second electromagnet; 20. third spring; 21. shell; 22. round plate; 23. rotating column; 24. third electromagnet; 25. fourth spring; 26. blade; 27. push rod; 28. fifth spring; 29. ​​inclined plane; 30. squeeze rod; 31. sonic device; 32. round hole; 33. push switch. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments.

[0032] The present invention provides a UAV aileron structural component, such as Figures 1 to 7 As shown, it includes a tail 1, an aileron 2 and a control assembly 5 for controlling the aileron 2. The control assembly 5 is a control assembly used for controlling the rotation of the aileron 2 on a UAV in the prior art. A mounting opening is provided on the tail 1. The aileron 2 is rotatably connected in the mounting opening through a connecting assembly. A protective assembly is provided outside the tail 1 for separating the aileron 2 and the control assembly 5 from the tail 1 for protection.

[0033] The protection assembly includes: a pair of side plates 3, a box body 4, a carrier plate 6, a first spring 7, a parachute 8, a limiting film 9, a puncturing assembly for puncturing the limiting film 9, a rotating assembly for rotatably connecting the box body 4 and the pair of side plates 3, and a limiting assembly for limiting the rotation of the box body 4. The limiting film 9 is a thin film member, and its own strength can overcome the elastic force of the first spring 7 to limit the parachute 8 in the box body 4;

[0034] A pair of side panels 3 are fixed to the bottom of the tail 1, the box body 4 is fixed to one side of the operating assembly 5, the carrier plate 6 is slidably set in the box body 4, the first spring 7 connects the carrier plate 6 to the inner wall of the box body 4, the parachute 8 is set on the carrier plate 6, and the two ends of the limiting membrane 9 are respectively connected to the two sides of the opening of the box body 4.

[0035] When the drone is in use, if it cannot be controlled in the air, the connection between the aileron 2 and the tail wing 1 by the connecting component is canceled, and then the rotation restriction of the box body 4 by the limiting component is canceled. Under the action of gravity, the aileron 2, the operating component 5, and the box body 4 rotate downward by relying on the rotating component, so that the aileron 2 is rotated to the bottom of the box body 4, and then the rotating component cancels the connection with the side panel 3. Then, under the action of gravity, the aileron 2, the operating component 5, and the box body 4 descend and detach from the drone. At the same time, the piercing component pierces one side of the limiting film 9, and then the first spring 7 releases the force to move the carrier plate 6 and the parachute 8 out of the box body 4, so that the parachute 8 is exposed to the outside world. As the drone descends, the parachute 8 opens, and then descends with the box body 4, the operating component 5, and the aileron 2, and finally slowly falls to the ground, so that the aileron 2 is protected, so that when the drone cannot be controlled and falls, the aileron 2 and the operating component 5 are protected, thereby reducing losses.

[0036] like Figures 2 to 5 As shown, the connection assembly includes: a pair of slide plates 10, a rotating shaft 11, a second spring 12, a first electromagnet 13, a controller 14, and a power supply 15;

[0037] Both ends of the aileron 2 are provided with a cavity, and a skateboard 10 is slidably arranged in the cavity. The inner wall of the cavity is symmetrically provided with vertical grooves, and the two ends of the skateboard 10 are located in adjacent vertical grooves. The second spring 12 connects the skateboard 10 to the inner wall of the vertical groove. The inner wall of the mounting opening is provided with a rotating groove corresponding to the rotating shaft 11. The rotating shaft 11 is fixed to a side of the skateboard 10 close to the rotating groove and extends into the rotating groove. The first electromagnet 13 is fixedly connected to the inner wall of the cavity away from the rotating groove. The controller 14 and the power supply 15 are fixed at the bottom of the operating component 5. The controller 14 can control the power supply 15 to supply power to the first electromagnet 13. The material of the skateboard 10 is iron. The controller 14 is a remote controller and can be operated on the ground.

[0038] The controller 14 controls the first electromagnet 13 to be energized to make it magnetic, so that the attracted slide plate 10 moves with the rotating shaft 11 in the direction away from the rotating groove. At the same time, the slide plate 10 compresses the second spring 12 to deform it and generate a force. As the rotating shaft 11 is separated from the rotating groove, the connection between the aileron 2 and the tail wing 1 is cancelled, and the first electromagnet 13 is powered off to make it lose its magnetism. At this time, the second spring 12 restores the slide plate 10 and the rotating shaft 11.

[0039] like Figure 6 to Figure 7 As shown, the limiting assembly includes: a pair of mounting cylinders 16, an iron plate 17, a limiting rod 18, a second electromagnet 19, and a third spring 20;

[0040] A pair of mounting tubes 16 are respectively fixed at the two ends of the box body 4, the iron plate 17 is slidably arranged inside the mounting tube 16, the inner wall of the mounting tube 16 is symmetrically provided with movable grooves, the two ends of the iron plate 17 are arranged in the movable grooves, the third spring 20 connects the inner wall of the movable groove with the iron plate 17, the second electromagnet 19 is fixed on the inner wall of the mounting tube 16 close to the box body 4, the limiting rod 18 is fixedly connected to the side of the iron plate 17 close to the side plate 3, the inner side of the side plate 3 is provided with a limiting hole cooperating with the limiting rod 18, one end of the limiting rod 18 extends into the limiting hole, and the controller 14 can control the power supply 15 to supply power to the second electromagnet 19.

[0041] The second electromagnet 19 is energized by the controller 14 to make it magnetic, so that it attracts the iron plate 17 and moves it with the limiting rod 18 in the direction away from the limiting hole. At the same time, the iron plate 17 compresses the third spring 20 to deform it and generate a force. After the limiting rod 18 is separated from the limiting hole, the restriction on the rotation of the box body 4 is cancelled.

[0042] like Figure 6 and Figure 7 As shown, the rotating assembly includes: a pair of housings 21, a circular plate 22, a rotating column 23, a third electromagnet 24, and a fourth spring 25;

[0043] A pair of shells 21 are fixedly mounted at both ends of the box body 4, respectively, and a circular plate 22 is slidably arranged in the shell 21. The inner wall of the shell 21 is symmetrically provided with sliding grooves, and both sides of the circular plate 22 are located in the sliding grooves. The fourth spring 25 connects the circular plate 22 with the inner wall of the sliding groove. The rotating column 23 is fixedly mounted on one side of the circular plate 22 close to the side plate 3. The inner side of the side plate 3 is provided with a circular groove matching the rotating column 23. One end of the rotating column 23 extends into the circular groove. The material of the circular plate 22 is iron. The third electromagnet 24 is fixedly mounted on the inner wall of the shell 21 close to the box body 4. The controller 14 can control the power supply 15 to supply power to the third electromagnet 24.

[0044] When the limiting rod 18 leaves the limiting hole, the box body 4, the operating assembly 5, and the aileron 2 rotate around the rotating column 23, and then the third electromagnet 24 is energized through the controller 14 to make it magnetic, so that the attracting circular plate 22 moves with the rotating column 23 in the direction away from the circular groove, and at the same time, the fourth spring 25 is compressed to deform it to generate a force. When the rotating column 23 leaves the circular groove, the box body 4 can separate from the side plate 3 and descend.

[0045] like Figures 3 to 7 As shown, the piercing assembly includes: a blade 26, a push rod 27, a fifth spring 28, a slope 29 arranged at one end of the push rod 27, and a squeeze rod 30;

[0046] Both sides of the box body 4 are provided with movable openings, the push rod 27 is located in the movable opening, the fifth spring 28 connects the push rod 27 to the inner wall of the movable opening, the blade 26 is fixedly connected to the two push rods 27 and the blade 26 is arranged in the box body 4, the squeezing rod 30 is fixedly connected to the side of the circular plate 22 close to the push rod 27, and an extension hole corresponding to the push rod 27 is opened on the shell 21.

[0047] The circular plate 22 moves in the direction away from the circular groove, carrying the squeezing rod 30 with it. The squeezing rod 30 cooperates with the inclined surface 29 to squeeze the push rod 27 so that it moves with the blade 26 in the direction close to the limiting membrane 9, so that the end of the limiting membrane 9 connected to the box body 4 is punctured, so that the limiting membrane 9 removes the restriction on the parachute 8. While the push rod 27 moves, the fifth spring 28 is compressed to deform it and generate a force, so that the limiting membrane 9 is punctured.

[0048] like Figure 3 As shown, a sound wave device 31 is fixedly connected to the inner wall of the box body 4, and a plurality of circular holes 32 communicating with the interior of the box body 4 are provided on the outer side of the box body 4, wherein a push switch 33 cooperating with the sound wave device 31 is provided in one of the circular holes 32, and one end of the push switch 33 extending into the box body 4 is set as an arc end, and the sound wave device 31 is a repelling sound wave device used for repelling birds in the prior art.

[0049] After the limiting film 9 is punctured, the compressed first spring 7 releases its force to move the carrier plate 6 and the parachute 8 out of the box body 4. As the carrier plate 6 moves, the arc end of the press switch 33 is squeezed, thereby pressing the press switch 33, and then starting the sound wave device 31 to emit sound waves. The sound waves emitted by the sound wave device can drive away birds and prevent birds from interfering with the descent of the aileron 2.

[0050] like Figure 2 As shown, the weight of the aileron 2 is greater than the total weight of the control assembly 5, the box body 4, the control assembly 5 and all the components installed and connected on the box body 4. The box body 4 can be rotated by the rotating column 23. The weight of the aileron 2 is enough to rotate downward with the control assembly 5, the box body 4, the control assembly 5 and all the components installed and connected on the box body 4 in the air by gravity.

[0051] The present invention also provides a UAV, comprising the UAV aileron structure as described above.

[0052] Working principle: When the drone is in use and cannot be controlled in the air, the controller 14 controls the first electromagnet 13 to be energized to make it magnetic, so that the attracting slide plate 10 moves with the rotating shaft 11 in the direction away from the rotating groove, and the slide plate 10 compresses the second spring 12 to deform and generate a force. As the rotating shaft 11 is separated from the rotating groove, the connection between the aileron 2 and the tail 1 is cancelled. Then, the controller 14 controls the second electromagnet 19 to be energized to make it magnetic, so that the attracting iron plate 17 moves with the limiting rod 18 in the direction away from the limiting hole, and the iron plate 17 compresses the second spring 12 to deform and generate a force. The third spring 20 deforms it to generate a force. After the limit rod 18 is separated from the limit hole, the restriction on the rotation of the box body 4 is cancelled. Under the action of gravity, the aileron 2, the control assembly 5, and the box body 4 rotate along the rotating column 23, so that the aileron 2 is rotated to the bottom of the box body 4. Then, the controller 14 controls the third electromagnet 24 to be energized to make it magnetic, so that the circular plate 22 is attracted to move with the rotating column 23 in the direction away from the circular groove, and the fourth spring 25 is compressed to deform it to generate a force. When the rotating column 23 leaves the circular groove, the box body 4 can separate from the side plate 3 and descend, and the circular plate 22 moves away from the circular groove. The extrusion rod 30 moves with it, and the extrusion rod 30 cooperates with the inclined surface 29 to squeeze the push rod 27 so that it moves with the blade 26 in the direction close to the limiting film 9, so that the end of the limiting film 9 connected to the box body 4 is punctured, so that the limiting film 9 cancels the restriction on the parachute 8. When the push rod 27 moves, the fifth spring 28 is compressed to deform and generate a force, so that the limiting film 9 is punctured. Then the first spring 7 releases the force and moves the carrier plate 6 and the parachute 8 out of the box body 4, so that the parachute 8 is exposed to the outside world. As it descends, the parachute 8 opens, and then the box body 4 is lifted. , the operating component 5, and the aileron 2 descend, and finally slowly land on the ground, so that the aileron 2 is protected, so that when the drone cannot be controlled and falls, the aileron 2 and the operating component 5 are protected, thereby reducing losses; after the limiting membrane 9 is punctured, the compressed first spring 7 releases the force to move the carrier plate 6 and the parachute 8 out of the box body 4, and with the movement of the carrier plate 6, the arc end of the pressing switch 33 is squeezed, thereby pressing the pressing switch 33, and then starting the sound wave device 31 to emit sound waves, which can drive away birds and prevent birds from interfering with the descent of the aileron 2.

[0053] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them.

Claims

1. An aileron structure of an unmanned aerial vehicle, comprising a tail wing (1), an aileron (2) and a control assembly (5) for controlling the aileron (2), characterized in that: The tail wing (1) is provided with a mounting opening, the aileron (2) is rotatably connected in the mounting opening through a connecting assembly, and a protection assembly for separating the aileron (2) and the operating assembly (5) from the tail wing (1) is provided outside the tail wing (1) for protecting; the protection assembly comprises: a pair of side plates (3), a box body (4), a carrier plate (6), a first spring (7), a parachute (8), a limiting film (9), a piercing assembly for piercing the limiting film (9), a rotating assembly for rotatably connecting the box body (4) and the pair of side plates (3), and a limiting assembly for limiting the rotation of the box body (4); the pair of side plates (3) are fixed to the bottom of the tail wing (1), the box body (4) is fixed to one side of the operating assembly (5), the carrier plate (6) is slidably arranged in the box body (4), the first spring (7) connects the carrier plate (6) to the inner wall of the box body (4), the parachute (8) is arranged on the carrier plate (6), and the two ends of the limiting film (9) are respectively connected to the two sides of the opening of the box body (4).

2. The UAV aileron structure according to claim 1, characterized in that: The connecting component comprises: a pair of slide plates (10), a rotating shaft (11), a second spring (12), a first electromagnet (13), a controller (14), and a power supply (15); both ends of the aileron (2) are provided with a cavity, the slide plate (10) is slidably arranged in the cavity, the inner wall of the cavity is symmetrically provided with vertical grooves, the two ends of the slide plate (10) are located in adjacent vertical grooves, the second spring (12) connects the slide plate (10) with the inner wall of the vertical groove, the inner wall of the mounting opening is provided with a rotating groove corresponding to the rotating shaft (11), the rotating shaft (11) is fixed to a side of the slide plate (10) close to the rotating groove and extends into the rotating groove, the first electromagnet (13) is fixedly connected to the inner wall of the cavity away from the rotating groove, the controller (14) and the power supply (15) are fixed to the bottom of the operating component (5), the controller (14) can control the power supply (15) to supply power to the first electromagnet (13), and the material of the slide plate (10) is iron.

3. The UAV aileron structure according to claim 2, characterized in that: The limiting assembly comprises: a pair of mounting tubes (16), an iron plate (17), a limiting rod (18), a second electromagnet (19), and a third spring (20); the pair of mounting tubes (16) are respectively fixed at two ends of the box body (4); the iron plate (17) is slidably arranged inside the mounting tube (16); the inner wall of the mounting tube (16) is symmetrically provided with movable grooves; the two ends of the iron plate (17) are arranged in the movable grooves; the third spring (20) connects the inner wall of the movable groove with the iron plate (17); the second electromagnet (19) is fixed on the inner wall of the mounting tube (16) close to the box body (4); the limiting rod (18) is fixedly connected to a side of the iron plate (17) close to the side plate (3); the inner side of the side plate (3) is provided with a limiting hole matched with the limiting rod (18); one end of the limiting rod (18) extends into the limiting hole; and the controller (14) can control the power supply (15) to supply power to the second electromagnet (19).

4. The UAV aileron structure according to claim 3, characterized in that: The rotating assembly comprises: a pair of shells (21), a circular plate (22), a rotating column (23), a third electromagnet (24), and a fourth spring (25); the pair of shells (21) are respectively fixedly mounted at two ends of the box body (4); the circular plate (22) is slidably arranged in the shell (21); the inner wall of the shell (21) is symmetrically provided with sliding grooves; the two sides of the circular plate (22) are located in the sliding grooves; the fourth spring (25) connects the circular plate (22) with the inner wall of the sliding groove; the rotating column (23) is fixedly mounted on a side of the circular plate (22) close to the side plate (3); the inner side of the side plate (3) is provided with a circular groove matching the rotating column (23); one end of the rotating column (23) extends into the circular groove; the circular plate (22) is made of iron; the third electromagnet (24) is fixedly mounted on an inner wall of the shell (21) close to the box body (4); and the controller (14) can control the power supply (15) to supply power to the third electromagnet (24).

5. The UAV aileron structure according to claim 4, characterized in that: The piercing assembly comprises: a blade (26), a push rod (27), a fifth spring (28), an inclined surface (29) arranged at one end of the push rod (27), and an extrusion rod (30); movable openings are provided on both sides of the box body (4), the push rod (27) is located in the movable opening, the fifth spring (28) connects the push rod (27) with the inner wall of the movable opening, the blade (26) is fixedly connected to the two push rods (27) and the blade (26) is arranged in the box body (4), the extrusion rod (30) is fixedly connected to a side of the circular plate (22) close to the push rod (27), and an extension hole corresponding to the push rod (27) is provided on the shell (21).

6. The UAV aileron structure according to claim 5, characterized in that: The inner wall of the box body (4) is fixedly connected to a sound wave device (31); the outer side of the box body (4) is provided with a plurality of circular holes (32) communicating with the interior thereof; a push switch (33) cooperating with the sound wave device (31) is provided in one of the circular holes (32); and one end of the push switch (33) extending into the box body (4) is arranged as an arc end.

7. The UAV aileron structure according to claim 6, characterized in that: The weight of the aileron (2) is greater than the total weight of the operating assembly (5), the box body (4), the operating assembly (5) and all components installed and connected to the box body (4), and the box body (4) can be rotated by a rotating column (23).

8. An unmanned aerial vehicle, comprising the unmanned aerial vehicle aileron structure as described in claim 7.

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