Control surface linkage structure of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a control surface linkage structure of an unmanned aerial vehicle, which comprises a main body and a frame, the frame is fixedly connected below the main body, a linkage mechanism is arranged in the frame, the surface of the main body is fixedly connected with a bracket, a dismounting mechanism is arranged in the bracket, and the main body is fixedly connected with the frame. The interior of the support is in threaded connection with a locking screw, and a control surface is arranged below the main body. The motor drives the worm to rotate, the worm drives the worm gear to rotate, the worm gear drives the rotating rod to rotate, the rotating rod drives the two first connecting cylinders to rotate, the first connecting cylinders drive the second connecting rod to rotate, the second connecting rod drives the control surface to rotate to adjust the inclination angle of the control surface, and the motor is closed after the inclination angle is adjusted to the needed angle. And the inclination angle of the control surface does not change under the condition that the motor is not started, so that the angle of the control surface can be conveniently fixed after the control surface rotates to the required angle.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a rudder surface linkage structure of an unmanned aerial vehicle. Background Technique

[0002] An unmanned aerial vehicle, abbreviated as "UAV", is an unpiloted aircraft controlled by a radio remote control device and a self - contained program control device. The rudder surface is a hinged small wing surface or an adjustable small vane at the trailing edge of the main control surface of the aircraft. In terms of outline, the trim tab is the trailing edge part of the main control surface. Controlling the deflection of the trim tab can change the hinge moment on the main control surface.

[0003] For example, a rudder surface linkage structure of an unmanned aerial vehicle with the patent number CN220518603U includes a main body and a first rudder surface and a second rudder surface located on one side of the main body. Symmetrically arranged first rudder surface connectors are provided at the bottom ends of the first rudder surface and the second rudder surface, and a number of second rudder surface connectors corresponding to the positions of the first rudder surface connectors are provided at the bottom end of the main body. However, the above - mentioned document still has deficiencies. During use, the power component rotates to drive a connecting rod kit composed of a ball - head fixing part, a ball head, a connecting rod, and a self - locking nut, driving the rudder surface # to rotate a certain angle around the rudder surface rotating shaft. A rudder surface linkage mechanism is assembled by a first rudder surface linkage part and a second rudder surface linkage part, and the first rudder surface linkage part and the second rudder surface linkage part are respectively installed on the first rudder surface and the second rudder surface. When the first rudder surface rotates, it drives the second rudder surface to rotate. However, in the above - mentioned document, the rotation of the rudder surface is controlled by the power component. After the rudder surface rotates to a certain angle, the linkage mechanism does not have a self - locking function, making it inconvenient to fix the angle of the rudder surface after it rotates to the required angle. At the same time, when the rudder surface is used for a long time, there will be a certain amount of wear. When the rudder surface is worn, it is inconvenient to replace the rudder surface. Content of the Utility Model

[0004] The purpose of the utility model is to solve the problem that it is inconvenient to fix the angle of the rudder surface after it rotates to the required angle, and to provide a rudder surface linkage structure of an unmanned aerial vehicle.

[0005] To achieve the above - mentioned purpose, the utility model provides the following technical solutions:

[0006] Design a rudder surface linkage structure of an unmanned aerial vehicle, including a main body and a frame. The frame is fixedly connected below the main body. A linkage mechanism is arranged inside the frame. A bracket is fixedly connected to the surface of the main body. A disassembly mechanism is arranged inside the bracket. A locking screw is threadedly connected inside the bracket. A rudder surface is arranged below the main body. A first connecting rod is fixedly connected to the left side of the rudder surface.

[0007] Preferably, the linkage mechanism includes a motor fixedly connected to the upper surface of the frame. A worm is fixedly connected to the output shaft of the motor. The outer walls at both ends of the worm are rotatably connected to the frame through bearings. The worm is meshed with a worm gear. The worm gear is fixedly connected to the outer wall of a rotating rod. The outer walls at both ends of the rotating rod are rotatably connected to the frame through bearings. First connecting cylinders are fixedly connected to both ends of the rotating rod.

[0008] Preferably, the disassembly mechanism includes a screw rod. The outer walls at both ends of the screw rod are rotatably connected to a bracket through bearings. A handle is fixedly connected to the end of the screw rod. A threaded block is threadedly connected to the outer wall of the screw rod. The outer wall of the threaded block is slidably connected to the bracket. A connecting rod is fixedly connected to the outer wall of the threaded block. A support plate is fixedly connected to the end of the connecting rod.

[0009] Preferably, a second connecting cylinder is rotatably connected to the inside of the support plate through a bearing. The second connecting cylinder is in clearance fit with the outer wall of the first connecting rod.

[0010] Preferably, a second connecting rod is in clearance fit with the inside of the first connecting cylinder. The second connecting rod is fixedly connected to the right end of the control surface.

[0011] Preferably, a groove is provided inside the main body.

[0012] For a control surface linkage structure of an unmanned aerial vehicle proposed by the present utility model, the beneficial effects are as follows: Through the cooperation among the motor, the worm, the worm gear, the rotating rod and the first connecting cylinder, the motor drives the worm to rotate, the worm drives the worm gear to rotate, the worm gear drives the rotating rod to rotate, the rotating rod drives the two first connecting cylinders to rotate, the first connecting cylinder drives the second connecting rod to rotate, and the second connecting rod drives the control surface to rotate to adjust the inclination angle of the control surface. After adjusting to the required angle, the motor is turned off. The worm and the worm gear have a self-locking function, and the inclination angle of the control surface will not change without starting the motor, making it convenient to fix the angle of the control surface after the control surface rotates to the required angle.

[0013] Through the cooperation among the screw rod, the handle, the threaded block, the connecting rod and the support plate, rotate the handle corresponding to the control surface that needs to be replaced. The handle drives the screw rod to rotate, the screw rod drives the threaded block to slide, the threaded block drives the connecting rod to move, the connecting rod drives the support plate to move, the support plate drives the second connecting cylinder to move, the second connecting cylinder separates from the first connecting rod, hold the control surface and pull it. The control surface drives the second connecting rod to move, and the second connecting rod separates from the first connecting cylinder, so as to disassemble and replace the control surface. When the control surface is worn, it is convenient to replace the control surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a schematic structural diagram of the present utility model;

[0015] Figure 2 is a structural sectional view of the present utility model;

[0016] Figure 3 It is a structural schematic diagram of the connection between the screw rod, the handle and the threaded block in the utility model;

[0017] Figure 4 It is a structural schematic diagram of the connection between the first connecting rod and the second connecting tube in the utility model;

[0018] Figure 5 It is a structural schematic diagram of the connection between the motor, the worm and the worm wheel in the utility model;

[0019] Figure 6 It is a structural schematic diagram of the connection between the rudder surface, the second connecting rod and the first connecting rod in the utility model.

[0020] In the figure: 1. main body, 2. frame, 3. linkage structure, 301. motor, 302. worm, 303. worm wheel, 304. rotating rod, 305. first connecting tube, 4. disassembly mechanism, 401. screw, 402. handle, 403. threaded block, 404. connecting rod, 405. support plate, 5. bracket, 6. locking screw, 7. rudder surface, 8. first connecting rod, 9. second connecting tube, 10. second connecting rod, 11. groove. DETAILED DESCRIPTION

[0021] The utility model is further described below in conjunction with the accompanying drawings:

[0022] See attached Figure 1-6 In the present embodiment, a rudder surface linkage structure of an unmanned aerial vehicle includes a main body 1 and a frame 2, wherein the frame 2 is fixedly connected to the bottom of the main body 1, and the main body 1 is the main body of the unmanned aerial vehicle. A linkage mechanism 3 is arranged inside the frame 2, and the linkage mechanism 3 causes two rudder surfaces 7 to rotate in a linked manner. A bracket 5 is fixedly connected to the surface of the main body 1, and a disassembly mechanism 4 is arranged inside the bracket 5, and the disassembly mechanism 4 is convenient for disassembly of the rudder surface 7. A locking screw 6 is connected to the internal thread of the bracket 5, and the locking screw 6 can lock and fix the threaded block 403 inside the bracket 5. A rudder surface 7 is arranged below the main body 1, and a first connecting rod 8 is fixedly connected to the left side of the rudder surface 7, and the first connecting rod 8 moves together with the rudder surface 7. A groove 11 is arranged inside the main body 1, and the groove 11 is arranged at the motor 301 to avoid the motor 301 for heat dissipation of the motor 301.

[0023] The linkage mechanism 3 includes a motor 301, a worm 302, a worm gear 303, a rotating rod 304 and a first connecting cylinder 305. The motor 301 is fixedly connected to the upper surface of the frame 2. The output shaft of the motor 301 is fixedly connected with the worm 302. The motor 301 drives the worm 302 to rotate. The outer walls at both ends of the worm 302 are rotatably connected to the frame 2 through bearings. The worm 302 is meshed with the worm gear 303. The worm 302 drives the worm gear 303 to rotate. The worm gear 303 is fixedly connected to the outer wall of the rotating rod 304. The worm gear 303 drives the rotating rod 304 to rotate;

[0024] The outer walls at both ends of the rotating rod 304 are rotatably connected to the frame 2 through bearings. Both ends of the rotating rod 304 are fixedly connected with the first connecting cylinder 305. The rotating rod 304 drives the first connecting cylinder 305 to rotate. The second connecting rod 10 is in clearance fit with the inside of the first connecting cylinder 305. The first connecting cylinder 305 drives the second connecting rod 10 to rotate. Matching key grooves are provided inside the first connecting cylinder 305 and the second connecting rod 10. The second connecting rod 10 is fixedly connected to the right end of the rudder surface 7. The second connecting rod 10 drives the rudder surface 7 to rotate;

[0025] The motor 301 drives the worm 302 to rotate. The worm 302 drives the worm gear 303 to rotate. The worm gear 303 drives the rotating rod 304 to rotate. The rotating rod 304 drives the two first connecting cylinders 305 to rotate. The first connecting cylinder 305 drives the second connecting rod 10 to rotate. The second connecting rod 10 drives the rudder surface 7 to rotate to adjust the inclination angle of the rudder surface 7. After adjusting to the required angle, the motor 301 is turned off. The worm 302 and the worm gear 303 have a self-locking function. The inclination angle of the rudder surface 7 will not change without starting the motor 301, so that the inclination angle of the rudder surface 7 can be fixed conveniently after rotating to the required angle.

[0026] The disassembly mechanism 4 includes a screw rod 401, a handle 402, a threaded block 403, a connecting rod 404 and a support plate 405. The outer walls at both ends of the screw rod 401 are rotatably connected to the support 5 through bearings. The end of the screw rod 401 is fixedly connected with the handle 402. The handle 402 drives the screw rod 401 to rotate. The threaded block 403 is threadedly connected to the outer wall of the screw rod 401. The screw rod 401 drives the threaded block 403 to slide. The outer wall of the threaded block 403 is slidably connected to the support 5. The outer wall of the threaded block 403 is fixedly connected with the connecting rod 404. The threaded block 403 drives the connecting rod 404 to move;

[0027] The end of the connecting rod 404 is fixedly connected with the support plate 405. The connecting rod 404 drives the support plate 405 to move. The second connecting cylinder 9 is rotatably connected to the inside of the support plate 405 through a bearing. The support plate 405 drives the second connecting cylinder 9 to move. The second connecting cylinder 9 is in clearance fit with the outer wall of the first connecting rod 8. Matching key grooves are provided between the second connecting cylinder 9 and the first connecting rod 8;

[0028] Turn the handle 402 corresponding to the rudder surface 7 that needs to be replaced, the handle 402 drives the screw 401 to rotate, the screw 401 drives the threaded block 403 to slide, the threaded block 403 drives the connecting rod 404 to move, the connecting rod 404 drives the support plate 405 to move, the support plate 405 drives the second connecting tube 9 to move, the second connecting tube 9 is separated from the first connecting rod 8, the rudder surface 7 is held and pulled, the rudder surface 9 drives the second connecting rod 10 to move, the second connecting rod 10 is separated from the first connecting tube 305, the rudder surface 7 is disassembled and replaced, and when the rudder surface is worn, it is convenient to replace the rudder surface 7.

[0029] Working principle:

[0030] When the control surface linkage structure of the unmanned aerial vehicle is in use, the main body 1 flies under the action of the external controller;

[0031] Rudder angle adjustment stage:

[0032] When the inclination angle of the rudder surface 7 needs to be adjusted, the motor 301 is started, the motor 301 drives the worm 302 to rotate, the worm 302 drives the worm wheel 303 to rotate, the worm wheel 303 drives the rotating rod 304 to rotate, the rotating rod 304 drives the two first connecting cylinders 305 to rotate, the first connecting cylinders 305 drive the second connecting rod 10 to rotate, the second connecting rod 10 drives the rudder surface 7 to rotate to adjust the inclination angle of the rudder surface 7, and the motor 301 is turned off after adjusting to the required angle. The worm 302 and the worm wheel 303 have a self-locking function, and the inclination angle of the rudder surface 7 will not change when the motor 301 is not started, so that the angle of the rudder surface 7 can be easily fixed after the rudder surface 7 rotates to the required angle.

[0033] Rudder replacement stage:

[0034] When the rudder surface 7 is worn out after long-term use and needs to be replaced, the handle 402 corresponding to the rudder surface 7 that needs to be replaced is turned, the handle 402 drives the screw rod 401 to rotate, the screw rod 401 drives the threaded block 403 to slide, the threaded block 403 drives the connecting rod 404 to move, the connecting rod 404 drives the support plate 405 to move, the support plate 405 drives the second connecting tube 9 to move, the second connecting tube 9 is separated from the first connecting rod 8, the rudder surface 7 is held and pulled, the rudder surface 9 drives the second connecting rod 10 to move, the second connecting rod 10 is connected to the first connecting rod 8, The rudder surface 7 is disassembled and replaced by the first connecting tube 305, and the second connecting rod 10 corresponding to the replaced rudder surface 7 is inserted into the first connecting tube 305. The handle 402 is rotated in the opposite direction, and the second connecting tube 9 is moved in the opposite direction to be sleeved on the outer wall of the first connecting rod 8. The replacement of the rudder surface 7 is completed. When the rudder surface is worn out, it is convenient to replace the rudder surface 7. The locking bolt 6 corresponding to the upper part of the threaded block 403 is rotated, and the end of the locking bolt 6 is fitted with the threaded block 403 to tighten the threaded block 403 to prevent the second connecting tube 9 from being separated from the first connecting rod.

[0035] Although the present utility model has been illustrated and described with reference to the preferred embodiments, those skilled in the art should understand that various changes in form and detail may be made within the scope of the claims.

Claims

1. A control surface linkage structure of an unmanned aerial vehicle, comprising a main body (1) and a frame (2), wherein the frame (2) is fixedly connected to the lower side of the main body (1), and characterized in that: A linkage mechanism (3) is arranged inside the frame (2); a bracket (5) is fixedly connected to the surface of the main body (1); a disassembly mechanism (4) is arranged inside the bracket (5); a locking screw (6) is threadedly connected to the inside of the bracket (5); a rudder surface (7) is arranged below the main body (1); a first connecting rod (8) is fixedly connected to the left side of the rudder surface (7).

2. The control surface linkage structure of an unmanned aerial vehicle according to claim 1, characterized in that: The linkage mechanism (3) comprises a motor (301), the motor (301) is fixedly connected to the upper surface of the frame (2), the output shaft of the motor (301) is fixedly connected to a worm (302), the outer walls at both ends of the worm (302) are rotatably connected to the frame (2) via bearings, the worm (302) is meshedly connected to a worm wheel (303), the worm wheel (303) is fixedly connected to the outer wall of a rotating rod (304), the outer walls at both ends of the rotating rod (304) are rotatably connected to the frame (2) via bearings, and the first connecting tube (305) is fixedly connected to both ends of the rotating rod (304).

3. The control surface linkage structure of an unmanned aerial vehicle according to claim 1, characterized in that: The disassembly mechanism (4) comprises a screw rod (401), the outer walls at both ends of the screw rod (401) are rotatably connected to the bracket (5) via bearings, a handle (402) is fixedly connected to the end of the screw rod (401), a threaded block (403) is threadedly connected to the outer wall of the screw rod (401), the outer wall of the threaded block (403) is slidably connected to the bracket (5), a connecting rod (404) is fixedly connected to the outer wall of the threaded block (403), and a support plate (405) is fixedly connected to the end of the connecting rod (404).

4. The control surface linkage structure of an unmanned aerial vehicle according to claim 3, characterized in that: The interior of the support plate (405) is rotatably connected to a second connecting tube (9) via a bearing, and the second connecting tube (9) is clearance-matched with the outer wall of the first connecting rod (8).

5. The control surface linkage structure of an unmanned aerial vehicle according to claim 2, characterized in that: The internal clearance of the first connecting tube (305) is matched with a second connecting rod (10), and the second connecting rod (10) is fixedly connected to the right end of the rudder surface (7).

6. The control surface linkage structure of an unmanned aerial vehicle according to claim 1, characterized in that: A groove (11) is provided inside the main body (1).

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