Rotor shaft active tilting type wind disturbance resisting structure of coaxial dual-rotor unmanned aerial vehicle

Abstract

The invention provides a rotor shaft active tilting type wind disturbance resisting structure of a coaxial dual-rotor unmanned aerial vehicle, and relates to the technical field of coaxial dual-rotor unmanned aerial vehicles. The rotor shaft active tilting type wind disturbance resisting structure of the coaxial double-rotor unmanned aerial vehicle comprises an unmanned aerial vehicle body and a supporting and adjusting device, a driving motor is arranged at the center of the upper end face of the unmanned aerial vehicle body, and a wind resisting structure is arranged at the center of the outer side of the driving motor in a sleeving mode and comprises a bearing sleeve; and the bearing sleeve is arranged at the center of the outer side of the driving motor in a sleeving mode, the center of the outer side of the bearing sleeve is sleeved with a fixed shell, and conical blocks are arranged at the centers of the two sides of the fixed shell correspondingly. According to the wind-resistant unmanned aerial vehicle, through the wind speed in the environment and the acting force during flight, the requirement that the conical block is rotationally adjusted according to different flight directions and wind speed orientations can be met, then the conical block guides airflow so that the direct impact of wind power on the unmanned aerial vehicle can be reduced, and therefore the wind-resistant capacity of the unmanned aerial vehicle is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of coaxial twin-rotor UAVs, and in particular to a coaxial twin-rotor UAV rotor shaft active tilting anti-wind disturbance structure. Background Art

[0002] In the field of drone technology, coaxial twin-rotor drones have gradually become an important branch of drone applications due to their unique structural design and excellent flight performance. Coaxial twin-rotor drones can not only provide strong lift through the opposite rotation of the upper and lower rotors, but also effectively offset the rotational torque, thereby improving flight stability.

[0003] In the use of existing coaxial twin-rotor UAVs, current UAVs often face complex and changeable wind field environments, especially under strong wind conditions, which will seriously affect the flight stability and controllability of the UAV, and may even cause the flight mission to fail, making it difficult to ensure flight stability, thereby reducing the UAV's wind resistance. Therefore, technical personnel in this field provide a coaxial twin-rotor UAV rotor shaft active tilting anti-wind disturbance structure to solve the problems raised in the above background technology. Summary of the Invention

[0004] (1) Technical problems solved

[0005] In response to the shortcomings of the existing technology, the present invention provides a coaxial twin-rotor UAV rotor shaft active tilting anti-wind disturbance structure, which solves the problem that current UAVs are often faced with complex and changeable wind field environments, especially in strong wind conditions, which seriously affect the flight stability and controllability of the UAV, and may even cause the flight mission to fail, making it difficult to ensure flight stability, thereby reducing the UAV's wind resistance.

[0006] (2) Technical solution

[0007] To achieve the above objectives, the present invention is implemented through the following technical solutions: a coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure, comprising a UAV body and a support adjustment device, the support adjustment device being arranged at the center of the lower end surface of the UAV body, a drive motor being arranged at the center of the upper end surface of the UAV body, and a wind resistance structure being sleeved at the center of the outer side of the drive motor;

[0008] The wind-resistant structure includes a bearing sleeve, which is sleeved on the outer center of the driving motor. A fixed shell is sleeved on the outer center of the bearing sleeve. Cone blocks are provided at the centers of both sides of the fixed shell. The bearing sleeve satisfies the rotation of the fixed shell and the cone block. During the flight of the UAV, the wind speed in the environment and the force during flight are used to rotate the cone block according to different flight directions and wind speed directions. The airflow is then guided by the cone block, which reduces the direct impact of wind on the UAV, ensures flight stability, and thus improves the UAV's wind resistance.

[0009] Preferably, the bearing sleeve is rotationally connected to the outer side of the driving motor via a bearing, and the bearing sleeve is rotationally connected to the driving motor via a bearing, so that the rotation requirement of the cone block is met.

[0010] Preferably, the support adjustment device includes six support rods, and the six support rods are divided into three groups. The support rods in one group are arranged at one side of the center of the lower end surface of the drone body, and the support rods in the three groups are arranged in a triangular shape at the lower end surface of the drone body. The two support rods in one group are arranged in parallel, and a rotating shaft is provided at the center between the two support rods in each group. A rotating motor is provided at the center of one side of the support rods in each group. The output ends of the three rotating motors are fixedly connected to the ends of the three rotating shafts respectively, and the outer centers of the three rotating shafts are fixedly connected to support legs. A fixed plate is provided at the center of the lower end surface of the drone body, and the rotating motor drives the rotating shaft to rotate, and then the rotating shaft drives the support legs to rotate and adjust, so that the angle of the support legs can be adjusted according to the take-off and landing requirements of the drone body. During flight, the support legs can be retracted, which can reduce the overall wind resistance of the drone and avoid affecting the flight stability of the drone when it is extended, thereby improving the support flexibility.

[0011] Preferably, three sleeves are arranged in a triangle at the center of the lower end surface of the fixed plate, and the three sleeves are respectively connected to the ends of the three supporting legs, and the three ends of the supporting legs are respectively connected to the upper inner walls of the three sleeves by electromagnetic blocks. The sleeve connection between the supporting legs and the sleeves meets the requirements of the supporting legs, and the support legs and the sleeves are then connected by electromagnetic blocks to ensure fixation after the supporting legs are recovered, thereby avoiding the shaking of the drone during flight and causing it to unfold.

[0012] Preferably, a rotor main shaft is provided at the output end of the driving motor, and a casing is provided at the upper and lower centers on both sides of the rotor main shaft. A connecting device is provided at the center of one side of the four casings, and an upper rotor is sleeved at the inner center of the two upper connecting devices, and a lower rotor is sleeved at the inner center of the two lower connecting devices. The upper rotor and the lower rotor are fixed respectively by the connecting device, and then the rotor main shaft is driven to rotate by the driving motor, and then the rotor main shaft is used to drive the upper rotor and the lower rotor to rotate in opposite directions, which can effectively offset the rotational torque, reduce air turbulence and eddy currents, and improve lift efficiency.

[0013] Preferably, the four connecting devices include four slots, which are respectively arranged on one side wall of the four casings, and a circular groove is provided at the front and back upper and lower centers of the inner side walls of the four slots, and a micromotor is provided at the center of the inner side walls of multiple circular grooves, and a screw is provided at the output end of multiple micromotors. One end of the two upper rotors and the two lower rotors is respectively sleeved inside the four slots, and a threaded hole is provided at the front and back upper and lower centers of one side wall of the two upper rotors and the two lower rotors. The lower end surfaces of the two upper casings and the upper ends of the two lower casings are provided with screws. There are bolts on one side of the center of the end face, near the front and rear. The two bolts pass through the casing and the upper rotor and the lower rotor in turn to the inside of the upper rotor and the lower rotor, and are respectively sleeved in the slots through the upper rotor and the lower rotor. The screw is driven to rotate by a micromotor, so that the screw thread is sleeved in the threaded hole, and then the bolts pass through, so that the upper rotor and the lower rotor can be quickly installed and uninstalled, which is convenient for the staff to install, unload, inspect and replace them. The operation is simple, which greatly reduces the maintenance time, thereby improving the availability of the UAV and the mission execution efficiency.

[0014] Preferably, the four screw rods are respectively arranged corresponding to the four threaded holes and are threadedly sleeved with the four threaded holes. By respectively setting the screw rods corresponding to the four threaded holes and being threadedly sleeved with the four threaded holes, the upper rotor and the lower rotor are fixed.

[0015] Preferably, a rotating device is provided at the outer center of the rotor main shaft, and elastic connecting rings are provided at the upper and lower parts of the outer center. The outer walls of the two elastic connecting rings are fixedly connected to the four casings respectively. The rotating device enables the upper rotor and the lower rotor to rotate in opposite directions, so that it can effectively offset the rotational torque, reduce air turbulence and eddy currents, and improve lift efficiency. The elastic connecting ring is then used to ensure the elastic connection between the casing and the rotor main shaft, and the casing can be adjusted to drive the upper rotor and the lower rotor to tilt, thereby improving the overall anti-wind disturbance performance.

[0016] Preferably, grooves are provided at the front and rear centers of the upper and lower inner walls of the rotor main shaft, and micro-telescopic rods are provided at the centers of the eight grooves. Rubber pads are provided at the output ends of the eight micro-telescopic rods. The grooves are used to fix the micro-telescopic rods, and the micro-telescopic rods are used to push the shell so that the rubber pads and the elastic connecting rings can be squeezed, thereby achieving angle adjustment of the shell and the angle adjustment of the upper and lower rotors, thereby achieving a tilting effect and reducing the impact of wind disturbance on the flight of the drone.

[0017] (3) Beneficial effects

[0018] The present invention provides a coaxial dual-rotor UAV rotor shaft active tilting anti-wind disturbance structure, which has the following beneficial effects:

[0019] 1. In the present invention, when the active tilting anti-wind disturbance structure of the rotor shaft of a coaxial twin-rotor UAV is used, the rotation of the fixed shell and the cone block is satisfied through the bearing sleeve. During the flight of the UAV, the wind speed in the environment and the force during flight are used to adjust the rotation of the cone block according to different flight directions and wind speed directions. The airflow is then guided by the cone block, which reduces the direct impact of the wind on the UAV, ensures flight stability, and thus improves the UAV's wind resistance.

[0020] 2. In the present invention, the upper rotor and the lower rotor are respectively sleeved inside the slots, and the micromotor drives the screw to rotate, so that the screw thread is sleeved inside the threaded hole, and then the bolt is penetrated to meet the requirements of rapid assembly and disassembly of the upper rotor and the lower rotor, which is convenient for the staff to load, unload, repair and replace them. The operation is simple, which greatly reduces the maintenance time, thereby improving the availability of the UAV and the mission execution efficiency.

[0021] 3. In the present invention, the rotating shaft is driven to rotate by a rotating motor, and the rotation of the rotating shaft drives the support legs to rotate and adjust, so that the angle of the support legs can be adjusted according to the take-off and landing requirements of the UAV body. During the flight, the support legs and the sleeves are adsorbed and connected by electromagnetic blocks, so that the support legs can be retracted and fixed, and the overall wind resistance of the UAV can be reduced, avoiding affecting the flight stability of the UAV when the legs are extended, thereby improving the support flexibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A perspective view of the present invention;

[0023] Figure 2 This is a three-dimensional diagram of the support and adjustment device of the present invention after closing;

[0024] Figure 3 is a cross-sectional view of the present invention;

[0025] Figure 4 for Figure 3 A magnified schematic diagram of point A in the middle;

[0026] Figure 5 for Figure 3 A magnified schematic diagram of point B in the middle;

[0027] Figure 6 for Figure 3 Enlarged schematic diagram of point C in the middle.

[0028] Among them, 1. UAV body; 2. Support and adjustment device; 201. Support rod; 202. Rotating shaft; 203. Rotating motor; 204. Support leg; 205. Fixed plate; 206. Sleeve; 3. Drive motor; 4. Wind-resistant structure; 401. Bearing sleeve; 402. Fixed shell; 403. Cone block; 5. Rotor main shaft; 6. Sleeve; 7. Connecting device; 701. Slot; 702. Circular groove; 703. Micro motor; 704. Screw; 705. Threaded hole; 706. Bolt; 8. Upper rotor; 9. Lower rotor; 10. Rotating device; 11. Elastic connecting ring; 12. Groove; 13. Micro telescopic rod; 14. Rubber pad. DETAILED DESCRIPTION

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0030] Example 1:

[0031] like Figure 1-6 As shown, an embodiment of the present invention provides an active tilting anti-wind disturbance structure for the rotor shaft of a coaxial twin-rotor UAV, comprising a UAV body 1 and a support and adjustment device 2, the support and adjustment device 2 being arranged at the center of the lower end surface of the UAV body 1, a drive motor 3 being provided at the center of the upper end surface of the UAV body 1, and a wind-resistant structure 4 being sleeved at the center of the outer side of the drive motor 3.

[0032] The wind-resistant structure 4 includes a bearing sleeve 401, which is sleeved on the outer center of the driving motor 3. A fixed shell 402 is sleeved on the outer center of the bearing sleeve 401. Cone blocks 403 are provided at the centers of both sides of the fixed shell 402. The bearing sleeve 401 satisfies the rotation of the fixed shell 402 and the cone block 403. During the flight of the UAV, the wind speed in the environment and the force during flight are used to rotate the cone block 403 according to different flight directions and wind speed directions. The airflow is then guided by the cone block 403, which reduces the direct impact of wind on the UAV, ensures flight stability, and thus improves the wind resistance of the UAV.

[0033] The bearing sleeve 401 is rotatably connected to the outer side of the driving motor 3 via a bearing, and the rotation requirement of the cone block 403 is met through the rotatable connection between the bearing sleeve 401 and the driving motor 3 via a bearing.

[0034] A rotor main shaft 5 is provided at the output end of the drive motor 3, and a casing 6 is provided at the upper and lower centers on both sides of the rotor main shaft 5. A connecting device 7 is provided at the center of one side of the four casings 6. The upper rotor 8 is sleeved at the center of the two connecting devices 7 at the upper end, and the lower rotor 9 is sleeved at the center of the two connecting devices 7 at the lower end. The upper rotor 8 and the lower rotor 9 are fixed respectively by the connecting device 7, and then the rotor main shaft 5 is driven to rotate by the drive motor 3, and then the rotor main shaft 5 is used to drive the upper rotor 8 and the lower rotor 9 to rotate in opposite directions, which can effectively offset the rotational torque, reduce air turbulence and eddy currents, and improve lift efficiency.

[0035] The four connecting devices 7 include four slots 701, which are respectively arranged on the side walls of the four casings 6. A circular groove 702 is provided at the front and back upper and lower centers of the inner wall of the four slots 701. A micro motor 703 is provided at the center of the inner wall of the multiple circular grooves 702. A screw 704 is provided at the output end of the multiple micro motors 703. One end of the two upper rotors 8 and the two lower rotors 9 is respectively sleeved inside the four slots 701. A threaded hole 705 is provided at the front and back upper and lower centers of the side walls of the two upper rotors 8 and the two lower rotors 9. The center side of the lower end surface of the two upper casings 6 and the upper end surface of the two lower casings 6 is provided. Bolts 706 are provided at the front and rear ends. The two bolts 706 respectively penetrate the casing 6 and the upper rotor 8 and the lower rotor 9 in turn to reach the interior of the upper rotor 8 and the lower rotor 9. The upper rotor 8 and the lower rotor 9 are respectively sleeved in the interior of the slot 701, and then the micromotor 703 drives the screw 704 to rotate, so that the screw 704 is threadedly sleeved in the threaded hole 705. Then, the bolts 706 penetrate, so that the upper rotor 8 and the lower rotor 9 can be quickly assembled and disassembled, which is convenient for the staff to load, unload, inspect and replace them. The operation is simple, which greatly reduces the maintenance time, thereby improving the availability and mission execution efficiency of the UAV.

[0036] The four screw rods 704 are respectively arranged corresponding to the four threaded holes 705 and are threadedly connected to the four threaded holes 705. By setting the four screw rods 704 corresponding to the four threaded holes 705 and threadedly connected to the four threaded holes 705, the upper rotor 8 and the lower rotor 9 are fixed.

[0037] A rotating device 10 is provided at the outer center of the rotor main shaft 5, and elastic connecting rings 11 are provided at the upper and lower parts of the outer center. The outer walls of the two elastic connecting rings 11 are fixedly connected to the four sleeves 6 respectively. The rotating device 10 enables the upper rotor 8 and the lower rotor 9 to rotate in opposite directions, so that they can effectively offset the rotational torque, reduce air turbulence and eddy currents, and improve lift efficiency. The elastic connecting rings 11 then satisfy the elastic connection between the sleeve 6 and the rotor main shaft 5, and the adjustable sleeve 6 drives the upper rotor 8 and the lower rotor 9 to tilt, thereby improving the overall anti-wind disturbance performance.

[0038] Grooves 12 are provided at the front and rear centers of the upper and lower inner walls of the rotor main shaft 5, and micro telescopic rods 13 are provided at the centers of the eight grooves 12. Rubber pads 14 are provided at the output ends of the eight micro telescopic rods 13. The grooves 12 are used to fix the micro telescopic rods 13, and then the micro telescopic rods 13 push the shell 6 to squeeze the rubber pads 14 and the elastic connecting ring 11, thereby realizing the angle adjustment of the shell 6 and the angle adjustment of the upper rotor 8 and the lower rotor 9, achieving its tilting effect and reducing the impact of wind disturbance on the flight of the drone.

[0039] Example 2:

[0040] This embodiment is based on the first embodiment:

[0041] The support adjustment device 2 includes six support rods 201, and the six support rods 201 are divided into three groups. One group of support rods 201 is arranged at one side of the center of the lower end surface of the drone body 1. The three groups of support rods 201 are arranged in a triangular shape at the lower end surface of the drone body 1. A group of two support rods 201 are arranged in parallel. A rotating shaft 202 is provided at the center between the two support rods 201 of each group. A rotating motor 203 is provided at the center of one side of the support rod 201 of each group. The output ends of the three rotating motors 203 are fixedly connected to the ends of the three rotating shafts 202 respectively. The center of the outer side of the shaft 202 is fixedly connected to the support leg 204, and the center of the lower end surface of the drone body 1 is provided with a fixed plate 205. The rotating shaft 202 is driven to rotate by the rotating motor 203, and the rotation of the rotating shaft 202 drives the support leg 204 to rotate and adjust, so that the angle of the support leg 204 can be adjusted according to the take-off and landing requirements of the drone body 1. During the flight, the support leg 204 can be retracted, which can reduce the overall wind resistance of the drone and avoid affecting the flight stability of the drone when it is extended, thereby improving the support flexibility.

[0042] Three sleeves 206 are arranged in a triangle at the center of the lower end surface of the fixing plate 205. The three sleeves 206 are respectively connected to the ends of the three supporting legs 204. The ends of the three supporting legs 204 are respectively connected to the upper inner walls of the three sleeves 206 by electromagnetic blocks. The sleeve connection between the supporting legs 204 and the sleeves 206 meets the requirements of the supporting legs 204. The support legs 204 and the sleeves 206 are then connected to each other by electromagnetic blocks, so that the support legs 204 are fixed after they are recovered, thereby preventing the drone from shaking during flight and causing it to unfold.

[0043] Working principle: When the active tilt-type anti-wind disturbance structure of the coaxial twin-rotor UAV rotor shaft is in use, the upper rotor 8 and the lower rotor 9 are respectively sleeved inside the slot 701, and then the micro motor 703 drives the screw 704 to rotate, so that the screw 704 is threadedly sleeved inside the threaded hole 705, and then the bolt 706 is penetrated to meet the needs of rapid assembly and disassembly of the upper rotor 8 and the lower rotor 9, which is convenient for the staff to load, unload, inspect and replace them. The operation is simple, which greatly reduces maintenance time, thereby improving the availability of the UAV and the efficiency of mission execution.

[0044] The rotating motor 203 drives the rotating shaft 202 to rotate, and the rotating shaft 202 drives the supporting legs 204 to rotate and adjust, so that the angle of the supporting legs 204 can be adjusted according to the take-off and landing requirements of the drone body 1. During the flight, the supporting legs 204 can be retracted, which can reduce the overall wind resistance of the drone and avoid affecting the flight stability of the drone when it is extended, thereby improving the support flexibility.

[0045] The upper rotor 8 and the lower rotor 9 are fixed respectively by the connecting device 7, and then the rotor main shaft 5 is driven to rotate by the driving motor 3. Then, the upper rotor 8 and the lower rotor 9 are rotated in opposite directions by the rotating device 10, so that they can effectively offset the rotational torque, reduce air turbulence and eddy currents, and improve lift efficiency. Then, the elastic connection between the casing 6 and the rotor main shaft 5 is satisfied by the elastic connecting ring 11, and the casing 6 is adjustable to drive the upper rotor 8 and the lower rotor 9 to tilt, thereby improving the overall anti-wind disturbance performance.

[0046] When the UAV is flying, the bearing sleeve 401 satisfies the rotation of the fixed shell 402 and the cone block 403. During the flight of the UAV, the wind speed in the environment and the force during flight enable the cone block 403 to be rotated and adjusted according to different flight directions and wind speed directions. The airflow is then guided by the cone block 403, reducing the direct impact of the wind on the UAV, ensuring flight stability, and thus improving the UAV's wind resistance.

[0047] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A coaxial twin-rotor unmanned aerial vehicle (UAV) rotor shaft active tilting anti-wind disturbance structure, comprising an UAV body (1) and a support adjustment device (2), wherein the support adjustment device (2) is arranged at the center of the lower end surface of the UAV body (1), and is characterized in that: A driving motor (3) is provided at the center of the upper end surface of the drone body (1), and a wind-resistant structure (4) is sleeved at the center of the outer side of the driving motor (3); The wind-resistant structure (4) comprises a bearing sleeve (401), the bearing sleeve (401) being sleeved at the center of the outer side of the driving motor (3), a fixed housing (402) being sleeved at the center of the outer side of the bearing sleeve (401), and cone blocks (403) being provided at the centers of both sides of the fixed housing (402).

2. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 1, characterized in that: The bearing sleeve (401) is rotatably connected to the outer side of the drive motor (3) via a bearing.

3. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 1, characterized in that: The support adjustment device (2) comprises six support rods (201), and the six support rods (201) are respectively divided into three groups. One group of support rods (201) is arranged at one side of the center of the lower end surface of the drone body (1). The three groups of support rods (201) are respectively arranged in a triangular arrangement at the lower end surface of the drone body (1). Two support rods (201) in a group are arranged in parallel. A rotating shaft (202) is provided at the center between the two support rods (201) in each group. A rotating motor (203) is provided at the center of one side of the support rods (201) in each group. The output ends of the three rotating motors (203) are respectively fixedly connected to the ends of the three rotating shafts (202). The outer centers of the three rotating shafts (202) are fixedly connected to support legs (204). A fixing plate (205) is provided at the center of the lower end surface of the drone body (1).

4. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 3, characterized in that: Three sleeve grooves (206) are arranged in a triangular pattern at the center of the lower end surface of the fixed plate (205), and the three sleeve grooves (206) are respectively sleeved and connected to the ends of the three support legs (204), and the ends of the three support legs (204) are respectively connected to the upper inner walls of the three sleeve grooves (206) through electromagnetic blocks.

5. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 1, characterized in that: A rotor main shaft (5) is provided at the output end of the driving motor (3), and casings (6) are provided at the upper and lower centers of both sides of the rotor main shaft (5). Connecting devices (7) are provided at the centers of one side of the four casings (6), and upper rotors (8) are provided at the centers of the two upper connecting devices (7), and lower rotors (9) are provided at the centers of the two lower connecting devices (7).

6. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 5, characterized in that: The four connecting devices (7) include four slots (701), the four slots (701) are respectively arranged on the side walls of the four housings (6), a circular groove (702) is provided at the center of the inner side wall of the four slots (701) at the front and back sides and the upper and lower sides, a micro motor (703) is provided at the center of the inner side wall of the plurality of circular grooves (702), a screw (704) is provided at the output end of the plurality of micro motors (703), one end of the two upper rotors (8) and the two lower rotors (9) The parts are respectively sleeved inside the four slots (701), and threaded holes (705) are provided at the front and back upper and lower positions of the center of one side wall of the two upper rotors (8) and the two lower rotors (9), and bolts (706) are provided at the front and back positions of the center of one side of the lower end surface of the two upper casings (6) and the upper end surface of the two lower casings (6). The two bolts (706) respectively penetrate the casing (6) and the upper rotor (8) and the lower rotor (9) in sequence and pass into the interior of the upper rotor (8) and the lower rotor (9).

7. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 6, characterized in that: The four screw rods (704) are respectively arranged corresponding to the four threaded holes (705) and are threadedly sleeved with the four threaded holes (705).

8. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 5, characterized in that: A rotating device (10) is provided at the outer center of the rotor main shaft (5), and elastic connecting rings (11) are provided at the upper and lower parts of the outer center. The outer side walls of the two elastic connecting rings (11) are fixedly connected to the four casings (6) respectively.

9. The coaxial twin-rotor UAV rotor shaft active tilting wind disturbance resistant structure according to claim 5, characterized in that: Grooves (12) are provided at the front and rear centers of the upper and lower inner walls of the rotor main shaft (5); miniature telescopic rods (13) are provided at the centers of the eight grooves (12); and rubber pads (14) are provided at the output ends of the eight miniature telescopic rods (13).

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