Multipurpose amphibious unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multipurpose amphibious unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a support and a connecting frame, and a supporting mechanism is mounted on the connecting frame; the flying mechanism is mounted on the bracket and comprises a flying part and a heat dissipation part; an air pump is installed at the bottom of the unmanned aerial vehicle body, and the exhaust end of the air pump is connected with an air conveying pipe. Wherein the supporting mechanism comprises an outer cylinder, the outer cylinder is installed on the connecting frame, inner cylinders are slidably connected to the two ends of the outer cylinder in an inserted mode, a control part is installed between the two inner cylinders, buoyancy parts are installed at the front end and the rear end of each inner cylinder, and limiting grooves are annularly distributed in the inner wall of the outer cylinder; through holes are further formed in the two ends of the limiting groove, and a blocking part is arranged on the inner cylinder. The unmanned aerial vehicle can show remarkable advantages in the aspects of improving flight efficiency, enhancing waterproof protection, improving use convenience and adaptability and the like.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a multi-purpose amphibious unmanned aerial vehicle. Background Art

[0002] In today's society, drone technology is widely used in agriculture, forestry, environmental monitoring, rescue, film and television shooting and other fields due to its high efficiency and flexibility. However, most traditional drone designs are only for aerial flight, and their application scope is limited to a certain extent, especially in water environments. Therefore, it is particularly important to develop a multi-purpose amphibious drone that can both stably fly in the air and safely land and float on the water.

[0003] There are also many types of amphibious drones in the prior art, such as a multi-purpose take-off and landing device and a drone including the multi-purpose take-off and landing device with application number: CN202123428292.3; the drone has a simple structure and is easy to install. It adopts a support component to achieve support and connection, and a sleeve to achieve floating on the water surface. It is suitable for drones of different specifications, so that the drone can be used both in water and on land.

[0004] Another example is the amphibious UAV with application number: CN201721582530.7. The sealed buoys on the UAV can be quickly installed and disassembled, making the UAV amphibious. When the UAV is used on the water surface, the sealed buoys are installed and filled with gas, so that it can take off and land safely on the water surface to prevent sinking to the bottom of the water. When flying on land, the sealed buoys can be quickly removed to reduce the additional load of the UAV.

[0005] However, in actual application, the above-mentioned drone adopts a fixed buoy structure. Although this design can achieve a good floating effect on the water surface, it brings huge wind resistance during flight. The existence of this wind resistance will undoubtedly have a negative impact on the flight efficiency and stability of the drone, thereby affecting the overall use; in addition, the lack of waterproof protection for internal mechanical and electronic components may cause damage to the drone once splashed during takeoff and landing on the water. Summary of the invention

[0006] The purpose of the present invention is to provide a multi-purpose amphibious UAV that can show significant advantages in improving flight efficiency, enhancing waterproof protection, and improving ease of use and adaptability.

[0007] The technical solution adopted by the present invention is as follows:

[0008] A multi-purpose amphibious UAV comprises a UAV body, wherein four corners of the UAV body are provided with brackets;

[0009] A flying mechanism, which is mounted on a bracket and includes a flying part and a heat dissipation part;

[0010] A connecting frame, the connecting frame is connected to the bottom surface of the drone body, and a supporting mechanism is installed on the connecting frame;

[0011] An air pump is installed at the bottom of the drone body, an exhaust end of the air pump is connected to an air pipe, and the air pipe is connected to the support mechanism;

[0012] Among them, the supporting mechanism includes an outer cylinder, which is installed on a connecting frame, and inner cylinders are slidably inserted at both ends of the outer cylinder, a control part is installed between the two inner cylinders, and a buoyancy part is installed at the front and rear ends of each inner cylinder. The inner wall of the outer cylinder is provided with limiting grooves in an annular shape, and through holes are also provided at both ends of the limiting grooves. A sealing part is provided on the inner cylinder, and the sealing part is slidably arranged in the limiting groove.

[0013] In a preferred embodiment, the flying part includes a shell, the shell is connected to a bracket, a driving motor is installed inside the shell, and a rotor is installed on an output shaft of the driving motor.

[0014] In a preferred embodiment, the heat dissipation part includes a heat dissipation groove and a slide groove, and the heat dissipation groove and the slide groove are both opened on the outer shell. A hollow ring is slidably connected in the slide groove, and an annular baffle is fixedly connected to one side of the hollow ring. A first spring is arranged between the hollow ring and the slide groove, and a round rod is fixedly connected to the other side of the hollow ring, and the lower end of the round rod passes through the outer shell, and the lower end of the round rod is fixedly connected to the base.

[0015] In a preferred embodiment, the control unit includes a bidirectional electric push rod, which is installed between two inner cylinders and fixedly connected to the inner wall of the outer cylinder by a support rod. A sleeve is also provided between the two inner cylinders, and telescopic rods are slidably inserted at both ends of the sleeve, and one end of the telescopic rod is fixedly connected to the inner cylinder. A second spring is sleeved on one end of the telescopic rod, and one end of the second spring is fixedly connected to the inner cylinder, and the other end is fixedly connected to the sleeve.

[0016] In a preferred embodiment, the buoyancy part includes a first hollow cylinder, which is fixedly embedded in an inner cylinder, a second hollow cylinder is piston-connected in the first hollow cylinder, a third hollow cylinder is piston-connected in the second hollow cylinder, a first tension spring is fixedly connected between the first hollow cylinder and the second hollow cylinder, a second tension spring is fixedly connected to the third hollow cylinder, and an inner wall of the inner cylinder is fixedly connected to a support plate by a support rod, and the support plate is fixedly connected to the second tension spring.

[0017] In a preferred embodiment, the sealing portion includes a movable groove, which is opened on the inner cylinder, a movable block is inserted into the movable groove, a compression spring is fixedly connected between the movable block and the movable groove, a sealing block is fixedly connected to one side of the movable block, and a rubber pad is arranged on one surface of the sealing block.

[0018] In a preferred embodiment, trapezoidal protrusions are provided at both ends of the limiting groove, and balls are provided in an array on the inner wall of the limiting groove.

[0019] In a preferred embodiment, an annular sealing ring is provided at one end of the inner cylinder, and annular sealing grooves are provided at both ends of the outer cylinder.

[0020] In a preferred embodiment, a shock-absorbing pad is provided at the lower end of the outer tube, and anti-slip grooves are provided on the bottom surface of the shock-absorbing pad.

[0021] The technical effects achieved by the present invention are:

[0022] The present invention adopts a retractable buoy design, which enables the drone to reduce the volume of the buoy during flight and reduce wind resistance, thereby effectively improving flight efficiency and stability. In flight, the inner tube is retracted inside the outer tube, reducing air resistance and enabling the drone to fly more efficiently in the air. When it is necessary to land on the water, the volume of the buoy can be quickly increased by controlling the extension of the buoyancy part, ensuring that the drone lands smoothly on the water without affecting flight stability.

[0023] When the UAV lands on the water, the hollow ring moves upward through the change of the pulling force of the traction rope on the base and the reset force of the spring, driving the annular baffle to move upward, closing the heat dissipation slot, and effectively preventing the splashes stirred up during landing from entering the shell and causing damage to key components such as the drive motor. This design not only protects the internal mechanical and electronic components from water damage, but also ensures the normal use of the UAV after landing on the water, enhancing the reliability of the UAV;

[0024] The amphibious UAV provided by the present invention can not only fly stably in the air, but also land and float safely on the water surface, which greatly broadens the application scope of the UAV. Whether it is water rescue, water surface environment monitoring or other water operations, it can be competent. In addition, the conversion between the two environments of air and water surface can be realized through simple operation, which greatly improves the flexibility and practicality of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0026] Figure 2 is a front sectional view of the support mechanism of the present invention;

[0027] Figure 3 is a side sectional view of the support mechanism of the present invention;

[0028] Figure 4 The present invention Figure 3 An enlarged schematic diagram of part A shown in FIG.

[0029] Figure 5 It is a schematic diagram of the structure inside the outer cylinder of the present invention;

[0030] Figure 6 It is a structural schematic diagram of the buoyancy part of the present invention;

[0031] Figure 7 It is a schematic diagram of the internal structure of the first hollow cylinder of the present invention;

[0032] Figure 8 It is a structural schematic diagram of the flight mechanism of the present invention;

[0033] Fig. 9 It is a schematic diagram of the internal structure of the shell of the present invention.

[0034] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0035] 1. UAV body; 2. Bracket; 3. Flight mechanism; 4. Connecting frame; 5. Support mechanism; 6. Air pump; 7. Air pipe;

[0036] 31. Flight unit; 32. Heat dissipation unit;

[0037] 311. housing; 312. drive motor; 313. rotor;

[0038] 321, heat dissipation groove; 322, slide groove; 323, hollow ring; 324, annular baffle; 325, first spring; 326, round rod; 327, base;

[0039] 51. outer tube; 52. inner tube; 53. control part; 54. buoyancy part; 55. limit groove; 56. through hole; 57. blocking part; 58. annular sealing ring; 59. annular sealing groove;

[0040] 531, bidirectional electric push rod; 532, sleeve; 533, telescopic rod; 534, second spring;

[0041] 541, first hollow tube; 542, second hollow tube; 543, third hollow tube; 544, first tension spring; 545, second tension spring; 546, support plate;

[0042] 571. Movable groove; 572. Movable block; 573. Compression spring; 574. Sealing block. DETAILED DESCRIPTION

[0043] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0044] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0045] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The phrase "in a preferred embodiment" that appears in different places in this specification does not refer to the same embodiment, nor is it a separate or selective embodiment that is mutually exclusive with other embodiments.

[0046] Secondly, the present invention is described in detail with reference to the schematic diagram. When describing the embodiments of the present invention in detail, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0047] Please see attached Figure 1-Figure 9 As shown, this embodiment provides a multi-purpose amphibious UAV, including a UAV body 1, and brackets 2 are installed at the four corners of the UAV body 1;

[0048] The flying mechanism 3 is installed on the bracket 2 and includes a flying part 31 and a heat dissipation part 32;

[0049] A connecting frame 4, the connecting frame 4 is connected to the bottom surface of the drone body 1, and a supporting mechanism 5 is installed on the connecting frame 4;

[0050] An air pump 6 is installed at the bottom of the drone body 1, and an air pipe 7 is connected to the exhaust end of the air pump 6, and the air pipe 7 is connected to the support mechanism 5;

[0051] Among them, the supporting mechanism 5 includes an outer cylinder 51, which is installed on the connecting frame 4, and inner cylinders 52 are slidably inserted at both ends of the outer cylinder 51. A control part 53 is installed between the two inner cylinders 52, and a buoyancy part 54 is installed at the front and rear ends of each inner cylinder 52. The inner wall of the outer cylinder 51 is provided with limiting grooves 55 in an annular shape, and through holes 56 are also provided at both ends of the limiting grooves 55. A sealing part 57 is provided on the inner cylinder 52, and the sealing part 57 is slidably set in the limiting groove 55.

[0052] In this embodiment, the air pump 6 and the air pipe 7 provide gas to the support mechanism 5 to expand it and provide buoyancy, so that the UAV can float on the water. The design of the flight part 31 and the heat dissipation part 32 ensures the stability and heat dissipation requirements of the UAV during flight. The entire design enables the UAV to work effectively in a variety of environments.

[0053] Next, please refer to Figure 8 and Fig. 9 The flight part 31 includes a shell 311 , which is connected to the bracket 2 , a driving motor 312 is installed inside the shell 311 , and a rotor 313 is installed on the output shaft of the driving motor 312 .

[0054] In this embodiment, the housing 311 is the main structure of the flight unit 31 and serves to protect the internal components. The drive motor 312 is installed inside the housing 311 and is the power source for driving the rotor 313 to rotate. The rotor 313 is installed on the output shaft of the drive motor 312 and generates lift through the rotation of the motor, so that the aircraft can fly.

[0055] Next, please refer to Figure 2 and Figure 3 The control unit 53 includes a bidirectional electric push rod 531, which is installed between the two inner cylinders 52 and fixedly connected to the inner wall of the outer cylinder 51 by a support rod. A sleeve 532 is also provided between the two inner cylinders 52. Telescopic rods 533 are slidably inserted at both ends of the sleeve 532, and one end of the telescopic rod 533 is fixedly connected to the inner cylinder 52. A second spring 534 is sleeved on one end of the telescopic rod 533, and one end of the second spring 534 is fixedly connected to the inner cylinder 52, and the other end is fixedly connected to the sleeve 532, wherein an annular sealing ring 58 is provided at one end of the inner cylinder 52, and annular sealing grooves 59 are provided at both ends of the outer cylinder 51.

[0056] In this embodiment, when the drone needs to land on the water, the two inner cylinders 52 are gradually extended from the outer cylinder 51 by controlling the extension of the bidirectional electric push rod 531. During this extension process, the blocking portion 57 slides along the limiting groove 55. When the inner cylinder 52 is fully extended, the annular sealing ring 58 on the inner cylinder 52 is in close contact with the annular sealing groove 59 on the outer cylinder 51, thereby achieving a sealing effect and effectively preventing water from entering the interior.

[0057] In addition, during the extension and retraction of the inner cylinder 52, the two telescopic rods 533 will slide along the sleeve 532. This sliding process not only plays a role of limiting, but also plays a role of guiding, ensuring the stability and accuracy of the extension and retraction process of the inner cylinder 52. At the same time, the second spring 534 plays a role of buffering power in this process, which can effectively absorb and alleviate the impact force generated by the extension and retraction action, thereby protecting the device from damage. Through this design, the entire device can be more stable and safe when landing on the water surface, ensuring the reliability and durability of the device in the water.

[0058] Please refer again Figure 6 and Figure 7 The buoyancy part 54 includes a first hollow cylinder 541, which is fixedly embedded in the inner cylinder 52. The second hollow cylinder 542 is piston-plugged in the first hollow cylinder 541, and the third hollow cylinder 543 is piston-plugged in the second hollow cylinder 542. A first tension spring 544 is fixedly connected between the first hollow cylinder 541 and the second hollow cylinder 542, and a second tension spring 545 is fixedly connected to the third hollow cylinder 543. The inner wall of the inner cylinder 52 is fixedly connected to a support plate 546 by a support rod, and the support plate 546 is fixedly connected to the second tension spring 545.

[0059] In this embodiment, the air pump 6 is first started to deliver air to the outer tube 51 and the inner tube 52 of the drone through the air pipe 7. As the pressure increases, the second hollow tube 542 moves along the first hollow tube 541 under the action of the air pressure, and stretches the first tension spring 544. At the same time, the third hollow tube 543 also moves along the second hollow tube 542 under the action of the air pressure, and stretches the second tension spring 545. This series of actions continues until the second hollow tube 542 and the third hollow tube 543 are extended. Through this structural design, the movement of the second hollow tube 542 and the third hollow tube 543 can significantly improve the buoyancy of the drone, thereby ensuring that the drone can land smoothly on the water surface.

[0060] In addition, through this structural design, during the flight of the drone, the buoyancy portion 54 can be retracted in the inner tube 52, and the inner tube 52 can be retracted in the outer tube 51. This design greatly reduces the volume of the float, effectively reduces wind resistance, and thus improves the flight efficiency of the drone. When landing, by increasing the volume of the float and increasing buoyancy, the drone can land and float smoothly on the water surface, thereby expanding the use environment of the drone.

[0061] When the UAV needs to take off from the water surface, the bidirectional electric push rod 531 is controlled to shorten, driving the two inner tubes 52 to shrink into the inner part of the outer tube 51. In this process, the blocking portion 57 will leave the through hole 56, so that the air inside can be discharged along the through hole 56. As the air is discharged, the internal air pressure gradually decreases. Subsequently, under the reset force of the first tension spring 544 and the second tension spring 545, the second hollow tube 542 and the third hollow tube 543 begin to reset and retract into the first hollow tube 541. Then, the bidirectional electric push rod 531 continues to shorten until the inner tube 52 is completely reset and retracted into the outer tube 51. This series of actions ensures that the UAV can remain stable during takeoff and landing, while also improving its overall performance and reliability.

[0062] Please refer again Figure 4 The sealing portion 57 includes a movable groove 571, which is opened on the inner tube 52, and a movable block 572 is inserted into the movable groove 571. A compression spring 573 is fixedly connected between the movable block 572 and the movable groove 571, and a sealing block 574 is fixedly connected to one side of the movable block 572, and a rubber pad is arranged on one surface of the sealing block 574; wherein, trapezoidal protrusions are arranged at both ends of the limiting groove 55, and balls are arranged in an array on the inner wall of the limiting groove 55.

[0063] In this embodiment, when the inner cylinder 52 is extended, the blocking portion 57 will also move to the position of the through hole 56. Since a trapezoidal protrusion is designed at the through hole 56, the protrusion will exert a certain pressure on the sealing block 574. This pressure makes the lower end of the sealing block 574, that is, the movable block 572, forced to shrink inward into the pre-designed movable groove 571. At the same time, this contraction action will exert pressure on the compression spring 573, causing it to generate a corresponding reaction force. This reaction force will further push the sealing block 574 to move upward, ensuring that the sealing block 574 can fit tightly at the opening of the through hole 56, thereby achieving effective sealing of the through hole 56. In this way, it can be ensured that the sealing of the through hole 56 is guaranteed during the extension of the inner cylinder 52 to prevent air leakage or water from entering; and the design of the ball can reduce the friction generated by the sealing block 574 and the limit groove 55 during the movement process, thereby reducing the transmission resistance.

[0064] Secondly, please also refer to Figure 8 and Fig. 9The heat dissipation part 32 includes a heat dissipation groove 321 and a slide groove 322. The heat dissipation groove 321 and the slide groove 322 are both opened on the shell 311. A hollow ring 323 is slidably connected in the slide groove 322. An annular baffle 324 is fixedly connected to one side of the hollow ring 323. A first spring 325 is arranged between the hollow ring 323 and the slide groove 322. A round rod 326 is fixedly connected to the other side of the hollow ring 323, and the lower end of the round rod 326 passes through the shell 311. The lower end of the round rod 326 is fixedly connected to the base 327.

[0065] In this embodiment, the inner cylinder 52 is connected to the base 327 by a traction rope. When the two inner cylinders 52 gradually move away from each other, the pulling force of the traction rope on the base 327 gradually weakens, and finally, under the action of the reset force of the first tension spring 544, the hollow ring 323 is pulled upward. The upward movement of the hollow ring 323 drives the annular baffle 324 to move upward, thereby closing the heat dissipation groove 321, preventing the water source stirred up during the landing process from entering the shell 311 through the heat dissipation groove 321, thereby avoiding damage to the drive motor 312. When the two inner cylinders 52 approach each other, the traction rope pulls the base 327 to move downward, and the downward movement of the base 327 drives the round rod 326, the hollow ring 323 and the annular baffle 324 to move downward together, and stretches the first spring 325. At this time, the heat dissipation groove 321 is opened, so that the outside air can enter the shell 311, thereby facilitating the heat dissipation of the drive motor 312.

[0066] Please refer again Figure 3 A shock-absorbing pad is installed at the lower end of the outer tube 51. This shock-absorbing pad not only has the function of shock absorption, but also has anti-slip grooves on its bottom surface. This design allows the shock-absorbing pad made of rubber material to effectively contact the ground when the drone safely lands on hard ground after performing a mission. In this way, the outer tube 51 will not directly rub against the ground, thereby avoiding damage that may be caused by friction. The presence of this shock-absorbing pad not only extends the service life of the drone outer tube 51, but also improves its adaptability and stability in various complex terrains.

[0067] The working principle of the present invention is:

[0068] The driving motor 312 is started to drive the rotor 313 to rotate and realize flight. During the flight, the inner tube 52 is retracted inside the outer tube 51. If it is necessary to land on the water surface, the two inner tubes 52 are gradually extended from the outer tube 51 by controlling the bidirectional electric push rod 531 to extend. During the extension process, the blocking part 57 slides along the limiting groove 55 until it is fully extended. At this time, the annular sealing ring 58 on the inner tube 52 is in close contact with the annular sealing groove 59 on the outer tube 51 to form a seal to prevent water from penetrating.

[0069] Then, the air pump 6 is started to deliver air to the inner tube 52 and the outer tube 51 through the air delivery pipe 7 to increase the internal pressure. Under the action of air pressure, the second hollow tube 542 moves along the first hollow tube 541 and stretches the first tension spring 544, and the third hollow tube 543 moves along the second hollow tube 542 and stretches the second tension spring 545 until the second hollow tube 542 and the third hollow tube 543 extend. The extension of the second hollow tube 542 and the third hollow tube 543 can increase the buoyancy.

[0070] In addition, a traction rope is connected between the inner cylinder 52 and the base 327. As the two inner cylinders 52 move away from each other, the pulling force of the traction rope on the base 327 gradually weakens, and then under the action of the reset force of the first tension spring 544, the hollow ring 323 moves upward, driving the annular baffle 324 to move upward, closing the heat dissipation slot 321, and preventing the splashes stirred up during landing from entering the housing 311 and causing damage to the drive motor 312.

[0071] After the drone takes off from the water, the two-way electric push rod 531 is controlled to shorten, driving the two inner cylinders 52 to shrink into the outer cylinder 51, and the blocking portion 57 leaves the through hole 56, and the internal air can be discharged along the through hole 56, and the internal air pressure gradually decreases. Subsequently, under the reset force of the first tension spring 544 and the second tension spring 545, the second hollow cylinder 542 and the third hollow cylinder 543 are reset and retracted into the first hollow cylinder 541. Then, the two-way electric push rod 531 continues to shorten until the inner cylinder 52 is completely retracted into the outer cylinder 51. At the same time, the two inner cylinders 52 approach each other, and the base 327 moves downward through the traction rope. The downward movement of the base 327 drives the round rod 326, the hollow ring 323 and the annular baffle 324 to move downward, and stretches the first spring 325. At this time, the heat dissipation slot 321 is opened, and the outside air can enter the shell 311, which is convenient for the drive motor 312 to dissipate heat.

[0072] The above is only a preferred embodiment of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be considered as the protection scope of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to the conventional means in the art unless otherwise specified and limited.

Claims

1. A multi-purpose amphibious unmanned aerial vehicle, characterized in that: It comprises a drone body (1), wherein four corners of the drone body (1) are each provided with a bracket (2); A flying mechanism (3), the flying mechanism (3) being mounted on the bracket (2), comprising a flying portion (31) and a heat dissipation portion (32); A connecting frame (4), the connecting frame (4) being connected to the bottom surface of the drone body (1), and a supporting mechanism (5) being installed on the connecting frame (4); An air pump (6) is installed at the bottom of the drone body (1); an exhaust end of the air pump (6) is connected to an air pipe (7), and the air pipe (7) is connected to the support mechanism (5); The support mechanism (5) comprises an outer cylinder (51), the outer cylinder (51) is mounted on the connecting frame (4), both ends of the outer cylinder (51) are slidably connected with inner cylinders (52), a control part (53) is mounted between the two inner cylinders (52), a buoyancy part (54) is mounted at both front and rear ends of each inner cylinder (52), the inner wall of the outer cylinder (51) is provided with limiting grooves (55) in an annular distribution, through holes (56) are also provided at both ends of the limiting grooves (55), a blocking part (57) is arranged on the inner cylinder (52), and the blocking part (57) is slidably arranged in the limiting grooves (55).

2. A multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: The flying part (31) comprises a shell (311), the shell (311) is connected to the bracket (2), a driving motor (312) is installed inside the shell (311), and a rotor (313) is installed on the output shaft of the driving motor (312).

3. A multi-purpose amphibious UAV according to claim 2, characterized in that: The heat dissipation portion (32) comprises a heat dissipation groove (321) and a slide groove (322), the heat dissipation groove (321) and the slide groove (322) are both provided on the outer shell (311), a hollow ring (323) is slidably connected in the slide groove (322), an annular baffle (324) is fixedly connected to one side of the hollow ring (323), a first spring (325) is provided between the hollow ring (323) and the slide groove (322), a round rod (326) is fixedly connected to the other side of the hollow ring (323), and the lower end of the round rod (326) passes through the outer shell (311), and the lower end of the round rod (326) is fixedly connected to a base (327).

4. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: The control unit (53) comprises a bidirectional electric push rod (531), which is installed between the two inner cylinders (52) and fixedly connected to the inner wall of the outer cylinder (51) by a support rod. A sleeve (532) is also provided between the two inner cylinders (52), and telescopic rods (533) are slidably inserted at both ends of the sleeve (532), and one end of the telescopic rod (533) is fixedly connected to the inner cylinder (52). A second spring (534) is sleeved on one end of the telescopic rod (533), and one end of the second spring (534) is fixedly connected to the inner cylinder (52), and the other end is fixedly connected to the sleeve (532).

5. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: The buoyancy part (54) comprises a first hollow cylinder (541), wherein the first hollow cylinder (541) is fixedly embedded in the inner cylinder (52), a second hollow cylinder (542) is piston-inserted in the first hollow cylinder (541), a third hollow cylinder (543) is piston-inserted in the second hollow cylinder (542), a first tension spring (544) is fixedly connected between the first hollow cylinder (541) and the second hollow cylinder (542), a second tension spring (545) is fixedly connected to the third hollow cylinder (543), and an inner wall of the inner cylinder (52) is fixedly connected to a support plate (546) by means of a support rod, and the support plate (546) is fixedly connected to the second tension spring (545).

6. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: The blocking portion (57) comprises a movable groove (571), wherein the movable groove (571) is provided on the inner cylinder (52), a movable block (572) is inserted into the movable groove (571), a compression spring (573) is fixedly connected between the movable block (572) and the movable groove (571), a sealing block (574) is fixedly connected to one side of the movable block (572), and a rubber pad is provided on one surface of the sealing block (574).

7. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: Trapezoidal protrusions are arranged at both ends of the limiting groove (55), and balls are arranged in an array on the inner wall of the limiting groove (55).

8. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: An annular sealing ring (58) is provided at one end of the inner cylinder (52), and annular sealing grooves (59) are provided at both ends of the outer cylinder (51).

9. The multi-purpose amphibious unmanned aerial vehicle according to claim 1, characterized in that: A shock absorbing pad is arranged at the lower end of the outer cylinder (51), and the bottom surface of the shock absorbing pad is provided with anti-slip grooves.

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