Amphibious unmanned aerial vehicle power switching mechanism

Abstract

The utility model belongs to the unmanned aerial vehicle technical field, concretely relates to amphibious unmanned aerial vehicle power switching mechanism, including unmanned aerial vehicle main part, installation shell, buoy and sealing cover, still include: power unit, power unit includes setting on the driving portion of installation shell and the linkage portion that links to driving portion; Air output unit, air output unit sets up the upper end of installation shell, underwater output unit, underwater output unit sets up one end at buoy, two control units, two control units are separately installed on the two installation shells of the same end of unmanned aerial vehicle main part. Two auxiliary units, two auxiliary units are separately installed on the installation shell of two installation control units. The utility model can realize the automatic switching of low resistance high efficiency flight and reliable underwater propulsion through the shared power source and the retractable propulsion mechanism, significantly improve the endurance, mobility and cross-media operation reliability of amphibious unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a power switching mechanism for amphibious UAVs. Background Technology

[0002] Amphibious unmanned aerial vehicles (UAVs) are highly integrated advanced unmanned systems that require not only stable and reliable aerial flight capabilities but also flexible and efficient underwater navigation. In the air, they need to achieve long-endurance, highly maneuverable flight missions and adapt to various complex weather conditions; underwater, they must overcome water resistance to maintain their course. This cross-medium operational capability makes them promising for applications in environmental monitoring, resource exploration, emergency rescue, and many other fields.

[0003] For example, a vertical take-off amphibious unmanned aerial vehicle (UAV) with Chinese patent application number CN202321281124.2 includes a frame, a pair of floats, and a power unit. The frame includes a nose, fuselage, wings, and tail connected in sequence. A float is fixedly installed on the underside of each wing. The floats can support the UAV to float on the water surface. In addition, the frame and floats are equipped with a power unit. It has the advantages of enabling the UAV to fly continuously in the air and navigate on the water surface in cooperation with the floats and the power unit.

[0004] While amphibious drones of the types described above possess the ability to fly in the air and navigate underwater, they still have some shortcomings in practical use: First, separate motors and thrusters are installed for aerial and underwater operations. While this approach simplifies control, it increases the drone's weight, size, and power consumption, reducing its endurance. Secondly, the underwater propulsion rotor components are completely exposed to the external environment and lack corresponding streamlined shell protection, which leads to a significant increase in air resistance during high-speed flight, seriously affecting the aircraft's maneuverability and energy efficiency. Utility Model Content

[0005] The purpose of this invention is to provide a power switching mechanism for amphibious unmanned aerial vehicles (UAVs) that can automatically switch between low-drag, high-efficiency flight and reliable underwater propulsion by sharing a power source and a retractable propulsion mechanism, thereby significantly improving the endurance, maneuverability, and reliability of cross-medium operations of amphibious UAVs.

[0006] The specific technical solution adopted in this utility model is as follows: An amphibious unmanned aerial vehicle (UAV) power switching mechanism includes a UAV body, mounting shells disposed at the four corners of the UAV body, and floats located below the UAV body to provide buoyancy. One end of each float is hinged with a sealing cap. The mechanism also includes: A power unit, the power unit including a drive unit disposed on a mounting housing and a linkage unit linked with the drive unit; An air output unit, which is disposed at the upper end of the mounting housing, is used to provide airborne flight power; An underwater output unit, which is located at one end of the float, is used to provide underwater propulsion power; Two control units are located on two mounting shells at the same end of the UAV body. By pushing the linkage to move, the air output unit or the underwater output unit can be selectively driven to switch between air mode and underwater mode.

[0007] Two auxiliary units are located on two mounting shells equipped with control units. These units are used to extend the underwater output unit out of the float and into contact with the water source when the UAV is in underwater mode.

[0008] In a preferred embodiment, the drive unit includes a drive motor, which is fixedly mounted inside the mounting housing, and a drive gear is fixedly mounted on the output shaft of the drive motor.

[0009] In a preferred embodiment, the linkage part includes linkage gears. Linkage gears are floatingly disposed in both of the two mounting housings where the control unit is installed, and docking rods are installed on both sides of the linkage gears. Linkage gears are rotatably connected in the other two mounting housings via bearings.

[0010] In a preferred embodiment, the air output unit includes support rods, a plurality of support rods are connected to the upper end of the mounting housing in a ring distribution, and a bearing seat is fixedly installed at one end of the plurality of support rods that are close to each other. A first drive shaft is rotatably connected to the bearing seat through a bearing, and blades are installed on the first drive shaft.

[0011] In a preferred embodiment, the underwater output unit includes a support frame fixedly connected inside a float. A rotating rod is rotatably connected to the support frame via bearings. A hexagonal prism is slidably inserted into a hexagonal slot on the rotating rod. A first bevel gear is fixedly installed at one end of the rotating rod, and a propeller is fixedly installed at one end of the hexagonal prism. A second drive shaft is rotatably connected to two mounting housings containing a control unit via bearings, and the lower end of the second drive shaft extends into the float and is fitted with a second bevel gear. A first disk is fixedly connected to one end of the hexagonal prism, and a second disk is rotatably connected to one side of the first disk via bearings. A third disk is fixedly sleeved at one end of the rotating rod, and a compression spring is fixedly connected between the third disk and the first disk.

[0012] In a preferred embodiment, the control unit includes an electric push rod, which is fixedly mounted on a support rod. The lower end of the electric push rod is fixedly connected to a first ring, and the first ring is rotatably connected to a linkage gear via a bearing.

[0013] In a preferred embodiment, the auxiliary unit includes an annular groove formed on a mounting housing on which a control unit is mounted. A first piston rod is piston-type inserted into the annular groove. A piston ring is fixedly mounted on one end of the first piston rod within the annular groove. The other end of the first piston rod is fixedly connected to a second ring, which is rotatably connected to a linkage gear via a bearing. A connecting rod is fixedly connected between the mounting housing and the float. A piston chamber is formed on the float. A second piston rod is piston-type inserted into one end of the piston chamber. A piston plate is fixedly connected to one end of the second piston rod within the piston chamber. An oil pipe is connected between the piston chamber and the annular groove. A limit groove is formed on the float. A limit rod is slidably connected within the limit groove and is fixedly connected to a second disc.

[0014] In a preferred embodiment, a traction rope is fixedly connected to the sealing cover, and the traction rope extends into the interior of the float and is fixedly connected to the second disc.

[0015] The technical effects achieved by this utility model are as follows: This utility model employs a power switching mechanism comprised of a drive unit, a linkage unit, an air output unit, and an underwater output unit. This mechanism allows the same set of drive motors to selectively drive either the air rotor or the underwater propeller, avoiding the redundancy inherent in traditional amphibious UAVs which require separate propulsion systems for each medium. This integrated design effectively reduces the airframe load, decreases the overall size, and significantly lowers power consumption, thereby substantially extending the overall endurance of the UAV in air-to-water cross-medium missions. This utility model utilizes a linkage control mechanism between the auxiliary unit and the sealing cover to completely house the propeller and transmission components within the float in aerial mode, with the sealing cover closing to form a smooth and continuous outer shell surface. This design completely solves the high wind resistance problem caused by exposed underwater propulsion in existing technologies, enabling the UAV to maintain excellent aerodynamic performance during high-speed flight, thereby improving flight stability, maneuverability, and energy efficiency. This utility model achieves rapid and stable switching between air and underwater propulsion paths by driving the linkage gear axially through a control unit and using a hexagonal docking structure. Simultaneously, a closed hydraulic system constructed with auxiliary units converts the displacement of the linkage gear into hydraulic pressure, automatically pushing the underwater propulsion component out and simultaneously opening the sealing cover. The entire switching process requires no additional actuators, featuring a compact structure, rapid response, and strong coordination, effectively ensuring the reliability and ease of operation when switching from air to underwater mode. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a partial structural schematic diagram of the present invention; Figure 3 This is a partial structural cross-sectional view of the present invention; Figure 4 This is a utility model Figure 3 An enlarged schematic diagram of part A shown in the image; Figure 5 This is a utility model Figure 3 An enlarged schematic diagram of part B shown in the image; Figure 6 This is a schematic diagram showing the connection between the underwater output unit and the auxiliary unit of this utility model; Figure 7 This is a utility model Figure 6 The front view.

[0017] The attached diagram lists the components represented by each number as follows: 1. Unmanned Aerial Vehicle (UAV) body; 11. Mounting shell; 12. Float; 13. Sealing cover; 2. Power unit; 3. Air output unit; 4. Underwater output unit; 5. Control unit; 6. Auxiliary unit; 7. Towing rope; 21. Drive unit; 22. Linkage unit; 211. Drive motor; 212. Drive gear; 221. Linkage gear; 222. Connecting rod; 31. Support rod; 32. Bearing housing; 33. First drive shaft; 34. Blade; 41. Support frame; 42. Rotating rod; 43. Hexagonal prism; 44. First bevel gear; 45. Propeller; 46. Second drive shaft; 47. Second bevel gear; 48. First disk; 49. Second disk; 410. Third disk; 411. Compression spring; 51. Electric actuator; 52. First ring; 61. Annular groove; 62. First piston rod; 63. Piston ring; 64. Second ring; 65. Connecting rod; 66. Piston chamber; 67. Second piston rod; 68. Piston plate; 69. Oil pipe; 610. Limiting groove; 611. Limiting rod. Detailed Implementation

[0018] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0019] Many specific details are set forth in the following description in order to provide a full understanding of this utility model. However, this utility model may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed below.

[0020] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of this utility model. The phrase "in a preferred embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that mutually excludes other embodiments.

[0021] Secondly, this utility model is described in detail with reference to the schematic diagrams. When detailing the embodiments of this utility model, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of this utility model. In addition, actual manufacturing should include the three-dimensional spatial dimensions of length, width, and depth.

[0022] Please see the appendix Figures 1-3 As shown, this utility model provides a power switching mechanism for an amphibious unmanned aerial vehicle (UAV), including a UAV body 1, mounting shells 11 disposed at the four corners of the UAV body 1, and floats 12 located below the UAV body 1 to provide buoyancy. One end of each float 12 is hinged with a sealing cap 13. The mechanism also includes: Power unit 2, which includes a drive unit 21 disposed on the mounting housing 11 and a linkage unit 22 that is linked to the drive unit 21; Air output unit 3, which is located at the upper end of the mounting shell 11, is used to provide air flight power; The underwater output unit 4 is located at one end of the float 12 and is used to provide underwater propulsion power. Two control units 5 are located on two mounting shells 11 at the same end of the UAV body 1. By pushing the linkage 22 to move, they can selectively drive the air output unit 3 or the underwater output unit 4 to switch between air mode and underwater mode.

[0023] Two auxiliary units 6 are respectively installed on two mounting shells 11 on which control units 5 are installed, and are used to push the underwater output unit 4 out of the float 12 to contact the water source when the UAV is in underwater mode.

[0024] In this embodiment, through the coordinated action of the power unit 2, control unit 5, and auxiliary unit 6, the UAV can selectively drive either the airborne output unit 3 or the underwater output unit 4 using only a single drive source, thereby achieving switching between airborne and underwater modes. The overall workflow is as follows: the drive unit 21 provides power, which is transmitted to the output unit via the linkage unit 22; the control unit 5 moves the linkage unit 22, changing the power transmission path; and the auxiliary unit 6 ensures that the underwater thruster is in contact with the water source in underwater mode. This design reduces the weight and drag caused by independent motors, improving endurance and maneuverability.

[0025] In a preferred embodiment, please refer to Figures 2-4 The drive unit 21 includes a drive motor 211, which is fixedly installed inside the mounting housing 11. A drive gear 212 is fixedly installed on the output shaft of the drive motor 211. The linkage unit 22 includes a linkage gear 221. The linkage gear 221 is floatingly disposed in both of the two mounting shells 11 in which the control unit 5 is installed, and a docking rod 222 is installed on both sides of the linkage gear 221. The linkage gear 221 is rotatably connected to the other two mounting shells 11 through bearings.

[0026] Secondly, please refer to it again. Figure 2 and Figure 4 The control unit 5 includes an electric push rod 51, which is fixedly mounted on the support rod 31. The lower end of the electric push rod 51 is fixedly connected to a first ring 52, and the first ring 52 is rotatably connected to the linkage gear 221 through a bearing.

[0027] Secondly, please refer to the following as well. Figure 2 and Figure 3 The air output unit 3 includes a support rod 31. Multiple support rods 31 are connected to the upper end of the mounting shell 11 in a ring. Bearing seats 32 are fixedly installed at the ends of the multiple support rods 31 that are close to each other. A first drive shaft 33 is rotatably connected to the bearing seat 32 through a bearing. A blade 34 is installed on the first drive shaft 33.

[0028] In this embodiment, when the drone needs to perform an aerial flight mission, the control unit 5 starts working. Specifically, the electric push rod 51 mounted on the support rod 31 retracts, driving the linkage gear 221, which is rotatably connected to it via a bearing, to move upward through the first ring 52. After the linkage gear 221 moves upward, the docking rod 222 on its top surface inserts into the docking groove opened at the lower end of the first drive shaft 33 (e.g., ...). Figure 3 (As shown). At this time, the transmission path between the linkage gear 221 and the underwater output unit 4 is disconnected from the second drive shaft 46.

[0029] The drive motor 211 starts, driving the drive gear 212 to rotate, which in turn drives the meshing linkage gear 221 to rotate. The rotational power of the linkage gear 221 is directly transmitted to the first drive shaft 33, causing the blades 34 mounted on the shaft to rotate at high speed, generating lift and thrust, enabling the UAV to fly in the air.

[0030] It should be noted that regardless of whether the linkage gear 221 is in the highest or lowest position, it can always maintain a meshing state with the drive gear 212.

[0031] The linkage gear 221 inside the mounting housing 11 without the control unit 5 is rotatably connected to the mounting housing 11 via a bearing, and the linkage gear 221 here is fixedly connected to the first drive shaft 33, thereby driving the blade 34 to rotate; in addition, when the UAV is in aerial mode, the four power units 2 are started simultaneously.

[0032] In a preferred embodiment, please refer to Figures 3-7 The underwater output unit 4 includes a support frame 41, which is fixedly connected inside the float 12. A rotating rod 42 is rotatably connected to the support frame 41 via bearings. A hexagonal prism 43 is slidably inserted into a hexagonal slot on the rotating rod 42. A first bevel gear 44 is fixedly installed at one end of the rotating rod 42, and a propeller 45 is fixedly installed at one end of the hexagonal prism 43. A second drive shaft 46 is rotatably connected to both mounting shells 11 where the control unit 5 is installed via bearings. The lower end of the second drive shaft 46 extends into the float 12 and is equipped with a second bevel gear 47. A first disk 48 is fixedly connected to one end of the hexagonal prism 43. A second disk 49 is rotatably connected to one side of the first disk 48 via bearings. A third disk 410 is fixedly sleeved on one end of the rotating rod 42. A compression spring 411 is fixedly connected between the third disk 410 and the first disk 48. In addition, the second drive shaft 46 is rotatably connected to the float 12 via bearings.

[0033] In this embodiment, when the UAV lands on the water and needs to transition to underwater navigation, the electric push rod 51 of the control unit 5 extends, pushing the linkage gear 221 downward. After the linkage gear 221 moves downward, it disengages from the first drive shaft 33 of the air output unit 3. Simultaneously, the docking rod 222 on its bottom surface inserts into the docking groove opened at the upper end of the second drive shaft 46, establishing a power path to underwater propulsion.

[0034] The drive motor 211 starts, and power is transmitted sequentially through the drive gear 212 and the lowered linkage gear 221 to the second drive shaft 46. The second bevel gear 47 at the lower end of the second drive shaft 46 meshes with the first bevel gear 44 fixed to one end of the rotating rod 42, causing the rotating rod 42 to rotate. Power is transmitted through the rotating rod 42. Since the hexagonal prism 43 is slidably inserted into the hexagonal slot of the rotating rod 42, the two are locked in the circumferential direction. Therefore, the rotation of the rotating rod 42 directly drives the hexagonal prism 43 and the propeller 45 fixed at its end to rotate, generating a backward water thrust, propelling the UAV underwater. When navigating on the water surface, only the two power units 2 connected to the control unit 5 need to be activated.

[0035] It should be added that hexagonal slots are provided at the ends of the first drive shaft 33 and the second drive shaft 46 within the mounting housing 11 where the control unit 5 is installed, and the mating rod 222 is hexagonal with a slightly reduced end diameter. This design can act as a self-guided mechanism when there is a slight deviation in axial alignment, helping the mating rod 222 to be inserted into the hexagonal slot.

[0036] Secondly, please refer to it again. Figures 3-7 The auxiliary unit 6 includes an annular groove 61, which is formed on the mounting housing 11 on which the control unit 5 is installed. A first piston rod 62 is piston-type inserted into the annular groove 61. A piston ring 63 is fixedly installed at one end of the first piston rod 62 located in the annular groove 61, and a second ring 64 is fixedly connected to the other end of the first piston rod 62. The second ring 64 is rotatably connected to the linkage gear 221 through a bearing. A connecting rod 65 is fixedly connected between the mounting housing 11 and the float 12. A piston cavity 66 is formed on the float 12. A second piston rod 67 is piston-type inserted into one end of the piston chamber 66. A piston plate 68 is fixedly connected to one end of the second piston rod 67 located in the piston chamber 66. An oil pipe 69 is connected between the piston chamber 66 and the annular groove 61. A limit groove 610 is opened on the float 12. A limit rod 611 is slidably connected in the limit groove 610, and the limit rod 611 is fixedly connected to the second disc 49. A traction rope 7 is fixedly connected to the sealing cover 13, and the traction rope 7 passes through the inside of the float 12 and is fixedly connected to the second disc 49.

[0037] In this embodiment, when the linkage gear 221 moves downward, the second ring 64 connected to it via a bearing is also pushed downward, thereby driving the first piston rod 62 and piston ring 63 to move downward within the annular groove 61. The annular groove 61 is connected to the piston chamber 66 on the float 12 via an oil pipe 69, forming a closed hydraulic or oil pressure system. The downward movement of the piston ring 63 compresses the oil in the lower chamber of the annular groove 61, and the pressure is transmitted to the piston chamber 66 through the oil pipe 69, pushing the piston plate 68 and the second piston rod 67 to move.

[0038] The end of the second piston rod 67 is connected to the second disk 49, thereby pushing the entire underwater propulsion assembly (including the first disk 48, hexagonal prism 43, propeller 45, etc.) to overcome the elastic force of the compression spring 411 and slide outward along the rotating rod 42 until the propeller 45 is fully extended beyond the float 12 and enters the water. Furthermore, as the underwater propulsion assembly extends outward, the traction rope 7 fixed to the second disk 49 is tightened, thereby pulling the sealing cover 13 at the end of the float 12 upward around the hinge, providing a clear water flow channel for the extension and rotation of the propeller 45. It should be noted that a torsion spring connects the sealing cover 13 and the float 12; when the sealing cover 13 loses the pull of the traction rope 7, it resets under the restoring force of the torsion spring.

[0039] When the UAV is performing an aerial flight mission, the auxiliary unit 6 is in a non-operating state. The oil in the annular groove 61 is not compressed into the oil pipe 69, and there is no pressure change in the piston chamber 66. The underwater propulsion component of the underwater output unit 4, which is linked to the auxiliary unit 6, pushes the first disk 48 away from the third disk 410 under the elastic restoring force of the compression spring 411, and drives the hexagonal prism 43 to slide inward along the hexagonal groove of the rotating rod 42. Finally, the propeller 45 is completely retracted into the float 12.

[0040] Simultaneously, the traction rope 7 fixed to the second disc 49 is released. Under the action of the torsion spring, the sealing cover 13 rotates downward around the hinge point, closing the opening at the bottom of the float 12 and forming a streamlined shell, which greatly reduces wind resistance during flight.

[0041] It should be noted that the limiting groove 610 and the limiting rod 611 provide guidance and limit for the extension movement of the second disk 49, ensuring that its movement trajectory is stable and that it will not rotate with the first disk 48.

[0042] The working principle of this utility model is as follows: The control unit 5 drives the linkage gear 221 to move axially, selectively transmitting the power of the drive motor 211 to the blades 34 of the air output unit 3 or the propeller 45 of the underwater output unit 4. In air mode, the propeller 45 is retracted into the float 12 and the sealing cover 13 is closed to reduce wind resistance. When switching to underwater mode, the linkage gear 221 moves down to engage the underwater transmission path, and at the same time, the hydraulic linkage mechanism of the auxiliary unit 6 automatically pushes out the propeller 45 and opens the sealing cover 13, realizing integrated automatic control of power path switching and propeller deployment.

[0043] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model, unless otherwise specified or limited, shall be implemented using conventional methods in the art.

Claims

1. An amphibious unmanned aerial vehicle (UAV) power switching mechanism, comprising a UAV body (1), mounting shells (11) disposed at the four corners of the UAV body (1), and floats (12) located below the UAV body (1) to provide buoyancy, wherein one end of the floats (12) is hinged with a sealing cap (13), characterized in that, Also includes: The power unit (2) includes a drive unit (21) disposed on the mounting shell (11) and a linkage unit (22) that is linked with the drive unit (21). An air output unit (3) is disposed at the upper end of the mounting housing (11) and is used to provide air flight power; The underwater output unit (4) is located at one end of the float (12) and is used to provide underwater propulsion power. Two control units (5) are respectively located on two mounting shells (11) at the same end of the UAV body (1). By pushing the linkage (22) to move, the air output unit (3) or the underwater output unit (4) can be selectively driven to achieve the switching between air mode and underwater mode. Two auxiliary units (6) are respectively installed on two mounting shells (11) on which control units (5) are installed, and are used to push the underwater output unit (4) out of the float (12) to contact the water source when the UAV is in underwater mode.

2. The amphibious unmanned aerial vehicle power switching mechanism according to claim 1, characterized in that: The drive unit (21) includes a drive motor (211), which is fixedly installed inside the mounting housing (11), and a drive gear (212) is fixedly installed on the output shaft of the drive motor (211).

3. The amphibious unmanned aerial vehicle power switching mechanism according to claim 1, characterized in that: The linkage part (22) includes a linkage gear (221). The linkage gear (221) is floatingly installed in both of the two mounting shells (11) where the control unit (5) is installed, and a docking rod (222) is installed on both sides of the linkage gear (221). The linkage gear (221) is rotatably connected to the other two mounting shells (11) through bearings.

4. The amphibious unmanned aerial vehicle power switching mechanism according to claim 1, characterized in that: The air output unit (3) includes a support rod (31), and multiple support rods (31) are connected to the upper end of the mounting shell (11) in a ring distribution. A bearing seat (32) is fixedly installed at one end of the multiple support rods (31) that are close to each other. A first drive shaft (33) is rotatably connected to the bearing seat (32) through a bearing. A blade (34) is installed on the first drive shaft (33).

5. The amphibious unmanned aerial vehicle power switching mechanism according to claim 3, characterized in that: The underwater output unit (4) includes a support frame (41), which is fixedly connected inside the float (12). A rotating rod (42) is rotatably connected to the support frame (41) via a bearing. A hexagonal prism (43) is slidably inserted into the hexagonal slot on the rotating rod (42). A first bevel gear (44) is fixedly installed at one end of the rotating rod (42), and a propeller (45) is fixedly installed at one end of the hexagonal prism (43). The control unit (5) is installed in both of the two mounting shells (11) through which the propeller (45) is mounted. The bearing is rotatably connected to the second drive shaft (46), and the lower end of the second drive shaft (46) passes through the float (12) and is equipped with the second bevel gear (47). One end of the hexagonal prism (43) is fixedly connected to the first disk (48). One side of the first disk (48) is rotatably connected to the second disk (49) through the bearing. One end of the rotating rod (42) is fixedly fitted with the third disk (410). A compression spring (411) is fixedly connected between the third disk (410) and the first disk (48).

6. The amphibious unmanned aerial vehicle power switching mechanism according to claim 3, characterized in that: The control unit (5) includes an electric push rod (51), which is fixedly mounted on a support rod (31). The lower end of the electric push rod (51) is fixedly connected to a first ring (52), and the first ring (52) is rotatably connected to the linkage gear (221) through a bearing.

7. The amphibious unmanned aerial vehicle power switching mechanism according to claim 5, characterized in that: The auxiliary unit (6) includes an annular groove (61), which is formed on the mounting shell (11) on which the control unit (5) is installed. A first piston rod (62) is piston-type inserted into the annular groove (61). A piston ring (63) is fixedly installed at one end of the first piston rod (62) located in the annular groove (61). A second ring (64) is fixedly connected to the other end of the first piston rod (62), and the second ring (64) is rotatably connected to the linkage gear (221) through a bearing. The mounting shell (11) and the float (12) are fixedly connected. A connecting rod (65) is connected to the float (12), and a piston chamber (66) is opened on the float (12). A second piston rod (67) is piston-type inserted into one end of the piston chamber (66). A piston plate (68) is fixedly connected to one end of the second piston rod (67) located in the piston chamber (66). An oil pipe (69) is connected between the piston chamber (66) and the annular groove (61). A limit groove (610) is opened on the float (12). A limit rod (611) is slidably connected in the limit groove (610), and the limit rod (611) is fixedly connected to the second disc (49).

8. The amphibious unmanned aerial vehicle power switching mechanism according to claim 5, characterized in that: A traction rope (7) is fixedly connected to the sealing cover (13), and the traction rope (7) passes through the inside of the float (12) and is fixedly connected to the second disc (49).

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