UAV oil-electric hybrid power device and UAV

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles, and in particular, relates to an unmanned aerial vehicle oil-electric hybrid power device and an unmanned aerial vehicle, the device comprising a fuselage, a mounting groove is provided at the bottom of the fuselage, a mounting plate is horizontally arranged in the mounting groove, a first connecting block is fixedly connected to the middle position of the top of the mounting plate, a first connecting ball is rotatably connected to the top of the first connecting block, a first connecting column is fixedly connected to the top of the first connecting ball, and the first connecting column is fixedly connected to the top groove wall of the mounting groove. The present invention is provided with a shock absorbing component, and during the flight of the unmanned aerial vehicle, when the mounting plate is subjected to vibration from the engine, the mounting plate can be deflected by a certain amplitude with the first connecting ball as the center of the circle, so that multiple telescopic rods and corresponding shock absorbing springs can be adaptively extended and retracted, and then the vibration received by the mounting plate is converted into the elastic potential energy of the shock absorbing spring, thereby reducing the impact of the vibration on the unmanned aerial vehicle and ensuring the relative stability of the unmanned aerial vehicle flight.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to an unmanned aerial vehicle oil-electric hybrid power device and the unmanned aerial vehicle. Background Art

[0002] Hybrid UAVs are a new type of UAV that combines the advantages of fuel engines and electric systems. Due to their long flight time, large load capacity, and high environmental adaptability, hybrid UAVs are widely used in industry, agriculture, geographic information mapping, emergency rescue, military reconnaissance and combat, and other fields.

[0003] The power unit (engine and generator) of existing hybrid UAVs is mainly installed at the bottom of the fuselage. However, due to the lack of suitable shock-absorbing devices at the bottom of the fuselage, the vibration generated by the engine during the process of the engine providing power to the generator will affect the flight of the UAV. In addition, since the engine mainly relies on fuel, as the fuel in the tank decreases, the fuel is more likely to shake in the tank. Therefore, during the acceleration or deceleration of the UAV, the fuel in the tank will hit the tank wall, which will also affect the stable flight of the UAV.

[0004] Therefore, it is necessary to invent a UAV oil-electric hybrid power device and a UAV to solve the above problems. Summary of the invention

[0005] In view of the above problems, the present invention provides a hybrid power device for a drone and a drone to solve the problems raised in the above background technology.

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

[0007] A hybrid electric device for unmanned aerial vehicles and a unmanned aerial vehicle, comprising a fuselage, a mounting groove is provided at the bottom of the fuselage, a mounting plate is horizontally arranged in the mounting groove, a first connecting block is fixedly connected to the middle position of the top of the mounting plate, a first connecting ball is rotatably connected to the top of the first connecting block, a first connecting column is fixedly connected to the top of the first connecting ball, the first connecting column is fixedly connected to the top groove wall of the mounting groove, mounting holes are provided at the top groove wall of the mounting groove and the four corners of the top of the mounting plate, a shock absorbing assembly is arranged in the mounting hole, an engine and a generator are installed at the bottom of the mounting plate, and the output shaft of the engine and the input shaft of the generator are connected together by belt drive, the bottom of the mounting plate near the four corners is vertically fixedly connected to the limiting columns, a bottom plate is fixedly connected between the bottom ends of the plurality of limiting columns, and a protective assembly is arranged at the bottom of the bottom plate.

[0008] Furthermore, the shock absorbing assembly includes a telescopic rod, which is fixedly connected to the top inner wall of the mounting hole, and a shock absorbing spring is sleeved on the telescopic rod, and a fixing plate matching the size of the mounting hole opening is fixedly sleeved on the position of the telescopic rod near the bottom end, the edge of the fixing plate protrudes upward, and the height of the upward protruding part of the fixing plate is greater than the maximum telescopic amount of the shock absorbing spring, and the two ends of the shock absorbing spring are respectively fixedly connected to the top of the fixing plate and the top of the telescopic rod, and a second connecting ball is rotatably installed on the bottom end of the telescopic rod, and a second connecting column is fixedly connected to the bottom of the second connecting ball, and the bottom end of the second connecting column is fixedly connected to a limiting plate, and a limiting tube is sleeved on the outer side of the limiting plate, and the limiting tube is fixedly connected to the top of the mounting plate, and the top edge of the limiting tube protrudes in the direction close to the second connecting column, and the diameter of the limiting plate is between the inner diameter of the top and bottom ends of the limiting tube.

[0009] Furthermore, the protective component includes a protective cover, which is slidably sleeved on the outer side of the base plate, and a plurality of limit blocks are fixedly connected to the inner wall of the side of the protective cover, and the plurality of limit blocks are respectively slidably sleeved on a plurality of limit columns, a partition matching the size of the top opening of the protective cover is horizontally fixedly connected to the inner side of the protective cover, a second connecting block is fixedly connected at the bottom center of the partition, a third connecting ball is rotatably installed at the bottom end of the second connecting block, a conical counterweight block is fixedly connected to the bottom of the third connecting ball, and the tip of the counterweight block faces downward, a rectangular first magnetic ring is fixedly sleeved on the outer side of the protective cover, a second magnetic ring matching the first magnetic ring is fixedly connected to the side groove wall of the mounting groove, the second magnetic ring has an opposite magnetic pole to the first magnetic ring, and the second magnetic ring can be adsorbed together with the first magnetic ring.

[0010] Furthermore, a fixing ring is installed at the bottom of the fuselage, and the mounting groove is located at the inner center of the fixing ring. A plurality of bow-shaped spring pieces are evenly and fixedly connected to the bottom of the fixing ring. The bow-shaped spring pieces protrude in a direction close to the protective cover, and when the protective cover moves downward to the maximum displacement, the bottom end of the bow-shaped spring piece fits with the bottom edge of the first magnetic ring.

[0011] Furthermore, a retaining ring is arranged on the periphery of the fixing ring, and the retaining ring is fixedly connected to the bottom of the fuselage, and the bottom edge of the retaining ring is always higher than the top edge of the protective cover, a strip-shaped heat dissipation hole is opened on the rear side of the retaining ring, and an air inlet is opened on the front side of the retaining ring, and a first guide plate and a second guide plate are fixedly connected between the inner walls on both sides of the air inlet, the first guide plate is located on the top of the second guide plate, and the bottom edge of the first guide plate and the top edge of the second guide plate are both inclined in the direction close to the protective cover, the top edge of the second guide plate is closer to the protective cover than the bottom edge of the first guide plate, and the top edge of the second guide plate is fixedly connected with a water retaining strip matching its length.

[0012] Furthermore, the diameter of the lower part of the protective cover gradually decreases from top to bottom, and the buoyancy that the protective cover can generate is greater than the gravity of the counterweight block and the protective cover itself.

[0013] Furthermore, a sealing ring is fixedly connected to the inner side of the second magnetic ring, and when the first magnetic ring and the second magnetic ring are adsorbed together, the sealing ring is just in close contact with the top edge of the protective cover.

[0014] Furthermore, strip grooves are horizontally opened on the outer sides of the four sides of the first magnetic ring, and a roller is rotatably installed between the inner walls on both sides of the strip groove. The side of the roller away from the protective cover is located outside the strip groove, and the roller can contact the bow-shaped spring piece.

[0015] The present invention also provides a UAV, comprising the above-mentioned UAV oil-electric hybrid power device.

[0016] Technical effects and advantages of the present invention:

[0017] 1. The present invention is provided with a shock-absorbing assembly. When the mounting plate is subjected to vibration from the engine during the flight of the UAV, the mounting plate can be deflected by a certain amplitude with the first connecting ball as the center, so that the multiple telescopic rods and the corresponding shock-absorbing springs can be adaptively extended and retracted, thereby converting the vibration of the mounting plate into the elastic potential energy of the shock-absorbing spring, thereby reducing the impact of the vibration on the UAV and ensuring the relative stability of the UAV flight;

[0018] 2. The present invention is provided with a counterweight block. During the flight of the drone, the counterweight block can always remain in a vertical state under the action of gravity. When the fuel in the drone tank hits the inner wall of the tank due to the acceleration or deceleration of the drone, the counterweight block can always maintain a relatively stable vertical state at the bottom of the drone due to the effect of inertia, thereby playing a certain stabilizing role on the drone, reducing the impact of the fuel impacting the tank on the flight state of the drone, and improving the stability of the drone flight;

[0019] 3. The present invention is provided with a protective cover, so that when the drone is not in use, the engine and the generator can be protected by the protective cover, thereby preventing the engine and the generator from colliding with external objects during the storage of the drone. When the drone falls into the water due to an emergency, the first magnetic ring can be adsorbed together with the second magnetic ring, so that the engine and the generator can be protected by the protective cover, thereby protecting the engine and the generator from being soaked in water;

[0020] 4. The present invention is provided with a bow-shaped spring piece. When the protective cover drives the first magnetic ring to separate from the second magnetic ring, as the protective cover moves downward to the maximum displacement, the bow-shaped spring piece can keep in contact with the first on the protective cover. Therefore, when the engine vibrates during the flight of the UAV, the vibration will be transmitted to the protective cover along the limit column. At this time, the bow-shaped spring piece can absorb the vibration generated by the protective cover, and further assist the shock-absorbing spring to reduce the impact of the vibration on the UAV.

[0021] 5. The present invention is provided with a retaining ring. When the UAV is flying, the retaining ring can be blocked between the top edge of the protective cover and the bottom edge of the fuselage, thereby preventing rain from entering the inside of the protective cover through the gap between the protective cover and the fuselage when flying in rainy days, and when air enters the air inlet, the airflow can enter the inside of the retaining ring through the gap between the first guide plate and the second guide plate under the guiding effect of the first guide plate and the second guide plate, thereby cooling the engine. In addition, since a water retaining strip is provided on the top edge of the second guide plate, when part of the rain is blown onto the engine along the second guide plate driven by the airflow, the water retaining strip can block the rain, thereby preventing the rain from entering the inside of the protective cover along the airflow. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 It is a schematic diagram of the bottom three-dimensional structure of the fuselage in the present invention;

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

[0025] Figure 4 The present invention Figure 3 A magnified view of part A;

[0026] Figure 5 It is a three-dimensional schematic diagram of part of the shock absorbing assembly in the present invention;

[0027] Figure 6 It is a three-dimensional schematic diagram of all structures in the installation slot of the present invention;

[0028] Figure 7 The present invention Figure 6 A magnified view of part B;

[0029] Figure 8 It is a three-dimensional schematic diagram of the mounting plate, the engine, the generator, the limit column and the bottom plate in the present invention;

[0030] Fig. 9 is a three-dimensional schematic diagram of the protection component in the present invention;

[0031] Fig.10It is a three-dimensional schematic diagram of the retaining ring, the first guide plate, the second guide plate and the water retaining strip in the present invention.

[0032] In the figure: 1. fuselage; 2. mounting plate; 3. first connecting block; 4. first connecting ball; 5. first connecting column; 6. shock absorbing assembly; 61. telescopic rod; 62. shock absorbing spring; 63. fixing plate; 64. second connecting ball; 65. second connecting column; 66. limit plate; 67. limit tube; 7. engine; 8. motor; 9. limit column; 10. bottom plate; 11. protection assembly; 111. protective cover; 112. limit block; 113. partition; 114. second connecting block; 115. third connecting ball; 116. counterweight; 117. first magnetic ring; 118. second magnetic ring; 12. fixing ring; 13. bow-shaped spring piece; 14. retaining ring; 15. first guide plate; 16. second guide plate; 17. water retaining strip; 18. sealing ring; 19. roller shaft. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments.

[0034] The present invention provides Figures 1 to 10 A hybrid electric device for unmanned aerial vehicle shown in the figure comprises a fuselage 1, a mounting groove is provided at the bottom of the fuselage 1, a mounting plate 2 is horizontally arranged in the mounting groove, a first connecting block 3 is fixedly connected to the middle position of the top of the mounting plate 2, a first connecting ball 4 is rotatably connected to the top of the first connecting block 3, a first connecting column 5 is fixedly connected to the top of the first connecting ball 4, the first connecting column 5 is fixedly connected to the top groove wall of the mounting groove, mounting holes are provided at the top groove wall of the mounting groove and the four corners of the top of the mounting plate 2, a shock absorbing assembly 6 is arranged in the mounting hole, an engine 7 and a generator 8 are installed at the bottom of the mounting plate 2, and the output shaft of the engine 7 and the input shaft of the generator 8 are connected together by belt drive, and the positions near the four corners of the bottom of the mounting plate 2 are vertically fixedly connected to limiting columns 9, a bottom plate 10 is fixedly connected between the bottom ends of a plurality of the limiting columns 9, and a protective assembly 11 is arranged at the bottom of the bottom plate 10;

[0035] The shock absorbing assembly 6 comprises a telescopic rod 61, which is fixedly connected to the inner wall at the top of the mounting hole, and a shock absorbing spring 62 is sleeved on the telescopic rod 61, and a fixing plate 63 matching the size of the mounting hole opening is fixedly sleeved near the bottom end of the telescopic rod 61, the edge of the fixing plate 63 protrudes upward, and the height of the upward protruding part of the fixing plate 63 is greater than the maximum telescopic amount of the shock absorbing spring 62, and the two ends of the shock absorbing spring 62 are respectively fixedly connected to the top of the fixing plate 63 and the top of the telescopic rod 61, and a second connecting ball 64 is rotatably installed at the bottom end of the telescopic rod 61, and a second connecting column 65 is fixedly connected to the bottom of the second connecting ball 64, and a limiting plate 66 is fixedly connected to the bottom end of the second connecting column 65, and a limiting tube 67 is sleeved on the outer side of the limiting plate 66, and the limiting tube 67 is fixedly connected to the top of the mounting plate 2, and the top edge of the limiting tube 67 protrudes in the direction close to the second connecting column 65, and the diameter of the limiting plate 66 is between the inner diameter of the top and bottom ends of the limiting tube 67;

[0036] By providing the shock absorbing assembly 6, during the flight of the UAV, as the engine 7 works, the vibration generated by the engine 7 can be transmitted to the mounting plate 2, and when the mounting plate 2 is vibrated, the mounting plate 2 can deflect to a certain extent with the first connecting ball 4 as the center, and as the mounting plate 2 deflects, the side of the mounting plate 2 that deflects downward can pull the second connecting column 65 and the telescopic rod 61 through the limiting tube 67, and as the telescopic rod 61 is stretched, the shock absorbing spring 62 can also be stretched accordingly;

[0037] The side of the mounting plate 2 that deflects upward can push the second connecting column 65 and the telescopic rod 61 through the limit plate 66, so that the telescopic rod 61 can be compressed. As the telescopic rod 61 is compressed, the shock absorbing spring 62 can also be compressed. As the mounting plate 2 deflects as described above, the mounting plate 2 can convert the vibration it receives into the elastic potential energy of the shock absorbing spring 62, thereby reducing the impact of the vibration on the drone and ensuring the relative stability of the drone's flight.

[0038] During the deflection of the above-mentioned mounting plate 2, the limit plate 66 can move slightly in the limit tube 67, and the second connecting column 65 can drive the second connecting ball 64 to deflect at a certain angle with the center of the second connecting ball 64 as the center, thereby meeting the extension or shortening operation requirements of the telescopic rod 61.

[0039] like Figures 6 to 9As shown, the protective assembly 11 includes a protective cover 111, which is slidably sleeved on the outer side of the bottom plate 10, and a plurality of limit blocks 112 are fixedly connected to the inner wall of the side of the protective cover 111, and the plurality of limit blocks 112 are respectively slidably sleeved on a plurality of limit columns 9, and a partition 113 matching the size of the top opening of the protective cover 111 is horizontally fixedly connected to the inner side of the protective cover 111, and a second connecting block 114 is fixedly connected to the bottom center of the partition 113, and a third connecting ball 115 is rotatably installed at the bottom end of the second connecting block 114, and a conical counterweight block 116 is fixedly connected to the bottom of the third connecting ball 115, and the tip of the counterweight block 116 faces downward, and the protective cover 11 1 is fixedly sleeved with a rectangular first magnetic ring 117 on the outside, and a second magnetic ring 118 matching the first magnetic ring 117 is fixedly connected to the side wall of the installation groove. The second magnetic ring 118 has a magnetic pole opposite to the first magnetic ring 117, and the second magnetic ring 118 can be adsorbed together with the first magnetic ring 117. A sealing ring 18 is fixedly connected to the inside of the second magnetic ring 118, and when the first magnetic ring 117 and the second magnetic ring 118 are adsorbed together, the sealing ring 18 is just in close contact with the top edge of the protective cover 111, the diameter of the lower half of the protective cover 111 gradually decreases from top to bottom, and the buoyancy generated by the protective cover 111 is greater than the weight of the counterweight 116 and the protective cover 111 itself;

[0040] By providing the protection component 11, when the drone is not in use, the protection cover 111 can be inserted into the installation groove, and the first magnetic ring 117 on the protection cover 111 is adsorbed together with the second magnetic ring 118 in the installation groove, so as to fix the protection cover 111. At this time, the engine 7 and the generator 8 can be protected by the protection cover 111, thereby preventing the engine 7 and the generator 8 from colliding with external objects during the process of storing the drone.

[0041] When the drone is flying, the protective cover 111 can be pulled downward so that the protective cover 111 remains separated from the bottom of the fuselage 1. At this time, during the flight of the drone, the external airflow can smoothly enter the bottom of the fuselage 1, thereby cooling the engine 7. In addition, since a counterweight 116 is provided in the protective cover 111, during the flight of the drone, the counterweight 116 can always remain in a vertical state under the action of gravity. When the fuel in the drone tank hits the inner wall of the tank due to the acceleration or deceleration of the drone, due to the effect of inertia, the counterweight 116 can always remain in a relatively stable vertical state at the bottom of the drone, thereby playing a certain stabilizing role on the drone, reducing the impact of the fuel impacting the tank on the flight state of the drone, and improving the stability of the drone flight.

[0042] In addition, during the flight of the UAV, when an emergency situation or insufficient battery life occurs and there is a water source below the UAV, as the UAV lands on the water, the protective cover 111 can move upward under the action of buoyancy. During this process, as the protective cover 111 moves upward, the first magnetic ring 117 can also gradually approach the second magnetic ring 118 as the protective cover 111 moves upward. When the first magnetic ring 117 and the second magnetic ring 118 approach each other, the first magnetic ring 117 can be adsorbed together with the second magnetic ring 118, and the top edge of the protective cover 111 can also be pressed together with the sealing ring 18, so that the engine 7 and the generator 8 are protected by the protective cover 111, thereby protecting the engine 7 and the generator 8 from being soaked in water.

[0043] like Figure 2 As shown, a fixing ring 12 is installed at the bottom of the fuselage 1, and the mounting groove is located at the inner center of the fixing ring 12. A plurality of bow-shaped spring pieces 13 are evenly fixedly connected to the bottom of the fixing ring 12. The bow-shaped spring pieces 13 protrude in a direction close to the protective cover 111, and when the protective cover 111 moves downward to the maximum displacement, the bottom end of the bow-shaped spring piece 13 fits with the bottom edge of the first magnetic ring 117;

[0044] By providing the bow-shaped spring piece 13, when the protective cover 111 drives the first magnetic ring 117 to separate from the second magnetic ring 118, as the protective cover 111 moves downward to the maximum displacement, the bow-shaped spring piece 13 can be kept in contact with the first on the protective cover 111, so that when the engine 7 vibrates during the flight of the UAV, the vibration will be transmitted to the protective cover 111 along the limit column 9. At this time, the bow-shaped spring piece 13 can absorb the vibration generated by the protective cover 111, and further can assist the shock-absorbing spring 62 to reduce the impact of the vibration on the UAV;

[0045] In addition, during the flight of the drone, since the protective cover 111 is also affected by the airflow, the bow-shaped spring pieces 13 can also dampen the protective cover 111, reduce the impact of the airflow on the protective cover 111, and ensure the relative stability of the drone flight.

[0046] like Figure 1 and Fig.10As shown, a baffle ring 14 is arranged on the periphery of the fixing ring 12, the baffle ring 14 is fixedly connected to the bottom of the fuselage 1, and the bottom edge of the baffle ring 14 is always higher than the top edge of the protective cover 111, a strip-shaped heat dissipation hole is opened on the rear side of the baffle ring 14, an air inlet is opened on the front side of the baffle ring 14, a first guide plate 15 and a second guide plate 16 are fixedly connected between the inner walls on both sides of the air inlet, the first guide plate 15 is located on the top of the second guide plate 16, and the bottom edge of the first guide plate 15 and the top edge of the second guide plate 16 are both inclined in the direction close to the protective cover 111, the top edge of the second guide plate 16 is closer to the protective cover 111 than the bottom edge of the first guide plate 15, and a water retaining strip 17 matching its length is fixedly connected to the top edge of the second guide plate 16;

[0047] By providing the retaining ring 14, when the protective cover 111 is separated from the fuselage 1 under the action of gravity, the retaining ring 14 can be blocked between the top edge of the protective cover 111 and the bottom edge of the fuselage 1, thereby preventing rainwater from entering the inner side of the protective cover 111 through the gap between the protective cover 111 and the fuselage 1 when flying in rainy days;

[0048] At the same time, by opening an air inlet on the front side of the retaining ring 14, during the flight of the UAV, when the air enters the air inlet, the airflow can enter the inner side of the retaining ring 14 through the gap between the first guide plate 15 and the second guide plate 16 under the guiding effect of the first guide plate 15 and the second guide plate 16, thereby cooling the engine 7, and because the top edge of the second guide plate 16 is provided with a water retaining strip 17, when part of the rainwater is blown onto the engine 7 along the second guide plate 16 driven by the airflow, the water retaining strip 17 can block the rainwater, thereby preventing the rainwater from entering the inner side of the protective cover 111 along the airflow.

[0049] like Figure 6 and Fig. 9 As shown, the outer sides of the four sides of the first magnetic ring 117 are horizontally provided with strip grooves, and a roller 19 is rotatably installed between the inner walls of the two sides of the strip groove. The side of the roller 19 away from the protective cover 111 is located outside the strip groove, and the roller 19 can contact the bow-shaped spring piece 13;

[0050] By providing a roller 19, when the first magnetic ring 117 contacts the bow-shaped spring piece 13 during the up and down movement of the protective cover 111, the roller 19 can replace the first magnetic ring 117 to rub against the bow-shaped spring piece 13, thereby converting the sliding friction between the first magnetic ring 117 and the bow-shaped spring piece 13 into rolling friction between the bow-shaped spring piece 13 and the roller 19, thereby reducing the friction and protecting the first magnetic ring 117 and the bow-shaped spring piece 13.

[0051] The present invention also provides a UAV, comprising the above-mentioned UAV oil-electric hybrid power device.

[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them.

Claims

1. A hybrid electric power device for an unmanned aerial vehicle, comprising a fuselage (1), characterized in that: The bottom of the fuselage (1) is provided with a mounting groove, a mounting plate (2) is horizontally arranged in the mounting groove, a first connecting block (3) is fixedly connected to the middle position of the top of the mounting plate (2), a first connecting ball (4) is rotatably connected to the top of the first connecting block (3), a first connecting column (5) is fixedly connected to the top of the first connecting ball (4), the first connecting column (5) is fixedly connected to the top groove wall of the mounting groove, mounting holes are provided at positions of the top groove wall of the mounting groove and the four corners of the top of the mounting plate (2), a shock absorbing assembly (6) is arranged in the mounting hole, an engine (7) and a generator (8) are installed at the bottom of the mounting plate (2), and the output shaft of the engine (7) and the input shaft of the generator (8) are connected together through a belt drive, and the positions of the bottom of the mounting plate (2) near the four corners are vertically fixedly connected to limit columns (9), a bottom plate (10) is fixedly connected between the bottom ends of the plurality of limit columns (9), and a protective assembly (11) is arranged at the bottom of the bottom plate (10).

2. The hybrid power device for unmanned aerial vehicle according to claim 1, characterized in that: The shock absorbing assembly (6) comprises a telescopic rod (61), the telescopic rod (61) being fixedly connected to the inner wall at the top of the mounting hole, and a shock absorbing spring (62) being sleeved on the telescopic rod (61), a fixing plate (63) matching the size of the mounting hole opening being fixedly sleeved at a position near the bottom end of the telescopic rod (61), the edge of the fixing plate (63) protruding upward, and the height of the upward protruding portion of the fixing plate (63) being greater than the maximum telescopic amount of the shock absorbing spring (62), and the two ends of the shock absorbing spring (62) being respectively fixed to the top of the fixing plate (63) and the top end of the telescopic rod (61). The bottom end of the telescopic rod (61) is rotatably mounted with a second connecting ball (64), the bottom of the second connecting ball (64) is fixedly connected with a second connecting column (65), the bottom end of the second connecting column (65) is fixedly connected with a limiting plate (66), the outer side of the limiting plate (66) is sleeved with a limiting tube (67), the limiting tube (67) is fixedly connected to the top of the mounting plate (2), the top edge of the limiting tube (67) protrudes in a direction close to the second connecting column (65), and the diameter of the limiting plate (66) is between the inner diameter of the top end and the bottom end of the limiting tube (67).

3. The hybrid power device for unmanned aerial vehicle according to claim 1, characterized in that: The protection assembly (11) comprises a protection cover (111), the protection cover (111) is slidably sleeved on the outside of the bottom plate (10), a plurality of limit blocks (112) are fixedly connected to the inner wall of the side of the protection cover (111), and the plurality of limit blocks (112) are respectively slidably sleeved on the plurality of limit columns (9), a partition (113) matching the size of the top opening of the protection cover (111) is horizontally fixedly connected to the inside of the protection cover (111), a second connection block (114) is fixedly connected at the bottom center of the partition (113), and the second connection block (114) ) is rotatably mounted on the bottom end of the third connecting ball (115), the bottom of the third connecting ball (115) is fixedly connected to a conical counterweight (116), and the tip of the counterweight (116) faces downwards, a rectangular first magnetic ring (117) is fixedly sleeved on the outer side of the protective cover (111), and a second magnetic ring (118) matching the first magnetic ring (117) is fixedly connected to the side wall of the installation groove, the second magnetic ring (118) has an opposite magnetic pole to the first magnetic ring (117), and the second magnetic ring (118) can be adsorbed together with the first magnetic ring (117).

4. The hybrid power device for unmanned aerial vehicle according to claim 3, characterized in that: A fixing ring (12) is installed at the bottom of the fuselage (1), and the installation groove is located at the inner center of the fixing ring (12). A plurality of bow-shaped spring pieces (13) are evenly fixedly connected to the bottom of the fixing ring (12). The bow-shaped spring pieces (13) protrude in a direction close to the protective cover (111), and when the protective cover (111) moves downward to a maximum displacement position, the bottom end of the bow-shaped spring piece (13) fits with the bottom edge of the first magnetic ring (117).

5. The hybrid power device for unmanned aerial vehicle according to claim 4, characterized in that: A baffle ring (14) is arranged on the periphery of the fixing ring (12); the baffle ring (14) is fixedly connected to the bottom of the fuselage (1), and the bottom edge of the baffle ring (14) is always higher than the top edge of the protective cover (111); a strip-shaped heat dissipation hole is provided on the rear side of the baffle ring (14); an air inlet is provided on the front side of the baffle ring (14); a first guide plate (15) and a second guide plate (16) are fixedly connected between the inner walls on both sides of the air inlet; the first guide plate (15) is located on the top of the second guide plate (16), and the bottom edge of the first guide plate (15) and the top edge of the second guide plate (16) are both inclined in a direction close to the protective cover (111); the top edge of the second guide plate (16) is closer to the protective cover (111) than the bottom edge of the first guide plate (15), and a water retaining strip (17) having a length matching that of the second guide plate (16) is fixedly connected to the top edge of the second guide plate (16).

6. The hybrid power device for unmanned aerial vehicle according to claim 5, characterized in that: The diameter of the lower half of the protective cover (111) gradually decreases from top to bottom, and the buoyancy generated by the protective cover (111) is greater than the weight of the counterweight (116) and the protective cover (111) itself.

7. The hybrid power device for unmanned aerial vehicle according to claim 6, characterized in that: A sealing ring (18) is fixedly connected to the inner side of the second magnetic ring (118), and when the first magnetic ring (117) and the second magnetic ring (118) are adsorbed together, the sealing ring (18) is exactly in close contact with the top edge of the protective cover (111).

8. The hybrid power device for unmanned aerial vehicle according to claim 7, characterized in that: The outer sides of the four sides of the first magnetic ring (117) are horizontally provided with strip grooves, and a roller (19) is rotatably mounted between the inner walls on both sides of the strip groove, and the side of the roller (19) away from the protective cover (111) is located outside the strip groove, and the roller (19) can contact the bow-shaped spring piece (13).

9. An unmanned aerial vehicle, comprising the unmanned aerial vehicle oil-electric hybrid power device according to any one of claims 1 to 8.

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