Solar-powered endurance unmanned aerial vehicle

Abstract

This invention relates to the technical field of aerospace engineering and discloses a solar-powered unmanned aerial vehicle (UAV), comprising a fuselage, wings respectively adapted and installed on the outer surfaces of both sides of the fuselage, a photovoltaic panel fixedly connected to the top of the fuselage, a camera fixedly installed on the inner surface of the fuselage, outriggers respectively fixedly connected to the bottom of both sides of the fuselage, and tires respectively disposed on the lower sides of both sides of the fuselage. Through the cooperation of the load-bearing components and the drive components, this invention enables the tires to be moved to the back of the fuselage during flight, significantly reducing air resistance during flight. By reducing air resistance, the energy consumed by the aircraft during flight is reduced. The ability to disassemble and assemble the components allows operators to quickly adjust the tire type according to different landing environments, enabling rapid tire replacement for tasks such as environmental monitoring, geographic mapping, and emergency rescue.

Description

Technical Field

[0001] This invention relates to the technical field of aerospace engineering, and more particularly to a solar-powered unmanned aerial vehicle. Background Technology

[0002] In recent years, with the development of solar cell technology, a more powerful energy source has been provided for solar-powered unmanned aerial vehicles (UAVs). These high-efficiency solar cells can better convert sunlight into electrical energy, thereby increasing the flight time of the aircraft. Many solar-powered UAVs use lightweight and high-strength materials such as carbon fiber composites, making the structure of the fuselage lighter and stronger, which helps to improve flight efficiency and payload capacity.

[0003] Some existing solar-powered unmanned aerial vehicles (UAVs) typically retract their landing gear into the fuselage. While this method reduces air resistance, improves flight efficiency, and increases endurance, it can take up valuable internal space for solar-powered aircraft that rely on high-efficiency batteries for extended flight, thus affecting battery installation space. Furthermore, the landing gear tires of some solar-powered UAVs often have the drawback of being difficult to replace flexibly. Different landing environments may require different types of tires (e.g., smooth tires on hard surfaces to reduce rolling resistance, and tires with deep treads on soft ground to increase traction). If the tires are not easy to replace, it may limit the aircraft's adaptability to various ground conditions. Summary of the Invention

[0004] In view of the problems existing in the current solar-powered unmanned aerial vehicles, the present invention is proposed.

[0005] Therefore, the purpose of this invention is to provide a solar-powered unmanned aerial vehicle.

[0006] To solve the above-mentioned technical problems, the present invention provides the following technical solution: including, The aircraft body includes a fuselage, wings respectively adapted to be installed on the outer surfaces of both sides of the fuselage, a photovoltaic panel fixedly connected to the top of the fuselage, a camera fixedly installed on the inner surface of the fuselage, outriggers respectively fixedly connected to the bottom of both sides of the fuselage, and tires respectively disposed on the lower sides of both sides of the fuselage. The take-up and take-down mechanism includes a support component fixedly connected to the bottom of the body, a drive component disposed on the surface of the body and used to take the tires off and put them on from the back of the body, and a disassembly and assembly component disposed on the outer surface of the drive component and used to quickly change different types of tires. The load-bearing component includes a connecting column fixedly installed at the bottom of the fuselage, and a fixing plate fixedly connected to the other end of the connecting column; The drive assembly includes an inlet cylinder adapted to be installed on the top of the connecting column, a connecting block fixedly installed on the output end of the inlet cylinder, a rack fixedly connected to the outer end face of the connecting block, a gear meshing with the outer surface of the rack, a drive rod fixedly connected to the inner surface of the gear, universal joints fixedly connected to both ends of the drive rod, a transmission rod fixedly installed on the other end of the universal joint, a swing arm fixedly connected to the inner surface of the transmission rod, and support blocks fixedly connected to the bottom of both sides of the connecting column and used in conjunction with the transmission rod. When the output end of the top-inlet cylinder is fully extended, it can drive the swing arm to move to a position parallel to the bottom of the fuselage, and through the disassembly and assembly assembly, drive the tire to move to the back of the fuselage to reduce wind resistance during flight.

[0007] As a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the fuselage is provided with a battery for use with the photovoltaic panel, and the outriggers are used to support the fuselage when the tires are retracted.

[0008] As a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the connecting column further includes a limiting groove formed at the top of the connecting column and used in conjunction with the rack, and a sliding groove formed at the bottom of the connecting column and used in conjunction with the connecting block.

[0009] In a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the outer surface of the connecting block is in sliding contact with the inner surface of the slide groove, and the rack is slidably connected to the inner wall of the limiting groove.

[0010] In a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, a rotating bearing sleeve is installed at the connection between the drive rod and the connecting column, and the outer end face of the transmission rod is fixedly mounted on the outer surface of the support block by a bearing.

[0011] As a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the assembly includes: a mounting shaft fixedly mounted on the outer surface of the swing arm via a bearing, a star-shaped guide rail fixedly connected to the other end of the mounting shaft, a fixing block fixedly mounted on the outer surface of the star-shaped guide rail, and a worm gear rotatably connected to the inner surface of the fixing block.

[0012] As a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the disassembly and assembly assembly further includes a worm wheel meshing with the outer surface of the worm, a plurality of arc-shaped grooves arranged in a circumferential array on the outer surface of the worm wheel, a limiting post located inside the arc-shaped groove, and a sliding rod fixedly connected to the outer end face of the limiting post and located inside the star-shaped guide rail.

[0013] As a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the disassembly and assembly assembly further includes a support plate fixedly connected to the outer end face of the sliding rod and used in conjunction with the tire, and a positioning column fixedly installed on the outer surface of the star-shaped guide rail and used in conjunction with the worm gear.

[0014] In a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the outer surface of the limiting post slides in contact with the inner wall of the arc-shaped groove, and the outer surface of the sliding rod slides in contact with the inner wall of the star-shaped guide rail.

[0015] In a preferred embodiment of the solar-powered unmanned aerial vehicle of the present invention, the outer surface of the support disk is in contact with the inner surface of the tire, and the worm gear is rotatably sleeved on the outer surface of the positioning post.

[0016] The beneficial effects of this invention are as follows: By cooperating with the support component and the drive component, the tires can be moved to the back of the fuselage during the flight of the aircraft, significantly reducing air resistance during flight. By reducing air resistance, the energy consumed by the aircraft during flight is reduced, thereby improving the flight efficiency and endurance of the aircraft. By disassembling and assembling the components, operators can quickly adjust the type of tires according to different landing environments of the aircraft. Whether performing tasks such as environmental monitoring, geographic mapping, or emergency rescue, the tires of the aircraft can be changed in a short time, thereby greatly improving the adaptability and mission execution flexibility of the aircraft. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein: Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0018] Figure 2 This is a structural schematic diagram of the invention from another perspective.

[0019] Figure 3 For the present invention Figure 2 A magnified schematic diagram of the local structure at point A in the middle.

[0020] Figure 4 This is a schematic diagram of the overall structure of the take-up and take-down mechanism in this invention.

[0021] Figure 5 For the present invention Figure 4 A magnified schematic diagram of the local structure at point B.

[0022] Figure 6 This is a schematic diagram of the overall structure of the disassembly and assembly components in this invention.

[0023] Figure 7 This is a schematic diagram of the internal structure of the star-shaped guide rail in this invention.

[0024] In the diagram: 100, Aircraft body; 101, Fuselage; 102, Wing; 103, Photovoltaic panel; 104, Camera; 105, Outriggers; 106, Tires; 200, Retraction and deployment mechanism; 201, Load-bearing component; 201a, Connecting column; 201b, Fixing plate; 201c, Limiting groove; 201d, Slide groove; 202, Drive component; 202a, Top-in cylinder; 202b, Connecting block; 202c, Rack; 20 2d, Gear; 202e, Drive rod; 202f, Universal joint; 202g, Transmission rod; 202h, Swing arm; 202i, Support block; 203, Assembly / disassembly assembly; 203a, Mounting shaft; 203b, Star guide rail; 203c, Fixing block; 203d, Worm gear; 203e, Worm wheel; 203f, Arc groove; 203g, Limiting post; 203h, Sliding rod; 203i, Support plate; 203j, Positioning post. Detailed Implementation

[0025] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0026] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0027] 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 one 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 is mutually exclusive with other embodiments.

[0028] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, 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 the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0029] Example 1 Reference Figures 1-5This is the first embodiment of the present invention, which provides a solar-powered unmanned aerial vehicle, the device comprising: The aircraft body 100 includes a fuselage 101, wings 102 respectively adapted to be installed on the outer surfaces of both sides of the fuselage 101, a photovoltaic panel 103 fixedly connected to the top of the fuselage 101, a camera 104 fixedly installed on the inner surface of the fuselage 101, legs 105 respectively fixedly connected to the bottom of both sides of the fuselage 101, and tires 106 respectively disposed on the lower sides of both sides of the fuselage 101. It should be noted that the fuselage 101 is the main structure of the entire aircraft body 100 and is used to install other components. The wings 102 are used to provide lift, the photovoltaic panels 103 are used to collect solar energy and convert it into electrical energy, the camera 104 is used for shooting and monitoring, the outriggers 105 are used to support the fuselage 101 when the tires 106 are retracted, and the tires 106 are used to cushion the take-off, landing and movement of the aircraft body 100.

[0030] The take-up and take-down mechanism 200 includes a support component 201 fixedly connected to the bottom of the body 101, a drive component 202 disposed on the surface of the body 101 and used to take up and put down the tire 106 from the back of the body 101, and a disassembly and assembly component 203 disposed on the outer surface of the drive component 202 and used to quickly change different types of tires 106. The load-bearing component 201 includes a connecting column 201a fixedly installed at the bottom of the body 101, and a fixing plate 201b fixedly connected to the other end of the connecting column 201a.

[0031] The drive assembly 202 includes an inlet cylinder 202a adapted to be installed on the top of the connecting column 201a, a connecting block 202b fixedly installed on the output end of the inlet cylinder 202a, a rack 202c fixedly connected to the outer end face of the connecting block 202b, a gear 202d meshing with the outer surface of the rack 202c, a drive rod 202e fixedly connected to the inner surface of the gear 202d, a universal joint 202f fixedly connected to both ends of the drive rod 202e, a transmission rod 202g fixedly installed on the other end of the universal joint 202f, a swing arm 202h fixedly connected to the inner surface of the transmission rod 202g, and support blocks 202i fixedly connected to the bottom of both sides of the connecting column 201a and used in conjunction with the transmission rod 202g. It should be noted that the connecting column 201a is used to connect the fixing plate 201b, and the fixing plate 201b is used to support the drive assembly 202. When the output end of the jacking cylinder 202a extends, it can drive the rack 202c to move linearly along the limiting groove 201c. The rack 202c drives the gear 202d and the drive rod 202e to rotate. Then, the support block 202i limits the transmission rod 202g, so that the drive rod 202e drives the transmission rod 202g, the swing arm 202h, the disassembly assembly 203 and the tire 106 to rotate synchronously through the universal joint 202f.

[0032] When the output end of the jacking cylinder 202a is fully extended, it can drive the swing arm 202h to move to a position parallel to the bottom of the fuselage 101, and drive the tire 106 to the back of the fuselage 101 through the disassembly and assembly component 203 to reduce wind resistance during flight.

[0033] Specifically, the inner cavity of the fuselage 101 is equipped with a battery for use with the photovoltaic panel 103, and the outriggers 105 are used to support the fuselage 101 when the tires 106 are retracted.

[0034] Furthermore, the connecting post 201a also includes a limiting groove 201c opened at the top of the connecting post 201a and used in conjunction with the rack 202c, and a sliding groove 201d opened at the bottom of the connecting post 201a and used in conjunction with the connecting block 202b.

[0035] The outer surface of the connecting block 202b is in sliding contact with the inner surface of the slide groove 201d, and the rack 202c is slidably connected to the inner wall of the limiting groove 201c.

[0036] Preferably, a rotating bearing sleeve is installed at the connection between the drive rod 202e and the connecting column 201a, and the outer end face of the transmission rod 202g is fixedly installed on the outer surface of the support block 202i by the bearing.

[0037] During use, in the flight preparation phase: before flight, the tires 106 are located on both sides of the fuselage 101. At this time, the outriggers 105 are suspended in the air, while the photovoltaic panels 103 begin to collect solar energy and convert it into electrical energy, which is stored in the battery inside the fuselage 101 to provide energy support for subsequent flight. When the aircraft body 100 takes off: the jacking cylinder 202a is activated, so that the output end of the jacking cylinder 202a is fully extended, and the connecting block 202b is driven to move linearly along the limiting groove 201c. The connecting block 202b drives the rack 202c to move synchronously, and the rack 202c drives the gear 202d to rotate accordingly. The rotation of the gear 202d is transmitted to the universal joints 202f at both ends through the drive rod 202e, and then the universal joints 202f drive the transmission rod 202g to rotate. The rotation of the transmission rod 202g finally drives the disassembly and assembly assembly 203 and the tire 106 to rotate synchronously through the swing arm 202h. During this process: the support block 202i limits the transmission rod 202g, ensuring that the transmission rod 202g can only rotate around the predetermined axis and will not deviate from the track; As the output end of the top-mounted cylinder 202a is fully extended, the swing arm 202h and the disassembly assembly 203 are moved to a position parallel to the bottom of the fuselage 101. At this time, the disassembly assembly 203 will drive the tire 106 to move to the back of the fuselage 101 to reduce air resistance during flight and improve flight efficiency. When the aircraft body 100 completes its mission and needs to land: the output end of the control jacking cylinder 202a retracts, a process opposite to that during takeoff: the rack 202c slides in the opposite direction along the limiting groove 201c, driving the gear 202d to rotate in the opposite direction, thereby causing the drive rod 202e, universal joint 202f, transmission rod 202g, and swing arm 202h to rotate in the opposite direction in sequence. Finally, the disassembly and assembly assembly 203 moves the tires 106 back to their original positions on both sides of the fuselage 101 to facilitate a smooth landing of the aircraft body 100. After the aircraft body 100 stops gliding, the outriggers 105 take over the task of supporting the fuselage, enabling the aircraft body 100 to remain stable on the ground.

[0038] In summary, through the cooperation of the support component 201 and the drive component 202, the tires 106 can be moved to the back of the fuselage 101 during the flight of the aircraft body 100, which significantly reduces air resistance during flight. By reducing air resistance, the energy consumed by the aircraft body 100 during flight is reduced, thereby improving the flight efficiency and endurance of the aircraft body 100.

[0039] Example 2 Reference Figure 3 , Figure 4 , Figure 6 and Figure 7 This is a second embodiment of the present invention, which differs from the first embodiment in that: this embodiment provides a disassembly and assembly assembly 203 that can quickly replace different types of tires 106 according to different landing environments.

[0040] It should be noted that the disassembly and assembly assembly 203 includes a mounting shaft 203a fixedly mounted on the outer surface of the swing arm 202h via a bearing, a star-shaped guide rail 203b fixedly connected to the other end of the mounting shaft 203a, a fixing block 203c fixedly mounted on the outer surface of the star-shaped guide rail 203b, and a worm gear 203d rotatably connected to the inner surface of the fixing block 203c.

[0041] It should also be noted that the mounting shaft 203a serves as a bridge connecting the swing arm 202h and the star-shaped guide rail 203b, ensuring that the entire assembly 203 can rotate synchronously under the drive of the swing arm 202h. The fixing block 203c is used to install the worm gear 203d.

[0042] Furthermore, the disassembly and assembly assembly 203 also includes a worm wheel 203e meshing with the outer surface of the worm 203d, a plurality of arc-shaped grooves 203f arranged in a circumferential array on the outer surface of the worm wheel 203e, a limiting post 203g located inside the arc-shaped groove 203f, and a sliding rod 203h fixedly connected to the outer end face of the limiting post 203g and located inside the star-shaped guide rail 203b.

[0043] The rotation of the worm 203d directly drives the worm wheel 203e meshing with it, thereby triggering the subsequent extension and retraction of the support plate 203i. The arc-shaped groove 203f changes position with the rotation of the worm wheel 203e and provides a sliding path for the limiting post 203g, ensuring that the limiting post 203g moves along a predetermined trajectory. The shape of the star-shaped guide rail 203b is used to limit the sliding rod 203h, so that the sliding rod 203h can only expand or contract in a circular manner within it through the movement of the limiting post 203g, thereby achieving the effect of driving the support plate 203i to extend and retract.

[0044] Furthermore, the assembly / disassembly assembly 203 also includes a support plate 203i fixedly connected to the outer end face of the sliding rod 203h and used in conjunction with the tire 106, and a positioning column 203j fixedly installed on the outer surface of the star-shaped guide rail 203b and used in conjunction with the worm gear 203e.

[0045] It should be explained that the sliding rod 203h is responsible for transmitting the linear motion of the limiting post 203g to the support plate 203i, enabling it to extend and retract to load and unload the tire 106. The extension and retraction of the support plate 203i can achieve the effect of installing and removing the tire 106, allowing the aircraft body 100 to quickly change to a tire 106 type suitable for the current landing environment according to the actual situation.

[0046] Specifically, the outer surface of the limiting post 203g slides in contact with the inner wall of the arc groove 203f, and the outer surface of the sliding rod 203h slides in contact with the inner wall of the star-shaped guide rail 203b.

[0047] Preferably, the outer surface of the support plate 203i contacts the inner surface of the tire 106, and the worm gear 203e is rotated and sleeved on the outer surface of the positioning post 203j.

[0048] In use, manually rotating the worm 203d causes the worm wheel 203e to rotate, and the arc groove 203f moves accordingly, so that the limiting post 203g slides along the inner wall of the arc groove 203f, causing the sliding rod 203h to move inward. As the sliding rod 203h moves, the support plate 203i gradually detaches from the currently installed tire 106. At this time, the old tire 106 can be easily removed. After the new tire 106 is fitted onto the outside of the support plate 203i, the direction of the worm 203d is reversed, causing the worm wheel 203e to rotate in the opposite direction. Through the cooperation of the arc groove 203f and the limiting post 203g, the sliding rod 203h is pushed back to its original position, so that the support plate 203i can firmly support and fix the new tire 106.

[0049] In summary, by disassembling and assembling component 203, operators can quickly adjust the type of tires 106 according to different landing environments of the aircraft body 100. Whether performing tasks such as environmental monitoring, geographic mapping or emergency rescue, the tires 106 of the aircraft body 100 can be replaced in a short time, thereby greatly improving the adaptability and mission execution flexibility of the aircraft body 100.

[0050] It is important to note that the constructions and arrangements of this application shown in several different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, those who consult this disclosure will readily understand that many modifications are possible (e.g., changes in the size, dimensions, structure, shape, and proportions of various elements, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, orientation, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in this application). For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of elements may be inverted or otherwise altered, and the nature or number or position of discrete elements may be changed or altered. Therefore, all such modifications are intended to be included within the scope of the invention. The order or sequence of any process or method steps may be changed or rearranged according to alternative embodiments. In the claims, any "device plus function" clause is intended to cover the structure described herein that performs the function, and not only structurally equivalent but also equivalent in structure. Other substitutions, modifications, alterations, and omissions may be made in the design, operation, and arrangement of the exemplary embodiments without departing from the scope of the invention. Therefore, the present invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0051] Furthermore, in order to provide a concise description of exemplary embodiments, not all features of actual embodiments (i.e., those features that are not relevant to the currently considered best mode for carrying out the invention, or those features that are not relevant to implementing the invention) may be omitted.

[0052] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A solar-powered endurance unmanned aerial vehicle, characterized by: include, The aircraft body (100) includes a fuselage (101), wings (102) respectively adapted to be installed on the outer surfaces of both sides of the fuselage (101), a photovoltaic panel (103) fixedly connected to the top of the fuselage (101), a camera (104) fixedly installed on the inner surface of the fuselage (101), legs (105) respectively fixedly connected to the bottom of both sides of the fuselage (101), and tires (106) respectively disposed on the lower sides of both sides of the fuselage (101). The take-up and take-down mechanism (200) includes a support component (201) fixedly connected to the bottom of the body (101), a drive component (202) disposed on the surface of the body (101) and used to take up and put down the tire (106) from the back of the body (101), and a disassembly and assembly component (203) disposed on the outer surface of the drive component (202) and used to quickly replace different types of tires (106). The load-bearing component (201) includes a connecting column (201a) fixedly installed at the bottom of the fuselage (101) and a fixing plate (201b) fixedly connected to the other end of the connecting column (201a). The drive assembly (202) includes a top-inlet cylinder (202a) adapted to be installed on the top of the connecting column (201a), a connecting block (202b) fixedly installed on the output end of the top-inlet cylinder (202a), a rack (202c) fixedly connected to the outer end face of the connecting block (202b), a gear (202d) meshing with the outer surface of the rack (202c), a drive rod (202e) fixedly connected to the inner surface of the gear (202d), universal joints (202f) fixedly connected to both ends of the drive rod (202e), a transmission rod (202g) fixedly installed on the other end of the universal joint (202f), a swing arm (202h) fixedly connected to the inner surface of the transmission rod (202g), and support blocks (202i) fixedly connected to the bottom of both sides of the connecting column (201a) and used in conjunction with the transmission rod (202g). When the output end of the top-inlet cylinder (202a) is fully extended, it can drive the swing arm (202h) to move to a position parallel to the bottom of the fuselage (101), and drive the tire (106) to the back of the fuselage (101) through the disassembly assembly (203) to reduce wind resistance during flight.

2. The solar endurance unmanned aerial vehicle of claim 1, wherein: The inner cavity of the fuselage (101) is provided with a battery for use with the photovoltaic panel (103), and the support leg (105) is used to support the fuselage (101) when the tire (106) is retracted.

3. The solar endurance unmanned aerial vehicle of claim 2, wherein: The connecting post (201a) further includes a limiting groove (201c) opened at the top of the connecting post (201a) and used in conjunction with the rack (202c), and a sliding groove (201d) opened at the bottom of the connecting post (201a) and used in conjunction with the connecting block (202b).

4. The solar endurance unmanned aerial vehicle of claim 3, wherein: The outer surface of the connecting block (202b) slides in contact with the inner surface of the slide groove (201d), and the rack (202c) is slidably connected to the inner wall of the limiting groove (201c).

5. The solar endurance unmanned aerial vehicle of claim 4, wherein: A rotating bearing sleeve is installed at the connection between the drive rod (202e) and the connecting column (201a), and the outer end face of the transmission rod (202g) is fixedly installed on the outer surface of the support block (202i) by the bearing.

6. The solar endurance unmanned aerial vehicle of claim 5, wherein: The assembly / disassembly assembly (203) includes a mounting shaft (203a) fixedly mounted on the outer surface of the swing arm (202h) via a bearing, a star-shaped guide rail (203b) fixedly connected to the other end of the mounting shaft (203a), a fixing block (203c) fixedly mounted on the outer surface of the star-shaped guide rail (203b), and a worm gear (203d) rotatably connected to the inner surface of the fixing block (203c).

7. The solar endurance unmanned aerial vehicle of claim 6, wherein: The assembly / disassembly assembly (203) further includes a worm wheel (203e) meshing with the outer surface of the worm (203d), a plurality of arc-shaped grooves (203f) arranged in a circumferential array on the outer surface of the worm wheel (203e), a limiting post (203g) located inside the arc-shaped groove (203f), and a sliding rod (203h) fixedly connected to the outer end face of the limiting post (203g) and located inside the star-shaped guide rail (203b).

8. The solar endurance unmanned aerial vehicle of claim 7, wherein: The assembly / disassembly assembly (203) also includes a support plate (203i) fixedly connected to the outer end face of the sliding rod (203h) and used in conjunction with the tire (106), and a positioning pin (203j) fixedly installed on the outer surface of the star-shaped guide rail (203b) and used in conjunction with the worm gear (203e).

9. The solar-powered endurance unmanned aerial vehicle of claim 8, wherein: The outer surface of the limiting post (203g) slides in contact with the inner wall of the arc groove (203f), and the outer surface of the sliding rod (203h) slides in contact with the inner wall of the star-shaped guide rail (203b).

10. The solar-powered endurance unmanned aerial vehicle of claim 9, wherein: The outer surface of the support plate (203i) is in contact with the inner surface of the tire (106), and the worm gear (203e) is rotated and sleeved on the outer surface of the positioning post (203j).

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