A wing-extendable UAV

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles, and specifically relates to a wing-expandable unmanned aerial vehicle, comprising an unmanned aerial vehicle body, wherein the four corners of the unmanned aerial vehicle body are fixedly connected with mounting seats; a shell, wherein the shell is arranged in the mounting seat; a fixing mechanism, wherein the fixing mechanism is arranged between the mounting seat and the shell; a buffer mechanism, wherein the buffer mechanism is arranged at the lower end of the shell; and a flying mechanism, wherein the flying mechanism is arranged at the upper end of the shell; wherein the flying mechanism comprises a hollow shell, wherein the hollow shell is arranged above the shell, wherein a driving part is arranged at the lower end of the hollow shell, a wing part is arranged outside the hollow shell, a control part is arranged inside the shell, and a heat dissipation part is also arranged inside the hollow shell. The present invention can quickly install and disassemble the wing, and also has a simple wing expansion mechanism and an effective heat dissipation mechanism, thereby significantly improving the flight performance and practicality of the unmanned aerial vehicle.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to an unmanned aerial vehicle with expandable wings. Background Art

[0002] Currently, UAV technology is experiencing rapid development and is widely used in many fields. The wing design of a UAV has a significant impact on its flight performance. For example, when performing reconnaissance missions that require long-term flight, a smaller wing size may reduce flight efficiency; while in missions with heavier loads, a larger wing size can provide stronger lift support. Therefore, it is particularly important to develop a UAV that can adjust the wing size according to actual mission requirements.

[0003] There are also many types of retractable wings in the prior art, such as a wing retractable mechanism, wing and wing retractable method with application number: CN202310650714.6. Although the retractable function of the UAV wing is realized, its complex wing structure design leads to increased weight, which in turn has an adverse effect on the flight performance of the UAV.

[0004] Another example is a retractable wing drone with application number: CN202310114977.5, which also realizes the retractability of the drone wings. However, its motor needs to drive the power shaft and the fixed center tube to rotate, and the rotation of the fixed center tube will drive the fixed propeller and the retractable propeller to rotate together, thereby realizing the take-off of the drone. At the same time, the rotation of the DC brushless motor will drive the rotating support, electric push rod, rotating ring and hydraulic pipe to rotate together. During the flight, the DC brushless motor needs to drive multiple components to rotate at the same time. This design results in high energy consumption and reduces the endurance of the drone. In addition, as the size of the wing increases, the motor power required to drive the wing rotation also increases accordingly, which will cause the motor temperature to rise. If the heat dissipation effect is not good, it may affect the life of the motor and the stability of the entire system. Summary of the invention

[0005] The purpose of the present invention is to provide a wing-expandable UAV, which can quickly install and disassemble the wings, and also has a simple wing expansion mechanism and an effective heat dissipation mechanism. At the same time, by using lightweight and high-strength composite materials to make the wings, the goal of reducing weight while maintaining good structural strength is achieved, thereby significantly improving the flight performance and practicality of the UAV.

[0006] The technical solution adopted by the present invention is as follows:

[0007] A wing-expandable UAV comprises a UAV body, wherein four corners of the UAV body are fixedly connected with mounting seats;

[0008] A housing, the housing being disposed in a mounting seat;

[0009] A fixing mechanism, which is disposed between the mounting seat and the housing and is used to fix the mounting seat and the housing;

[0010] A buffer mechanism, wherein the buffer mechanism is arranged at the lower end of the shell;

[0011] A flying mechanism, wherein the flying mechanism is arranged at the upper end of the housing;

[0012] Among them, the flying mechanism includes a hollow shell, which is arranged above the outer shell, a driving part is arranged at the lower end of the hollow shell, a wing part is arranged on the outer side of the hollow shell, a control part is arranged inside the outer shell for controlling the extension of the wing, and a heat dissipation part is also arranged inside the hollow shell.

[0013] In a preferred embodiment, the fixing mechanism includes an annular groove, which is provided on a mounting seat, a slot hole is provided on the inner side of the annular groove, and a locking block is slidably inserted therein, support plates are fixedly connected to the upper and lower sides of the locking block, a spring is fixedly connected to one side of the support plate, and the other end of the spring is fixedly connected to the inner wall of the annular groove, a circular ring is rotatably connected in the annular groove, a trapezoidal block is connected to the inner ring of the circular ring in a circular shape, a through groove is also provided on the outer ring of the mounting seat, and a handle is fixedly connected to the outer ring of the circular ring.

[0014] In a preferred embodiment, the buffer mechanism includes an installation groove, which is opened at the lower end of the shell, and a support seat is inserted into the lower end of the installation groove. The top surface of the support seat is connected with a rubber column in an annular distribution, and the outer wall of the rubber column is sleeved with a shock-absorbing spring. The inner wall of the installation groove is evenly distributed with grooves, and the upper outer ring of the support seat is provided with bumps in an annular distribution.

[0015] In a preferred embodiment, the driving unit includes a motor, which is mounted on the top surface of the inner cavity of the outer shell. An output shaft is mounted on the output end of the motor, and the upper end of the output shaft is fixedly connected to the hollow shell.

[0016] In a preferred embodiment, the wing portion includes a fixed wing, which is arranged on the outside of a hollow shell, and a telescopic wing is slidably connected inside the fixed wing. A hollow rod is fixedly embedded in one end of the fixed wing close to the hollow shell, and the hollow rod is fixedly connected to the hollow shell and communicated with each other. A movable rod is slidably inserted in the hollow rod, one end of the movable rod is fixedly connected to a piston block, and the other end of the movable rod is fixedly connected to a push block, and the push block is fixedly connected to the telescopic wing. A tension spring is also sleeved on the outer wall of one end of the movable rod, and one end of the tension spring is fixedly connected to the push block, and the other end is fixedly connected to the hollow rod.

[0017] In a preferred embodiment, the control part includes an annular shell, which is fixedly connected to the top surface of the inner cavity of the shell, a sliding block is slidably inserted at the lower end of the annular shell, and an annular piston plate is fixedly connected to the upper end of the sliding block. An electric push rod is installed on the embedded bottom surface of the shell, and a disc is fixedly connected to the upper end of the electric push rod, and a round rod is fixedly connected to the top surface of the disc, and the upper end of the round rod is fixedly connected to the sliding block. The outer ring of the hollow shell is rotatably connected to a liquid storage box, and the lower end of the liquid storage box is connected to an infusion tube in an annular manner, and the lower end of the infusion tube is connected to the annular shell, and the hollow shell is also provided with infusion holes in an annular manner.

[0018] In a preferred embodiment, the heat dissipation part includes ventilation grooves, which are distributed in an annular shape on the outer shell. The bottom surface of the disc is fixedly connected to a first annular baffle plate by an L-shaped rod, a second annular baffle plate is arranged above the first annular baffle plate, a compression spring is arranged between the first annular baffle plate and the second annular baffle plate, and the compression spring is made of memory alloy.

[0019] In a preferred embodiment, the groove and the projection are uniformly hemispherical and have corresponding sizes, and the projection is made of rubber.

[0020] In a preferred embodiment, the upper end of the shell is provided with lock holes in an annular shape, and a contact switch is installed inside the lock holes. The upper end of the shell is provided with a warning light.

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

[0022] The present invention designs an expandable wing structure so that the UAV can adjust the length of its wings according to different flight missions and environmental requirements. This design optimizes flight performance and space occupancy, allowing the UAV to adjust the length of its arms according to different load requirements, thereby enhancing load-bearing capacity and stability. For missions that require long-term flight, the wings can be shortened to reduce air resistance and improve flight efficiency; for missions that require carrying heavier loads, the wings can be extended to provide stronger lift support; at the same time, the wings are only provided with pipelines for conveying hydraulic oil, the overall weight of the wings is low, and the motor has fewer components to drive to rotate, which reduces energy consumption and improves endurance.

[0023] The present invention adopts a quick-release locking mechanism, so that the wing and the flight mechanism thereon can be quickly disassembled and installed. This design is not only convenient for disassembling a certain flight mechanism for maintenance or replacement, but also allows the staff to more intuitively monitor the locking status by setting the electrical connection between the contact switch and the warning light, ensuring that all wings have been correctly installed and locked before flight, thereby improving the safety of use and the convenience of maintenance;

[0024] The present invention designs ventilation slots and linkage structures to increase the size of the ventilation slot opening as the size of the wing increases, effectively dissipating heat from the motor, preventing the motor from overheating, and extending the service life of the motor and the entire system. In addition, in hot weather or when the internal temperature is high, the compression spring made of memory alloy can automatically adjust the opening and closing of the ventilation slots, further ensuring the heat dissipation effect and maintaining the stable operation of the system. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0026] Figure 2 It is a schematic diagram of disassembling the mounting base and the housing of the present invention;

[0027] Figure 3 It is a structural schematic diagram of the housing and the fixing mechanism of the present invention;

[0028] Figure 4 The present invention Figure 3 A cross-sectional view of

[0029] Figure 5 The present invention Figure 4 An enlarged schematic diagram of part A shown in FIG.

[0030] Figure 6 The present invention Figure 4 An enlarged schematic diagram of part B shown in;

[0031] Figure 7 is a cross-sectional view of a wing portion of the present invention;

[0032] Figure 8 is a cross-sectional view of the mounting seat of the present invention;

[0033] Fig. 9 The present invention Figure 8 An enlarged schematic diagram of part C is shown in FIG.

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

[0035] 1. UAV body; 2. Mounting seat; 3. Shell; 4. Fixing mechanism; 5. Buffer mechanism; 6. Flight mechanism; 7. Lock hole; 8. Contact switch; 9. Warning light;

[0036] 401, annular groove; 402, locking block; 403, supporting plate; 404, spring; 405, circular ring; 406, trapezoidal block; 407, through groove; 408, handle;

[0037] 501, mounting groove; 502, support seat; 503, rubber column; 504, shock absorbing spring; 505, groove; 506, bump;

[0038] 61. hollow shell; 62. driving part; 63. wing part; 64. control part; 65. heat dissipation part;

[0039] 621, electric motor; 622, output shaft;

[0040] 631, fixed wing; 632, telescopic wing; 633, hollow rod; 634, movable rod; 635, piston block; 636, push block; 637, tension spring;

[0041] 641, annular housing; 642, sliding block; 643, annular piston plate; 644, electric push rod; 645, disc; 646, round rod; 647, liquid storage box; 648, infusion tube; 649, infusion hole.

[0042] 651, ventilation slot; 652, first annular baffle; 653, second annular baffle; 654, compression spring. DETAILED DESCRIPTION

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

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

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

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

[0047] Please see attached Figure 1-Figure 9 As shown, this embodiment provides a wing-expandable UAV, including a UAV body 1, and four corners of the UAV body 1 are fixedly connected with mounting seats 2;

[0048] The housing 3 is arranged in the mounting seat 2. The upper end of the housing 3 is provided with lock holes 7 in an annular distribution, and a contact switch 8 is installed inside the lock hole 7. The upper end of the housing 3 is provided with a warning light 9;

[0049] A fixing mechanism 4, which is disposed between the mounting base 2 and the housing 3 and is used to fix the mounting base 2 and the housing 3;

[0050] A buffer mechanism 5, which is disposed at the lower end of the housing 3;

[0051] A flying mechanism 6, which is arranged at the upper end of the housing 3;

[0052] Among them, the flying mechanism 6 includes a hollow shell 61, which is arranged above the outer shell 3, a driving part 62 is arranged at the lower end of the hollow shell 61, a wing part 63 is arranged on the outer side of the hollow shell 61, and a control part 64 is arranged inside the outer shell 3 for controlling the extension of the wing. A heat dissipation part 65 is also arranged inside the hollow shell 61.

[0053] In this embodiment, the drone body 1 is the core of the entire drone. The mounting base 2 is a structure for fixing and connecting other components, and the four corners of the drone body 1 are connected to it. The shell 3 is a protective structure for parts and is located inside the mounting base 2. The upper end of the shell 3 is designed with a ring-shaped lock hole 7 for locking or unlocking the shell 3. A contact switch 8 is installed on the inside of the lock hole 7 for sensing whether the shell 3 is correctly connected. A warning light 9 is also provided at the upper end of the shell 3 for sending a warning signal to the outside. The fixing mechanism 4 is located between the mounting base 2 and the shell 3. Its function is to ensure a firm connection between the mounting base 2 and the shell 3 and to ensure the structural stability of the drone. The buffer mechanism 5 is located at the lower end of the shell 3. Its function is to absorb the impact force during landing to protect the drone from damage.

[0054] The flight mechanism 6 is located at the upper end of the housing 3 and is the core part of the UAV flight function, including:

[0055] The hollow shell 61 is located above the outer shell 3 and is a hollow structure.

[0056] The driving part 62 is located at the lower end of the hollow shell 61 and is used to drive the propeller of the drone.

[0057] The wing portion 63 is located outside the hollow shell 61 .

[0058] The control unit 64 is located inside the housing 3 and is used to control the extension of the wings to ensure the flight stability and maneuverability of the drone.

[0059] The heat dissipation portion 65 is located inside the hollow shell 61 and is used to dissipate the heat generated by the flight mechanism 6 during operation to ensure that the electronic components are not damaged due to overheating.

[0060] It should be noted that the drone body 1 is equipped with a battery pack, and the structure on the outer shell 3 is electrically connected to the battery pack using a quick-release plug (not shown in the figure).

[0061] Next, please refer to Figure 8 and Fig. 9 The fixing mechanism 4 includes an annular groove 401, which is provided on the mounting seat 2. A slot is provided on the inner side of the annular groove 401, and a locking block 402 is slidably inserted therein. Support plates 403 are fixedly connected to the upper and lower sides of the locking block 402. A spring 404 is fixedly connected to one side of the support plate 403, and the other end of the spring 404 is fixedly connected to the inner wall of the annular groove 401. A circular ring 405 is rotatably connected in the annular groove 401, and a trapezoidal block 406 is connected to the inner ring of the circular ring 405 in an annular distribution. A through groove 407 is also provided on the outer ring of the mounting seat 2, and a handle 408 is fixedly connected to the outer ring of the circular ring 405.

[0062] In this embodiment, when performing the installation operation, the housing 3 needs to be fully inserted into the mounting base 2 first. Then, the user needs to operate the handle 408 to drive the ring 405 to rotate by pulling the handle 408. As the ring 405 rotates, the trapezoidal block 406 moves accordingly. The movement of the trapezoidal block 406 applies a resisting force to the locking block 402, so that the four locking blocks 402 are close to each other and apply pressure to the spring 404. This process continues until the four locking blocks 402 are fully inserted into the corresponding locking holes 7. At this point, the fixing between the housing 3 and the mounting base 2 is completed.

[0063] During the disassembly process, the user needs to operate the handle 408 in the reverse direction. As the handle 408 is pulled in the reverse direction, the trapezoidal block 406 will gradually lose its resistance to the locking block 402. After losing its resistance, the spring 404 will generate a restoring force to push the support plate 403 to move. The movement of the support plate 403 will drive the locking block 402 to move accordingly, so that the locking block 402 is separated from the lock hole 7. When the housing 3 loses its limit, the user can easily disassemble the housing 3 and the flight mechanism 6 installed thereon, so as to facilitate the maintenance or replacement of a certain flight mechanism 6.

[0064] It should be noted that some limiting grooves are distributed in an annular manner on the inner ring of the mounting seat 2. Some limiting strips are also provided on the outer ring of the housing 3. When installing the housing 3, the limiting strips need to be aligned with the limiting grooves and ensure that the limiting strips are fully inserted into the limiting grooves. In this way, the position of the locking block 402 will correspond to the locking hole 7, thereby improving the convenience and accuracy of installation.

[0065] In addition, some rubber balls are specially arranged on the outer ring part of the ring 405. There is friction between these rubber balls and the annular groove 401, which can play a damping effect and prevent the ring 405 from rotating randomly.

[0066] A contact switch 8 is provided inside the lock hole 7. When the lock block 402 is fully inserted into the lock hole 7, it will contact the contact switch 8. The contact switch 8 is electrically connected to the warning light 9, so when the lock block 402 contacts the contact switch 8, the warning light 9 will light up. If it is loose, the lock block 402 will no longer contact the contact switch 8, and the warning light 9 will turn off. This design allows the staff to monitor the locking status more intuitively, ensuring that all wings are properly installed and locked before flight, thereby ensuring the safety of flight.

[0067] Secondly, please also refer to Figure 4 The buffer mechanism 5 includes a mounting groove 501, which is opened at the lower end of the shell 3. A support seat 502 is inserted at the lower end of the mounting groove 501. The top surface of the support seat 502 is connected with a rubber column 503 in an annular distribution. The outer wall of the rubber column 503 is sleeved with a shock-absorbing spring 504. The inner wall of the mounting groove 501 is evenly distributed with grooves 505. The upper outer ring of the support seat 502 is annularly distributed with a protrusion 506, wherein the groove 505 and the protrusion 506 are uniformly hemispherical and have the same size. The protrusion 506 is made of rubber.

[0068] In this embodiment, during the landing process of the drone, its support seat 502 will first contact the ground. Subsequently, the support seat 502 will be subjected to the force from the ground, causing it to shrink toward the inside of the mounting groove 501. In this process, the support seat 502 will squeeze the shock-absorbing spring 504 and the rubber column 503. The presence of the shock-absorbing spring 504 and the rubber column 503 can effectively absorb and buffer the impact force generated during landing, thereby protecting the structure of the drone from damage. In addition, a bump 506 is provided at the upper end of the support seat 502. When the support seat 502 shrinks, the bump 506 will rub against the groove 505 in the mounting groove 501. This friction can further increase the damping effect, making the drone more stable during landing and reducing the damage caused by excessive impact force during landing. Through this design, the drone can not only effectively absorb the impact force during landing, but also further improve the stability of landing through friction damping, thereby ensuring the safety and reliability of the drone.

[0069] Next, please refer to Figure 4 The driving part 62 includes a motor 621 , which is mounted on the top surface of the inner cavity of the outer shell 3 . An output shaft 622 is mounted on the output end of the motor 621 , and the upper end of the output shaft 622 is fixedly connected to the hollow shell 61 .

[0070] In this embodiment, the motor 621 is the core component of the driving unit 62, responsible for converting electrical energy into mechanical energy, i.e., rotation. The output shaft 622 is a shaft connected to the output end of the motor 621, used to transmit the rotational power of the motor 621 to other mechanical components.

[0071] Please refer again Figure 4-Figure 7 The wing portion 63 includes a fixed wing 631, which is arranged on the outside of the hollow shell 61, and a telescopic wing 632 is slidably connected inside the fixed wing 631. A hollow rod 633 is fixedly embedded in one end of the fixed wing 631 located close to the hollow shell 61, and the hollow rod 633 is fixedly connected to the hollow shell 61 and communicated with each other. A movable rod 634 is slidably inserted in the hollow rod 633, and one end of the movable rod 634 is fixedly connected to a piston block 635, and the other end of the movable rod 634 is fixedly connected to a push block 636, and the push block 636 is fixedly connected to the telescopic wing 632. A tension spring 637 is also sleeved on the outer wall of one end of the movable rod 634, and one end of the tension spring 637 is fixedly connected to the push block 636, and the other end is fixedly connected to the hollow rod 633.

[0072] In this embodiment, the fixed wing 631 is a main component of the wing part 63, which is a fixed part and is installed on the outside of the hollow shell 61. The telescopic wing 632 is telescopic and slidably connected to the fixed wing 631, and can move along the length direction of the fixed wing 631 to change the size of the wing. The hollow rod 633 is a hollow rod-shaped structure, which is embedded in one end of the fixed wing 631 close to the hollow shell 61 and is fixedly connected to the hollow shell 61. The hollow rod 633 is connected to the hollow shell 61. The movable rod 634 can be slidably inserted in the hollow rod 633. One end of it is fixedly connected to a piston block 635, and the other end is fixedly connected to a push block 636. The push block 636 is fixedly connected to the telescopic wing 632, which means that when the movable rod 634 moves, the push block 636 will push the telescopic wing 632 to perform a telescopic action. One end of the tension spring 637 is fixedly connected to the push block 636, and the other end is fixedly connected to the hollow rod 633. The function of the tension spring 637 is to provide a restoring force. When the movable rod 634 is moved by an external force, the tension spring 637 can help the movable rod 634 return to its original position.

[0073] In general, the extension and retraction of the retractable wing 632 is controlled by the movement of the movable rod 634, so as to adjust the size of the wing during flight to adapt to different flight conditions.

[0074] Please refer again Figure 3-Figure 4The control unit 64 includes an annular shell 641, which is fixedly connected to the top surface of the inner cavity of the shell 3. A sliding block 642 is slidably inserted at the lower end of the annular shell 641, and an annular piston plate 643 is fixedly connected to the upper end of the sliding block 642. An electric push rod 644 is installed on the embedded bottom surface of the shell 3. A disc 645 is fixedly connected to the upper end of the electric push rod 644. A round rod 646 is fixedly connected to the top surface of the disc 645, and the upper end of the round rod 646 is fixedly connected to the sliding block 642. The outer ring of the hollow shell 61 is rotatably connected to a liquid storage box 647. The lower end of the liquid storage box 647 is connected to an infusion tube 648 in an annular manner, and the lower end of the infusion tube 648 is connected to the annular shell 641. Infusion holes 649 are also opened in an annular manner on the hollow shell 61.

[0075] In this embodiment, the output shaft 622 is driven to rotate by starting the motor 621, thereby driving the hollow shell 61 to rotate. The rotation of the hollow shell 61 drives the fixed wing 631 and the telescopic wing 632 to rotate, thereby achieving flight. When the length of the wing needs to be adjusted, it is achieved by controlling the extension of the electric push rod 644. After the electric push rod 644 is extended, it drives the disc 645 to move upward. The upward movement of the disc 645 further drives the round rod 646, the sliding block 642 and the annular piston plate 643 to move upward. During the upward movement of the annular piston plate 643, the hydraulic oil in the annular housing 641 is squeezed, so that the hydraulic oil flows into the liquid storage box 647 along the infusion pipe 648. The hydraulic oil flows into the hollow shell 61 through the infusion hole 649 in the liquid storage box 647, and then flows into the hollow rod 633 along the hollow shell 61. The hydraulic oil entering the hollow rod 633 pushes the piston block 635 to move the movable rod 634. The movement of the movable rod 634 will drive the movement of the push block 636 and the telescopic wing 632, and stretch the tension spring 637, so that the telescopic wing 632 gradually extends out of the fixed wing 631. When the wing needs to be shortened, it is only necessary to control the electric push rod 644 to shorten, and the hydraulic oil will be drawn back into the annular housing 641. At this time, the piston block 635 will lose the extrusion of the hydraulic oil, and the tension spring 637 will immediately generate a reset force, pulling the push block 636 to move, so that the telescopic wing 632 shrinks inside the fixed wing 631. Through the mutual cooperation of this structure, the wing length can be flexibly adjusted. According to different flight requirements, the wing can be expanded or contracted, thereby optimizing the flight performance and space occupancy. This allows the drone to adjust the arm length according to different load requirements, thereby enhancing the load capacity and stability. In addition, the wing is made of lightweight and high-strength composite materials, which not only reduces the weight but also enhances the structural strength. And through this structural design, only pipelines for transporting hydraulic oil are set on the wings, which greatly reduces the overall weight of the wings, thereby reducing energy consumption and improving the endurance of the UAV.

[0076] Please refer again Figure 4The heat dissipation portion 65 includes ventilation slots 651, which are distributed in an annular shape and opened on the outer shell 3. The bottom surface of the disk 645 is fixedly connected with a first annular baffle plate 652 by an L-shaped rod. A second annular baffle plate 653 is arranged above the first annular baffle plate 652. A compression spring 654 is arranged between the first annular baffle plate 652 and the second annular baffle plate 653, and the compression spring 654 is made of memory alloy.

[0077] In this embodiment, as the size of the wing increases, the power consumption of the motor 621 will also increase accordingly. However, in this case, when the electric push rod 644 drives the disc 645 to move upward, it will also drive the first annular baffle 652 and the second annular baffle 653 to move upward together. This action will cause the ventilation slot 651 to open, thereby allowing outside air to enter, so as to effectively dissipate the heat of the motor 621 and prevent the motor 621 from being damaged due to overheating. In a normal flight state, when the disc 645 is in a lower position, the first annular baffle 652 and the second annular baffle 653 will close the ventilation slot 651 to prevent air from entering. However, as the wing expands, the ventilation slot 651 will gradually open, and through the linkage structure, the opening size of the ventilation slot 651 will increase accordingly with the increase in the size of the wing. In addition, under hot weather conditions, even if the drone is in flight and the wings are at their smallest size, if the temperature inside the housing 3 is high, the compression spring 654 made of memory alloy will elongate due to the temperature increase, thereby pushing the second annular baffle 653 to move upward, thereby opening the ventilation slot 651 and ensuring the heat dissipation effect to maintain the normal operating temperature of the motor 621.

[0078] The working principle of the present invention is:

[0079] During the installation process, the housing 3 is embedded in the mounting seat 2, and then the operator rotates the ring 405 by operating the handle 408, thereby driving the trapezoidal block 406 to move. The movement of the trapezoidal block 406 will exert pressure on the locking block 402, causing the four locking blocks 402 to move closer to each other and compress the spring 404 until the locking block 402 is completely embedded in the corresponding locking hole 7, thereby completing the fixation. When disassembling, the operator needs to operate the handle 408 in the reverse direction, and the trapezoidal block 406 will gradually reduce the pressure on the locking block 402, and the spring 404 will then generate a reset force, pushing the support plate 403 to move, thereby driving the locking block 402 to disengage from the locking hole 7. At this time, the housing 3 is no longer restricted, and the operator can remove the housing 3 and the flight mechanism 6 installed thereon, which is convenient for maintenance or replacement of the flight mechanism 6.

[0080] Start the motor 621 to drive the output shaft 622 to rotate, so that the hollow shell 61 rotates, and then drives the fixed wing 631 and the telescopic wing 632 to rotate for flight. If the wings need to be adjusted, control the electric push rod 644 to extend, so that the disc 645 moves upward, and then drives the round rod 646, the sliding block 642 and the annular piston plate 643 to move upward. When the annular piston plate 643 moves upward, it squeezes the hydraulic oil in the annular shell 641 (the upper end of the hollow shell 61 is provided with an oil filling hole and a sealing cover, and before use, the inside should be filled with hydraulic oil), and the hydraulic oil flows into the liquid storage box 647 through the infusion tube 648, and then the hydraulic oil flows into the hollow shell 61 through the infusion hole 649, and then flows into the hollow rod 633 along the hollow shell 61. The hydraulic oil in the hollow rod 633 pushes the piston block 635 to move the movable rod 634. The movement of the movable rod 634 drives the push block 636 and the telescopic wing 632 to move, and stretches the tension spring 637 to gradually extend the telescopic wing 632 from the fixed wing 631. If the wing needs to be shortened, the electric push rod 644 is controlled to shorten, so that the hydraulic oil flows back into the annular housing 641, the piston block 635 loses the hydraulic oil pressure, and the tension spring 637 generates a reset force, pulling the push block 636 to move, so that the telescopic wing 632 shrinks toward the inside of the fixed wing 631. Through the mutual cooperation of these structures, the wing length can be adjusted to meet different flight requirements. It should be noted that the liquid storage box 647 is rotatably connected to the hollow shell 61, and the liquid storage box 647 will not be driven to rotate during the rotation of the hollow shell 61.

[0081] As the size of the wing increases, the power consumption of the motor 621 increases accordingly. However, in the process of the electric push rod 644 driving the disc 645 to move upward, the first annular baffle 652 and the second annular baffle 653 will also move upward, and the ventilation slot 651 will be opened to allow outside air to enter to dissipate heat from the motor 621 and avoid overheating. During normal flight, when the disc 645 is at a low position, the first annular baffle 652 and the second annular baffle 653 will close the ventilation slot 651. As the wing expands, the ventilation slot 651 gradually opens, and through the linkage structure, the opening size of the ventilation slot 651 increases with the increase of the wing size. In addition, in hot weather, during the flight of the drone, even if the wing is in the minimum size state, when the temperature inside the shell 3 is high, the compression spring 654 made of memory alloy will stretch and push the second annular baffle 653 to move upward, and the ventilation slot 651 will also open to ensure the heat dissipation effect.

[0082] The above is only a preferred embodiment of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be considered as the protection scope of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to the conventional means in the art unless otherwise specified and limited.

Claims

1. A wing-expandable UAV, characterized in that: It comprises a drone body (1), wherein four corners of the drone body (1) are fixedly connected to mounting seats (2); A housing (3), wherein the housing (3) is arranged in the mounting seat (2); A fixing mechanism (4), the fixing mechanism (4) being arranged between the mounting seat (2) and the housing (3) and being used to fix the mounting seat (2) and the housing (3); A buffer mechanism (5), wherein the buffer mechanism (5) is arranged at the lower end of the housing (3); A flying mechanism (6), wherein the flying mechanism (6) is arranged at the upper end of the housing (3); The flight mechanism (6) comprises a hollow shell (61), the hollow shell (61) is arranged above the outer shell (3), a driving part (62) is arranged at the lower end of the hollow shell (61), a wing part (63) is arranged on the outer side of the hollow shell (61), a control part (64) is arranged inside the outer shell (3) for controlling the extension of the wing, and a heat dissipation part (65) is also arranged inside the hollow shell (61); The wing portion (63) comprises a fixed wing (631), the fixed wing (631) is arranged on the outside of the hollow shell (61), a telescopic wing (632) is slidably connected inside the fixed wing (631), a hollow rod (633) is fixedly embedded at one end of the fixed wing (631) located close to the hollow shell (61), and the hollow rod (633) is fixedly connected to the hollow shell (61) and communicated with each other, and a telescopic wing (632) is slidably connected inside the fixed wing (631). A movable rod (634) is provided, one end of the movable rod (634) is fixedly connected to a piston block (635), the other end of the movable rod (634) is fixedly connected to a push block (636), and the push block (636) is fixedly connected to the telescopic wing (632), and a tension spring (637) is sleeved on the outer wall of one end of the movable rod (634), and one end of the tension spring (637) is fixedly connected to the push block (636), and the other end is fixedly connected to the hollow rod (633); The control unit (64) comprises an annular shell (641), the annular shell (641) is fixedly connected to the top surface of the inner cavity of the outer shell (3), a sliding block (642) is slidably inserted at the lower end of the annular shell (641), and an annular piston plate (643) is fixedly connected to the upper end of the sliding block (642), an electric push rod (644) is installed on the embedded bottom surface of the outer shell (3), and a disc (645) is fixedly connected to the upper end of the electric push rod (644). The top surface of the circular disc (645) is fixedly connected to a round rod (646), and the upper end of the round rod (646) is fixedly connected to the sliding block (642). The outer ring of the hollow shell (61) is rotatably connected to a liquid storage box (647). The lower end of the liquid storage box (647) is connected to an infusion tube (648) in an annular arrangement, and the lower end of the infusion tube (648) is connected to the annular shell (641). Infusion holes (649) are also arranged in an annular arrangement on the hollow shell (61).

2. The wing-expandable UAV according to claim 1, characterized in that: The fixing mechanism (4) comprises an annular groove (401), the annular groove (401) is provided on the mounting seat (2), a slot hole is provided on the inner side of the annular groove (401), and a locking block (402) is slidably inserted therein, the upper and lower sides of the locking block (402) are fixedly connected to support plates (403), one side of the support plate (403) is fixedly connected to a spring (404), and the other end of the spring (404) is fixedly connected to the inner wall of the annular groove (401), a circular ring (405) is rotatably connected in the annular groove (401), the inner ring of the circular ring (405) is connected to a trapezoidal block (406) in an annular distribution, the outer ring of the mounting seat (2) is also provided with a through groove (407), and the outer ring of the circular ring (405) is fixedly connected to a handle (408).

3. The wing-expandable UAV according to claim 1, characterized in that: The buffer mechanism (5) comprises a mounting groove (501), wherein the mounting groove (501) is provided at the lower end of the housing (3), a support seat (502) is inserted into the lower end of the mounting groove (501), a rubber column (503) is connected to the top surface of the support seat (502) in an annular manner, a shock absorbing spring (504) is sleeved on the outer wall of the rubber column (503), grooves (505) are evenly distributed on the inner wall of the mounting groove (501), and a protrusion (506) is provided in an annular manner on the outer ring of the upper end of the support seat (502).

4. The wing-expandable UAV according to claim 1, characterized in that: The driving part (62) comprises a motor (621), the motor (621) is mounted on the top surface of the inner cavity of the outer shell (3), an output shaft (622) is mounted on the output end of the motor (621), and the upper end of the output shaft (622) is fixedly connected to the hollow shell (61).

5. The wing-expandable UAV according to claim 1, characterized in that: The heat dissipation portion (65) comprises ventilation slots (651), which are arranged in an annular shape on the outer shell (3); the bottom surface of the disk (645) is fixedly connected to a first annular baffle plate (652) by an L-shaped rod; a second annular baffle plate (653) is arranged above the first annular baffle plate (652); a compression spring (654) is arranged between the first annular baffle plate (652) and the second annular baffle plate (653), and the compression spring (654) is made of a memory alloy.

6. The wing-expandable UAV according to claim 3, characterized in that: The groove (505) and the protrusion (506) are uniformly hemispherical and have corresponding sizes, and the protrusion (506) is made of rubber.

7. The wing-expandable UAV according to claim 1, characterized in that: The upper end of the housing (3) is provided with lock holes (7) in an annular arrangement, and a contact switch (8) is installed inside the lock holes (7). The upper end of the housing (3) is provided with a warning light (9).

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