Portable unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle equipment, in particular to a portable unmanned aerial vehicle which comprises an aerial vehicle body and two undercarriages arranged below the aerial vehicle body in a bilateral symmetry mode, rotating assemblies are arranged on the undercarriages, and locking assemblies used for fixing the rotating angle are arranged on the rotating assemblies. The undercarriage is provided with a telescopic assembly used for adjusting the relative position of the aircraft body and the undercarriage, the outer edge face of the undercarriage is connected with a buffering cushion, the undercarriage is provided with an injection assembly used for controlling the buffering cushion to expand and contract, and the undercarriage is rotationally connected with a nylon cloth roll used for covering the aircraft body. Under the working state, the vehicle-mounted state and the handheld state, the undercarriage can be subjected to corresponding angle conversion through the rotating assembly, so that the function of the undercarriage, the function of the supporting frame and the function of the handheld frame are switched, the portability and stability can be improved under the transportation state, and the stability and the use convenience can be improved under the working state.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV equipment, and particularly to a portable unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle is an aircraft that does not require a crew on board and can fly autonomously or by remote control. It is widely used in fields such as plant protection operations, rescue, and surveying.

[0003] An unmanned aerial vehicle for operations needs to carry a variety of equipment, and its size is often large and cannot be carried around like a small drone for photography. Therefore, when transporting an unmanned aerial vehicle for operations to the operation location, it usually goes through two states: being carried by vehicle and being held by hand. During the vehicle-carrying process, there will inevitably be bumps. Existing unmanned aerial vehicles are prone to accidental situations such as component loosening when subjected to bumps. When held by hand, existing unmanned aerial vehicles have the problem of being inconvenient to hold. Generally speaking, existing unmanned aerial vehicles have poor portability.

[0004] Therefore, a portable unmanned aerial vehicle is proposed. Summary of the Invention

[0005] In order to overcome the deficiencies of the prior art, the present invention provides a portable unmanned aerial vehicle.

[0006] To solve the above technical problems, the present invention provides the following technical solution: A portable unmanned aerial vehicle, comprising an aircraft body and two landing gears symmetrically arranged on the lower side of the aircraft body. A rotating assembly is provided on the landing gear, and the rotating assembly is fixedly arranged on the aircraft body. The landing gear can achieve the function of rotating and adjusting the angle through the rotating assembly, and the landing gear has three rotation angles relative to the aircraft body. At the first rotation angle, the landing gear obliquely supports under the aircraft body. At the second rotation angle, the landing gear is placed flat under the aircraft body. At the third rotation angle, the landing gear covers above the aircraft body. A locking assembly for fixing the rotation angle is provided on the rotating assembly. A telescopic assembly for adjusting the relative position between the aircraft body and the landing gear is provided on the landing gear. A buffer pad is connected to the outer edge surface of the landing gear. An injection assembly for controlling the expansion and contraction of the buffer pad is provided on the landing gear. A nylon cloth roll for covering the aircraft body is rotatably connected to the landing gear.

[0007] As a preferred technical solution of the present invention, the rotating assembly includes a mounting disc, the mounting disc is connected to the bottom surface of the aircraft body, two outrigger arms extending in the same side are fixedly connected to the bottom surface of the mounting disc, a connecting shaft is rotatably connected to the end of the outrigger arm, sleeve sliding keys are connected to both the front and rear ends of the connecting shaft, grooves are provided on the corresponding surfaces of the two sleeve sliding keys and both end side walls of the landing gear are sleeved therein, a driving disc is connected to the middle section of the connecting shaft, the driving disc is located between the two outrigger arms, the free end of the driving disc extends upward in a fan shape, a fan-shaped tooth groove is provided on one side surface of the driving disc, teeth are provided on the bottom wall of the tooth groove, a rotating motor is installed on the outrigger arm corresponding to the tooth groove surface, the rotating motor uses a motor, a rotating gear is connected to the transmission shaft of the rotating motor, and the rotating gear meshes with the tooth groove.

[0008] As a preferred technical solution of the present invention, the locking assembly includes a retractable sleeve, a plurality of slots are provided on the surface of the driving disc facing away from the tooth groove, the retractable sleeve is fixedly connected to the outrigger arm corresponding to one surface of the slot, a through hole is provided on the surface of the retractable sleeve corresponding to the driving disc and a locking plug shaft is sleeved therein, a sensor is connected to the outer end of the locking plug shaft, an electromagnet is installed on the outrigger arm, the electromagnet is located inside the retractable sleeve and corresponds to the locking plug shaft, and a return spring abuts against one end of the locking plug shaft located inside the retractable sleeve.

[0009] As a preferred technical solution of the present invention, the telescopic assembly includes an air cushion chamber, air cushion chambers are connected to the side surfaces of the vertical walls at both ends of the landing gear, an expansion groove is provided on the surface of the air cushion chamber corresponding to the vertical center line of the aircraft body, a buffer pad is connected inside the expansion groove, a linear tooth groove is provided on the side surface of the air cushion chamber, a row of teeth is provided on the side surface of the linear tooth groove, through holes are provided on the opposite surfaces of the two sleeve sliding keys and cover plates are connected, a gear set is connected to the cover plate, one of the gears of the gear set is inserted into and meshes with the linear tooth groove, a driving motor is installed on the cover plate, and the transmission shaft of the driving motor is connected to one of the gears of the gear set.

[0010] As a preferred technical solution of the present invention, the injection assembly includes a medium cylinder, the number of the medium cylinders is two and they are connected to the bottom side of the landing gear in a front-back distribution, piston grooves are provided on the medium cylinders and filled with a medium, a connecting pipe is connected and communicated to the bottom end of the buffer pad, the free end of the connecting pipe is connected and communicated with the medium cylinder, a compression device is installed on the medium cylinder, a piston is connected to the transmission shaft of the compression device, and the piston is sleeved in the piston groove on the medium cylinder.

[0011] As a preferred technical solution of the present invention, fixed disks are connected to the corresponding surfaces at the bottom sides of the vertical walls at both ends of the landing gear. A rotating shaft is rotatably connected between the two fixed disks, and a torsion spring is arranged between the rotating shaft and the fixed disks. The width of the nylon cloth roll is greater than the distance between the landing gears, and the middle part of the nylon cloth roll is in a folded state. Sliding holes are formed in the corresponding surfaces of the two air cushion chambers, and inserting rods are inserted into the sliding holes. The free end of the nylon cloth roll is connected to the inserting rod, and rolling columns are connected to both ends of the inserting rod. The rolling columns are located inside the air cushion chamber and abut against the buffer pads.

[0012] As a preferred technical solution of the present invention, a control chamber is installed on the installation disk. Inside the control chamber, there is a circuit for controlling the motor, a processor for setting control logic, a backup power supply, and several sensors set as required, such as attitude sensors.

[0013] Compared with the prior art, the beneficial effects that the present invention can achieve are as follows:

[0014] 1. In the working state, vehicle-mounted state, and hand-held state, the landing gear can be changed by a corresponding angle through the rotating assembly, so as to realize the switching of the landing gear function, support frame function, and hand-held frame function. Furthermore, in the transportation state, portability and stability can be improved, and in the working state, stability and convenience of use can be improved.

[0015] 2. When at the third angle, the aircraft body is shielded inside and blocked by the nylon cloth roll, blocking influencing factors such as sunlight and rain in the external environment, improving the efficiency and convenience of the installation operation of the user, and further protecting the aircraft body.

[0016] 3. Through the control of the position of the landing gear by the telescopic assembly, the occupation of the lateral space by the landing gear can be reduced at the second angle, so as to facilitate the utilization of the placement space of the aircraft. At the third angle, the position of the aircraft body is closer to the top, reducing the length of the force arm formed by the aircraft body and the user's arm, and further reducing the magnitude of the inertial force generated when the user's arm swings, thereby realizing the protection effect on the aircraft body.

[0017] 4. By injecting components to inflate the buffer pads, the shock force can be buffered in the vehicle-mounted state, improving the stability of the aircraft body during vehicle-mounted transportation. And using the pushing force of the inflated buffer pads on the nylon cloth roll, when the aircraft body accidentally drops during flight, due to the increased area of the unfolded nylon cloth roll and large-area contact with the air below, a huge air resistance is generated, buffering the dropping speed of the aircraft body, greatly reducing the speed, and reducing the damage degree of the aircraft body after dropping, thus having a certain protection function when an accident occurs to the aircraft body. Description of the Drawings

[0018] Figure 1Schematic diagram of the three-dimensional structure of the present invention;

[0019] Figure 2 Schematic diagram of the structure of the landing gear of the present invention;

[0020] Figure 3 Partial sectional view schematic diagram of the landing gear of the present invention;

[0021] Figure 4 Schematic diagram of the structure of the mounting plate of the present invention;

[0022] Figure 5 Schematic sectional view of the advancing and retracting sleeve of the present invention.

[0023] Wherein: 10, aircraft main body; 11, landing gear; 12, buffer pad; 13, nylon cloth roll; 14, mounting plate; 15, outrigger arm; 16, connecting shaft; 17, sliding key sleeve; 18, drive disk; 19, gear slot; 20, rotating gear; 21, rotating motor; 22, advancing and retracting sleeve; 23, electromagnet; 24, locking insertion shaft; 25, sensor; 26, return spring; 27, linear tooth groove; 28, cover plate; 29, gear set; 30, drive motor; 31, air cushion chamber; 32, expansion groove; 33, medium cylinder; 34, connecting pipe; 35, compression device; 36, piston; 37, fixed disk; 38, rotating shaft; 39, insertion rod; 40, rolling column; 41, control chamber. Specific embodiments

[0024] In order to make the technical means, creative features, achieved purposes and functions of the present invention easy to understand, the present invention will be further described below in conjunction with specific embodiments. However, the following embodiments are only the preferred embodiments of the present invention, not all of them. Based on the embodiments in the implementation manners, other embodiments obtained by those skilled in the art without creative efforts all belong to the protection scope of the present invention. The experimental methods in the following embodiments, unless otherwise specified, are all conventional methods. The materials, reagents, etc. used in the following embodiments, unless otherwise specified, can all be obtained from commercial channels.

[0025] Example: As Figures 1-5As shown in the figure, a portable unmanned aerial vehicle includes a vehicle body 10 and two landing gears 11 symmetrically arranged on the left and right below the vehicle body 10. The landing gears 11 are U-shaped and the bottom ends are bent outward from the vehicle body 10. A rotating assembly is provided on the landing gears 11, and the rotating assembly is fixedly arranged on the vehicle body 10. The landing gears 11 can realize the function of rotating and adjusting the angle through the rotating assembly, and the landing gears 11 have three rotating angles relative to the vehicle body 10. At the first rotating angle, the landing gears 11 obliquely support below the vehicle body 10. At the second rotating angle, the landing gears 11 are placed flat below the vehicle body 10. At the third rotating angle, the landing gears 11 cover above the vehicle body 10. The power device of the vehicle body 10 is hinged so as to be stowed in the vehicle body 10 at the third rotating angle. A locking assembly for fixing the rotating angle is provided on the rotating assembly. A telescopic assembly for adjusting the relative position between the vehicle body 10 and the landing gears 11 is provided on the landing gears 11. A buffer pad 12 is connected to the outer edge surface of the landing gears 11. The buffer pad 12 is made of an elastic material. An injection assembly for controlling the expansion and contraction of the buffer pad 12 is provided on the landing gears 11. A nylon cloth roll 13 for covering the vehicle body 10 is rotatably connected to the landing gears 11.

[0026] Specifically, the rotating component starts to rotate the buffer pad 12. After rotating to a certain angle, the locking component starts to lock the angle, controlling the angle of the buffer pad 12 on the aircraft body 10. The landing gear 11 at the first angle can act as a support structure before the aircraft body 10 takes off and when it lands, ensuring that the camera, sensor or other hanging devices on the aircraft body 10 do not touch the ground. The landing gear 11 at the second angle can be stored flat under the aircraft body 10 during the flight of the aircraft body 10, reducing the air resistance during flight. In addition, when the aircraft body 10 is placed on a vehicle body or other transportation occasions, the flat landing gear 11 reduces the overall space occupied by the aircraft body 10, facilitating the spatial layout of the placement of the aircraft body 10. Starting the telescopic component to make the ends of the two landing gears 11 approach can further reduce the lateral space occupied by the landing gear 11 and replace the aircraft body 10 to contact the bottom surface of the placement area such as the carriage. The flat landing gear 11 increases the contact area and is less likely to tip over in the case of vibration or the like. In addition, the buffer pad 12 can be inflated through the injection component, and the inflated buffer pad 12 is used to contact the bottom surface of the placement area such as the carriage, and the elasticity of the buffer pad 12 is used to absorb kinetic energy, improving the stability of the aircraft body 10 during transportation. The landing gear 11 at the third angle rotates itself above the aircraft body 10 and places the aircraft body 10 inside. The user can lift the aircraft body 10 by grasping the buffer pad 12 and carry the aircraft body 10 in a handbag manner, improving the portability of manually carrying the aircraft body 10. During the process of manually carrying the aircraft body 10, the telescopic component starts to lift the aircraft body 10 inside the landing gear 11, making the position of the aircraft body 10 closer to the top, reducing the length of the force arm formed between the aircraft body 10 and the user's arm, and thus reducing the magnitude of the inertial force generated when the user's arm swings, achieving a protective effect on the aircraft body 10. When the aircraft body 10 is placed on the ground for takeoff preparation work, the telescopic component can also be used to move the aircraft body 10 away from the ground, creating space to complete the installation of the equipment required for the operation on the aircraft body 10. In addition, the nylon cloth roll 13 can be unfolded on the aircraft body 10 to cover the aircraft body 10 inside, blocking the influencing factors such as sunlight and rain in the external environment, improving the efficiency and convenience of the installation operation, and further protecting the aircraft body 10.

[0027] Such as Figure 1 , Figure 2 and Figure 4As shown in the figure, the rotating assembly includes a mounting disk 14, which is connected to the bottom surface of the aircraft body 10. Two outstretched arms 15 that both extend to the same side are fixedly connected to the bottom surface of the mounting disk 14. A connecting shaft 16 is rotatably connected to the end of the outstretched arm 15. Sleeve sliding keys 17 are connected to both the front and rear ends of the connecting shaft 16. Grooves are provided on the corresponding surfaces of the two sleeve sliding keys 17, and both ends of the landing gear 11 are sleeved therein. A driving disk 18 is connected to the middle section of the connecting shaft 16. The driving disk 18 is located between the two outstretched arms 15. The free end of the driving disk 18 extends upward in a fan shape. A fan-shaped gear slot 19 is provided on one side surface of the driving disk 18. Teeth are provided on the bottom wall of the gear slot 19. A rotating motor 21 is installed on the outstretched arm 15 corresponding to the gear slot 19. The rotating motor 21 uses a motor. The transmission shaft of the rotating motor 21 is connected to a rotating gear 20, and the rotating gear 20 meshes with the gear slot 19.

[0028] Specifically, the rotating motor 21 drives the transmission shaft to drive the rotating gear 20 to rotate. By using the meshing of the rotating gear 20 and the gear slot 19, the driving disk 18 is pushed to drive the connecting shaft 16 to rotate, thereby driving the landing gear 11 having a connection relationship with the connecting shaft 16 to rotate and adjusting the angle of the landing gear 11.

[0029] As Figure 2 and Figure 5 As shown in the figure, the locking assembly includes an advancing and retreating sleeve 22. A plurality of slots are provided in a fan shape on the surface of the driving disk 18 facing away from the gear slot 19. The advancing and retreating sleeve 22 is fixedly connected to the outstretched arm 15 corresponding to the slots. A through hole is provided on the surface of the advancing and retreating sleeve 22 corresponding to the driving disk 18, and a locking insertion shaft 24 is sleeved therein. The locking insertion shaft 24 can slide on the advancing and retreating sleeve 22. The locking insertion shaft 24 is made of a metal material that can be magnetically attracted. An inductor 25 is connected to the outer end of the locking insertion shaft 24. A central hole is provided in the locking insertion shaft 24 for the circuit of the inductor 25 to pass through. An electromagnet 23 is installed on the outstretched arm 15. The electromagnet 23 is located inside the advancing and retreating sleeve 22 and corresponds to the locking insertion shaft 24. A return spring 26 abuts against one end of the locking insertion shaft 24 located inside the advancing and retreating sleeve 22.

[0030] Specifically, when a rotation instruction is received, the electromagnet 23 is energized to generate magnetic force. Under the attraction of the magnetic force of the electromagnet 23, the locking plug shaft 24 slides into the advance and retreat sleeve 22, so that the locking plug shaft 24 disengages from the slot, releasing the lock on the drive disk 18. Then, the rotating assembly drives the connecting shaft 16 to rotate. During the rotation, the electromagnet 23 can be de-energized. The locking plug shaft 24 is kept in contact with the drive disk 18 by the spring of the return spring 26 until the locking plug shaft 24 corresponds to the slot. The energy release of the return spring 26 causes the locking plug shaft 24 to insert into the slot. After the inductor 25 touches the inner wall of the slot, it sends a signal, and the rotating assembly stops driving the connecting shaft 16 to rotate, completing the limit and locking of the angle of the landing gear 11. When the required angle is not reached, the processing system controls to repeat the above unlocking, rotating and locking actions.

[0031] As Figure 2 and Figure 3 shown, the telescopic assembly includes an air cushion chamber 31. The sides of the vertical walls at both ends of the landing gear 11 are connected to the air cushion chamber 31. An expansion groove 32 is formed on one side of the air cushion chamber 31 corresponding to the vertical center line of the aircraft body 10. The buffer pad 12 is connected in the expansion groove 32. A linear tooth groove 27 is formed on the side of the air cushion chamber 31. A row of teeth is provided on the side of the linear tooth groove 27. Through holes are formed on the opposite surfaces of the two sliding keys 17 and are connected with a cover plate 28. A gear set 29 is connected to the cover plate 28. The gear set 29 is composed of several meshing gears. One of the gears of the gear set 29 is inserted into and meshed with the linear tooth groove 27. A drive motor 30 is installed on the cover plate 28. The drive motor 30 uses a motor with a self-locking function. The transmission shaft of the drive motor 30 is connected to one of the gears of the gear set 29.

[0032] Specifically, the drive motor 30 drives the gears in the gear set 29 to rotate, and the meshing of the gear set 29 with the linear tooth groove 27 drives the landing gear 11 to slide on the sliding key 17, thereby realizing the telescopic function.

[0033] As Figure 2 and Figure 3 shown, the injection assembly includes a medium cylinder 33. The number of the medium cylinders 33 is two and they are connected to the bottom side of the landing gear 11 in a front-back distribution. A piston groove is formed on the medium cylinder 33 and is filled with a medium. The medium is hydraulic oil or air. The bottom end of the buffer pad 12 is connected and communicated with a connecting pipe 34. The free end of the connecting pipe 34 is connected and communicated with the medium cylinder 33. A compression device 35 is installed on the medium cylinder 33. The compression device 35 uses a telescopic motor. The transmission shaft of the compression device 35 is connected with a piston 36. The piston 36 is sleeved in the piston groove on the medium cylinder 33.

[0034] Specifically, the compression device 35 is activated to push the piston 36 to slide within the medium cylinder 33, and the medium within the medium cylinder 33 is injected into the buffer pad 12 through the connecting pipe 34. The buffer pad 12 expands upon receiving the filling of the internal medium and then extends out of the air cushion bin 31 to play a role in buffering and shock absorption. When the transmission shaft of the compression device 35 retracts, the buffer pad 12 rebounds by its own elastic force and is retracted into the air cushion bin 31.

[0035] As Figure 2 shown, fixed disks 37 are connected to the corresponding bottom sides of the vertical walls at both ends of the landing gear 11. A rotating shaft 38 is rotatably connected between the two fixed disks 37. A torsion spring (not shown in the figure) is provided between the rotating shaft 38 and the fixed disk 37. The torsion spring is a well-known prior art and belongs to a helical spring, which is used to store and release rotational force. Details are not elaborated here. The nylon cloth roll 13 is wound around the rotating shaft 38.

[0036] Specifically, by pulling the nylon cloth roll 13 to unroll it on the landing gear 11, the aircraft body 10 is covered and protected inside. When the nylon cloth roll 13 is released, the rotational force of the torsion spring is released to enable the rotating shaft 38 to rewind the nylon cloth roll 13.

[0037] As Figure 2 and Figure 3 shown, the width of the nylon cloth roll 13 is greater than the spacing of the landing gear 11, and the middle part of the nylon cloth roll 13 is in a folded state. Sliding holes are formed on the corresponding surfaces of the two air cushion bins 31, and insertion rods 39 are inserted into the sliding holes. The free end of the nylon cloth roll 13 is connected to the insertion rod 39, and rolling columns 40 are connected to both ends of the insertion rod 39. The rolling columns 40 are located inside the air cushion bin 31 and abut against the buffer pad 12.

[0038] Specifically, when the medium cylinder 33 injects the medium into the buffer pad 12, the medium is injected from bottom to top, and the buffer pad 12 gradually expands from bottom to top under the injection of the medium. During the expansion process, the rolling column 40 is pushed, and then the insertion rod 39 is driven to slide along the vertical wall of the landing gear 11, thereby pulling the nylon cloth roll 13 to unfold naturally. After unfolding, the buffer pad 12 maintains the stability of its position when it does not contract.

[0039] As Figure 2 shown, a control bin 41 is installed on the mounting disk 14. Inside the control bin 41, there is a circuit for controlling the motor, a processor for setting control logic, a backup power supply, and several sensors set as required, such as an attitude sensor.

[0040] Specifically, during the flight of the aircraft body 10, when an unexpected situation occurs, such as a collision or power outage, and the aircraft body 10 loses its flight ability and falls, the backup power supply maintains the normal operation of multiple components. The attitude sensor in the control cabin 41 determines the angle at which the aircraft body 10 falls. The processor operates the circuit to control the rotation of the rotating component. The rotating component rotates the landing gear 11 towards the corresponding angle. After the locking component locks, the injection component controls the inflation of the buffer pad 12, and automatically unfolds the nylon cloth roll 13 during the inflation process. By increasing the area of the unfolded nylon cloth roll 13 and making large-area contact with the air below, a huge air resistance is generated to buffer the falling speed of the aircraft body 10, significantly reducing the speed and mitigating the damage degree of the aircraft body 10 after falling, thus providing a certain protection function when an unexpected situation occurs to the aircraft body 10.

[0041] Working principle:

[0042] Before use: First step, in the vehicle-mounted state, the rotating component drives the landing gear 11 to rotate to the second angle and then locks it with the locking component. The telescopic component controls the distance between the landing gears 11 to reduce space occupancy, and then the injection component drives the buffer pad 12 to inflate to buffer and dampen the shock force.

[0043] Second step, in the hand-held state, the rotating component drives the landing gear 11 to rotate to the third angle and then locks it with the locking component. The user holds the landing gear 11 from above to lift the aircraft body 10, and the telescopic component controls the aircraft body 10 to move up closer to the user's holding position to reduce the length of the force arm.

[0044] During use: First step, before operation, the rotating component drives the landing gear 11 to rotate to the third angle and then locks it with the locking component. The injection component drives the buffer pad 12 to inflate to drive the unfolding of the nylon cloth roll 13 to shield the aircraft body 10 from the external environment. The telescopic component controls the distance between the aircraft body 10 and the ground to create an operating space, providing a good operating space for the user.

[0045] Second step, the rotating component drives the landing gear 11 to rotate to the first angle and then locks it with the locking component. The landing gear 11 is used as a landing structure. During operation, the rotating component drives the landing gear 11 to rotate to the second angle and then locks it with the locking component. The landing gear 11 is retracted under the aircraft body 10 to provide a better operating environment. When the aircraft body 10 lands, the rotating component drives the landing gear 11 to rotate to the first angle and then locks it with the locking component, and then the landing gear 11 is used as a landing structure again.

[0046] After use: During the flight of the aircraft body 10, when an unexpected situation occurs, such as a collision or a power failure, and the aircraft body 10 loses its flight ability and falls, the backup power supply maintains the normal operation of multiple components. The attitude sensor in the control cabin 41 judges the falling angle of the aircraft body 10, and the processor operates the circuit to control the rotation of the rotating component. The rotating component rotates the landing gear 11 towards the corresponding angle. After the locking component is locked, the injection component controls the cushion 12 to expand, and automatically unfolds the nylon cloth roll 13 during the expansion process. By increasing the area of the unfolded nylon cloth roll 13 and making large-area contact with the air below, a huge air resistance is generated, and the falling speed of the aircraft body 10 is buffered by the nylon cloth roll 13.

[0047] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited thereto. Various changes can be made without departing from the spirit of the present invention within the scope of knowledge possessed by those skilled in the art to which the present invention pertains.

Claims

1. A portable unmanned aerial vehicle, characterized in that, It includes an aircraft body (10) and two landing gears (11) symmetrically arranged on the left and right below the aircraft body (10). A rotating assembly is provided on the landing gear (11), and the rotating assembly is fixedly arranged on the aircraft body (10). The landing gear (11) realizes the function of rotatable angle adjustment through the rotating assembly, and the landing gear (11) has three rotation angles relative to the aircraft body (10). At the first rotation angle, the landing gear (11) obliquely supports below the aircraft body (10). At the second rotation angle, the landing gear (11) is placed flat below the aircraft body (10). At the third rotation angle, the landing gear (11) covers above the aircraft body (10). A locking assembly for fixing the rotation angle is provided on the rotating assembly, and a telescopic assembly for adjusting the relative position between the aircraft body (10) and the landing gear (11) is provided on the landing gear (11). A buffer pad (12) is connected to the outer edge surface of the landing gear (11), and an injection assembly for controlling the expansion and contraction of the buffer pad (12) is provided on the landing gear (11). A nylon cloth roll (13) for covering the aircraft body (10) is rotatably connected to the landing gear (11).

2. A portable unmanned aerial vehicle according to claim 1, wherein The rotating assembly includes a mounting disk (14), and the mounting disk (14) is connected to the bottom surface of the aircraft body (10). Two outstretched arms (15) that both extend to the same side are fixedly connected to the bottom surface of the mounting disk (14). A connecting shaft (16) is rotatably connected to the end of the outstretched arm (15). Sleeve sliding keys (17) are connected to both the front and rear ends of the connecting shaft (16). Grooves are provided on the corresponding surfaces of the two sleeve sliding keys (17), and the two end side walls of the landing gear (11) are sleeved therein. The middle section of the connecting shaft (16) is connected with a driving disk (18). The driving disk (18) is located between the two outstretched arms (15). The free end of the driving disk (18) extends upward in a fan shape. A fan-shaped tooth groove (19) is formed on one side surface of the driving disk (18). Teeth are provided on the bottom wall of the tooth groove (19). A rotating motor (21) is installed on the outstretched arm (15) corresponding to the tooth groove (19). The rotating motor (21) uses a motor. The transmission shaft of the rotating motor (21) is connected with a rotating gear (20), and the rotating gear (20) meshes with the tooth groove (19).

3. A portable unmanned aerial vehicle according to claim 2, characterized in that, The locking assembly includes an advancing and retracting sleeve (22). A number of slots are formed on the surface of the driving disk (18) facing away from the tooth groove (19). The advancing and retracting sleeve (22) is fixedly connected to the outstretched arm (15) on the surface corresponding to the slot. A through hole is formed on the surface of the advancing and retracting sleeve (22) corresponding to the driving disk (18), and a locking insertion shaft (24) is sleeved therein. An inductor (25) is connected to the outer end of the locking insertion shaft (24). An electromagnet (23) is installed on the outstretched arm (15). The electromagnet (23) is located inside the advancing and retracting sleeve (22) and corresponds to the locking insertion shaft (24). A reset spring (26) abuts against one end of the locking insertion shaft (24) located inside the advancing and retracting sleeve (22).

4. A portable unmanned aerial vehicle according to claim 2, wherein, The telescopic component includes an air cushion chamber (31). The sides of the vertical walls at both ends of the landing gear (11) are connected to the air cushion chamber (31). An expansion groove (32) is formed on one side of the air cushion chamber (31) corresponding to the vertical center line of the aircraft body (10). A buffer pad (12) is connected in the expansion groove (32). A linear tooth groove (27) is formed on the side of the air cushion chamber (31). A row of teeth is provided on the side of the linear tooth groove (27). Through holes are formed on the opposite surfaces of the two sliding keys (17), and covers (28) are connected thereto. A gear set (29) is connected to the cover (28). One of the gears of the gear set (29) is inserted into and meshed with the linear tooth groove (27). A driving motor (30) is installed on the cover (28). The transmission shaft of the driving motor (30) is connected to one of the gears of the gear set (29).

5. A portable unmanned aerial vehicle according to claim 4, wherein The injection component includes a medium cylinder (33). The number of the medium cylinders (33) is two, and they are distributed front and back and connected to the bottom side of the landing gear (11). A piston groove is formed on the medium cylinder (33) and filled with a medium. The bottom end of the buffer pad (12) is connected and communicated with a connecting pipe (34). The free end of the connecting pipe (34) is connected and communicated with the medium cylinder (33). A compression device (35) is installed on the medium cylinder (33). The transmission shaft of the compression device (35) is connected with a piston (36). The piston (36) is sleeved with the piston groove on the medium cylinder (33).

6. A portable unmanned aerial vehicle according to claim 5, characterized in that, Fixed disks (37) are connected to the corresponding surfaces at the bottom sides of the vertical walls at both ends of the landing gear (11). A rotating shaft (38) is rotatably connected between the two fixed disks (37). A torsion spring is arranged between the rotating shaft (38) and the fixed disk (37).

7. A portable unmanned aerial vehicle according to claim 6, characterized in that, The width of the nylon cloth roll (13) is greater than the distance between the landing gears (11). The middle part of the nylon cloth roll (13) is in a folded state. Sliding holes are formed on the corresponding surfaces of the two air cushion chambers (31), and inserting rods (39) are inserted into the sliding holes. The free end of the nylon cloth roll (13) is connected to the inserting rod (39). Rolling columns (40) are connected to both ends of the inserting rod (39). The rolling columns (40) are located inside the air cushion chamber (31) and abutted against the buffer pad (12).

8. A portable unmanned aerial vehicle according to claim 7, characterized in that, A control chamber (41) is installed on the mounting disk (14). A circuit for controlling the motor, a processor for setting control logic, a backup power supply, and several sensors set as required, such as an attitude sensor, are arranged in the control chamber (41).

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