Vertical take-off and landing unmanned aerial vehicle

Abstract

The utility model discloses a vertical take-off and landing unmanned aerial vehicle which comprises a vehicle body, a lifting assembly is arranged on the inner wall of the vehicle body, auxiliary assemblies are arranged on the two sides of the vehicle body, buffering assemblies are installed on one sides of the auxiliary assemblies, and protection assemblies are arranged on the periphery of the vehicle body. According to the unmanned aerial vehicle, the protection parts during landing can be folded and stored when the unmanned aerial vehicle flies, the electric quantity loss of the unmanned aerial vehicle due to resistance in the flying process is reduced, the unfolded protection parts can be subjected to auxiliary limitation when the unmanned aerial vehicle lands, and the stability of the protection parts of the unmanned aerial vehicle is improved; the unmanned aerial vehicle can be prevented from being impacted by the external environment in the flight process, meanwhile, the lifting assembly is arranged on the vehicle body, vertical take-off and landing of the unmanned aerial vehicle can be achieved, the flexibility and adaptability of the unmanned aerial vehicle are improved, and meanwhile the buffering assembly is arranged on the auxiliary assembly, so that the buffering effect of the unmanned aerial vehicle in the landing process can be achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a vertical take-off and landing UAV. Background Art

[0002] A vertical take-off and landing drone is an aircraft that can take off vertically from the ground, hover in the air, and then land vertically. This type of drone combines the advantages of helicopters and fixed-wing aircraft. It can operate without a runway and maintain high efficiency when flying horizontally.

[0003] A search of Chinese patent publication number CN 220518607 U discloses a vertical take-off and landing (VTOL) drone comprising a fuselage, the side walls of which are fixedly connected to legs; a fixed plate fixedly connected to the bottom of the legs, a slide groove formed at the bottom of the fixed plate, a slider slidably connected to the inner sidewall of the slide groove, a connecting rod rotatably connected to the bottom of the slider, and a bidirectional threaded rod threadedly connected to the slider. This utility model can change the height of the drone above the ground, allowing the drone to be installed with testing equipment at different heights, expanding the scope of use of the device and facilitating its use. It can also absorb the impact force generated by the drone landing, preventing damage to the drone caused by the large impact force. Furthermore, the anti-slip grooves prevent the drone from sliding when landing on sloped ground, causing the drone to fall and be damaged, thus providing good protection for the drone and extending its service life.

[0004] However, the above patent has certain deficiencies in actual use. Although it can prevent the drone from sliding when landing on a sloping ground, causing the drone to fall over and be damaged, and provides good protection for the drone and extends the service life of the drone, the drone cannot retract the landing protective components during flight, making the drone susceptible to resistance during flight and easily increasing the power loss of the drone. At the same time, the drone is affected by the external environment during flight, such as when the drone is hit, which can easily cause the drone to be damaged.

[0005] Currently, no effective solutions have been proposed for the problems in related technologies. Utility Model Content

[0006] In response to the problems in the related technologies, the present invention proposes a vertical take-off and landing UAV to overcome the above technical problems existing in the existing related technologies.

[0007] To this end, the specific technical solutions adopted in this utility model are as follows:

[0008] A vertical take-off and landing (VTOL) drone comprises a body, an inner wall of the body being provided with a lifting assembly, and two sides of the body being provided with auxiliary assemblies, the auxiliary assemblies comprising a plurality of mounting slots provided below the body, a plurality of motors 1 being provided on the inner walls of the mounting slots, an auxiliary block being provided at the output end of the motor 1, a ratchet being provided on the surface of the auxiliary block, a limiting block being meshedly connected to the teeth of the ratchet, the limiting block being fixedly connected to the inner wall of the mounting slot via a rotating rod 1, an auxiliary spring being provided on the other side of the limiting block, a mounting plate being fixedly fixed to one end of the auxiliary spring, and one end of the mounting plate being fixedly connected to the inner wall of the mounting slot;

[0009] A buffer component is installed on one side of the auxiliary component, and a protective component is arranged around the body. The protective component includes a protective groove opened around the body. The inner wall of the protective groove is fixedly connected with multiple spring-set telescopic rods. A protective plate is provided at one end of the spring-set telescopic rod, and the protective plate is opposite to the protective groove.

[0010] Furthermore, in order to better perform vertical lifting and lowering of the drone, the lifting assembly includes several lifting holes opened on the inner wall of the fuselage, multiple mounting frames 1 fixedly arranged on the inner wall of the fuselage, several motors 2 are installed on the mounting frames 1, and the output ends of the motors 2 are installed with lifting propellers, multiple mounting frames 2 are arranged on both sides of the fuselage, motors 3 are installed on the mounting frames 2, and propulsion propellers are installed on the output ends of the motors 3.

[0011] Furthermore, in order to better provide buffering protection for the landing of the drone, the buffer assembly includes multiple connecting frames 1 fixedly installed on one side of the auxiliary block, wherein the inner walls of two connecting frames 1 are connected to the connecting rod through the rotating rod 2, and the inner walls of the other two connecting frames 1 are connected to the damper through the rotating rod 3, and the damper and one end of the connecting rod are connected to the connecting frame 2 through the rotating rod 4. A fixed block is provided on one side of the connecting frame 2, and a buffer wheel is installed on one side of the fixed block.

[0012] Furthermore, a connecting block is provided on the damper, and one end of the connecting block is connected to the surface of the connecting rod.

[0013] Furthermore, in order to better assist in the storage and restriction of the buffer assembly, a plurality of snap-fit ​​seats are provided on the inner wall of the installation groove, and the inner wall of the snap-fit ​​seat is adapted to the fixing block.

[0014] Furthermore, in order to better assist in limiting the limiting block, one side of the limiting block is in contact with a limiting column, and one end of the limiting column is fixedly connected to the inner wall of the installation groove.

[0015] Furthermore, in order to supplement the energy of the UAV during flight, an auxiliary frame is fixedly connected to the top of the body, and a solar photovoltaic panel is provided on the auxiliary frame.

[0016] The beneficial effects of the utility model are:

[0017] (1) By setting up auxiliary components on the fuselage, not only can the protective components for landing be folded and stored when the drone is flying, thereby reducing the power loss caused by resistance during flight, but also the unfolded protective components can be assisted and restricted when the drone lands, thereby improving the stability of the drone's protective components. At the same time, the protective components set up on the fuselage can prevent the drone from being affected by the impact of the external environment during flight, thereby increasing the service life of the drone.

[0018] (2) The lifting components installed on the fuselage can realize vertical take-off and landing of the UAV, which improves the flexibility and adaptability of the UAV. At the same time, the buffer components installed on the auxiliary components can realize the buffering effect of the UAV during landing, which helps to reduce the impact of the UAV during landing and protect the structure of the UAV from damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 This is a schematic diagram of a vertical take-off and landing UAV according to an embodiment of the present invention;

[0021] Figure 2 This is a schematic structural diagram of a vertical take-off and landing UAV according to an embodiment of the present utility model;

[0022] Figure 3 This is a schematic diagram of the structure of a vertical take-off and landing UAV according to an embodiment of the present utility model when viewed from above;

[0023] Figure 4 This is a schematic diagram of the structure of a lifting assembly of a vertical take-off and landing UAV according to an embodiment of the present utility model;

[0024] Figure 5 This is a schematic structural diagram of a lifting assembly and a protective assembly of a vertical take-off and landing UAV according to an embodiment of the present utility model;

[0025] Figure 6 This is a schematic diagram of the auxiliary components and buffer components of a vertical take-off and landing UAV according to an embodiment of the utility model. Figure 1 ;

[0026] Figure 7 This is a schematic diagram of the auxiliary components and buffer components of a vertical take-off and landing UAV according to an embodiment of the utility model. Figure 2 .

[0027] In the picture:

[0028] 1. Body; 2. Lifting assembly; 201. Mounting frame 1; 202. Motor 2; 203. Lifting propeller; 204. Mounting frame 2; 205. Motor 3; 206. Propulsion propeller; 3. Auxiliary assembly; 301. Motor 1; 302. Auxiliary block; 303. Ratchet; 304. Limiting block; 305. Auxiliary spring; 306. Mounting plate; 4. Buffer assembly; 401. Connecting frame 1; 402. Connecting rod; 403. Damper; 404. Connecting frame 2; 405. Fixed block; 406. Buffer wheel; 5. Protective assembly; 501. Spring-set telescopic rod; 502. Protective plate; 6. Connecting block; 7. Adapter; 8. Limiting column; 9. Auxiliary frame; 10. Solar photovoltaic panel. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0030] According to an embodiment of the present utility model, a vertical take-off and landing UAV is provided.

[0031] Embodiment 1;

[0032] like Figure 1-Figure 7 As shown, a vertical take-off and landing UAV according to an embodiment of the present invention includes an airframe 1 for carrying all components. The airframe 1 is composed of a fuselage, fixed wings, a camera, a thermal imager, a flight control system, and a communication system. The flight control system is responsible for controlling the attitude, speed, altitude and other flight parameters of the UAV, and generally includes sensors such as a gyroscope, an accelerometer, a magnetometer, and a processor. The communication system is used to receive instructions from a ground station and transmit the status information of the UAV back to the operator, including a radio station or other forms of data link equipment. An auxiliary frame 9 is fixedly connected to the top of the airframe 1. A solar photovoltaic panel 10 is provided on the auxiliary frame 9 for auxiliary power replenishment. When in actual use, the solar photovoltaic panel 10 is electrically connected to a battery (not shown) through a converter. A lifting assembly 2 is provided on the inner wall of the airframe 1.

[0033] The lifting assembly 2 includes a plurality of lifting holes formed in the inner wall of the body 1. A plurality of mounting brackets 201 are fixedly provided on the inner wall of the body 1. There are two mounting brackets 201 for mounting and fixing a second motor 202. Six second motors 202 are mounted on the mounting brackets 201. A lifting propeller 203 is mounted on the output end of the second motor 202. A plurality of mounting brackets 204 are provided on both sides of the body 1 for mounting and fixing a third motor 205. The third motor 205 is mounted on the mounting brackets 204. A propulsion propeller 206 is mounted on the output end of the third motor 205.

[0034] Auxiliary components 3 are provided on both sides of the body 1. The auxiliary components 3 include multiple mounting slots opened below the body 1. There are two mounting slots. Multiple motors 301 are provided on the inner wall of the mounting slot. Two motors 301 are installed on the inner wall of each mounting slot. An auxiliary block 302 is installed at the output end of the motor 301. A ratchet 303 is provided on the surface of the auxiliary block 302. The teeth of the ratchet 303 are engaged with a limiting block 304 for cooperating with the ratchet 303 to assist in limiting the auxiliary block 302. One side of the limiting block 304 contacts a limiting column 8 for assisting in limiting the limiting block 304. One end of the limiting column 8 It is fixedly connected to the inner wall of the mounting groove, and the limiting block 304 is fixedly connected to the inner wall of the mounting groove through a rotating rod 1. An auxiliary spring 305 is provided on the other side of the limiting block 304, which is used to assist the limiting block 304. One end of the auxiliary spring 305 is fixed with a mounting plate 306, which is used to assist in fixing the auxiliary spring 305. One end of the mounting plate 306 is fixedly connected to the inner wall of the mounting groove. Motor 1 301, motor 3 205, and motor 2 202 are installed with a controller (not shown in the figure) when actually in use. The controller, motor 1 301, motor 3 205, and motor 2 202 are electrically connected to the battery, and the battery and the controller are installed on the body 1.

[0035] In actual application, the vertical take-off and landing of the UAV can be realized by setting the lifting component 2 on the body 1. At the same time, the auxiliary component 3 set on the body 1 can not only fold and store the protective components during landing when the UAV is flying, thereby reducing the power loss caused by resistance during flight, but also assist in limiting the unfolded protective components when the UAV lands.

[0036] Embodiment 2:

[0037] like Figure 1-Figure 7As shown, according to a vertical take-off and landing drone of an embodiment of the present invention, a buffer component 4 is installed on one side of the auxiliary component 3. The buffer component 4 includes a plurality of connecting frames 401 fixedly installed on one side of the auxiliary block 302. The number of the connecting frames 401 is four, wherein the inner walls of two connecting frames 401 are connected to the connecting rod 402 through the rotating rod 2, and the inner walls of the other two connecting frames 401 are connected to the damper 403 through the rotating rod 3, which is used to assist in buffering the drone when landing. A connecting block 6 is provided, one end of which is connected to the surface of the connecting rod 402. The damper 403 and one end of the connecting rod 402 are connected to a connecting frame 2 404 via a rotating rod 4. A fixing block 405 is provided on one side of the connecting frame 2 404. A buffer wheel 406 is installed on one side of the fixing block 405. A plurality of clamping seats 7 are provided on the inner wall of the mounting groove for limiting the fixing block 405 and improving stability when folded and stored. There are two clamping seats 7, and the inner wall of the clamping seat 7 is adapted to the fixing block 405.

[0038] A protective component 5 is provided around the body 1, and the protective component 5 includes protective grooves opened around the body 1. The inner walls of the protective grooves are fixedly connected with multiple spring-set telescopic rods 501, wherein the number of spring-set telescopic rods 501 in two protective grooves is four, and the number of spring-set telescopic rods 501 in the other two protective grooves is two. A protective plate 502 is provided at one end of the spring-set telescopic rod 501, and the protective plate 502 is opposite to the protective groove. A protective pad is provided on one side of the protective plate 502 during actual use to reduce damage to the protective plate 502.

[0039] In actual application, the buffer component 4 set in the auxiliary component 3 can achieve a buffering effect on the drone during landing, which helps to reduce the impact of the drone during landing and protect the structure of the drone from damage. At the same time, the protective component 5 set in the body 1 can prevent the drone from being affected by the impact of the external environment during flight.

[0040] In order to facilitate understanding of the above technical solutions of the present invention, the working principle or operation method of the present invention in actual process is described in detail below.

[0041] In summary, with the aid of the above-mentioned technical solution of the present invention, when in use, the mounting frame 1 201 provided on the body 1, the motor 2 202, and the lifting propeller 203 drive the body 1 to take off vertically, and then the mounting frame 204 provided on the body 1, the motor 3 205, and the propulsion propeller 206 drive the body 1 to propel flight. At the same time, the spring-set telescopic rod 501 provided on the body 1 and the protective plate 502 cooperate with each other to prevent the drone from being affected by external impact during flight. When the drone lands, the motor 1 301 provided in the mounting slot drives the auxiliary block 302, the connecting frame 1 401, the connecting rod 402, the damper 403, the connecting frame 2 404, and the buffer wheel 406 to rotate and unfold. When the drone is flying, the protective components for landing can be folded and stored, thereby reducing the resistance and power loss of the drone during flight. At the same time, the ratchet 303 provided on the auxiliary block 302 cooperates with the limiting block 304, the auxiliary spring 305, the mounting plate 306, and the limiting column 8 to assist in limiting the unfolded protective components when the drone lands.

[0042] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A vertical take-off and landing UAV, characterized in that: The invention comprises a machine body (1), wherein the inner wall of the machine body (1) is provided with a lifting assembly (2), and auxiliary assemblies (3) are provided on both sides of the machine body (1), wherein the auxiliary assemblies (3) comprise a plurality of mounting slots opened below the machine body (1), a plurality of motors (301) are provided on the inner wall of the mounting slot, an auxiliary block (302) is installed at the output end of the motor (301), a ratchet (303) is provided on the surface of the auxiliary block (302), and a limiting block (304) is meshedly connected to the teeth of the ratchet (303), and the limiting block (304) is fixedly connected to the inner wall of the mounting slot via a rotating rod (1), and an auxiliary spring (305) is provided on the other side of the limiting block (304), and a mounting plate (306) is fixed to one end of the auxiliary spring (305), and one end of the mounting plate (306) is fixedly connected to the inner wall of the mounting slot; A buffer component (4) is installed on one side of the auxiliary component (3), and a protective component (5) is arranged around the body (1). The protective component (5) includes a protective groove opened around the body (1), and the inner wall of the protective groove is fixedly connected to a plurality of spring-mounted telescopic rods (501). One end of the spring-mounted telescopic rod (501) is provided with a protective plate (502), and the protective plate (502) is opposite to the protective groove.

2. A vertical take-off and landing UAV according to claim 1, characterized in that: The lifting assembly (2) comprises a plurality of lifting holes provided on the inner wall of the machine body (1), a plurality of mounting frames (201) fixedly provided on the inner wall of the machine body (1), a plurality of motors (202) being installed on the mounting frames (201), a lifting propeller (203) being installed at the output end of the motors (202), a plurality of mounting frames (204) being provided on both sides of the machine body (1), a motor (205) being installed on the mounting frames (204), and a propulsion propeller (206) being installed at the output end of the motors (205).

3. The vertical take-off and landing UAV according to claim 2, characterized in that: The buffer assembly (4) comprises a plurality of connecting frames (401) fixedly mounted on one side of the auxiliary block (302), wherein the inner walls of two of the connecting frames (401) are connected to the connecting rod (402) via a rotating rod (2), and the inner walls of the other two connecting frames (401) are connected to the damper (403) via a rotating rod (3), and the damper (403) and one end of the connecting rod (402) are connected to the connecting frame (404) via a rotating rod (4), and a fixed block (405) is provided on one side of the connecting frame (404), and a buffer wheel (406) is installed on one side of the fixed block (405).

4. A vertical take-off and landing UAV according to claim 3, characterized in that: A connecting block (6) is provided on the damper (403), and one end of the connecting block (6) is connected to the surface of the connecting rod (402).

5. The vertical take-off and landing UAV according to claim 3, characterized in that: The inner wall of the installation groove is provided with a plurality of clamping seats (7), and the inner wall of the clamping seats (7) is adapted to the fixing block (405).

6. The vertical take-off and landing UAV according to claim 1, characterized in that: One side of the limiting block (304) contacts a limiting column (8), and one end of the limiting column (8) is fixedly connected to the inner wall of the installation groove.

7. The vertical take-off and landing UAV according to claim 1, characterized in that: An auxiliary frame (9) is fixedly connected above the machine body (1), and a solar photovoltaic panel (10) is provided on the auxiliary frame (9).

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