Vertical folding multi-rotor unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a vertically folded multi-rotor unmanned aerial vehicle, propeller hubs are arranged at the top and the bottom of a vehicle body, three groups of first vehicle arms are hinged to the propeller hub at the top, three groups of second vehicle arms are hinged to the propeller hub at the bottom, and the three groups of first vehicle arms and the three groups of second vehicle arms are arranged in a staggered manner; the fuselage is provided with storage grooves corresponding to the first vehicle arm and the second vehicle arm in the circumferential direction. Blades and motors are arranged on the first vehicle arm and the second vehicle arm, the blades are driven by the motors, a plurality of electronic speed controllers are arranged on the vehicle body, and photoelectric equipment is arranged at the bottom of the vehicle body; the propeller hub is provided with an adjusting assembly used for containing the first vehicle arm and the second vehicle arm, and an undercarriage is arranged at the bottom of the vehicle body.

Description

Technical Field

[0001] This utility model belongs to the technical field of unmanned aerial vehicles (UAVs), specifically a vertically folding multi-rotor UAV. Background Technology

[0002] Unmanned Aerial Vehicles (UAVs) are aircraft that do not require a pilot and are typically operated remotely or by an autonomous system. The applications of UAVs are becoming increasingly widespread, covering multiple fields.

[0003] Technical defects of existing technology: Most patented folding multirotor drones currently have their arms folded in one direction and cannot be folded vertically, which shortens the vertical dimension of the multirotor drone.

[0004] Currently, in patented vertically folding multirotor drones, all arms fold in one direction and cannot fold vertically in half, thus shortening the vertical dimension of the multirotor drone. Furthermore, current patented vertically folding multirotor drones cannot achieve a larger effective payload within a certain outer envelope size range. The arms of current patented vertically folding multirotor drones are mostly on a single plane or on a plane with close proximity between the upper and lower arms, and the arms fold in the same direction. This results in the lift plane generated by the multirotor drone's propellers being relatively high compared to the fuselage, leading to weaker drone stability and a significant increase in maximum forward speed. Finally, the current patented vertically folding multirotor drone structure, under the same load capacity, has a larger wheelbase and weaker wind resistance.

[0005] Therefore, this utility model designs a vertically folding multi-rotor drone to solve the technical problems existing in the prior art. Utility Model Content

[0006] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a vertically folding multi-rotor drone, which solves the above-mentioned technical problems.

[0007] The solution adopted in this utility model is: a vertically folding multi-rotor unmanned aerial vehicle, including a fuselage, characterized in that:

[0008] The fuselage is provided with a propeller hub at the top and bottom. The top propeller hub is hinged to three sets of first arms, and the bottom propeller hub is hinged to three sets of second arms. The three sets of first arms and second arms are staggered. The fuselage is provided with a storage slot along the circumference corresponding to the first arms and second arms.

[0009] The first and second arms are equipped with blades and motors. The blades are driven by the motors. The body is equipped with several electric speed controllers for controlling the motors, and the bottom is equipped with photoelectric devices.

[0010] The rotor hub is equipped with an adjustment assembly for housing the first and second arms, and the bottom of the fuselage is equipped with landing gear.

[0011] Preferably, the storage assembly includes an elongated groove on the propeller hub, a first auxiliary shaft and a second auxiliary shaft that are fixedly connected and slidably connected are fixedly connected to the elongated groove, a fixed shaft that is slidably connected to the second auxiliary shaft is fixedly connected to the first auxiliary shaft, a return spring is provided between the first auxiliary shaft and the second auxiliary shaft, a first torsion spring is provided between the first arm and the second arm and the propeller hub, and a limiting groove corresponding to the second auxiliary shaft is provided on the first arm and the second arm.

[0012] Preferably, the fuselage bottom is provided with at least three sets of fixed seats along the circumference, the fixed seats are hinged to the landing gear, and a second torsion spring is provided between the landing gear and the fixed seats.

[0013] Preferably, the landing gear is made of carbon tubing and has a rubber sleeve at the bottom.

[0014] Preferably, the three sets of first and second arms are evenly distributed along the circumference of the top and bottom rotor hubs, and the included angle between the three sets of first and second arms is 120 degrees.

[0015] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0016] Figure 1 This is a three-dimensional view of the unmanned aerial vehicle (UAV) of this utility model.

[0017] Figure 2 This is a 3D diagram of the drone storage of this utility model.

[0018] Figure 3 This is a partial three-dimensional schematic diagram of the present invention.

[0019] Figure 4 This is a three-dimensional schematic diagram of the propeller hub of this utility model.

[0020] Figure 5 yes Figure 4 A magnified view of part A.

[0021] Figure 6 This is one of the structural schematic diagrams of this utility model.

[0022] Reference numerals: 1. Fuselage; 2. Propeller hub; 3. First arm; 4. Second arm; 5. Storage slot; 6. Propeller blade; 7. Motor; 8. Electronic speed controller; 9. Landing gear; 10. Long slot; 11. First auxiliary shaft; 12. Second auxiliary shaft; 13. Fixed shaft; 14. Return spring; 15. First torsion spring; 16. Limiting slot; 17. Fixed base; 18. Second torsion spring; 19. Rubber sleeve. Detailed Implementation

[0023] The foregoing and other technical contents, features and effects of this utility model are described in conjunction with the appendix below. Figure 1-5 The detailed description of the embodiments will clearly demonstrate this. All structural details mentioned in the following embodiments are based on the accompanying drawings.

[0024] Exemplary embodiments of the present invention will now be described with reference to the accompanying drawings.

[0025] Example 1: A vertically folding multi-rotor unmanned aerial vehicle (UAV), comprising a fuselage 1, characterized in that:

[0026] The fuselage 1 is provided with a propeller hub 2 at the top and bottom. The propeller hub 2 at the top is hinged with three sets of first arms 3, and the propeller hub 2 at the bottom is hinged with three sets of second arms 4. The three sets of first arms 3 and second arms 4 are staggered. The fuselage 1 is provided with a storage slot 5 along the circumference that corresponds to the first arms 3 and second arms 4.

[0027] The first arm 3 and the second arm 4 are equipped with blades 6 and motors 7. The blades 6 are driven by motors 7. The body 1 is equipped with several electric speed controllers 8 that control the motors, and photoelectric devices are provided at the bottom.

[0028] The rotor hub 2 is provided with an adjustment assembly for housing the first arm 3 and the second arm 4, and the bottom of the fuselage 1 is provided with a landing gear 9.

[0029] As an optional embodiment of Example 1, the storage assembly includes an elongated groove 10 on the propeller hub 2. A first auxiliary shaft 11 and a second auxiliary shaft 12 are fixedly connected in the elongated groove 10. A fixed shaft 13 is fixedly connected to the first auxiliary shaft 11 and slidably connected to the second auxiliary shaft 12. A return spring 14 is provided between the first auxiliary shaft 11 and the second auxiliary shaft 12. A first torsion spring 15 is provided between the first arm 3 and the second arm 4 and the propeller hub 2. A limiting groove 16 corresponding to the second auxiliary shaft 12 is provided on the first arm 3 and the second arm 4.

[0030] As an optional embodiment of Example 1, the fuselage 1 has at least three sets of fixed seats 17 along the circumferential direction at its bottom. The fixed seats 17 are hinged to the landing gear 9, and a second torsion spring 18 is provided between the landing gear 9 and the fixed seats 17.

[0031] As an optional embodiment of Example 1, the landing gear 9 is made of carbon fiber and has a rubber sleeve 19 at the bottom.

[0032] As an optional embodiment of Example 1, the three sets of first arms 3 and second arms 4 are evenly distributed circumferentially along the top and bottom rotor hubs 2, and the included angle between the three sets of first arms 3 and second arms 4 is 120 degrees.

[0033] In practical applications, when the drone needs to be stored, the second auxiliary shaft 12 is pushed to move in the limiting groove 16. At the same time, the return spring 14 is compressed, and the fixed shaft moves closer to the center of the rotor hub 2 along the axis. When the second auxiliary shaft 12 is pushed to a certain amount, it exits the limiting groove 16 of the first arm 3. At this time, the arm is released from the limiting lock state. After the arm is folded, the second auxiliary shaft 12 is limited and compressed by the circular outer contour of the port of the limiting groove 16. Then the first arm 3 folds into the storage groove 5 outside the fuselage. The folding operation of the second arm 4 is the same as that of the first arm 3, but the folding direction is reversed. After the arm is folded, it can be first secured with Velcro. Pick up the drone and directly press down on the three support carbon tubes of the landing gear to achieve folding. Then secure it with Velcro and put it into the transport box.

[0034] When the drone needs to be deployed, first unfasten the Velcro straps on the landing gear. The three support carbon tubes and support shaft 19 of the landing gear will unfold under the elastic action of the second torsion spring 18. Place the multi-rotor drone on the ground, unfasten the Velcro straps on the fuselage, and the first arm 3 and the second arm 4 will unfold under the elastic action of the first torsion spring 15. Then, the second auxiliary shaft 12 will slide into the limiting groove 16 of the first arm 3 and the second arm 4 under the elastic force of the return spring 14 which is in a compressed state, so that the first arm 3 and the second arm 4 are locked in position. Then the multi-rotor drone can carry out subsequent tasks.

[0035] The limiting slot 16 adopts a U-shaped slot. The outer side of the fuselage 1 on the right side of the first arm 3 and the second arm 4 is reserved for installing the ESC of each motor. The heat dissipation teeth of the ESC face outward and are exposed, so that they can be fully dissipated when the UAV is flying, which is conducive to the high-throttle high-speed flight of the multi-rotor UAV.

[0036] Optical payload and other equipment can be installed in the middle of the bottom of the fuselage 1 according to the usage requirements. The landing gear 9 is installed around the bottom of the fuselage 1. The base of the landing gear 9 is fixed to the bottom of the fuselage 1 with screws. The base is connected to the pivot pin with screws. A torsion spring is installed on the screw. A carbon tube is installed at the end of the pivot pin. The end of the carbon tube is fitted with a buffer rubber sleeve 19 to reduce the ground impact when the multi-rotor UAV lands.

[0037] The interior of fuselage 1 can be fitted with partitions and support plates according to usage requirements, facilitating the installation of onboard equipment, batteries, and the bundling of the entire machine's cables. A pre-installed charging port for the battery is located at the bottom of fuselage 1, allowing for rapid recharging of the multi-rotor drone without removing the battery, enabling the drone to quickly resume flight. When not charging, the charging port is fitted with a dust cover to prevent corrosion from dust and water vapor.

[0038] Advantages of this application:

[0039] The vertical folding of the upper and lower arms of the multi-rotor drone described in this patent can reduce the vertical size of the multi-rotor drone. When folding the blades 6 is selected (the example is an integrated blade 6), the vertical size of the multi-rotor will be further reduced after the two blades 6 are folded along the blade clamp screws, which makes it easier to store, load and transport.

[0040] The multi-rotor drone arm described in this patent can automatically deploy and lock without manual deployment, which facilitates remote deployment and flight mission execution.

[0041] The landing gear 9 of the multi-rotor UAV described in this patent can be automatically deployed for easy landing, and can be folded for easy storage and loading.

[0042] The multi-rotor drone described in this patent can be equipped with different mission payloads such as optoelectronic payloads or warheads on its bottom as needed, making it suitable for a wide range of applications.

[0043] The multi-rotor drone described in this patent is not limited to the example of a vertically folding six-axis drone, but can also be a vertically folding four-axis, eight-axis, or even more even-numbered axes drone. This type of multi-rotor drone can have a large payload with a small outer envelope size, and has a higher payload capacity than a simple vertically folding four-axis multi-rotor drone.

[0044] The multi-rotor drone described in this patent has a polygonal cylindrical shape, which makes it easy for a remote vehicle to load multiple multi-rotor drones into a small space, facilitating remote deployment and execution of specific tasks.

[0045] The above description is only for illustrating the present utility model. It should be understood that the present utility model is not limited to the above embodiments, and various modifications that conform to the concept of the present utility model are within the protection scope of the present utility model.

Claims

1. A vertical foldable multi-rotor unmanned aerial vehicle, comprising a fuselage (1), characterized in that: the top and bottom of the fuselage (1) are provided with hubs (2), wherein the top hub (2) is hinged with three groups of first arms (3), and the bottom hub (2) is hinged with three groups of second arms (4), the three groups of first arms (3) and second arms (4) are arranged in a staggered manner, and the fuselage (1) is provided with receiving grooves (5) corresponding to the first arms (3) and second arms (4) along the circumference; the first arms (3) and second arms (4) are provided with blades (6) and motors (7), the blades (6) are driven by the motors (7), the fuselage (1) is provided with a plurality of electronic speed controllers (8) for controlling the motors, and the bottom is provided with photoelectric equipment; the hub (2) is provided with a adjusting assembly for receiving the first arms (3) and second arms (4), and the bottom of the fuselage (1) is provided with a landing gear (9).

2. The vertically folding multi-copter drone of claim 1, wherein, It also includes a receiving assembly, the receiving assembly includes a long slot (10) formed in the hub (2), the long slot (10) is fixedly connected with a first auxiliary shaft (11) and a second auxiliary shaft (12) in sliding connection, the first auxiliary shaft (11) is fixedly connected with a fixed shaft (13) in sliding connection with the second auxiliary shaft (12), a return spring (14) is arranged between the first auxiliary shaft (11) and the second auxiliary shaft (12), a first torsional spring (15) is arranged between the first arms (3) and the second arms (4) and the hub (2), and a limiting groove (16) corresponding to the second auxiliary shaft (12) is arranged on the first arms (3) and the second arms (4).

3. The vertically folding multi-copter drone of claim 1, wherein, The bottom of the fuselage (1) is provided with at least three groups of fixed seats (17) along the circumference, the fixed seats (17) are hinged with landing gears (9), and a second torsional spring (18) is arranged between the landing gears (9) and the fixed seats (17).

4. The vertically folding multi-copter drone of claim 3, wherein, The landing gear (9) is a carbon tube, and the bottom of the landing gear (9) is provided with a rubber sleeve (19).

5. The vertically folding multi-copter drone according to any one of claims 1-4, wherein, The three groups of first arms (3) and second arms (4) are evenly distributed along the top and bottom hubs (2) in a circumferential direction, and the included angle between the three groups of first arms (3) and second arms (4) is one hundred and twenty degrees.

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