Low-pressure FOC driving device of multi-rotor unmanned aerial vehicle

Abstract

The utility model relates to the technical field of multi-rotor unmanned aerial vehicles, and discloses a multi-rotor unmanned aerial vehicle low-pressure FOC driving device which comprises a vehicle body, a low-pressure FOC driving assembly is arranged in the vehicle body, a plurality of connecting rods are fixedly connected to the outer portion of the vehicle body, and electric motors are fixedly connected to the top ends of the connecting rods. The driving end of the electric motor is fixedly connected with a rotating wing, the bottom end of the fuselage is in threaded connection with a supporting assembly, the top end of the fuselage is fixedly connected with a plurality of connecting blocks, solar panels are slidably connected into the top ends of the connecting blocks, and a plurality of clamping holes are formed in the bottom ends of the solar panels; a push rod is slidably connected to the inner wall of one side of the connecting block. According to the unmanned aerial vehicle, light energy can be converted into electric energy through the solar panel, and an extra energy source is provided for the unmanned aerial vehicle, so that aerial operation can be continuously carried out, the requirement for frequently replacing a battery or charging is reduced, and the overall operation efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of multi-rotor unmanned aerial vehicles, in particular to a low-voltage FOC driving device for a multi-rotor unmanned aerial vehicle. Background Art

[0002] A multi-rotor drone is an aircraft that uses multiple electric motors to drive rotors to generate lift and achieves flight control by adjusting the rotor speed. FOC control technology can improve the efficiency of electric motors, enabling them to operate efficiently under various load and speed conditions.

[0003] After searching, the Chinese patent document announcement number is: CN213974470U. This utility model relates to the field of unmanned aerial vehicle laser radar detection, and in particular to a multi-rotor unmanned aerial vehicle. The multi-rotor unmanned aerial vehicle includes: an unmanned aerial vehicle body, a first laser radar with a horizontal scanning function, and a second laser radar with a vertical scanning function; a support component, the support component includes a prism-shaped support seat, a first connecting part arranged on the small-diameter end face of the support seat, and a second connecting part arranged on the side wall of the support seat, the first laser radar is detachably connected to the small-diameter end face through the first connecting part, and the second laser radar is detachably connected to the side wall of the support seat through the second connecting part; a connecting component, the connecting component is arranged on the large-diameter end face of the support seat, so that the supporting component can be detachably connected to the bottom of the unmanned aerial vehicle body. The multi-rotor unmanned aerial vehicle can expand the detection range on the premise of improving the vertical direction angle and vertical resolution of the spatial point cloud obtained by the multi-rotor unmanned aerial vehicle.

[0004] The above patent mentions in the beneficial effects that "a first connecting ear is provided on the edge of the large diameter end face 132; the mounting base 140 includes a base body and a second connecting ear provided on the edge of the base body; the first connecting ear and the second connecting ear are detachably connected by a fastener, and the disassembly and assembly structure is simple, and the connection structure has high rigidity, which avoids shaking of the support base and further improves the scanning stability of the first laser radar 11 and the second laser radar 12". However, it cannot support the UAV to operate in the air for a long time, and it needs to land to replace the battery or charge. Frequent replacement of batteries or charging will increase the cost and time of operation, which will reduce the overall operation efficiency. For this reason, a low-voltage FOC drive device for a multi-rotor UAV is proposed to solve the above problems. Utility Model Content

[0005] In order to make up for the above shortcomings, the utility model provides a low-voltage FOC drive device for a multi-rotor UAV, aiming to improve the problem in the prior art that the UAV has too low endurance and needs frequent battery replacement or charging.

[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:

[0007] A low-voltage FOC drive device for a multi-rotor unmanned aerial vehicle comprises a fuselage, a low-voltage FOC drive assembly is arranged inside the fuselage, a plurality of connecting rods are fixedly connected to the outside of the fuselage, the top of the connecting rods is fixedly connected to an electric motor, the driving end of the electric motor is fixedly connected to a rotating wing, the bottom end of the fuselage is threadedly connected to a supporting assembly, a plurality of connecting blocks are fixedly connected to the top of the fuselage, a solar panel is slidably connected to the top of the connecting block, a plurality of engaging holes are provided at the bottom end of the solar panel, a push rod is slidably connected to the inner wall of one side of the connecting block, a engaging block is fixedly connected to one side of the push rod, a movable hole is provided inside the connecting block, and two strong springs are provided inside the movable hole;

[0008] As a further description of the above technical solution:

[0009] The outside of the connecting rod is fixedly connected with a receiving column, the inside of the connecting rod is provided with a receiving hole, the inside of the connecting rod is slidably connected with a plurality of sliding rods, a strong spring 2 is arranged inside the receiving hole, the adjacent sides of the plurality of sliding rods are fixedly connected with a clamping block, and the distant sides of the plurality of sliding rods are fixedly connected with a baffle;

[0010] As a further description of the above technical solution:

[0011] The support assembly includes a connection plate, a plurality of support legs are fixedly connected to the bottom end of the connection plate, and the outer thread of the connection plate is connected to the inside of the bottom end of the fuselage;

[0012] As a further description of the above technical solution:

[0013] The low voltage FOC drive assembly is connected to the electric motor by wires;

[0014] As a further description of the above technical solution:

[0015] The outside of the engaging block is engaged with the inside of the engaging hole, and one side of the engaging block is slidably connected to one side of the inside of the movable hole;

[0016] As a further description of the above technical solution:

[0017] One end of the strong spring 1 is fixedly connected to one side of the locking block, and the other end of the strong spring 1 is fixedly connected to one side of the inner side of the movable hole;

[0018] As a further description of the above technical solution:

[0019] One side of the baffle plate is in contact with the outside of the connecting rod, and the second strong spring is sleeved on the outside of the sliding rod.

[0020] The utility model has the following beneficial effects:

[0021] 1. In the present invention, solar panels can convert light energy into electrical energy, providing an additional energy source for the drone, which can continuously perform aerial operations, reduce the need for frequent battery replacement or charging, and improve overall operating efficiency.

[0022] 2. In the utility model, the line connecting the FOC drive assembly and the electric motor can be tightened by the elastic support of the strong spring 2, and the wires can be fixed in a suitable position, thereby reducing the risk of wire wear or damage caused by the vibration generated during the flight of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a three-dimensional schematic diagram of the low-voltage FOC drive device for a multi-rotor UAV proposed in the utility model;

[0024] Figure 2 for Figure 1 A magnified image of point A;

[0025] Figure 3 This is a schematic diagram of the engagement block structure of the low-voltage FOC drive device for a multi-rotor UAV proposed in the utility model;

[0026] Figure 4 This is a schematic diagram of the sliding rod structure of the low-voltage FOC drive device of the multi-rotor UAV proposed in the utility model.

[0027] Legend:

[0028] 1. Fuselage; 2. Connecting rod; 3. Electric motor; 4. Rotating wing; 5. Connecting plate; 6. Support leg; 7. Connecting block; 8. Solar panel; 9. Engagement hole; 10. Push rod; 11. Engagement block; 12. Movable hole; 13. Powerful spring 1; 14. Accommodating column; 15. Accommodating hole; 16. Sliding rod; 17. Powerful spring 2; 18. Clamping block; 19. Stop plate. DETAILED DESCRIPTION

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

[0030] Reference Figure 1 - Figure 3The utility model provides an embodiment: a low-voltage FOC drive device for a multi-rotor UAV, including a fuselage 1, which is the main structure of the UAV. A low-voltage FOC drive component is arranged inside the fuselage 1. This component is responsible for controlling the operation of the motor to ensure high efficiency and high performance. FOC is a motor control strategy that can accurately control the torque and speed of the motor. The fuselage 1 is fixedly connected to the outside with multiple connecting rods 2 to provide structural support. The top of the connecting rod 2 is fixedly connected to an electric motor 3, which is the power source of the UAV. The low-voltage FOC drive component is connected to the electric motor 3 by wires. The driving end of the electric motor 3 is fixedly connected to a rotary wing 4. When the rotary wing 4 rotates, it generates lift to make the UAV take off. The bottom end of the fuselage 1 is threadedly connected to a support component. The support component includes a connecting plate 5. The bottom end of the connecting plate 5 is fixedly connected to multiple support legs 6 for stabilizing the UAV on the ground. The external thread of the connecting plate 5 is connected to the bottom end of the fuselage 1. This design allows the support component to be disassembled, so that the UAV can be better stored. The top of the fuselage 1 is fixedly connected to multiple connecting blocks 7 for installing subsequent components. The top of the connecting block 7 is internally slidably connected to a solar panel 8 that can be used in flight. Or collect solar energy on the ground and convert it into electrical energy to provide an additional energy source for the drone. A plurality of snap-in holes 9 are provided at the bottom end of the solar panel 8. A push rod 10 is slidably connected to the inner wall of one side of the connecting block 7 for easy operation by the user. A snap-in block 11 is fixedly connected to one side of the push rod 10. A movable hole 12 is provided inside the connecting block 7, in which the snap-in block 11 slides. The outside of the snap-in block 11 snaps with the inside of the snap-in hole 9. This design is used to fix the position of the solar panel 8. One side of the snap-in block 11 is slidably connected to one side of the inner part of the movable hole 12. Two strong springs 13 are arranged inside the movable hole 12. One end of the strong spring 13 is fixedly connected to one side of the snap-in block 11, and the other end of the strong spring 13 is fixedly connected to one side of the inner part of the movable hole 12. The strong spring 13 provides a restoring force when the snap-in block 11 moves, helping to lock or unlock the solar panel 8.

[0031] Reference Figure 1 - Figure 3 The outside of the connecting rod 2 is fixedly connected with a accommodating column 14 in order to provide additional expansion space and increase the structural support of the connecting rod 2. A accommodating hole 15 is opened inside the connecting rod 2 to accommodate other components. The inside of the connecting rod 2 is slidably connected with multiple sliding rods 16. This design allows the sliding rod 16 to move within a certain range. The inside of the accommodating hole 15 is provided with a strong spring 17. These springs provide elastic force. The strong spring 17 is sleeved on the outside of the sliding rod 16. The adjacent sides of the multiple sliding rods 16 are fixedly connected with a clamping block 18, and the distant sides of the multiple sliding rods 16 are fixedly connected with a baffle 19. A stopper designed to prevent the sliding rod 16 from excessive movement, one side of the baffle 19 is in contact with the outside of the connecting rod 2.

[0032] Working principle: The designed solar panel 8 can convert light energy into electrical energy, providing an additional energy source for the drone. This way of supplementing energy has a positive effect on increasing the flight time of the drone, allowing the drone to have a long endurance. Then, when the solar panel 8 needs to be installed, first pull the push rod 10, and the push rod 10 drives the locking block 11 to move inside the movable hole 12, and then the strong spring 13 is contracted. At this time, the solar panel 8 is inserted into the interior of the connecting block 7, so that the bottom end of the solar panel 8 slides into the interior of the locking block 11, and then the locking block 11 is rebounded under the rebound force of the strong spring 13, so that one side of the locking block 11 is engaged with the inside of the locking hole 9, so as to achieve the installation and fixation of the solar panel 8, and then when the line is bundled, the strong spring 2 17 is contracted, and then after the wires are put in, the strong spring 2 17 is contracted, and the generated rebound force rebounds to tighten the wires.

[0033] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A low-voltage FOC driving device for a multi-rotor UAV, comprising a fuselage (1), characterized in that: A low-voltage FOC drive assembly is arranged inside the fuselage (1); a plurality of connecting rods (2) are fixedly connected to the outside of the fuselage (1); the top of the connecting rod (2) is fixedly connected to an electric motor (3); the driving end of the electric motor (3) is fixedly connected to a rotating wing (4); the bottom end of the fuselage (1) is threadedly connected to a support assembly; a plurality of connecting blocks (7) are fixedly connected to the top of the fuselage (1); a solar panel (8) is slidably connected to the top of the connecting block (7); a plurality of engaging holes (9) are provided at the bottom end of the solar panel (8); a push rod (10) is slidably connected to the inner wall of one side of the connecting block (7); a engaging block (11) is fixedly connected to one side of the pushing rod (10); a movable hole (12) is provided inside the connecting block (7); two strong springs (13) are provided inside the movable hole (12).

2. The low-voltage FOC driving device for a multi-rotor UAV according to claim 1 is characterized in that: The outside of the connecting rod (2) is fixedly connected with a receiving column (14), the inside of the connecting rod (2) is provided with a receiving hole (15), the inside of the connecting rod (2) is slidably connected with a plurality of sliding rods (16), the inside of the receiving hole (15) is provided with a strong spring 2 (17), the adjacent sides of the plurality of sliding rods (16) are fixedly connected with a clamping block (18), and the distant sides of the plurality of sliding rods (16) are fixedly connected with a baffle (19).

3. The multi-rotor UAV low-voltage FOC driving device according to claim 1, characterized in that: The support assembly comprises a connection plate (5), the bottom end of which is fixedly connected to a plurality of support legs (6), and the external thread of the connection plate (5) is connected to the inside of the bottom end of the fuselage (1).

4. The multi-rotor UAV low-voltage FOC driving device according to claim 1, characterized in that: The low-voltage FOC drive component is connected to the electric motor (3) via electric wires.

5. The multi-rotor UAV low-voltage FOC driving device according to claim 1, characterized in that: The outside of the engaging block (11) engages with the inside of the engaging hole (9), and one side of the engaging block (11) is slidably connected to one side of the inside of the movable hole (12).

6. The multi-rotor UAV low-voltage FOC driving device according to claim 1, characterized in that: One end of the strong spring (13) is fixedly connected to one side of the locking block (11), and the other end of the strong spring (13) is fixedly connected to one side inside the movable hole (12).

7. The multi-rotor UAV low-voltage FOC driving device according to claim 2, characterized in that: One side of the baffle (19) contacts the outside of the connecting rod (2), and the second strong spring (17) is sleeved on the outside of the sliding rod (16).

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