Mooring unmanned aerial vehicle

Abstract

The mooring unmanned aerial vehicle comprises an unmanned aerial vehicle body, balance rotors are symmetrically arranged on the two sides of a fuselage of the unmanned aerial vehicle body respectively, a tail rotor is arranged on the side, adjacent to the balance rotors, of the fuselage, and the balance rotors and the tail rotor are connected with the fuselage through quick release mechanisms respectively. The balance rotors are arranged on the two sides of the unmanned aerial vehicle body, so that the lateral disturbance influence of the unmanned aerial vehicle is effectively counteracted, the attitude stability in a hovering mode is greatly improved, and the unmanned aerial vehicle can effectively cope with a complex airflow environment; meanwhile, a tail rotor wing is further arranged and is matched with the balance rotor wing, so that the height stability of the unmanned aerial vehicle in various flight attitudes is ensured, and the operation precision and the execution efficiency are effectively improved; the balance rotor wing and the tail rotor wing are connected and clamped with the fuselage of the unmanned aerial vehicle body through the quick disassembly mechanism, so that the balance rotor wing and the tail rotor wing can be quickly disassembled and assembled, the balance rotor wing and the tail rotor wing can be installed according to use requirements, and use is more flexible.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a tethered UAV. Background Technology

[0002] In the current field of fire and rescue, multi-rotor tethered drones play a crucial role in fire control due to their excellent stability. These drones can effectively reduce the risk of firefighters directly facing the fire scene and improve the efficiency and safety of rescue operations.

[0003] Traditional tethered drone systems typically include: a tethered drone, an environmental monitoring unit, and a fire suppression unit. The environmental monitoring and fire suppression units are both mounted on the tethered drone. The environmental monitoring unit monitors the surrounding environment, including images of the drone's surroundings, distances to objects, and temperature. The fire suppression unit sprays extinguishing agents such as water or dry powder. The tethered drone is also equipped with a rescue megaphone (such as a loudspeaker) and a rescue light. The megaphone allows for broadcasting or communication to trapped personnel, while the rescue light provides illumination to facilitate subsequent rescue operations.

[0004] Traditional multi-rotor tethered drones, due to the limitations of their design principles, are easily affected by external factors in high-altitude environments and complex and changeable airflow at fire sites, such as strong winds and turbulence. The drones are prone to deflection, resulting in unstable flight attitude, which affects operational accuracy and consequently impacts the efficiency and safety of firefighting missions. Utility Model Content

[0005] The purpose of this invention is to provide a tethered drone to solve the problem that existing multi-rotor tethered drones are prone to deflection and have difficulty maintaining stable hovering when performing high-altitude firefighting operations, thus affecting the accuracy of the operation.

[0006] The technical solution of this utility model to solve the above-mentioned technical problems is as follows:

[0007] A tethered drone includes a drone body, with symmetrically arranged counter-rotors on both sides of the fuselage of the drone body, and a tail rotor arranged on the side of the fuselage adjacent to the counter-rotors. The counter-rotors and the tail rotor are respectively connected to the fuselage through quick-release mechanisms.

[0008] The quick-release mechanism includes a grooved plate on the outer wall of the fuselage, two U-shaped plates that slide through the two side plates of the grooved plate and are symmetrical to each other, and a C-shaped connecting plate that engages with the horizontal plate of the two U-shaped plates. The two vertical rods of the U-shaped plate slide with the side plate of the grooved plate. The horizontal plate is located inside the grooved plate, and a spring is provided between the horizontal plate and the corresponding side plate of the grooved plate. The balance rotor and the tail rotor are respectively connected to the corresponding C-shaped connecting plates.

[0009] Furthermore, the aforementioned horizontal plate is provided with a through groove that matches the short plate of the C-shaped connecting plate, and the size of the groove on the grooved plate matches the size of the C-shaped connecting plate;

[0010] The short plate of the C-shaped connecting plate is engaged in the through groove on the horizontal plate by the elastic force of spring one.

[0011] Furthermore, the aforementioned spring is mounted on the outer wall of the corresponding vertical rod.

[0012] Furthermore, the aforementioned spring is provided in two sets.

[0013] Furthermore, a spring is connected between the horizontal plates of the two U-shaped plates.

[0014] Furthermore, the aforementioned balanced rotor includes a first link connected to a corresponding C-shaped connecting plate, a first motor disposed at the end of the first link, and a lateral propeller connected to the output shaft of the first motor. The first motor is communicatively connected to the UAV body, and the rotation direction of the lateral propeller is perpendicular to the rotation direction of the propeller on the UAV body.

[0015] Furthermore, the aforementioned tail rotor includes a second link connected to a corresponding C-shaped connecting plate, a second motor located at the end of the second link, and a tail propeller connected to the output shaft of the second motor. The second motor is communicatively connected to the UAV body, and the rotation direction of the tail propeller is perpendicular to the rotation direction of the propeller on the UAV body.

[0016] This utility model has the following beneficial effects:

[0017] This invention effectively counteracts lateral disturbances by incorporating balancing rotors on both sides of the drone body, significantly improving attitude stability in hovering mode and enabling it to effectively cope with complex airflow environments, thus enhancing flight stability. A tail rotor is also included, working in conjunction with the balancing rotors to ensure altitude stability of the drone in various flight attitudes, thereby effectively improving operational accuracy and efficiency. Both the balancing rotors and tail rotor are connected and secured to the drone body via quick-release mechanisms, allowing for rapid assembly and disassembly. The balancing rotors and tail rotor can be installed according to usage requirements, making them more flexible in use. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of a tethered drone;

[0019] Figure 2 A side view diagram of the tethered drone structure;

[0020] Figure 3 for Figure 2 A magnified structural diagram of part A;

[0021] Figure 4 This is a schematic diagram of the C-shaped connecting plate.

[0022] In the diagram: 1. UAV body; 11. Propeller; 2. Fuselage; 3. Balance rotor; 31. First link; 32. First motor; 33. Side propeller; 4. Tail rotor; 41. Second link; 42. Second motor; 43. Tail propeller; 5. Quick-release mechanism; 51. Groove plate; 511. Groove; 52. U-shaped plate; 521. Horizontal plate; 522. Vertical rod; 53. C-shaped connecting plate; 531. Short plate; 54. Spring 1; 55. Spring 2. Detailed Implementation

[0023] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0024] like Figure 1 As shown, an embodiment of this utility model provides a tethered drone, including a drone body 1. A symmetrical balance rotor 3 is symmetrically arranged on both sides of the fuselage 2 of the drone body 1. A tail rotor 4 is arranged on the side of the fuselage 2 adjacent to the balance rotor 3. The balance rotor 3 and the tail rotor 4 are connected to the fuselage 2 via quick-release mechanisms 5. In high-altitude conditions and when the airflow is unstable, the lateral balance rotor 3 can counteract the lateral airflow disturbance of the drone, thereby improving attitude stability in hovering mode. The tail rotor 4 is used to ensure the longitudinal stability of the drone. The quick-release mechanism 5 facilitates the rapid assembly and disassembly of the balance rotor 3 and the tail rotor 4, and allows for the installation of the balance rotor 3 and the tail rotor 4 according to usage requirements, making it more flexible in use.

[0025] like Figures 2 to 4As shown, the quick-release mechanism 5 includes a grooved plate 51 disposed on the outer wall of the fuselage 2, with a groove 511 inside the grooved plate 51; two U-shaped plates 52 slidably passing through the side plates of the grooved plate 51 and symmetrical to each other, each U-shaped plate 52 including two vertical rods 522 and a horizontal plate 521 connecting the two vertical rods 522; the side wall of the grooved plate 51 has sliding holes matching the vertical rods 522; the two vertical rods 522 of the U-shaped plate 52 slide in cooperation with the side plates of the grooved plate 51, and the horizontal plate 521 is located inside the grooved plate 51; and a C-shaped connecting plate 53 engaging with the horizontal plate 521 of the two U-shaped plates 52; a spring 54 is disposed between the horizontal plate 521 and the corresponding side plate of the grooved plate 51; the balance rotor 3 and the tail rotor 4 are respectively connected to the corresponding C-shaped connecting plate 53. In this embodiment, the spring 54 is sleeved on the outer wall of the corresponding vertical rod 522; and there are two sets of springs 54.

[0026] In this embodiment, the two U-shaped plates 52 are symmetrically distributed vertically, that is, one U-shaped plate 52 slides through the top plate of the grooved plate 51, and the other U-shaped plate 52 slides through the top plate of the grooved plate 51; the horizontal plates 521 of the two U-shaped plates 52 are adjacent, and there is a gap between the horizontal plates 521 of the two U-shaped plates 52. In other embodiments of this utility model, the two U-shaped plates 52 may also be symmetrically distributed horizontally, and no specific limitation is made here.

[0027] Specifically, the horizontal plate 521 has a through groove that matches the short plate 531 of the C-shaped connecting plate 53, and the size of the groove 511 on the grooved plate 51 matches the size of the C-shaped connecting plate 53; the short plate 531 of the C-shaped connecting plate 53 is inserted into the through groove on the horizontal plate 521 under the elastic force of the spring 54. A vertical rod 522 on one U-shaped plate 52 extends from the top of the grooved plate 51, and a vertical rod 522 on the other U-shaped plate 52 extends from the bottom of the grooved plate 51, making it easy to press. When it is necessary to install the balance rotor 3 and the tail rotor 4, press the vertical rods 522 at the top and bottom of the grooved plate 51 and bring the horizontal plates 521 of the two U-shaped plates 52 closer to each other. At this time, the spring 54 is stretched, and the C-shaped connecting plate 53 is inserted into the groove 511 of the grooved plate 51, and the short plate 531 is aligned with the through slot on the corresponding horizontal plate 521. When the U-shaped plate 52 is released, the U-shaped plate 52 is driven to return to its original position under the elastic force of the spring 54, and then the short plate 531 of the C-shaped connecting plate 53 is inserted into the through slot on the horizontal plate 521. Finally, the balance rotor 3 and the tail rotor 4 are respectively fastened to the fuselage 2, which is convenient to use.

[0028] A second spring 55 connects the horizontal plates 521 of the two U-shaped plates 52, and the second spring 55 is located on the side of the C-shaped connecting plate 53. The second spring 55 can work together with the first spring 54 to make it easy for the short plate 531 to be inserted into the through groove of the horizontal plate 521.

[0029] like Figure 1As shown, the balanced rotor 3 includes a first link 31 connected to a corresponding C-shaped connecting plate 53, a first motor 32 located at the end of the first link 31, and a lateral propeller 33 connected to the output shaft of the first motor 32. The first motor 32 is communicatively connected to the UAV body 1. The fuselage 2 of the UAV body 1 is provided with multiple interfaces electrically connected to its power module. The first motor 32 is connected to these interfaces via cables, and simultaneously, the first motor 32 is communicatively connected to the control module on the UAV body 1. The rotation direction of the lateral propeller 33 is perpendicular to the rotation direction of the propeller 11 on the UAV body 1. When there is lateral airflow disturbance on the UAV, the first motor 32 can be activated, and the lateral propeller 33 can be driven to rotate by the first motor 32, thereby effectively counteracting the lateral disturbance of the UAV and significantly improving the attitude stability in hovering mode.

[0030] The tail rotor 4 includes a second link 41 connected to a corresponding C-shaped connecting plate 53, a second motor 42 located at the end of the second link 41, and a tail propeller 43 connected to the output shaft of the second motor 42. The second motor 42 is communicatively connected to the UAV body 1 and electrically connected to an interface on the fuselage 2 via a cable. Simultaneously, the second motor 42 is communicatively connected to the control module on the UAV body 1, and the rotation direction of the tail propeller 43 is perpendicular to the rotation direction of the propeller 11 on the UAV body 1. When the UAV experiences longitudinal instability, the second motor 42 is activated, driving the tail propeller 43 to rotate, thereby ensuring the longitudinal stability of the UAV. Both the balance rotor 3 and the tail rotor 4 are connected and secured to the fuselage 2 of the UAV body 1 via a quick-release mechanism 5, allowing for quick assembly and disassembly of the balance rotor 3 and tail rotor 4. The balance rotor 3 and tail rotor 4 can be installed according to usage requirements, providing greater flexibility.

[0031] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A tethered drone comprising a drone body (1), characterized in that: The unmanned aerial vehicle body (1) is provided with balance rotors (3) on both sides of the fuselage (2) symmetrically, and a tail rotor (4) is arranged on the side of the fuselage (2) adjacent to the balance rotor (3); the balance rotor (3) and the tail rotor (4) are connected to the fuselage (2) through quick release mechanisms (5) respectively. The quick release mechanism (5) comprises a groove plate (51) arranged on the outer wall of the fuselage (2), two U-shaped plates (52) slidingly arranged on the two side plates of the groove plate (51) symmetrically, and a C-shaped connecting plate (53) clamped with the horizontal plates (521) of the two U-shaped plates (52); the two vertical rods (522) of the U-shaped plate (52) are slidingly matched with the side plates of the groove plate (51), the horizontal plate (521) is located inside the groove plate (51), and a spring (54) is arranged between the horizontal plate (521) and the corresponding side plate of the groove plate (51); the balance rotor (3) and the tail rotor (4) are connected with the corresponding C-shaped connecting plate (53) respectively.

2. The tethered drone of claim 1, wherein, A through groove is formed in the horizontal plate (521) and matched with the short plate (531) of the C-shaped connecting plate (53), and the size of the groove (511) of the groove plate (51) is matched with the size of the C-shaped connecting plate (53). The short plate (531) of the C-shaped connecting plate (53) is clamped into the through groove of the horizontal plate (521) under the elastic force of the spring (54).

3. The tethered drone of claim 1, wherein, The spring (54) is sleeved on the outer wall of the corresponding vertical rod (522).

4. The tethered drone of claim 3, wherein, The spring (54) is provided with two groups.

5. The tethered drone of any one of claims 1 to 4, wherein, A spring (55) is arranged between the horizontal plates (521) of the two U-shaped plates (52).

6. The tethered drone of claim 5, wherein, The balance rotor (3) comprises a first connecting rod (31) connected with the corresponding C-shaped connecting plate (53), a first motor (32) arranged at the end of the first connecting rod (31), and a lateral propeller (33) connected with the output shaft of the first motor (32); the first motor (32) is in communication connection with the unmanned aerial vehicle body (1), and the rotation direction of the lateral propeller (33) is perpendicular to the rotation direction of the propeller (11) on the unmanned aerial vehicle body (1).

7. The tethered drone of claim 5, wherein, The tail rotor (4) comprises a second connecting rod (41) connected with the corresponding C-shaped connecting plate (53), a second motor (42) arranged at the end of the second connecting rod (41), and a tail propeller (43) connected with the output shaft of the second motor (42); the second motor (42) is in communication connection with the unmanned aerial vehicle body (1), and the rotation direction of the tail propeller (43) is perpendicular to the rotation direction of the propeller (11) on the unmanned aerial vehicle body (1).

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