Traction unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a traction unmanned aerial vehicle, which is characterized in that horizontal spiral components are fixed on two sides of a vehicle body, each horizontal spiral component comprises a force arm, the force arms are fixed on two sides of the vehicle body, propellers are mounted on one side of the top end face of each force arm, and a detachable buffer device is mounted at the bottom of the vehicle body. The buffer device comprises a motor, the motor is fixedly installed on the bottom end face of the machine body, a telescopic rod is installed in the center of the bottom end face of the machine body, the telescopic rod is sleeved with a telescopic spring, a cross-shaped supporting seat is fixedly installed at the bottom end of the telescopic rod, and a traction assembly is fixedly installed on the upper surface of the cross-shaped supporting seat. The horizontal spiral assembly can adjust thrust through speed change in the vertical take-off and landing stage so as to maintain the front-back balance of the unmanned aerial vehicle body, the buffer device is arranged to protect the unmanned aerial vehicle from being damaged during landing, the traction assembly is arranged to achieve the traction function, and the unmanned aerial vehicle has flexibility.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a towing unmanned aerial vehicle. Background Art

[0002] With the continuous development of science and technology, UAV technology has been greatly improved in recent years, and many intelligent and multifunctional unmanned aerial vehicles have emerged. In response to the needs of transmitting information and monitoring in some small areas, unmanned aircraft are becoming more and more important. It is a new concept aircraft in rapid development, which has the advantages of flexibility, fast response, unmanned flight, and low operation requirements.

[0003] When traditional rotor-type UAVs want to generate a large horizontal pulling force, they generally need to tilt at a larger attitude angle. When tilting at a large angle, the vertical pulling force is reduced, making the UAV's load capacity weaker. When towing heavy objects, a large angle tilt will destroy the stability of the UAV and may cause it to lose control. Heavy objects will have a greater impact on the attitude and stability of the UAV. Utility Model Content

[0004] The utility model aims at the deficiencies of the prior art and provides the following technical solutions:

[0005] A traction drone comprises a drone body, wherein the drone body comprises a fuselage, vertical spiral assemblies are installed at the four corners of the top of the outer wall of the drone body, supporting feet are fixedly installed on both sides of the bottom of the fuselage, horizontal spiral assemblies are fixed on both sides of the fuselage, the horizontal spiral assemblies comprise force arms, the force arms are fixed on both sides of the fuselage, propellers are installed on one side of the top end surface of the force arms, a detachable buffer device is installed at the bottom of the fuselage, the buffer device comprises a motor, the motor is fixedly installed on the bottom end surface of the fuselage, a telescopic rod is installed in the center of the bottom end surface of the fuselage, a telescopic spring is sleeved on the outside of the telescopic rod, a cross support seat is fixedly installed on the bottom end of the telescopic rod, and a traction assembly is fixedly installed on the upper surface of the cross support seat.

[0006] As an improvement of the above technical solution, the propeller is oriented in the same direction as the fuselage, and the propeller and the vertical screw assembly are perpendicular to each other.

[0007] As an improvement of the above technical solution, the bottom bolt of the motor is fixed, the telescopic end of the telescopic spring is sleeved with a connecting seat, one end of the telescopic spring is connected to the center of the outer wall of the connecting seat, and the other end of the telescopic spring is fixedly connected to the mounting seat.

[0008] As an improvement of the above technical solution, grounding plates are fixedly installed at the four corners of the bottom of the cross support seat.

[0009] As an improvement of the above technical solution, the traction end of the traction assembly is connected to the center of the cross support seat.

[0010] Beneficial effects of the utility model:

[0011] 1. The utility model can adjust the thrust by speed change during the vertical take-off and landing stage through the horizontal spiral assembly to maintain the front and rear balance of the UAV body. Combining the capabilities of vertical take-off and landing and horizontal flight, it has a large pulling force in both the horizontal and vertical directions. It can fly at high speed and can also be used as a tractor. It is also equipped with a buffer device to protect the UAV from damage during landing, and a traction assembly to achieve the traction function. This design makes the UAV more flexible and versatile, and can be used for the aerial traction of unpowered aircraft such as paragliders, gliders, and delta wings, and is suitable for various application scenarios such as logistics transportation, aerial inspections, agricultural operations, and urban air travel.

[0012] 2. The utility model locates the vertical spiral components at the four corners of the top outer wall of the UAV body, which are perpendicular to the axis of the fuselage, do not rely on complex tilting mechanisms or direction-changing mechanisms, have a simpler structure, and reduce manufacturing and maintenance costs. The horizontal spiral components are installed on both sides of the top end surface of the lever arm, which are consistent with the orientation of the fuselage and perpendicular to the direction of the vertical spiral components. The propeller provides the UAV with propulsion for horizontal flight, allowing the UAV to perform forward, backward, turning and other maneuverable operations in the air. The switching and stabilization of the flight mode are achieved by fixing the angle of the horizontal spiral component and the layout of the relative positions of the vertical spiral component and the horizontal spiral component. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is the overall structure diagram of the utility model;

[0014] Figure 2 This is the main structure diagram of the UAV of the utility model;

[0015] Figure 3 This is a structural diagram of the horizontal spiral assembly of the utility model;

[0016] Figure 4 This is a structural diagram of the buffer device of the utility model;

[0017] Figure 5 for Figure 4 Enlarged view of point A in the middle.

[0018] Figure numerals: 1. UAV body; 11. Fuselage; 12. Vertical spiral assembly; 13. Support foot; 2. Horizontal spiral assembly; 21. Lever; 22. Propeller; 3. Buffer device; 31. Motor; 32. Connecting seat; 33. Telescopic rod; 34. Mounting seat; 35. Telescopic spring; 36. Cross support seat; 37. Traction assembly; 38. Ground plate. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below. It should be understood that the specific embodiments described here are only used to explain the utility model, and are not used to limit the utility model.

[0020] See also Figure 1-5 , the utility model provides a technical solution:

[0021] A towing drone comprises a drone body 1, wherein the drone body 1 comprises a fuselage 11, vertical spiral assemblies 12 are installed at the four corners of the top of the outer wall of the drone body 1, supporting feet 13 are fixedly installed on both sides of the bottom of the fuselage 11, horizontal spiral assemblies 2 are fixed on both sides of the fuselage 11, the horizontal spiral assemblies 2 comprise lever arms 21, the lever arms 21 are fixed on both sides of the fuselage 11, propellers 22 are installed on one side of the top end surface of the lever arms 21, a detachable buffer device 3 is installed at the bottom of the fuselage 11, the buffer device 3 comprises a motor 31, the motor 31 is fixedly installed on the bottom end surface of the fuselage 11, a telescopic rod 33 is installed in the center of the bottom end surface of the fuselage 11, a telescopic spring 35 is sleeved on the outside of the telescopic rod 33, a cross support seat 36 is fixedly installed on the bottom end of the telescopic rod 33, and a towing assembly 37 is fixedly installed on the upper surface of the cross support seat 36.

[0022] In this embodiment, the vertical spiral assembly 12 is installed at the four corners of the top of the outer wall of the drone body 1, and is used to provide the ability of vertical take-off and landing and hovering, and provide stable vertical thrust. The lever arm 21 provides a support and installation position for the propeller 22. The horizontal spiral assembly 2 is symmetrically installed at the front of the fuselage 11, and is used to provide thrust during horizontal flight. The horizontal spiral assembly 2 can adjust the thrust by changing speed during the vertical take-off and landing stage to maintain the front and rear balance of the drone body 1. It is installed on the bottom end surface of the fuselage 11 through the buffer device 3. The telescopic rod 33 of the buffer device 3 is installed at the bottom of the fuselage 11, and has a telescopic function. It can provide buffering when the drone lands to reduce impact and damage. The telescopic spring 35 is sleeved on the outside of the telescopic rod 33 The part further enhances the buffering effect and protects the UAV from damage during landing. It is installed at the bottom of the telescopic rod 33 through a cross support seat 36 to provide a stable support structure and is used to install a traction component 37 to achieve traction. The design of the traction UAV combines the capabilities of vertical take-off and landing and horizontal flight. It has a large pulling force in both the horizontal and vertical directions. It can fly at high speed and can also be used as a tractor. At the same time, it is equipped with a buffer device 3 to protect the UAV from damage during landing, and is equipped with a traction component 37 to achieve the traction function. This design makes the UAV more flexible and versatile, and can be used in a variety of application scenarios such as logistics transportation, aerial inspection, agricultural operations, and urban air travel.

[0023] Specifically, the propeller 22 is oriented in the same direction as the fuselage 11 , and the propeller 22 and the vertical propeller assembly 12 are perpendicular to each other.

[0024] In this embodiment, the vertical spiral assembly 12 is located at the four corners of the top outer wall of the drone body 1, perpendicular to the axis of the fuselage 11, and does not rely on complex tilting mechanisms or change-of-direction mechanisms. The structure is simpler and the manufacturing and maintenance costs are reduced. The horizontal spiral assembly 2 is installed on both sides of the top end surface of the lever arm 21, consistent with the orientation of the fuselage 11, and perpendicular to the direction of the vertical spiral assembly 12. The propeller 22 provides the drone with propulsion for horizontal flight, allowing the drone to perform forward, backward, turning and other maneuverable operations in the air. The switching and stabilization of the flight mode are achieved by fixing the angle of the horizontal spiral assembly 2 and the layout of the relative positions of the vertical spiral assembly 12 and the horizontal spiral assembly 2.

[0025] Specifically, the bottom bolts of the motor 31 are fixed with a connecting seat 32 , the telescopic end of the telescopic spring 35 is sleeved with a mounting seat 34 , one end of the telescopic spring 35 is connected to the center of the outer wall of the connecting seat 32 , and the other end of the telescopic spring 35 is fixedly connected to the mounting seat 34 .

[0026] In this embodiment, the motor 31 is located at the bottom end surface of the fuselage 11 and serves as a driving component of the buffer device 3. A connecting seat 32 is fixed to the bottom of the motor 31 by bolts. The connecting seat 32 serves as a connecting component between the motor 31 and the telescopic rod 33. The center of its outer wall is connected to one end of the telescopic spring 35, allowing the telescopic spring 35 to generate telescopic deformation when the drone lands, thereby providing a buffer effect.

[0027] Specifically, grounding plates 38 are fixedly mounted at the four corners of the bottom of the cross support seat 36 .

[0028] In this embodiment, the grounding plate 38 increases the stability of the drone during landing. When the drone lands, the grounding plate 38 first contacts the ground, and disperses the impact force of the drone landing through its larger contact area, thereby improving the landing stability of the drone. The grounding plate 38 can be made of a material with anti-slip function to ensure that the drone will not slide or overturn due to slippery or tilted ground during landing.

[0029] Specifically, the traction end of the traction assembly 37 is connected to the center of the cross support seat 36.

[0030] In this embodiment, the cross support seat 36 is not only connected to the telescopic rod 33 of the buffer device 3, but also connected to the traction assembly 37. This design enables the drone to perform traction tasks stably and ensures the transmission efficiency and stability of the traction force.

[0031] The above embodiments are only used to illustrate the technical solution of the present invention, but not to limit it.

Claims

1. A towing drone, comprising a drone body (1), the drone body (1) comprising a fuselage (11), vertical spiral assemblies (12) being installed at four corners of the top of the outer wall of the drone body (1), and supporting feet (13) being fixedly installed on both sides of the bottom of the fuselage (11), characterized in that: Horizontal screw assemblies (2) are fixed on both sides of the fuselage (11), and the horizontal screw assembly (2) comprises a force arm (21), and the force arm (21) is fixed on both sides of the fuselage (11). A propeller (22) is installed on one side of the top end surface of the force arm (21). A detachable buffer device (3) is installed at the bottom of the fuselage (11), and the buffer device (3) comprises a motor (31). The motor (31) is fixedly installed on the bottom end surface of the fuselage (11). A telescopic rod (33) is installed in the center of the bottom end surface of the fuselage (11), and a telescopic spring (35) is sleeved on the outside of the telescopic rod (33). A cross support seat (36) is fixedly installed at the bottom end of the telescopic rod (33), and a traction assembly (37) is fixedly installed on the upper surface of the cross support seat (36).

2. A towing drone according to claim 1, characterized in that: The propeller (22) and the fuselage (11) are oriented in the same direction, and the propeller (22) of the horizontal screw assembly (2) and the vertical screw assembly (12) are oriented perpendicular to each other.

3. A towing drone according to claim 1, characterized in that: A connecting seat (32) is bolted to the bottom of the motor (31), a mounting seat (34) is sleeved on the outside of the telescopic end of the telescopic spring (35), one end of the telescopic spring (35) is connected to the center of the outer wall of the connecting seat (32), and the other end of the telescopic spring (35) is fixedly connected to the mounting seat (34).

4. A towing drone according to claim 1, characterized in that: Grounding plates (38) are fixedly mounted at the four corners of the bottom of the cross support seat (36).

5. The towing drone according to claim 1, characterized in that: The traction end of the traction assembly (37) is connected to the center of the cross support seat (36).

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