Traction unmanned aerial vehicle

Abstract

The invention discloses a traction unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles, the traction unmanned aerial vehicle comprises an unmanned aerial vehicle structure, a power energy system is arranged at the lower end of the unmanned aerial vehicle structure, an avionics flight control system is arranged at the upper end of the unmanned aerial vehicle structure, the power energy system provides energy for the avionics flight control system, and the avionics flight control system drives the unmanned aerial vehicle to operate. The traction unmanned aerial vehicle has the advantages of being large in traction force, high in energy efficiency, high in safety, convenient to use and wide in application.

Description

Technical Field

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

[0002] The low-altitude economy is a comprehensive economic form that takes low-altitude flight activities as the core, and interacts with airspace, market and other factors through the interaction of new quality productivity composed of technologies such as unmanned flight and low-altitude intelligent network, and promotes the development of low-altitude infrastructure, low-altitude aircraft manufacturing, low-altitude operation services and low-altitude flight support. This economic form not only covers general aviation, drones, emergency rescue, logistics and distribution, but also promotes the efficient use of land space and the coordinated development of regional economy. Paragliding is an important part of low-altitude activities and is becoming more and more popular among young people. The paraglider itself has no power. The reason why it can fly is that in addition to the special shape of the canopy after it is filled with air, it depends entirely on the pilot's control and combined with the characteristics of the atmosphere to fly. Paragliders will generate speed and lift during flight in the air, and their speed and lift are far greater than their resistance, so paragliders need to fly under certain customs conditions. At present, the eastern region has a developed economy and there are many paragliding enthusiasts, but due to the low wind in the eastern region, the main active sites for paragliding are in the central and western regions with strong winds. Paragliding enthusiasts need to make a special trip to the central and western regions to paraglide, which is time-consuming and laborious. Therefore, there is an urgent need to design a drone that can take off and land vertically around the city and has greater traction to meet the needs of towing paragliders.

[0003] The Chinese utility model patent with application number "202323355616.4" discloses "a multifunctional intelligent traction drone", including a body, and also including: a connecting plate, the connecting plate is fixedly connected to the bottom of the body; a shell, the shell is rotatably connected to the bottom of the connecting plate; a movable block, the movable block is slidably connected to the bottom of the shell; a traction rope, the traction rope is fixedly connected to the bottom of the movable block; wherein, after the traction rope is actuated, the movable block is slid along the shell, and the shell is rotated on the connecting plate to prevent the traction rope from twisting. The utility model can make the connection between the traction rope and the drone move synchronously with the movement of the traction rope, avoid the traction rope from twisting, reduce the situation where the drone needs to follow the moving direction of the pet and frequently rotate the direction, improve convenience, and the legs of the drone can be retracted upwards during flight to avoid the legs hindering the movement of the traction rope, improve convenience. However, the propeller pulling direction is up and down, and when it is necessary to pull forward and backward, the energy consumption is high, the force is small, and a large pulling force cannot be generated. Based on this, the present invention proposes a traction drone. Summary of the invention

[0004] The purpose of the present invention is to provide a towing drone to solve the above-mentioned problems.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0006] The present invention discloses a towing UAV, comprising a UAV structure, wherein a power energy system is arranged at the lower end of the UAV structure, and an avionics flight control system is arranged at the upper end of the UAV structure. The power energy system provides energy to the avionics flight control system, and the avionics flight control system drives the UAV to operate.

[0007] Furthermore, the UAV structure includes a main load-bearing structure located at the bottom, a shell is provided at the upper end of the main load-bearing structure, and a traction system is provided at the rear end of the main load-bearing structure.

[0008] Furthermore, the main load-bearing structure includes a fuselage, a plurality of lift arms are symmetrically arranged on the outer side wall of the fuselage, a tension arm is arranged at the center position of the lower end of the fuselage, and landing gears are symmetrically arranged on the lower end surface of the fuselage; the landing gears are connected together by a crossbeam at the middle position.

[0009] Furthermore, the power energy system includes a lifting unit arranged on the lifting arm, a pulling unit arranged on the pulling arm, and a battery pack arranged on the crossbeam, and the battery pack is provided with an electric regulator.

[0010] Furthermore, the lift unit includes a lift motor lower bracket mounted on the end of the lift arm, an upper lift motor bracket is arranged on the upper end of the lift motor lower bracket, a lift motor is arranged on the upper end surface of the lift motor upper bracket, and a lift propeller is arranged on the output shaft of the lift motor.

[0011] Furthermore, the pulling unit comprises a pulling motor bracket sleeved on both ends of the pulling arm, a pulling motor is arranged on the pulling motor bracket, and a pulling propeller is arranged at the output end of the pulling motor.

[0012] Furthermore, the tension motor bracket includes a tension arm hole, one end of the tension arm hole is provided with a groove, and the end of the tension arm hole away from the groove is provided with a motor mounting platform; and a plurality of lightening holes are provided on the tension arm hole.

[0013] Furthermore, the shell includes a flight control computer located in the middle position inside the shell, and the flight control computer is respectively provided with a radar, a navigation device, a data transmission device, an altitude sensor and an image transmission device around it; the data transmission device and the image transmission device are respectively provided with antennas.

[0014] Furthermore, bosses are symmetrically arranged on the shell body of the shell, and holes are opened on the bosses for the antenna to pass through.

[0015] Furthermore, the electric speed regulator is electrically connected to the battery pack and is located inside the fuselage.

[0016] Compared with the prior art, the beneficial technical effects of the present invention are:

[0017] The towing UAV of the invention is composed of a UAV structure, a power energy system, and an avionics flight control system. The UAV structure serves as the load-bearing structure of the UAV, bearing the forces during the take-off, landing, and flight of the UAV. At the same time, the power energy system and the avionics flight control system are installed on the UAV structure to provide support for the two systems and ensure that the installation is secure. The power energy system provides power and energy for the take-off, landing, and flight of the UAV, ensuring that the UAV completes the set flight time and flight profile. The avionics flight control system provides attitude control, communication, navigation, etc. for the UAV flight, ensuring the flight safety of the UAV, and enabling the UAV to fly according to the designed state. In short, the towing UAV of the present invention has the characteristics of large traction, high energy efficiency, high safety, easy use, and wide application. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The present invention will be further described below in conjunction with the accompanying drawings.

[0019] Figure 1 It is an axonometric view of the towing drone of the present invention;

[0020] Figure 2 This is an exploded view of the towing drone of the present invention;

[0021] Figure 3 This is the axonometric view of the drone structure;

[0022] Figure 4 This is an exploded view of the drone structure;

[0023] Figure 5 Axonometric drawing of the main load-bearing structure;

[0024] Figure 6 It is the axonometric diagram of the power energy system;

[0025] Figure 7 This is the exploded diagram of the lift unit;

[0026] Figure 8 This is the exploded diagram of the tension unit;

[0027] Fig. 9 This is the axonometric view of the tension motor bracket;

[0028] Fig.10 This is a partial view of the ESC installed inside the fuselage;

[0029] Fig.11 A partial view of the battery pack installation;

[0030] Fig.12 This is an axonometric view of the avionics flight control system;

[0031] Fig.13 This is a partial picture of the avionics flight control equipment installed on the upper part of the fuselage;

[0032] Fig.14 An axonometric view of the antenna mounted on the housing;

[0033] Description of reference numerals: 1. UAV structure; 2. Power energy system; 3. Avionics flight control system;

[0034] 11. Main load-bearing structure; 111. Lifting arm; 112. Tension wall; 113. Fuselage; 114. Landing gear; 115. Crossbeam; 12. Traction system; 13. Shell;

[0035] 21. Lift unit; 211. Lift propeller; 212. Lift motor; 213. Lift motor upper bracket; 214. Lift motor lower bracket; 22. Pull unit; 221. Pull propeller; 222. Pull motor; 223. Pull motor bracket; 2231. Slot; 2232. Pull arm hole; 2233. Motor mounting platform; 2234. Lightening hole; 23. Electric speed controller; 24. Battery pack;

[0036] 31. Flight control computer; 32. Radar; 33. Navigation equipment; 34. Data transmission equipment; 35. Altitude sensor; 36. Image transmission equipment; 37. Antenna. DETAILED DESCRIPTION

[0037] like Figure 1-14 As shown, a towing UAV includes a UAV structure 1, a power energy system 2 is installed at the lower end of the UAV structure 1, an avionics flight control system 3 is installed at the upper end of the UAV structure 1, the power energy system 2 provides energy to the avionics flight control system 3, and the avionics flight control system 3 drives the UAV to operate.

[0038] like Figure 3 , 4As shown, the UAV structure 1 includes a main load-bearing structure 11 located at the bottom, and the main load-bearing structure 11 bears the main force of the UAV and participates in the force transmission of the UAV. The upper end of the main load-bearing structure 11 is installed with a shell 13, which provides protection and installation for the avionics flight control system 3 installed on the upper part of the UAV fuselage, prevents the external environment from affecting the avionics flight control system 3, and improves the life of the avionics flight control system 3; at the same time, when the UAV flies forward, especially when flying at high speed, maneuvering or being affected by airflow, the fuselage will be subjected to various stresses and forces, and the shell 13 can evenly distribute these forces to the entire structure, avoid local stress concentration leading to structural damage, and enhance the strength and stability of the overall structure of the UAV; the shape of the shell 13 can reduce air resistance, make the UAV smoother during flight, reduce energy consumption, and improve flight efficiency and endurance. The shell can be made of plastic, metal, carbon fiber composite material, etc. This example is made of T300 grade carbon fiber fabric, which improves strength while reducing the weight of the shell. A traction system 12 is installed at the rear end of the main load-bearing structure 11. The traction system 12 tows the paraglider at the rear of the drone. Fixing the traction rope within a certain length range at the rear of the drone can effectively prevent the traction rope from being blown by the propeller of the drone and then entangled with the blades to cause an accident, thereby ensuring that the traction rope is safe and reliable.

[0039] like Figure 5 As shown, the main load-bearing structure 11 includes a fuselage 113, a plurality of lifting arms 111 are symmetrically mounted on the outer side wall of the fuselage 113, a tension arm 112 is mounted at the center position of the lower end of the fuselage 113, and landing gears 114 are symmetrically mounted on the lower end surface of the fuselage 113; the landing gears 114 are connected together at the middle position by a crossbeam 115.

[0040] like Figure 6 As shown, the power energy system 2 includes a lift unit 21 installed on the lift arm 111, a tension unit 22 installed on the tension arm 112, and a battery pack 24 installed on the crossbeam 115, and an electric regulator 23 is installed on the battery pack 24. The lift unit 21 generates lift for the UAV and is fixed on the lift arm 111 to provide power for the UAV to take off, land, and fly; the tension unit 22 generates tension and is fixed on the tension arm 112, which is mainly used to provide traction for the rear paraglider; the electric regulator 23 controls the lift motor 212 and the tension motor 222 in the lift unit 21 and the tension unit 22, controls the speed of the motor, and further controls the magnitude of the force generated by the lift unit 21 and the tension unit 22 to meet the needs of the UAV; the battery pack 24 is an energy system, which provides electrical energy for the lift unit 21 and the tension unit 22 to meet the energy needs of the lift unit 21 and the tension unit 22. As shown Fig.10 As shown, the ESC 23 is electrically connected to the battery pack 24 and is located inside the body 113 .

[0041] Among them, the lifting arm 111 bears the lifting force generated by the lifting unit 21 and transmits it to the main structure of the UAV; the pulling arm 112 is connected to the pulling unit 22, bears the pulling force generated by the pulling unit 22, and transmits it to the main structure of the UAV; the landing gear 114 serves the purpose of supporting the structure of the UAV, and its lower part is in contact with the ground, bearing the gravity of the UAV on the ground and the overload of the UAV during landing; the crossbeam 115 is connected to the landing gear 114 of the UAV on both sides to improve the stability and carrying capacity of the landing gear 114, and at the same time, the crossbeam 115 bears the gravity and overload of the battery pack 24. In this example, the lifting arm 111, the pulling arm 112, the landing gear 114, and the crossbeam 115 are all made of T700 grade carbon fiber unidirectional tape and are round tube structures. They are connected together through joints processed from aluminum alloy to form a continuous force transmission structure. The lifting arm 111 and the tension arm 112 are foldable structures at the joints, which facilitates the folding and unfolding of the drone. When folded, the volume occupied by the drone is reduced, which improves the convenience of drone transportation. The fuselage 113 is a box-shaped structure, which is made of multiple carbon fiber composite material plates. The lifting arm 111 and the landing gear 114 are connected together to form an integral structure. The tension arm 112 is connected to the landing gear 114 through a joint, and the lower part is the battery pack 24, which is fixed up and down together with the crossbeam 115 (such as Fig.11 As shown), the secure installation of the battery pack 24 is improved, and when landing at a high speed, the battery pack 24 can be effectively protected to prevent the battery pack 24 from falling off and landing on the ground.

[0042] like Figure 7 As shown, the lift unit 21 includes a lift motor lower bracket 214 sleeved on the end of the lift arm 111, a lift motor upper bracket 213 is installed on the upper end of the lift motor lower bracket 214, a lift motor 212 is installed on the upper end surface of the lift motor upper bracket 213, and a lift propeller 211 is installed on the output shaft of the lift motor 212. The lift motor upper bracket 213 and the lift motor lower bracket 214 are both aluminum alloy structures, and the preferred material is 7050-T7451. The lift propeller 211 is a propeller, which is driven to rotate by the lift motor 212 to generate lift along the axis, and the size of the lift can be changed by changing the speed of the lift motor 212. The lift motor 212 is powered by the battery pack 24 and controlled by the electric regulator 23, and converts electrical energy into mechanical energy through rotation.

[0043] like Figure 8 As shown, the pulling unit 22 includes a pulling motor bracket 223 sleeved on both ends of the pulling arm 112, a pulling motor 222 is installed on the pulling motor bracket 223, and a pulling propeller 221 is installed at the output end of the pulling motor 222. The pulling motor bracket 223 is machined from aluminum alloy material, and the preferred material is 7050-T7451.

[0044] like Fig. 9 As shown, the tension motor bracket 223 includes a tension arm hole 2232, and a groove 2231 is provided at one end of the tension arm hole 2232. The structures on both sides of the groove 2231 are tightened by fasteners. When the fasteners are tightened, the groove 2231 becomes smaller, and then the inner diameter of the tension arm hole 2232 becomes smaller, and is compacted on the tension arm 112, completing the fixing of the tension motor bracket 223 and the tension arm 112. A motor mounting platform 2233 is installed at one end of the tension arm hole 2232 away from the groove 2231, which is used to fix the tension motor 222. A fastener hole connected to the tension motor 222 is designed on the motor mounting platform 2233. The tension motor 222 is fixed to the tension motor bracket 223 by the fasteners, ensuring the reliability of the connection between the tension motor 222 and the tension arm 112. The tension arm hole 2232 is provided with a plurality of lightening holes 2234 , and the lightening holes 2234 are used to lighten the weight of the UAV structure, thereby increasing the load of the UAV.

[0045] In addition, the above-mentioned lever arm is a hollow structure, and the wiring harness used to connect the motor and the battery pack 24 is placed in the hollow structure, so that the wiring harness is arranged reasonably, the weight of the wiring harness is reduced, and then the weight of the entire drone structure is reduced.

[0046] like Fig.12 , 13 As shown in Figures 1 and 14, the shell 13 includes a flight control computer 31 located in the middle of the shell. The flight control computer 31 is respectively equipped with a radar 32, a navigation device 33, a data transmission device 34, an altitude sensor 35 and an image transmission device 36; the data transmission device 34 and the image transmission device 36 are respectively equipped with antennas 37. The main equipment of the avionics flight control system 3 is arranged on the upper fuselage of the UAV structure and is wrapped by the shell 13 to improve the environmental adaptability of each device of the avionics flight control system 3. At the same time, it is separated from the equipment of the power energy system 2 to avoid electromagnetic interference between the two voltage devices, thereby improving electromagnetic compatibility. The shell 13 is symmetrically installed with bosses, and the bosses are provided with holes for the antenna 37 to pass through. The antenna 37 is arranged outside the UAV structure to ensure the strength of the signal transmitted by the antenna 37.

[0047] Specifically, the flight control computer 31 controls the flight attitude of the UAV to meet the flight attitude requirements of the UAV, and at the same time controls the control equipment in the traction system 12 to control the retraction and tension of the traction rope, etc., to ensure that there is a safe distance between the UAV and the rear paraglider. The radar 32 monitors the position of the rear paraglider and feeds back the monitored information to the flight control computer 31, so that the flight control computer 31 controls the flight attitude of the UAV to ensure that the rear paraglider is directly behind the UAV and ensures the safety of the paraglider flight. The navigation device 33 provides a navigation system for the UAV, so that the UAV flies according to the planned route or airspace to prevent the UAV from getting lost. The data transmission device 34 transmits control instructions, sensor data and other non-video data for remote control operation of the UAV, flight status monitoring, sensor data collection and transmission. The data transmission device 34 forms a two-way link, so that the ground control personnel can remotely monitor the flight status of the UAV and send instructions for remote control operation. The image transmission device 36 transmits real-time video data and provides real-time video streams captured by the UAV camera for real-time monitoring and operation by the ground station or operator to ensure safety during flight. The altitude sensor 35 monitors the altitude information of the drone in real time, especially the distance between the drone and the ground during landing, so that the drone can land at a lower sinking speed, reduce the overload of the drone, reduce the impact of the ground on the landing gear 114, and thus increase the life of the landing gear 114. The antenna 37 provides signal transmission between the drone and the ground station, and also provides signal transmission between the drone and the positioning satellite, ensuring the accuracy of the drone's positioning and the accuracy and timeliness of information transmission.

[0048] The action process of the present invention is as follows:

[0049] First, the traction system 12 is connected to the paraglider located behind the UAV structure 1 through a traction rope; then, the avionics flight control system 3 controls the lift unit 21 to start, and the UAV takes off; finally, the avionics flight control system 3 controls the tension unit 22 to start, the UAV moves upward and forward, and the traction system 12 pulls the paraglider behind to move synchronously, helping the paraglider to take off.

[0050] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A towing drone, characterized in that: The invention comprises an unmanned aerial vehicle structure (1), wherein a power energy system (2) is arranged at the lower end of the unmanned aerial vehicle structure (1), and an avionics flight control system (3) is arranged at the upper end of the unmanned aerial vehicle structure (1); the power energy system (2) provides energy to the avionics flight control system (3), and the avionics flight control system (3) drives the unmanned aerial vehicle to operate.

2. The towing drone according to claim 1, characterized in that: The drone structure (1) comprises a main load-bearing structure (11) located at the bottom, a shell (13) is provided at the upper end of the main load-bearing structure (11), and a traction system (12) is provided at the rear end of the main load-bearing structure (11).

3. The towing drone according to claim 2, characterized in that: The main load-bearing structure (11) comprises a fuselage (113), a plurality of lifting arms (111) are symmetrically arranged on the outer side wall of the fuselage (113), a pulling arm (112) is arranged at the center position of the lower end of the fuselage (113), and landing gears (114) are symmetrically arranged on the lower end surface of the fuselage (113); the landing gears (114) are connected together at the middle position by a crossbeam (115).

4. The towing drone according to claim 3, characterized in that: The power energy system (2) comprises a lifting unit (21) arranged on a lifting arm (111), a pulling unit (22) arranged on a pulling arm (112), and a battery pack (24) arranged on the crossbeam (115); an electric regulator (23) is arranged on the battery pack (24).

5. The towing drone according to claim 4, characterized in that: The lift unit (21) comprises a lift motor lower bracket (214) sleeved on the end of the lift arm (111); a lift motor upper bracket (213) is arranged at the upper end of the lift motor lower bracket (214); a lift motor (212) is arranged on the upper end surface of the lift motor upper bracket (213); and a lift propeller (211) is arranged on the output shaft of the lift motor (212).

6. The towing drone according to claim 4, characterized in that: The pulling unit (22) comprises a pulling motor bracket (223) sleeved on the two ends of the pulling arm (112), a pulling motor (222) is arranged on the pulling motor bracket (223), and a pulling paddle (221) is arranged at the output end of the pulling motor (222).

7. The towing drone according to claim 6, characterized in that: The tension motor bracket (223) comprises a tension arm hole (2232), one end of the tension arm hole (2232) is provided with a groove (2231), and the end of the tension arm hole (2232) away from the groove (2231) is provided with a motor mounting platform (2233); and a plurality of lightening holes (2234) are provided on the tension arm hole (2232).

8. The towing drone according to claim 2, characterized in that: The housing (13) includes a flight control computer (31) located in the middle of the housing, and the flight control computer (31) is respectively provided with a radar (32), a navigation device (33), a data transmission device (34), an altitude sensor (35) and an image transmission device (36) around it; the data transmission device (34) and the image transmission device (36) are respectively provided with an antenna (37).

9. The towing drone according to claim 8, characterized in that: The shell (13) is symmetrically provided with bosses, and the bosses are provided with holes for the antenna (37) to pass through.

10. The towing drone according to claim 4, characterized in that: The electric regulator (23) is electrically connected to the battery pack (24) and is located inside the body (113).

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