A multi-rotor drone

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles, and discloses a multi-rotor unmanned aerial vehicle, including a commutator, two engines located on both sides of the commutator and arranged in a central symmetric manner, a power transmission component driven to rotate by the engines, an input and output shaft driven to rotate by the power transmission component, the input and output shafts are connected to the commutator and drive the commutator output shaft of the commutator to rotate, and the rotation direction of the input and output shafts is opposite to the rotation direction of the commutator output shaft, and the input and output shafts and the commutator output shaft are both connected to rotors. Through the above structure, the present invention can increase the load capacity and endurance time, and by using two engines, when a single engine fails, it can land safely through another engine, effectively improving the safety performance of the unmanned aerial vehicle. Moreover, the above-mentioned multi-rotor unmanned aerial vehicle of the present invention has the characteristics of light weight, small size and low vibration.

Description

Technical Field

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

[0002] With the development of drone technology, it has played an indispensable role in aerial photography, detection, stabilization, reconnaissance, rescue, plant protection, etc., and has occupied an extremely important position in both civilian and military fields. In recent years, multi-rotor drones have gradually become the mainstream of the development of the drone field, and multi-rotor drones of various styles and functions have appeared in the market.

[0003] Most of the existing multi-rotor drones are powered by electric motors, but the energy density of batteries is much lower than that of fuel, so most of the existing multi-rotor drones have the disadvantages of small load capacity and short endurance, and these disadvantages seriously restrict the development of multi-rotor drones. There are also some oil-powered multi-rotor drones driven by piston engines in the prior art, but piston engines have disadvantages such as heavy weight, large vibration, and high noise, and require a special cooling system to ensure long-term stable operation. In addition, most existing drones are driven by one engine, and the operation of a single engine cannot meet the upgrade requirements of high power, large load capacity, and high safety. Summary of the invention

[0004] The purpose of the present invention is to provide a multi-rotor UAV, which can increase the load capacity and flight time and improve the safety performance of the UAV.

[0005] To achieve this object, the present invention adopts the following technical solutions:

[0006] A multi-rotor unmanned aerial vehicle comprises a commutator, two engines located on both sides of the commutator and arranged in a centrally symmetrical manner, a power transmission component driven to rotate by the engines, and an input and output shaft driven to rotate by the power transmission component, wherein the input and output shafts are connected to the commutator and drive the commutator output shaft of the commutator to rotate, and the rotation direction of the input and output shafts is opposite to the rotation direction of the commutator output shaft, and the input and output shafts and the commutator output shaft are both connected to rotors.

[0007] Preferably, the power transmission assembly includes a mounting frame, a driving synchronous pulley and a driven synchronous pulley located on the mounting frame, and a synchronous belt connecting the driving synchronous pulley and the driven synchronous pulley, the driving synchronous pulley is driven to rotate by the engine, and the driven synchronous pulley is connected to the input and output shafts.

[0008] Preferably, the power transmission assembly further comprises a belt pressure wheel rotatably mounted on the mounting frame, the belt pressure wheel being tightly pressed against the synchronous belt.

[0009] Preferably, bearings are provided on both sides of the driving synchronous pulley and the driven synchronous pulley.

[0010] Preferably, it further comprises a rotating shaft driven to rotate by the engine, wherein the rotating shaft is connected to the active synchronous pulley.

[0011] Preferably, a one-way clutch is provided between the rotating shaft and the active synchronous pulley.

[0012] Preferably, two first bearings are provided between the rotating shaft and the active synchronous pulley, and the two first bearings are located on both sides of the one-way clutch.

[0013] Preferably, two fixed frames are further included, and both ends of the rotating shaft are rotatably connected to the two fixed frames respectively, and a second bearing is provided between the rotating shaft and the fixed frames.

[0014] Preferably, it further comprises an elastic coupling, and the output end of the engine and the rotating shaft are connected via the elastic coupling.

[0015] Preferably, it further comprises an engine mounting pod, and the engine is detachably mounted on the engine mounting pod.

[0016] Beneficial effects of the present invention:

[0017] The above structure can increase the load capacity and flight time, and the use of two engines can effectively improve the safety performance of the drone by using the other engine when a single engine fails. In addition, the multi-rotor drone of the present invention has the characteristics of light weight, small size and low vibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 1 is a schematic diagram of the three-dimensional structure of a multi-rotor UAV according to an embodiment of the present invention;

[0019] Figure 2 is a top view of the multi-rotor drone according to an embodiment of the present invention;

[0020] Figure 3 It is a structural schematic diagram of a multi-rotor UAV according to an embodiment of the present invention showing a rotating shaft and a one-way clutch.

[0021] In the figure:

[0022] 1. Commutator; 2. Engine; 3. Power transmission assembly; 4. Input and output shafts; 5. Rotating shaft; 6. One-way clutch; 7. First bearing; 8. Fixed frame; 9. Second bearing; 10. Elastic coupling; 20. Engine mounting pod; 11. Commutator output shaft; 31. Mounting frame; 32. Driving synchronous pulley; 33. Driven synchronous pulley; 34. Synchronous belt; 35. Pressure pulley. DETAILED DESCRIPTION

[0023] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0024] The technical solution of the present invention is further described below with reference to the accompanying drawings and through specific implementation methods.

[0025] like Figure 1 and Figure 2 As shown, the present invention provides a multi-rotor UAV, including a commutator 1, an engine 2, a power transmission component 3 and an input and output shaft 4, wherein:

[0026] An input and output shaft 4 is connected to each of the two opposite sides of the commutator 1, and a commutator output shaft 11 is provided on the other two opposite sides. The input and output shaft 4 is connected to the commutator output shaft 11, and the commutator output shaft 11 can be driven to rotate by the input and output shaft 4, and the rotation directions of the input and output shaft 4 and the commutator output shaft 11 are opposite. The input and output shaft 4 and the commutator output shaft 11 are both connected to rotors (not shown in the figure), and the power is redistributed and reversed by the commutator 1, so that the rotation directions of two adjacent rotors among the four rotors are opposite.

[0027] There are two engines 2, which are located on both sides of the commutator 1 and are centrally symmetrically arranged. In this embodiment, the engine 2 is a turboshaft engine, which has the advantages of light weight, small size, small vibration, large load capacity, and long endurance.

[0028] The two engines 2 are arranged symmetrically, and the exhaust ports of the two engines 2 are arranged on the sides of the engine 2, which can ensure that the exhaust directions of the two engines 2 are in opposite states, thereby offsetting the force generated by the exhaust, so as not to affect the normal operation of the multi-rotor UAV. Moreover, by setting up two turboshaft engines, when one of the turboshaft engines fails, the unmanned helicopter can use the other turboshaft engine to land safely.

[0029] Of course, it is understandable that the exhaust ports of the above-mentioned two engines 2 of this embodiment can also be converted to downward exhaust through a switching channel. At this time, the downwardly discharged gas can generate a part of the lift to provide lifting power for the multi-rotor drone.

[0030] In this embodiment, refer to Figure 1 and Figure 2 The engine 2 is mounted on an engine mounting pod 20 , and the engine 2 can be easily installed and removed through the engine mounting pod 20 .

[0031] The output end of the engine 2 is connected with an elastic coupling 10, and the elastic coupling 10 is connected with a rotating shaft 5, and the rotating shaft 5 is connected to the power transmission assembly 3. By setting the elastic coupling 10, the power of the engine 2 can be transmitted to the rotating shaft 5, and then the rotating shaft 5 transmits the power to the power transmission assembly 3. In this embodiment, the elastic coupling 10 is a detachable elastic coupling 10, which has the characteristics of light weight and good performance, and can ensure reliable power transmission. Moreover, the setting of the detachable elastic coupling 10 can make the disassembly and assembly of the engine 2 faster and simpler.

[0032] In this embodiment, refer to Figure 1 as well as Figure 2 The power transmission assembly 3 includes a mounting frame 31, a driving synchronous pulley 32 and a driven synchronous pulley 33 located on the mounting frame 31, and a synchronous belt 34 connecting the driving synchronous pulley 32 and the driven synchronous pulley 33. The driving synchronous pulley 32 is connected to the rotating shaft 5 and driven to rotate by the rotating shaft 5. Specifically, a bearing (not shown in the figure) is arranged on the mounting frame 31, and the rotating shaft 5 passes through the bearing, the driving synchronous pulley 32 and the bearing arrangement in sequence. Through the arrangement of the bearing, the rotating shaft 5 can better drive the driving synchronous pulley 32 to rotate. The driven synchronous pulley 33 is connected to the input and output shaft 4 and can drive the input and output shaft 4 to rotate. Specifically, another group of bearings (not shown in the figure) is also arranged on the mounting frame 31, and the input and output shaft 4 is arranged with the bearing, the driven synchronous pulley 33 and the bearing in sequence.

[0033] In this embodiment, the power transmission assembly 3 further comprises a belt-pressing wheel 35 rotatably mounted on the mounting frame 31 , and the belt-pressing wheel 35 is pressed tightly against the synchronous belt 34 to tighten the synchronous belt 34 so as to make the power transmission more stable.

[0034] In this embodiment, refer to Figure 3A one-way clutch 6 is provided between the rotating shaft 5 and the active synchronous pulley 32, that is, the one-way clutch 6 is driven to rotate by the rotating shaft 5, and the one-way clutch 6 drives the active synchronous pulley 32 to rotate. By providing the one-way clutch 6, it can be ensured that the active synchronous pulley 32 rotates only in one direction, and the overrunning state of the one-way clutch 6 can also prevent the engine 2 from being damaged.

[0035] In this embodiment, first bearings 7 are further provided on both sides of the one-way clutch 6. Specifically, two first bearings 7 are sleeved on the rotating shaft 5 and are located between the rotating shaft 5 and the active synchronous pulley 32. By providing the first bearings 7, the safety of the one-way clutch 6 can be improved. When the one-way clutch 6 is in the overrunning state, the two first bearings 7 can withstand radial loads. In this embodiment, the first bearings 7 are deep groove ball bearings.

[0036] Please refer to Figure 3 In this embodiment, fixed frames 8 are provided at both ends of the rotating shaft 5. Specifically, one fixed frame 8 is provided at the end of the rotating shaft 5 not connected to the elastic coupling 10, and the other fixed frame 8 is provided at the end of the rotating shaft 5 close to the elastic coupling 10. A second bearing 9 is provided on each fixed frame 8. Both ends of the rotating shaft 5 are inserted into the second bearing 9. By providing the second bearing 9, the smooth rotation of the rotating shaft 5 can be ensured. In this embodiment, the second bearing 9 is a deep groove ball bearing.

[0037] The multi-rotor UAV of the present invention can increase the load capacity and flight time through the above structure, and effectively improve the safety performance of the multi-rotor UAV.

[0038] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the embodiments here. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A multi-rotor drone, characterized in that: The invention comprises a commutator (1), two engines (2) located on both sides of the commutator (1) and arranged symmetrically with respect to the center, a power transmission assembly (3) driven to rotate by the engines (2), and an input and output shaft (4) driven to rotate by the power transmission assembly (3), wherein the input and output shaft (4) is connected to the commutator (1) and drives a commutator output shaft (11) of the commutator (1) to rotate, and the rotation direction of the input and output shaft (4) is opposite to the rotation direction of the commutator output shaft (11), and the input and output shaft (4) and the commutator output shaft (11) are both connected to rotors; The power transmission assembly (3) comprises a mounting frame (31), a driving synchronous pulley (32) and a driven synchronous pulley (33) located on the mounting frame (31), and a synchronous belt (34) connecting the driving synchronous pulley (32) and the driven synchronous pulley (33), wherein the driving synchronous pulley (32) is driven to rotate by the engine (2), and the driven synchronous pulley (33) is connected to the input and output shafts (4); It also includes a rotating shaft (5) driven to rotate by the engine (2), wherein the rotating shaft (5) is connected to the driving synchronous pulley (32); A one-way clutch (6) is provided between the rotating shaft (5) and the active synchronous pulley (32); Two first bearings (7) are provided between the rotating shaft (5) and the active synchronous pulley (32), and the two first bearings (7) are located on both sides of the one-way clutch (6); It also comprises two fixed frames (8), the two ends of the rotating shaft (5) are rotatably connected to the two fixed frames (8) respectively, and a second bearing (9) is provided between the rotating shaft (5) and the fixed frames (8).

2. The multi-rotor drone according to claim 1, characterized in that: The power transmission assembly (3) also includes a belt-pressing wheel (35) rotatably mounted on the mounting frame (31), and the belt-pressing wheel (35) is tightly pressed on the synchronous belt (34).

3. The multi-rotor drone according to claim 2, characterized in that: Bearings are provided on both sides of the driving synchronous pulley (32) and the driven synchronous pulley (33).

4. The multi-rotor drone according to claim 1, characterized in that: It also comprises an elastic coupling (10), and the output end of the engine (2) and the rotating shaft (5) are connected via the elastic coupling (10).

5. The multi-rotor drone according to claim 1, characterized in that: It also comprises an engine mounting pod (20), on which the engine (2) can be detachably mounted.

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