Unmanned aerial vehicle

Abstract

The unmanned aerial vehicle comprises a fuselage, a flapping wing and a first driving assembly, the flapping wing is rotationally connected with the fuselage, the flapping wing comprises a supporting rod, the first driving assembly comprises a first power device and a first transmission assembly, the first transmission assembly is connected with the first power device and the supporting rod, and the first transmission assembly comprises a rotating disc and a rotating shaft; the rotating shaft drives the supporting rod to rotate, so that the flapping wings are driven to rotate. The unmanned aerial vehicle is provided with the first driving assembly, the first driving assembly drives the flapping wing to rotate through the rotating disc and the rotating shaft, rotating connection between the flapping wing and the vehicle body is achieved, the flapping wing can stably flap, the transmission stability and the flapping effect of the flapping wing are improved, and therefore the flight stability of the unmanned aerial vehicle is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle. BACKGROUND

[0002] Flapping wing is an important structure of a new type of aircraft designed and manufactured based on the principle of bionics, which imitates the flight of birds and insects. Compared with fixed wing and rotor, the main feature of flapping wing is that the lifting, hovering and propulsion functions are integrated into a flapping wing system, which can fly long distances with very small energy and has strong maneuverability.

[0003] The application of flapping wing to unmanned aerial vehicles can bring great convenience to various industries. However, the flapping wing unmanned aerial vehicle has not yet reached the practical stage. The main reason is that the traditional flapping wing has low efficiency and poor continuity of up-down reciprocating swing movement. The fatigue strength requirement of the movement device to the material is too high. SUMMARY

[0004] In order to overcome the above-mentioned shortcomings of the related art, the present application aims to provide an unmanned aerial vehicle.

[0005] To achieve the above-mentioned purposes, the present application adopts the following technical solutions:

[0006] According to a first aspect of the present application, an unmanned aerial vehicle is provided, comprising:

[0007] a fuselage;

[0008] a flapping wing, which is rotationally connected to the fuselage, the flapping wing comprising a support rod;

[0009] a first driving assembly comprising a first power device and a first transmission assembly, the first transmission assembly being connected to the first power device and the support rod respectively, the first transmission assembly comprising a rotating disc and a rotating shaft, the rotating disc driving the rotating shaft to move, the rotating shaft driving the support rod to rotate, thereby driving the flapping wing to rotate.

[0010] In a possible implementation, the flapping wing is rotationally connected to the fuselage through a first connecting assembly, the first connecting assembly comprising a first mounting portion and a connecting rod, the first mounting portion being fixedly connected to the fuselage, the connecting rod being fixedly connected to the flapping wing, and the connecting rod being rotationally connected to the first mounting portion.

[0011] In a possible implementation, the support rod comprises a first segment and a second segment connected in series, a connecting shaft being arranged between the first segment and the second segment, the connecting shaft being connected to the connecting rod, and the first segment and the connecting rod jointly constituting a frame of the flapping wing.

[0012] The second section is rotationally connected with the fuselage and is capable of sliding along the fuselage to drive the flapping wing to rotate.

[0013] In a possible implementation, the fuselage is provided with a first sliding groove, and the first transmission assembly comprises:

[0014] a first rotating shaft, one end of which is connected with the output end of the first power device, and the other end of which is connected with the rotating disc to drive the rotating disc to rotate;

[0015] a first connecting member, one end of which is connected with the rotating disc, and the other end of which is connected with a second connecting member;

[0016] the second connecting member, one end of which is connected with the first connecting member, and the other end of which is connected with the second section, and the second connecting member is capable of sliding along the first sliding groove.

[0017] In a possible implementation, the first transmission assembly further comprises a second rotating shaft, a third rotating shaft and a fourth rotating shaft.

[0018] the first connecting member and the rotating disc are connected through the second rotating shaft, the first connecting member and the second connecting member are connected through the third rotating shaft, and the second connecting member and the second section are connected through the fourth rotating shaft.

[0019] In a possible implementation, the second section is provided with a second sliding groove, and the fourth rotating shaft is capable of moving along the second sliding groove.

[0020] In a possible implementation, the unmanned aerial vehicle further comprises:

[0021] a tail wing, which is rotationally connected with the fuselage;

[0022] a second driving assembly, which comprises a second power device and a second transmission assembly, the second transmission assembly is connected with the second power device and the tail wing respectively, and the second power device drives the tail wing to rotate through the second transmission assembly.

[0023] In a possible implementation, the unmanned aerial vehicle comprises a connecting seat, the connecting seat is connected with the fuselage, and the tail wing is rotationally connected with the connecting seat;

[0024] the second transmission assembly comprises a lead screw and a third connecting member, one end of the lead screw is connected with the output end of the second power device, the other end of the lead screw is movably connected with the connecting seat, and the lead screw is connected with the tail wing through the third connecting member to drive the tail wing to rotate relative to the connecting seat.

[0025] In a possible implementation, the second transmission assembly further comprises a sliding block, the sliding block is sleeved on the lead screw, and the sliding block is movably connected with the connecting seat, so as to drive the sliding block to slide through rotation of the lead screw.

[0026] In a possible implementation, the inside of the fuselage is provided with at least one mounting groove, and the first power device and the second power device are both accommodated in the mounting groove.

[0027] The unmanned aerial vehicle is provided with the first driving assembly, the first driving assembly drives the flapping wing to rotate through the rotating disc and the rotating shaft, the rotating connection between the flapping wing and the fuselage is realized, the flapping wing can stably flap, the transmission stability and the flapping effect of the flapping wing are improved, and therefore the flight stability of the unmanned aerial vehicle is improved.

[0028] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent to those skilled in the art from the description, or can be learned by practice of the application, and the purposes and other advantages of the present application can be achieved and obtained by the structures particularly pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0029] The accompanying drawings, which are incorporated into and constitute a part of the specification, illustrate embodiments of the present application and, together with the description, serve to explain the principles of the present application. In these drawings, similar reference numerals are used to identify similar elements. The drawings in the following description are some embodiments of the present application, not all embodiments. For those skilled in the art, other drawings can be obtained from these drawings without creative labor.

[0030] Figure 1 is one of the structural schematic diagrams of the unmanned aerial vehicle according to an exemplary embodiment.

[0031] Figure 2 is Figure 1 is a local enlarged view of the A area in FIG.

[0032] Figure 3 is one of the structural schematic diagrams of the unmanned aerial vehicle according to an exemplary embodiment.

[0033] Figure 4 is one of the structural schematic diagrams of the unmanned aerial vehicle according to an exemplary embodiment.

[0034] Figure 5 is one of the structural schematic diagrams of the unmanned aerial vehicle according to an exemplary embodiment.

[0035] Figure 6 is a sectional schematic diagram of the fuselage according to an exemplary embodiment. DETAILED DESCRIPTION

[0036] In order to make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some but not all of the embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of the present application. It should be noted that the embodiments in the present application and the feature vectors in the embodiments can be combined with each other in any manner without conflict.

[0037] Flapping wing is an important structure of a new type of aircraft designed and manufactured based on the principle of bionics to simulate the flight of birds and insects. Compared with fixed wing and rotor, the main feature of flapping wing is that the lifting, hovering and propulsion functions are integrated into a flapping wing system, which can fly for a long distance with very small energy and has strong maneuverability.

[0038] The application of flapping wing to the wing of unmanned aerial vehicle can bring great convenience to various industries. However, the flapping wing unmanned aerial vehicle has not yet reached the practical stage, mainly because the traditional flapping wing has low efficiency and poor continuity of up-down reciprocating swing movement, and the motion device has too high requirement on the fatigue strength of materials.

[0039] To solve the above problems, the present application provides an unmanned aerial vehicle. The unmanned aerial vehicle of the present application is provided with a first driving assembly. The first driving assembly drives the flapping wing to rotate through a rotating disc and a rotating shaft, realizes the rotating connection between the flapping wing and the fuselage, makes the flapping wing fan stably, improves the transmission stability and fan effect of the flapping wing, and thus improves the flight stability of the unmanned aerial vehicle.

[0040] According to an exemplary embodiment, as shown in Figures 1-6 The present application provides an unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage 10 and a flapping wing 20. The flapping wing 20 comprises a supporting rod 21, and the flapping wing 20 is rotatably connected with the fuselage. The unmanned aerial vehicle further comprises a first driving assembly 30. The first driving assembly 30 comprises a first power device 31 and a first transmission assembly 32. The first transmission assembly 32 is connected with the first power device 31 and the supporting rod 21 respectively. The first transmission assembly 32 comprises a rotating disc 325 and a rotating shaft. The rotating disc 325 is connected with the first power device 31. The rotating disc 325 drives the rotating shaft to move. The rotating shaft is connected with the supporting rod 21. The rotating shaft drives the supporting rod 21 to rotate. Thus, the first power device 31 can drive the flapping wing 20 to rotate through the first transmission assembly 32, so as to realize the stable fanning of the flapping wing 20. The fanning of the flapping wing 20 provides flight power for the unmanned aerial vehicle. The flapping wing 20 improves the flight efficiency of the unmanned aerial vehicle and reduces the flight energy consumption of the unmanned aerial vehicle, so as to realize long endurance and long range.

[0041] In some embodiments, the flapping wing 20 is rotatably connected to the fuselage 10 via a first connecting assembly 40. The first connecting assembly 40 includes a first mounting part 41 and a connecting rod 42. The first mounting part 41 is fixedly connected to the fuselage 10, and the connecting rod 42 is fixedly connected to the flapping wing 20. The connecting rod 42 is rotatably connected to the first mounting part 41, thereby realizing the rotatable connection between the flapping wing 20 and the fuselage 10.

[0042] In some embodiments, the support rod 21 includes a first segment 211 and a second segment 212 connected together. For example... Figures 1-5 As shown, the first segment 211 and the connecting rod 42 together form the frame of the flapping wing 20, and the frame is covered with skin 22 to form an integral flapping wing 20. A connecting shaft 213 is provided between the first segment 211 and the second segment 212, and the connecting shaft 213 is connected to the connecting rod 42. The second segment 212 is rotatably connected to the fuselage 10, and the second segment 212 can slide along the fuselage 10 to drive the flapping wing 20 to rotate.

[0043] In one example, the fuselage 10 is provided with a first slide groove 13. For example... Figure 6 As shown, the first transmission assembly 32 includes a first rotating shaft 321, a first connecting member 326, and a second connecting member 327. One end of the first rotating shaft 321 is connected to the output end of the first power unit 31, and the other end is connected to a turntable 325, so that the first power unit 31 drives the turntable 325 to rotate. One end of the first connecting member 326 is connected to the turntable 325, and the other end is connected to the second connecting member 327. When the turntable 325 is driven to rotate by the first power unit 31, the turntable 325 drives the first connecting member 326 to rotate. One end of the second connecting member 327 is connected to the first connecting member 326, and the other end is connected to the second segment connecting 212. The second connecting member 327 can slide along the first slide groove 13. When the second connecting member 327 slides along the first slide groove 13, the second connecting member 327 drives the second segment 212 of the support rod 21 to slide relative to the fuselage 10, thereby driving the flapping wing 20 to flap.

[0044] In one example, the first transmission assembly 32 further includes a second rotating shaft 322, a third rotating shaft 323, and a fourth rotating shaft 324. For example... Figures 1-6 As shown, the first connecting member 326 and the turntable 325 are connected by the second rotating shaft 322, the first connecting member 326 and the second connecting member 327 are connected by the third rotating shaft 323, and the second connecting member 327 and the second segment 212 are connected by the fourth rotating shaft 324. The various parts of the first transmission assembly 32 are connected by multiple rotating shafts to ensure accurate and controllable motion transmission of the flapping wing 20, thereby achieving stable flapping of the flapping wing 20.

[0045] In one example, the second section 212 is provided with a second sliding groove 2121. As shown in Figures 1-6 the fourth rotating shaft 324 can move along the second sliding groove 2121, and the fourth rotating shaft 324 connects the second section 212 with the second connecting member 327, so that the second connecting member 327 can drive the fourth rotating shaft 324 to move up and down relative to the body 10, thereby driving the flapping wing 20 to flap, and at the same time, the fourth rotating shaft 324 moves along the second sliding groove 2121 on the second section 212, so as to ensure that the position of the first connecting assembly 40 relative to the body 10 remains constant when the flapping wing 20 moves to different angles, thereby ensuring the stability of the flapping wing 20. Figures 4-5

[0046] In some embodiments, the body 10 includes a first part 11 and a second part 12. As shown in Figures 1-5 the first part 11 and the second part 12 are connected, and the flapping wing 20 is rotatably connected to the first part 11.

[0047] In some embodiments, the unmanned aerial vehicle further includes a tail wing 51. As shown in Figures 1-5 the tail wing 51 is rotatably connected to the second part 12 of the body 10. The unmanned aerial vehicle further includes a second driving assembly 60, which includes a second power device 61 and a second transmission assembly 62, and the second transmission assembly 62 is connected to the second power device 61 and the tail wing 51, respectively, so that the second power device 61 can drive the tail wing 51 to rotate relative to the body 10 through the second transmission assembly 62. The tail wing 51 assists the flapping wing 20 to provide flight power for the unmanned aerial vehicle, thereby improving the flight stability and flight efficiency.

[0048] Since the flapping wing 20 and the tail wing 51 provided in the embodiments of the present application can flap to provide power for the flight of the unmanned aerial vehicle, the unmanned aerial vehicle can not need to be provided with a propeller, thereby reducing the self-weight of the unmanned aerial vehicle, which is conducive to improving the load capacity and endurance of the unmanned aerial vehicle. Of course, it can be understood that when greater flight power is required, a propeller can also be provided while the flapping wing 20 and the tail wing 51 are provided, so as to improve the flight efficiency. The embodiments of the present application do not make too many limitations thereon, and a person skilled in the art can select according to actual needs.

[0049] In some embodiments, the unmanned aerial vehicle further includes a connecting seat 52. As shown in Figures 1-5 the connecting seat 52 is connected to the second part 12 of the body 10, and the tail wing 51 is rotatably connected to the connecting seat 52, so that the tail wing 51 is rotatably connected to the body 10.

[0050] In one example, the second transmission assembly 62 includes a lead screw 621 and a third connecting member 622. As shown in Figures 1-5 ​As shown, the screw rod 621 extends from the head of the fuselage 10 to the tail of the fuselage 10 along the extending direction of the second part 12 of the fuselage 10. One end of the screw rod 621 is connected with the output end of the second power device 61, and the other end of the screw rod 621 is movably connected with the connecting base 52. The screw rod 621 is connected with the tail wing 51 through a third connecting piece 622 to drive the tail wing 51 to rotate relative to the connecting base 52.

[0051] In one example, the second transmission assembly 62 further comprises a sliding block 623. As shown, Figures 1-5 the sliding block 623 is sleeved on the end of the screw rod 621 away from the second power device 61, that is, Figure 5 the left end shown in FIG. 4, and the sliding block 623 is movably connected with the connecting base 52. The second power device 61 drives the screw rod 621 to rotate. The screw rod 621 is provided with external threads, and the sliding block 623 is provided with internal threads corresponding to the external threads. Thus, through the rotation of the screw rod 621, the sliding block 623 is driven to slide along Figure 5 the horizontal direction shown in FIG. 4.

[0052] The second transmission assembly 62 further comprises a connecting plate 624 and a fourth connecting piece 625. As shown, Figures 1-5 the sliding block 623 is connected with the connecting plate 624. When the sliding block 623 is driven to slide by the screw rod 621, the connecting plate 624 slides together with the sliding block 623. One end of the fourth connecting piece 625 is rotatably connected with the connecting base 52, and the tail wing 51 is connected with the end of the fourth connecting piece 625 rotatably connected with the connecting base 52. The other end of the fourth connecting piece 625 is provided with a third sliding groove 6251. The connecting plate 624 is movably connected with the fourth connecting piece 625. When the sliding block 623 is driven to slide by the screw rod 621, the connecting plate 624 is driven to slide along the third sliding groove 6251, and the fourth connecting piece 625 is driven by the connecting plate 624 to rotate relative to the connecting base 52, thereby driving the tail wing 51 to rotate relative to the fuselage 10 to provide flight power for the unmanned aerial vehicle and improve the flight efficiency of the unmanned aerial vehicle.

[0053] In some embodiments, the interior of the fuselage 10 is provided with at least one mounting groove 111. As shown, Figures 1-6As shown, the mounting groove 111 is arranged in the first part 11 of the fuselage 10, and the first power device 31 and the second power device 61 are both accommodated in the mounting groove 111. The number of the mounting groove 111 can be one, and the first power device 31 and the second power device 61 are both accommodated in the same mounting groove 111. The number of the mounting groove 111 can also be two, and the mounting groove 111 includes a first mounting groove 1111 and a second mounting groove 1112, wherein the first mounting groove 1111 is used to accommodate the first power device 31, and the second mounting groove 1112 is used to accommodate the second power device 61. In order to facilitate the circuit wire, the first power device 31 used to drive the flapping wing 20 can be arranged close to the flapping wing 20, and the second power device 61 used to drive the tail wing 51 can be arranged close to the tail wing 51, that is, the first mounting groove 1111 is arranged at one end of the first part 11 close to the flapping wing 20, and the second mounting groove 1112 is arranged at one end of the first part 11 close to the tail wing 51.

[0054] It is worth noting that in actual production, the mounting groove 111 can also be arranged at other positions of the fuselage 10. In one example, the first mounting groove 1111 and the second mounting groove 1112 can also be arranged inside the second part 12; in another example, the first mounting groove 1111 is arranged inside the first part 11, and the second mounting groove 1112 is arranged inside the second part 12. The number and arrangement position of the mounting groove 111 can be adjusted by those skilled in the art according to actual needs, and the present application embodiment does not make too many limitations on this.

[0055] Of course, it can be understood that in the present application embodiment, in order to protect the first power device 31 and the second power device 61, the first power device 31 and the second power device 61 are arranged inside the fuselage 10, and those skilled in the art can also adjust the arrangement position of the first power device 31 and the second power device 61 according to actual needs, for example, when the power of the first power device 31 and the second power device 61 is large, considering the heat dissipation demand, the first power device 31 and the second power device 61 can be arranged on the surface of the fuselage 10, or the first power device 31 and the second power device 61 are arranged inside the fuselage 10, while increasing the heat dissipation channel, heat dissipation hole or heat dissipation material and other structures to assist heat dissipation, to avoid overheating damage to the power device, affect the flight of the unmanned aerial vehicle, and even reduce the service life of the unmanned aerial vehicle.

[0056] It is to be noted that, in the present text, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0057] Finally, it should be noted that the above-mentioned embodiments are merely intended to illustrate the technical solutions of the present application, not to limit it, and the present application is described in detail only with reference to the preferred embodiments, and those skilled in the art should understand that the technical solutions of the present application can be modified or replaced equivalently without departing from the spirit and scope of the technical solutions of the present application, and all should be covered in the scope of the claims of the present application.

Claims

1. A drone, characterized in that, The unmanned aerial vehicle comprises: a fuselage; a wing, which is rotatably connected to the fuselage, and comprises a support rod; a first driving assembly, which comprises a first power device and a first transmission assembly, the first transmission assembly is respectively connected to the first power device and the support rod, the first transmission assembly comprises a rotating disc and a rotating shaft, the rotating disc drives the rotating shaft to move, and the rotating shaft drives the support rod to rotate, thereby driving the wing to rotate.

2. The drone of claim 1, wherein, The wing is rotatably connected to the fuselage through a first connecting assembly, the first connecting assembly comprises a first mounting portion and a connecting rod, the first mounting portion is fixedly connected to the fuselage, the connecting rod is fixedly connected to the wing, and the connecting rod is rotatably connected to the first mounting portion.

3. The drone of claim 2, wherein, The support rod comprises a first segment and a second segment connected to each other, a connecting shaft is arranged between the first segment and the second segment, the connecting shaft is connected to the connecting rod, and the first segment and the connecting rod jointly constitute a frame of the wing. The second segment is rotatably connected to the fuselage, and the second segment can slide along the fuselage to drive the wing to rotate.

4. The drone of claim 3, wherein, The fuselage is provided with a first sliding groove, and the first transmission assembly comprises: a first rotating shaft, one end of which is connected to an output end of the first power device, and the other end of which is connected to the rotating disc to drive the rotating disc to rotate; a first connecting piece, one end of which is connected to the rotating disc, and the other end of which is connected to a second connecting piece; the second connecting piece, one end of which is connected to the first connecting piece, and the other end of which is connected to the second segment, and the second connecting piece can slide along the first sliding groove.

5. The drone of claim 4, wherein, The first transmission assembly further comprises a second rotating shaft, a third rotating shaft and a fourth rotating shaft. The first connecting piece and the rotating disc are connected through the second rotating shaft, the first connecting piece and the second connecting piece are connected through the third rotating shaft, and the second connecting piece and the second segment are connected through the fourth rotating shaft.

6. The drone of claim 5, wherein, The second segment is provided with a second sliding groove, and the fourth rotating shaft can move along the second sliding groove.

7. The drone of claim 1, wherein, The unmanned aerial vehicle further comprises: a tail wing, which is rotatably connected to the fuselage; a second driving assembly, which comprises a second power device and a second transmission assembly, the second transmission assembly is respectively connected to the second power device and the tail wing, and the second power device drives the tail wing to rotate through the second transmission assembly.

8. The drone of claim 7, wherein, The unmanned aerial vehicle comprises a connecting seat, the connecting seat is connected to the fuselage, and the tail wing is rotatably connected to the connecting seat; The second transmission assembly comprises a lead screw and a third connecting piece, one end of the lead screw is connected to an output end of the second power device, the other end of the lead screw is movably connected to the connecting seat, and the lead screw is connected to the tail wing through the third connecting piece to drive the tail wing to rotate relative to the connecting seat.

9. The drone of claim 8, wherein, The second transmission assembly further comprises a sliding block, the sliding block is sleeved on the lead screw, and the sliding block is movably connected to the connecting seat to drive the sliding block to slide through rotation of the lead screw.

10. The drone of claim 7, wherein, The fuselage is internally provided with at least one mounting groove, and the first power device and the second power device are accommodated in the mounting groove.

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