Flight stabilizing structure on unmanned aerial vehicle

Abstract

The utility model relates to a flight stabilizing structure on an unmanned aerial vehicle, which comprises a protective cover mounted on rotor wings of the unmanned aerial vehicle, the protective cover comprises annular bodies with the number corresponding to that of the rotor wings, the annular bodies are tangentially connected, and the rotor wings are positioned in the centers of the annular bodies; the rotor wings are connected with the unmanned aerial vehicle host through wing rods; clamping grooves corresponding to the annular bodies are formed in the top surfaces of the wing rods, extending bodies are fixedly connected to the annular bodies, and the extending bodies are located on extension lines of the wing rods; a containing cavity is formed in the wing rod, an outlet is formed in the end, corresponding to the wing rod, of the containing cavity, and a supporting rod is movably arranged in the containing cavity and can move out of the outlet to be connected to the extending body. According to the six-rotor unmanned aerial vehicle, the detachable protective cover is installed on the six-rotor unmanned aerial vehicle, each rotor can be surrounded when the six-rotor unmanned aerial vehicle needs to be used, and therefore the crosswind resisting effect of the unmanned aerial vehicle is improved. The protective cover is simple in mounting structure and easy to operate. The protective cover can be of a hollow structure made of a carbon fiber material, the burden on the unmanned aerial vehicle is reduced, and the energy consumption increment is reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane field especially a flight stabilizing structure on unmanned plane. BACKGROUND

[0002] The type of unmanned plane can be divided into fixed wing unmanned plane, four rotor unmanned plane and six rotor unmanned plane. Six rotor unmanned plane is often used in load purpose because of its large power and large load. The rotor of current six rotor unmanned plane has no side protection structure, and the anti-crosswind performance is realized by power redundancy, but the effect is limited. However, the rotor protection ring obviously increases the self weight, which causes the energy consumption to increase. Therefore, the application provides a flight stabilizing structure, which can control the energy consumption increase and prevent crosswind to achieve stable flight effect. SUMMARY

[0003] The application aims to provide a flight stabilizing structure on unmanned plane, and solve the problems in the prior art.

[0004] The application provides a flight stabilizing structure on unmanned plane, which comprises a protective cover installed on a rotor of the unmanned plane, the protective cover comprises annular bodies corresponding in number to the rotors, the annular bodies are connected in tangency, and the rotors are located in the center of the annular bodies; the rotor is connected to a main machine of the unmanned plane through a wing rod; a clamping groove is formed in the top surface of the wing rod corresponding to the annular body; an extension body is fixedly connected to the annular body; the wing rod is internally provided with a receiving cavity, the receiving cavity is provided with an outlet corresponding to the end of the wing rod, and a supporting rod is movably arranged in the receiving cavity and can be moved out of the outlet and connected to the extension body.

[0005] Further, the two ends of the supporting rod are respectively provided with threaded sections with increased diameters, the inner walls of the two ends of the receiving cavity are respectively provided with first threaded portions and second threaded portions, and the supporting rod is threadedly connected to the first threaded portions and the second threaded portions at the two ends.

[0006] Further, a first screw hole is formed in the inner wall of the extension body corresponding to the supporting rod, the supporting rod is threadedly connected to the first screw hole after being moved out of the receiving cavity, and the other end of the supporting rod is threadedly connected to the first threaded portion.

[0007] Further, a touch window is formed in the bottom of the receiving cavity, and the touch window is in communication with the receiving cavity.

[0008] Further, a second screw hole is formed in the bottom of the side of the annular body opposite to the extension body, a third screw hole is formed in the clamping groove of the wing rod and penetrates the upper and lower portions, the second screw hole corresponds to the third screw hole, and the annular body and the wing rod are fixed by screwing a bolt between the second screw hole and the third screw hole.

[0009] The utility model discloses a beneficial effect is: the utility model discloses detachable protective cover is installed on six rotor unmanned aerial vehicle, can surround every rotor when needing using to improve the anti crosswind effect of unmanned aerial vehicle. The mounting structure of protective cover is simple, and easy operation. The hollow structure of carbon fiber material can be used to the protective cover, and the burden of unmanned aerial vehicle is reduced, and the energy consumption increase is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0010] Figure 1 It is the overhead angle structure schematic diagram of the utility model.

[0011] Figure 2 It is the structure schematic diagram of protective cover.

[0012] Figure 3 It is the cross section mounting structure schematic diagram of annular body.

[0013] Figure 4 It is the front upper view angle structure schematic diagram of wing rod.

[0014] Figure 5 It is the front lower view angle structure schematic diagram of wing rod.

[0015] In the drawing,

[0016] 1, protective cover, 2, rotor, 3, main machine, 4, wing rod, 5, annular body, 6, clamping groove, 7, extension body, 8, containing cavity, 9, support rod, 10, first threaded portion, 11, second threaded portion, 12, first screw hole, 13, touch window, 14, second screw hole, 15, third screw hole, 16, bolt. DETAILED DESCRIPTION

[0017] The technical scheme in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor belong to the scope of protection of the utility model.

[0018] As Figures 1-5 Shown in a kind of unmanned aerial vehicle flight stabilizing structure on installation in unmanned aerial vehicle rotor 2 protective cover 1, protective cover 1 surrounds around rotor 2, improves side wind stability. The protective cover 1 includes the annular body 5 corresponding to the number of rotor 2 number, the present application preferably adopts six rotor unmanned aerial vehicle 2, so the number of annular body 5 is also six. Six annular bodies 5 are tangentially connected, and the rotor 2 is located in the central annular body 5. Preferably, the overall material of protective cover 1 adopts carbon fiber, hollow inside, diameter is 15% larger than rotor 2 paddle, can reduce the weight of unmanned aerial vehicle, increase lift.

[0019] The rotor 2 is connected with the unmanned aerial vehicle main machine 3 through a wing rod 4; a clamping groove 6 is formed on the top surface of the wing rod 4 corresponding to an annular body 5, and an extension body 7 is fixedly connected to the annular body 5, as shown in Figure 2 and Figure 3 The extension body 7 is located on the extension line of the wing rod 4. An accommodating cavity 8 is formed in the wing rod 4, and an outlet is formed in the accommodating cavity 8 corresponding to the end of the wing rod 4. A supporting rod 9 is movably arranged in the accommodating cavity 8, and the supporting rod 9 can be moved out of the outlet and connected to the extension body 7. Threaded segments with increasing diameters are arranged at the two ends of the supporting rod 9, and first and second threaded portions 10 and 11 are arranged on the inner walls of the two ends of the accommodating cavity 8. The supporting rod 9 is threadedly connected to the first and second threaded portions 10 and 11 at the two ends, so that the supporting rod 9 is fixed in the accommodating cavity 8 and cannot be shaken out due to the flight of the unmanned aerial vehicle.

[0020] A first screw hole 12 is formed in the inner wall of the extension body 7 corresponding to the supporting rod 9. After the supporting rod 9 is moved out of the accommodating cavity 8, the supporting rod 9 is threadedly connected to the first screw hole 12, and the other end of the supporting rod 9 is threadedly connected to the first threaded portion 10. The outer end of the annular body 5 is fixed to the wing rod 4 through the supporting rod 9. A touch window 13 is formed in the bottom of the wing rod 4 and communicates with the accommodating cavity 8, as shown in Figure 5 The supporting rod 9 can be touched from the outside through the touch window 13. When the supporting rod 9 is in the accommodating cavity 8, the finger is upwardly attached to the touch window 13, the finger pad is in contact with the supporting rod 9, the supporting rod 9 is rotated and extended by the friction between the finger pad and the supporting rod 9, and when the two threaded segments of the supporting rod 9 are separated from the threaded portions, the supporting rod 9 can be directly pulled out of the opening. Then, the supporting rod 9 is aligned with the first screw hole 12 and the supporting rod 9 is rotated and screwed into the threaded portion.

[0021] As shown in Figure 3 and Figure 4 A second screw hole 14 is formed in the bottom of the side of the annular body 5 opposite to the extension body 7, and a third screw hole 15 penetratingly formed in the clamping groove 6 of the wing rod 4. The second screw hole 14 corresponds to the third screw hole 15, and the annular body 5 is fixed to the wing rod 4 by screwing a bolt 16 between the second screw hole 14 and the third screw hole 15.

[0022] Therefore, the protective cover 1 can be installed on the unmanned aerial vehicle through the supporting rod 9 and the bolt 16, and the functions of preventing crosswind and stabilizing flight are achieved. The protective cover 1 is a detachable structure, and can be used according to the weather conditions.

[0023] It is obvious for those skilled in the art that the present application is not limited to the details of the above exemplary embodiments, and the present application can be implemented in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, the embodiments should be regarded as exemplary and non-limiting from any point of view.

Claims

1. An aerial flight stabilizing structure on a drone, comprising a protective cover mounted on a rotor of the drone, characterized in that, The protective cover comprises a plurality of annular bodies corresponding to the number of rotors, the annular bodies are connected tangentially, and the rotors are located in the center of the annular bodies; the rotors are connected with the main machine of the unmanned aerial vehicle through wing rods; a clamping groove is formed on the top surface of the wing rod corresponding to the annular body, an extension body is fixedly connected to the annular body, and the extension body is located on the extension line of the wing rod; an accommodating cavity is formed in the wing rod, an outlet is formed in the end of the wing rod corresponding to the accommodating cavity, a supporting rod is movably arranged in the accommodating cavity, and the supporting rod can be moved out of the outlet and connected to the extension body.

2. The aerial flight stabilizing structure on the drone according to claim 1, wherein The two ends of the supporting rod are respectively provided with threaded segments with increased diameters, the inner walls of the two ends of the accommodating cavity are respectively provided with first threaded portions and second threaded portions, and the threaded segments at the two ends of the supporting rod are respectively threadedly connected to the first threaded portions and the second threaded portions in the accommodating cavity.

3. The aerial flight stabilizing structure on the drone according to claim 2, wherein, A first screw hole is formed in the inner wall of the extension body corresponding to the supporting rod, the supporting rod is threadedly connected in the first screw hole after being moved out of the accommodating cavity, and the threaded segment at the other end of the supporting rod is threadedly connected to the first threaded portion.

4. The aerial flight stabilizing structure on the drone according to claim 3, wherein, A touch window is formed in the bottom of the accommodating cavity, and the touch window is in communication with the accommodating cavity.

5. The aerial stabilization structure on a drone according to claim 1, wherein, A second screw hole is formed in the bottom of the side of the annular body opposite to the extension body, a third screw hole penetrating up and down is formed in the clamping groove of the wing rod, the second screw hole corresponds to the third screw hole, and the annular body and the wing rod are fixed by screwing a bolt between the second screw hole and the third screw hole.

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