Multi-rotor unmanned aerial vehicle

Abstract

The utility model discloses a multi-rotor unmanned aerial vehicle, which comprises a cabin, an unmanned aerial vehicle body and an unmanned aerial vehicle body, the rack comprises an undercarriage located at the lower end of the cabin and a fuselage support located in the containing cavity. One end of each machine arm penetrates through the wall of the cabin and is detachably assembled on the machine body support, and one end, away from the cabin, of each machine arm is further provided with a rotor wing assembly. According to the technical scheme, the arms can be detached without embedding flanges or folding structures on the outer wall of the cabin, the production and installation cost can be effectively reduced, the torque borne by the arms in the use state is smaller, and the installation firmness of the arms can be effectively enhanced.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, especially a kind of multi-rotor unmanned plane. BACKGROUND

[0002] Multi-rotor unmanned plane mainly includes four-rotor unmanned plane, six-rotor unmanned plane and other number of unmanned plane of rotor, to keep the firmness of the arm connected with rotor, currently commonly used scheme is to embed multiple flanges on the outer wall of cabin, and arm is assembled by flange, to ensure the stability of arm under the action of torque and make it can be disassembled, other scheme also uses detachable structure to assemble arm on the outer wall of cabin and uses other accessories to ensure the torsional strength of arm, the above two ways of installing arm inevitably make the cost of production and installation higher, and disassembly is not convenient. SUMMARY

[0003] In view of the above problems existing in prior art, the present application provides a kind of multi-rotor unmanned plane, to effectively reduce production and installation cost, to overcome at least one of the above technical defects.

[0004] The specific technical solutions are as follows:

[0005] A kind of multi-rotor unmanned plane, comprising:

[0006] Cabin, internally formed with containing cavity;

[0007] Frame, including landing gear at the lower end of cabin, and fuselage support in containing cavity;

[0008] Multiple arms, one end of each arm is respectively passed through the wall of cabin and detachably assembled on fuselage support, and one rotor assembly is further respectively arranged at the end of each arm away from cabin.

[0009] Preferably, the wall of cabin is provided with a number of through holes corresponding to the number of arms, for passing through the arms.

[0010] Preferably, a sleeve structure extending in outward direction is further formed in each through hole, and the sleeve structure is sleeved on the outer periphery of arm to support the arm.

[0011] Preferably, the end of each arm inserted into cabin is detachably fixed on fuselage support by a plurality of hoops.

[0012] Preferably, the number of hoops arranged in the axial direction of each arm is two.

[0013] Preferably, the number of arms and rotor assemblies is six, and the six arms are uniformly arranged on the outer periphery of cabin.

[0014] Preferably, the number of arms and rotor assemblies is four, and the four arms are evenly arranged in the circumferential direction of the cabin outer periphery.

[0015] Preferably, the fuselage support and the landing gear are integrally welded, and the bottom of the cabin has a passage for the longitudinal rod of the landing gear.

[0016] Preferably, the cabin has a hollow eggshell structure as a whole, and the top of the cabin has an opening for exposing the accommodation cavity.

[0017] The beneficial effects of the above technical solutions are:

[0018] (1) The multi-rotor unmanned aerial vehicle comprises a cabin, a frame, an arm, and a rotor assembly, the frame comprises a landing gear and a fuselage support, and one end of the arm penetrates the wall of the cabin and is detachably assembled on the fuselage support, so that the arm can be detached without embedding a flange or folding structure on the outer wall of the cabin, the production and installation costs can be effectively reduced, the torque received by the arm in use is smaller, and the installation firmness of the arm can be effectively enhanced.

[0019] (2) The arm has at least two hoop and sleeve structures and three circumferential limiting points in the axial direction, which can ensure that the arm does not jump axially and radially in the working state, and the stability is higher, and the installation cost of the hoop fixing mode is lower than that of the existing flange structure. BRIEF DESCRIPTION OF DRAWINGS

[0020] Fig. 1 It is a perspective view of the multi-rotor unmanned aerial vehicle of the present application;

[0021] Fig. 2 It is a perspective view of the multi-rotor unmanned aerial vehicle of the present application after the cabin is unloaded;

[0022] Fig. 3 It is a perspective view of the cabin of the multi-rotor unmanned aerial vehicle of the present application. DETAILED DESCRIPTION

[0023] In order to make the technical means, creative features, purposes and effects achieved by the present application easy to understand, the following embodiments will be specifically described in combination with the drawings.

[0024] Referring to Figs. 1 to 3 The multi-rotor unmanned aerial vehicle provided by the present embodiment comprises:

[0025] The cabin 1 is internally constituted by an accommodation cavity;

[0026] The frame 2 comprises a landing gear 5 located at the lower end of the cabin 1 and a fuselage support 6 located in the accommodation cavity;

[0027] A plurality of arms 3, one end of each arm 3 respectively passes through the wall of the cabin 1 and is detachably assembled on the fuselage support 6, and the end of each arm 3 away from the cabin 1 is also respectively provided with a rotor assembly 4.

[0028] Based on the above technical scheme, the multi-rotor unmanned aerial vehicle includes a cabin 1, a frame 2, an arm 3, and a rotor assembly 4. The frame 2 includes a landing gear 5 and a fuselage support 6. One end of the arm 3 passes through the wall of the cabin 1 and is detachably assembled on the fuselage support 6. This makes it possible to realize the detachability of the arm 3 without embedding a flange or folding structure on the outer wall of the cabin 1, effectively reducing the production and installation costs. The torque received by the arm 3 in the use state is smaller, which can effectively enhance the installation firmness of the arm 3.

[0029] In a preferred embodiment, a plurality of through holes are formed in the wall of the cabin 1 for passing through the arms 3. Further, a sleeve structure 8 extending in the outward direction is formed in each through hole, and the sleeve structure 8 is sleeved on the outer periphery of the arm 3 to support the arm 3, making the installation structure more stable.

[0030] As a further preferred embodiment, the end of each arm 3 extending into the cabin 1 is detachably secured to the fuselage support 6 by a plurality of hoops 7. Further, in the axial direction of each arm 3, the number of hoops 7 is two, but it is obvious that a plurality of hoops 7 can also be provided. This makes it possible to have at least two hoops 7 and three circumferential limiting points of the sleeve structure 8 in the axial direction of the arm 3, which can ensure that it will not jump axially and radially in the working state, and the stability is higher. The installation cost of the hoop 7 is lower than that of the existing flange structure, and the hoop 7 mechanism can also be realized by other means such as hinges, locks, etc., and is not limited thereto.

[0031] In a preferred embodiment, the number of arms 3 and rotor assemblies 4 is six, and the six arms 3 are uniformly arranged in the circumferential direction of the cabin 1. Alternatively, the number of arms 3 and rotor assemblies 4 is four, and the four arms 3 are uniformly arranged in the circumferential direction of the cabin 1. That is, this scheme is preferably applicable to conventional four-rotor unmanned aerial vehicles and six-rotor unmanned aerial vehicles, and is also applicable to two-rotor unmanned aerial vehicles or unmanned aerial vehicles with more rotors.

[0032] As a further preferred embodiment, the fuselage support 6 and the landing gear 5 are integrally welded, and the bottom of the cabin 1 has a passage for passing through the longitudinal rod of the landing gear 5. Further, the cabin 1 has a hollow eggshell structure as a whole, and the top of the cabin 1 has an opening for exposing the accommodation cavity, for placing the transported goods into the accommodation cavity and disassembling and maintaining the connection structure between the hoop 7 and the arm 3.

[0033] In addition, the cabin 1 is welded by two parts, the fuselage support 6 is welded in the cabin 1, and the fuselage support 6 is welded on the lower part of the cabin 1, so as to facilitate the welding of the upper and lower cabins, the rotor assembly 4 is arranged on the arm 3, has a communication receiver, a motor and a rotor, can act through the received signal, or a general controller and a power assembly can be further arranged in the accommodating cavity and electrically connected, the communication module or the motor control end of each rotor assembly 4 can be connected to the general controller along the pipe channel of the arm 3, and the action of each rotor assembly 4 is uniformly controlled by the general controller, and the unmanned aerial vehicle basic function can be realized, which is a conventional scheme commonly used in the related products, and is not the main innovation point of the scheme, so the description is omitted here.

[0034] The above only describes the preferred embodiments of the present application, which are only illustrative but not restrictive. It is understood by those skilled in the art that many changes, modifications and even equivalents can be made to the present application within the spirit and scope of the present application, but all will fall within the protection scope of the present application.

Claims

1. A multi-copter drone, characterized in that, Comprise: a cabin (1) internally formed with a containing cavity; a frame (2) comprising a landing gear (5) at a lower end of the cabin (1) and a fuselage support (6) in the containing cavity; a plurality of arms (3), each of the arms (3) having one end penetrating through a wall of the cabin (1) and detachably assembled to the fuselage support (6), and each of the arms (3) having one end away from the cabin (1) further configured with a rotor assembly (4); the wall of the cabin (1) is provided with a number of through holes corresponding to the number of the arms (3) for penetrating the arms (3), and each of the through holes is further formed with a sleeve structure (8) extending in an outward direction and sleeved on an outer periphery of the arm (3) for supporting the arm (3); each of the arms (3) penetrating into the cabin (1) is detachably fixed to the fuselage support (6) by a plurality of hoops (7).

2. The multicopter drone of claim 1, wherein, In the axial direction of each of the arms (3), the number of the hoops (7) is two.

3. The multicopter drone of claim 2, wherein, The number of the arms (3) and the rotor assemblies (4) is six, and the six arms (3) are uniformly arranged in a circumferential direction of the cabin (1).

4. The multicopter drone of claim 2, wherein, The number of the arms (3) and the rotor assemblies (4) is four, and the four arms (3) are uniformly arranged in a circumferential direction of the cabin (1).

5. The multicopter drone of claim 1, wherein, The fuselage support (6) and the landing gear (5) are integrally formed by welding, and the bottom of the cabin (1) has a passage for penetrating a longitudinal rod of the landing gear (5).

6. The multicopter drone of claim 1, wherein, The cabin (1) has a hollow eggshell structure as a whole, and the top of the cabin (1) has an opening for exposing the containing cavity.

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