Quick dismounting and mounting mechanism for unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick disassembly and assembly mechanism for an unmanned aerial vehicle. The device comprises a front machine body and a rear machine body, and the front machine body and the rear machine body are connected through two sets of quick disassembly and assembly assemblies. The quick dismounting and mounting assembly comprises a first connecting piece arranged at the tail of the front fuselage, a fixing column hole is formed in the first connecting piece, and a compression spring is arranged in the fixing column hole. The quick dismounting and mounting assembly further comprises a second connecting piece arranged at the top of the rear machine body, a fixing hole corresponding to the fixing column hole is formed in the second connecting piece, and a copper nut is arranged in the fixing hole. The problems that an existing unmanned aerial vehicle body or a main wing is designed into a whole or is bonded into a whole by a consumer after being disassembled, and the cost is high when the unmanned aerial vehicle is transported and stored due to the design are solved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a quick disassembly and assembly mechanism for unmanned aerial vehicles. Background Art

[0002] UAV, or unmanned aerial vehicle, is an unmanned aircraft controlled by radio remote control equipment and self-contained program control devices. They usually perform flight missions through remote control or preset plans. UAVs can be widely used in various fields, such as military, civil, scientific research, media, etc. They have the advantages of convenience, flexibility, efficiency and accuracy, and are increasingly widely used in logistics and transportation, search and rescue, agricultural plant protection, aerial photography and other fields.

[0003] In conventional designs of existing aircraft, for better appearance, the fuselage or main wing is usually designed as a whole, or disassembled and glued into a whole by consumers. Such a design leads to high costs when transporting and storing the aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide a rapid disassembly and assembly mechanism for a drone, so as to solve the problem in the background technology that the fuselage or main wing of the existing aircraft is designed as a whole, or is disassembled and glued into a whole by the consumer. Such a design leads to high costs when transporting and storing the aircraft.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solution, which includes a front fuselage and a rear fuselage, wherein the front fuselage and the rear fuselage are connected by two groups of quick-disassembly and assembly components.

[0006] As a preferred embodiment of the utility model, the quick disassembly assembly includes a connecting member 1 arranged at the tail of the front fuselage, the connecting member 1 is provided with a fixing column hole, and a compression spring is arranged in the fixing column hole.

[0007] As a preferred embodiment of the utility model, the quick disassembly assembly also includes a second connector arranged on the top of the rear fuselage, the second connector is provided with a fixing hole for the fixing column hole, and a copper nut is arranged in the fixing hole.

[0008] As a preferred embodiment of the present invention, the copper nut is connected to the fixing column hole by means of a hand-tightened nut in cooperation with a retaining spring.

[0009] As a preferred embodiment of the utility model, a pair of corresponding limiting holes 1 are further provided on the connecting member 1 and the connecting member 2, and a first connecting carbon rod is inserted into the limiting hole 1.

[0010] As a preferred embodiment of the utility model, a pair of corresponding limiting holes 2 are opened at the connection between the front fuselage and the rear fuselage, and a second connecting carbon rod is inserted between the two limiting holes 2.

[0011] As a preferred embodiment of the present invention, the first connecting carbon rod and the second connecting carbon rod are made of carbon fiber material.

[0012] Compared with the prior art, the above technical solution of the utility model has the following beneficial technical effects:

[0013] 1. The utility model sets two first connecting carbon rods and one first connecting carbon rod. These three carbon rods are responsible for positioning and aligning the front fuselage and the rear fuselage and limiting the relative freedom of the front and rear fuselages, so that the rear fuselage has only two degrees of freedom relative to the front fuselage: forward and backward movement.

[0014] 2. The utility model can make the installation and disassembly of the front fuselage and the rear fuselage more convenient and quick by providing a quick disassembly assembly component, so that the transportation and storage costs are greatly reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 It is a schematic diagram of the structure of the quick disassembly and assembly component of the utility model.

[0017] Figure numerals: front fuselage 1, rear fuselage 2, limiting hole 1 3, first connecting carbon rod 4, quick disassembly assembly 5, connecting part 1 50, connecting part 2 51, fixing column hole 52, copper nut 53, compression spring 54, hand screw 55, retaining spring 56, fixing hole 57, limiting hole 2 6, second connecting carbon rod 7. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solution and advantages of the utility model clearer, the utility model is further described in detail below in combination with specific implementation methods and with reference to the accompanying drawings. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the utility model. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the utility model.

[0019] like Figure 1 As shown, the utility model proposes a rapid disassembly and assembly mechanism for a UAV, which includes a front fuselage 1 and a rear fuselage 2, wherein the front fuselage 1 and the rear fuselage 2 are connected by two groups of rapid disassembly and assembly components 5; a pair of corresponding limiting holes 6 are opened at the connection between the front fuselage 1 and the rear fuselage 2, and a second connecting carbon rod 7 is inserted between the two limiting holes 6.

[0020] like Figure 2As shown, the quick disassembly assembly 5 includes a connecting piece 50 arranged at the tail of the front fuselage 1, and the connecting piece 50 is provided with a fixing column hole 52, and a compression spring 54 is arranged in the fixing column hole 52; the quick disassembly assembly 5 also includes a connecting piece 51 arranged at the top of the rear fuselage 2, and the connecting piece 51 is provided with a fixing hole 57 for the fixing column hole 52, and a copper nut 53 is arranged in the fixing hole 57; the copper nut 53 is connected to the fixing column hole 52 by a hand-tightening nut and a retaining spring 56; a pair of corresponding limiting holes 3 are also provided on the connecting piece 50 and the connecting piece 2, 51, and a first connecting carbon rod 4 is inserted in the limiting holes 3 of the connecting piece 50 and the connecting piece 2; a pair of corresponding limiting holes 2 6 are provided at the connection between the front fuselage 1 and the rear fuselage 2, and a second connecting carbon rod 7 is inserted between the two limiting holes 2 6; the first connecting carbon rod 4 and the second connecting carbon rod 7 are made of carbon fiber.

[0021] As an optimization scheme of the utility model, two first connecting carbon rods 4 and one first connecting carbon rod 4 are set, and these three carbon rods are responsible for positioning and aligning the front and rear fuselages 2 and limiting the relative freedom of the front and rear fuselages 2, so that the rear fuselage 2 has only two degrees of freedom of forward and backward movement relative to the front fuselage 1, and is fixed at three points by the front and rear fuselages 2 to prevent the front and rear fuselages 2 from being unreliably fixed; by setting a quick disassembly assembly 5, the installation and disassembly of the front fuselage 1 and the rear fuselage 2 can be made more convenient and quick, so that the transportation and storage costs are greatly reduced.

[0022] When in use, first connect the first connecting carbon rod 4 and the second connecting carbon rod 7 to the several limit holes 1 3 and the limit holes 2 6 respectively, then put the compression spring 54 on the hand screw 55, insert the hand screw 55 into the fixing column hole 52, and then screw the hand screw 55 into the copper nut 53, and finally clamp the retaining spring 56 to the top of the hand screw 55 to complete the installation; when disassembling, you only need to rotate the hand nut in the opposite direction, completely withdraw the hand nut thread from the copper nut 53 thread, and the compression spring 54 will pop out the hand nut to complete the unlocking.

[0023] It should be understood that the above specific embodiments of the present invention are only used to illustrate or explain the principles of the present invention, and do not constitute a limitation on the present invention. Therefore, any modifications, equivalent substitutions, improvements, etc. made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. In addition, the claims attached to the present invention are intended to cover all changes and modifications that fall within the scope and boundaries of the attached claims, or the equivalent forms of such scope and boundaries.

Claims

1. A rapid disassembly and assembly mechanism for an unmanned aerial vehicle, comprising a front fuselage (1) and a rear fuselage (2), characterized in that: The front fuselage (1) and the rear fuselage (2) are connected via two sets of quick disassembly and assembly components (5), wherein the quick disassembly and assembly components (5) comprise a first connecting member (50) arranged at the rear of the front fuselage (1), wherein the first connecting member (50) is provided with a fixing column hole (52), wherein a compression spring (54) is arranged in the fixing column hole (52), and the quick disassembly and assembly components (5) further comprise a second connecting member (51) arranged at the top of the rear fuselage (2), wherein the second connecting member (51) is provided with a fixing hole (57) corresponding to the fixing column hole (52), wherein a copper nut (53) is arranged in the fixing hole (57).

2. The UAV quick disassembly and assembly mechanism according to claim 1, characterized in that: The copper nut (53) is connected to the fixing column hole (52) by means of a hand-tightened nut and a matching retaining ring (56).

3. The UAV quick disassembly and assembly mechanism according to claim 2, characterized in that: A pair of corresponding limiting holes (3) are also provided on the connecting member (50) and the connecting member (51), and a first connecting carbon rod (4) is inserted into the limiting hole (3).

4. The UAV quick disassembly and assembly mechanism according to claim 3, characterized in that: A pair of corresponding second limiting holes (6) are provided at the connection between the front fuselage (1) and the rear fuselage (2), and a second connecting carbon rod (7) is inserted between the two second limiting holes (6).

5. The UAV quick disassembly and assembly mechanism according to claim 4, characterized in that: The first connecting carbon rod (4) and the second connecting carbon rod (7) are made of carbon fiber material.

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