CN219584497U

CN219584497U - Unmanned aerial vehicle's landing gear and unmanned aerial vehicle thereof

Info

Publication number: CN219584497U
Application number: CN202320992062.XU
Authority: CN
Inventors: 孙振峰
Original assignee: Liaoning Zhongfei Technology Co ltd
Current assignee: Liaoning Zhongfei Technology Co ltd
Priority date: 2023-04-27
Filing date: 2023-04-27
Publication date: 2023-08-25
Anticipated expiration: 2033-04-27

Abstract

The utility model relates to the technical field of unmanned aerial vehicle landing devices, in particular to an unmanned aerial vehicle landing device and an unmanned aerial vehicle thereof, comprising a body; four recesses have been seted up to the inside symmetry of fuselage, four electric telescopic handle is all installed on the inside top of recess, the laminating is installed to electric telescopic handle's bottom the pipe of recess inner wall, the bottom elastic connection of pipe has the plectane, through fuselage, recess, electric telescopic handle, pipe, attenuator, spring, plectane and the ring that are equipped with, by electric telescopic handle in the recess with pipe and plectane propelling movement out the lower terminal surface of fuselage, then when contacting ground by the plectane, through the ring extrusion spring shock attenuation, the power when slowing down the spring resilience by the attenuator, impact force when can reduce unmanned aerial vehicle and descend, avoid unmanned aerial vehicle organism to appear the atress phenomenon of damage, and when unmanned aerial vehicle flies, can accomodate landing gear, avoid interfering flight.

Description

Unmanned aerial vehicle's landing gear and unmanned aerial vehicle thereof

Technical Field

The utility model relates to the technical field of unmanned aerial vehicle landing devices, in particular to an unmanned aerial vehicle landing device and an unmanned aerial vehicle thereof.

Background

Unmanned aerial vehicles are called "unmanned aerial vehicles", and English abbreviations are called "UAVs", unmanned aerial vehicles which are operated by radio remote control equipment and self-contained program control devices or are operated by vehicle-mounted computers completely or intermittently and autonomously, and currently, unmanned aerial vehicles are widely applied to the fields of aerial photography, agriculture, plant protection, self-photography, express transportation, disaster relief, wild animal observation, video monitoring shooting, mapping, news reporting and the like, so that the unmanned aerial vehicles are also important for landing gear operation of the unmanned aerial vehicles.

The current unmanned aerial vehicle undercarriage adopts fixed metallic structure to realize more to directly fix on the unmanned aerial vehicle bottom, lead to unmanned aerial vehicle can receive great impact force when descending, can cause unmanned aerial vehicle organism to damage, lead to unmanned aerial vehicle's life to reduce.

Disclosure of Invention

The utility model aims to provide a landing gear of an unmanned aerial vehicle and the unmanned aerial vehicle, which aim to solve the problems that in the prior art, the existing landing gear of the unmanned aerial vehicle is mainly realized by adopting a fixed metal structure and is directly fixed on the bottom of the unmanned aerial vehicle, so that the unmanned aerial vehicle can receive larger impact force when landing, the unmanned aerial vehicle body can be damaged, and the service life of the unmanned aerial vehicle is reduced.

In order to achieve the above purpose, the present utility model provides the following technical solutions: an unmanned aerial vehicle landing gear comprises a fuselage;

four recesses have been seted up to the inside symmetry of fuselage, four electric telescopic handle is all installed on the inside top of recess, the laminating is installed to electric telescopic handle's bottom the pipe of recess inner wall, the bottom elastic connection of pipe has the plectane for alleviate the impact force to the unmanned aerial vehicle organism when descending.

Preferably, the circular tube internally provided with the damper, the outer edge surface of the damper is sleeved with a spring, and the top end of the circular plate is provided with a circular ring attached to the outer edge surface of the damper for reducing the impact force when the unmanned aerial vehicle falls.

Preferably, the outer edge surface of ring laminating the interior edge surface of pipe, the bottom butt of spring the up end of ring, the plectane embedding the bottom of fuselage can reduce the windage of landing gear when unmanned aerial vehicle flies.

Preferably, the bottom of the round tube is provided with a convex plate which is abutted to the lower end face of the round ring, and a hollow groove is formed between the convex plate and the round plate and used for reducing the impact force when the unmanned aerial vehicle falls.

The utility model provides an unmanned aerial vehicle, four quarter bars are installed to the top symmetry of fuselage, four the equal rotary mounting in one end top of fuselage is kept away from to the quarter bars has the screw for drive unmanned aerial vehicle and take off.

Compared with the prior art, the utility model has the beneficial effects that:

through fuselage, recess, electric telescopic handle, pipe, attenuator, spring, plectane and the ring that are equipped with, by the electric telescopic handle in the recess with the lower terminal surface of pipe and plectane propelling movement play fuselage, then when by plectane contact ground, through the ring extrusion spring shock attenuation, the power when spring resilience is slowed down to the attenuator, the impact force when can reducing unmanned aerial vehicle and descending, avoid unmanned aerial vehicle organism to appear the phenomenon that the atress damaged, and when unmanned aerial vehicle flies, can accomodate landing gear, avoid interfering flight.

Drawings

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a schematic cross-sectional view of the present utility model;

fig. 3 is an enlarged schematic view of the structure of fig. 2 a according to the present utility model.

In the figure: 1. a body; 101. a short bar; 102. a propeller; 2. a groove; 201. an electric telescopic rod; 3. a round tube; 301. a damper; 302. a spring; 303. a convex plate; 4. a circular plate; 401. a circular ring; 402. and a hollow groove.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Examples

Referring to fig. 1-3, there is shown: the embodiment is a preferred implementation manner in the technical scheme, and the landing gear of the unmanned aerial vehicle comprises a body 1;

four recesses 2 have been seted up to the inside symmetry of fuselage 1, and electric telescopic handle 201 is all installed on the inside top of four recesses 2, and the pipe 3 of laminating recess 2 inner wall is installed to electric telescopic handle 201's bottom, and the bottom elastic connection of pipe 3 has plectane 4.

As shown in fig. 1 and 2, a damper 301 is mounted in the circular tube 3, a spring 302 is mounted on the outer edge surface of the damper 301 in a sleeved mode, and a circular ring 401 attached to the outer edge surface of the damper 301 is formed at the top end of the circular plate 4;

as shown in fig. 1 and 2, the outer edge surface of the circular ring 401 is attached to the inner edge surface of the circular tube 3, the bottom end of the spring 302 is abutted against the upper end surface of the circular ring 401, and the circular plate 4 is embedded into the bottom end of the machine body 1;

as shown in fig. 2, the bottom end of the circular tube 3 is provided with a convex plate 303 abutting against the lower end surface of the circular ring 401, and a hollow groove 402 is formed between the convex plate 303 and the circular plate 4;

as shown in fig. 1, four short rods 101 are symmetrically installed at the top end of a machine body 1, a propeller 102 is rotatably installed at the top end of one end, far away from the machine body 1, of each of the four short rods 101, and in specific implementation, a battery module, a regulation module, a cooling module and the like required by normal operation of the unmanned aerial vehicle are installed in the machine body 1;

in this embodiment, the propeller 102 on the short rod 101 installed at four corners of the body 1 drives the body 1 to fly, when the unmanned aerial vehicle falls, the electric telescopic rod 201 in the groove 2 pushes the round tube 3 and the round plate 4 out of the lower end surface of the body 1, and then when the round plate 4 contacts the ground, the spring 302 is extruded through the circular ring 401 to absorb shock, and the damper 301 slows down the force of the spring 302 when rebounding, so that the impact force of the unmanned aerial vehicle when falling can be reduced.

In the description of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

Finally, it should be noted that: the foregoing description is only a preferred embodiment of the present utility model, and the present utility model is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present utility model has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.

Claims

1. An unmanned aerial vehicle landing gear comprises a fuselage (1);

the method is characterized in that:

four recesses (2) have been seted up to the inside symmetry of fuselage (1), four electric telescopic handle (201) are all installed on the inside top of recess (2), laminating pipe (3) of recess (2) inner wall are installed to the bottom of electric telescopic handle (201), the bottom elastic connection of pipe (3) has plectane (4).

2. The unmanned aerial vehicle landing gear of claim 1, wherein: the circular tube (3) is internally provided with a damper (301), the outer edge surface of the damper (301) is sleeved with a spring (302), and the top end of the circular plate (4) is provided with a circular ring (401) attached to the outer edge surface of the damper (301).

3. A landing gear for an unmanned aerial vehicle according to claim 2, wherein: the outer edge surface of the circular ring (401) is attached to the inner edge surface of the circular tube (3), the bottom end of the spring (302) is abutted to the upper end surface of the circular ring (401), and the circular plate (4) is embedded into the bottom end of the machine body (1).

4. A landing gear for an unmanned aerial vehicle according to claim 3, wherein: the bottom end of the round tube (3) is provided with a convex plate (303) which is abutted against the lower end face of the round ring (401), and a hollow groove (402) is formed between the convex plate (303) and the round plate (4).

5. A drone comprising a landing gear for a drone as claimed in any one of claims 1 to 4, wherein: four short rods (101) are symmetrically arranged at the top end of the machine body (1), and screw propellers (102) are rotatably arranged at the top end of the four short rods (101) far away from the machine body (1).