CN211107970U - A landing gear damping structure for unmanned aerial vehicles - Google Patents

Abstract

The utility model discloses a shock-absorbing structure of a landing gear for an unmanned aerial vehicle, which comprises a bracket, a work box is fixedly connected to the bottom of the bracket, an electric motor is fixedly connected to the inside of the work box, and an output end of the electric motor is fixedly connected. A conducting rod is fixedly connected, one end of the conducting rod is fixedly connected with a rotating rod, the outer surface of the rotating rod is fixedly connected with a movable rod, one end of the movable rod is fixedly connected with a buffer column, and the bottom of the buffer column is fixed A shock-absorbing spring is connected, and a buffer tube is movably connected to the outer surface of the buffer column. The UAV uses the landing gear shock absorber structure. Through the setting of the work box and the shock absorber spring, when the roller touches the ground, the shock absorber spring starts to accumulate force to buffer the descending force, which is convenient for shock absorption. , the electric motor inside the work box starts to work, driving the conduction rod to reverse, and then the roller is put away, so as to achieve the purpose of shock absorption and convenient storage.

Description

A landing gear damping structure for unmanned aerial vehicles

technical field

The utility model relates to the technical field of auxiliary structures of unmanned aerial vehicles, in particular to a shock absorption structure of a landing gear for unmanned aerial vehicles.

Background technique

Unmanned aerial vehicle is abbreviated as "UAV", and the English abbreviation is "UAV". It is an unmanned aircraft operated by radio remote control equipment and self-provided program control device, or operated completely or intermittently by the on-board computer. Compared with manned aircraft, drones are often more suitable for tasks that are too "dumb, dirty or dangerous". According to the application field, drones can be divided into military and civilian use. People often use them when taking pictures. The unmanned aerial vehicle works, but the shock absorption of the ordinary unmanned aerial vehicle is not perfect when it lands. Therefore, the utility model has developed a landing gear damping structure for the unmanned aerial vehicle.

Utility model content

(1) Technical problems solved

In view of the deficiencies of the prior art, the present invention provides a shock-absorbing structure of a landing gear for an unmanned aerial vehicle, which solves the problems raised in the above-mentioned background technology.

(2) Technical solutions

In order to achieve the above purpose, the present utility model is achieved through the following technical solutions: a shock-absorbing structure for a landing gear for an unmanned aerial vehicle, comprising a bracket, the bottom of the bracket is fixedly connected with a work box, and the interior of the work box is fixedly connected with a An electric motor, an output end of the electric motor is fixedly connected with a conduction rod, one end of the conduction rod is fixedly connected with a rotating rod, an outer surface of the rotating rod is fixedly connected with a movable rod, and one end of the movable rod is fixedly connected with a rotating rod. A buffer column, the bottom of the buffer column is fixedly connected with a shock-absorbing spring, the outer surface of the buffer column is movably connected with a buffer tube, and the bottom of the buffer tube is fixedly connected with a chassis.

Optionally, a connecting piece is fixedly connected to the lower surface of the chassis, and a rotating rod is movably connected to the outer surface of the connecting piece through a rotating shaft.

Optionally, a roller is fixedly connected to the outer surface of the rotating rod, and the number of the brackets is two.

Optionally, a movable hole is opened on the outer surface of the working box, and the width of the movable hole is adapted to the width of the movable rod.

Optionally, a wind panel is fixedly connected to the outer surface of the bracket, and the cross section of the wind panel is triangular.

Optionally, one end of the rotating rod is movably connected to the inner wall of the work box through a rotating shaft, and the bottom of the shock-absorbing spring is fixedly connected to the inner bottom wall of the buffer tube.

(3) Beneficial effects

The utility model provides a shock-absorbing structure of a landing gear for an unmanned aerial vehicle, which has the following beneficial effects:

The UAV uses the landing gear shock absorption structure. Through the setting of the working box and the shock-absorbing spring, when the UAV is landing, the electric motor inside the working box under the bracket starts to work, and the rotating rod is driven to rotate by the conduction rod. , so that the movable rod rotates, and then the movable rod drives the working components below it to rotate from a horizontal state to a vertical state. When the roller touches the ground, the shock-absorbing spring starts to accumulate force to buffer the descending force, which is convenient for shock absorption. When it is raised, the electric motor inside the work box starts to work, which drives the conduction rod to reverse, and then the roller is put away, so as to achieve the purpose of shock absorption and convenient storage.

Description of drawings

Fig. 1 is the structural representation of the utility model;

FIG. 2 is a schematic structural diagram of a connecting piece of the present invention;

Fig. 3 is the structural representation of the utility model work box;

4 is a schematic structural diagram of a buffer tube of the present invention;

FIG. 5 is a schematic diagram of the movable hole structure of the present invention.

In the figure: 1. Bracket; 2. Working box; 3. Electric motor; 4. Conducting rod; 5. Rotating rod; 6. Active rod; 7. Buffer column; 8. Shock-absorbing spring; 9. Buffer tube; 10. Chassis; 11, connecting piece; 12, rotating rod; 13, roller; 14, movable hole; 15, wind panel.

Detailed ways

The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the implementations. example.

Please refer to FIGS. 1 to 5 , the present invention provides a technical solution: a landing gear damping structure for an unmanned aerial vehicle, comprising a bracket 1 , a work box 2 is fixedly connected to the bottom of the bracket 1 , and the interior of the work box 2 is fixed An electric motor 3 is connected, and the electric motor provides power for the rotation of the movable rod 6. The output end of the electric motor 3 is fixedly connected with a conducting rod 4, and one end of the conducting rod 4 is fixedly connected with a rotating rod 5, and one end of the rotating rod 5 passes through the rotating shaft. Actively connected with the inner wall of the work box 2, the bottom of the shock-absorbing spring 8 is fixedly connected with the inner bottom wall of the buffer tube 9;

A movable rod 6 is fixedly connected to the outer surface of the rotating rod 5. The movable rod 6 penetrates through the interior of the movable hole 14. One end of the movable rod 6 is fixedly connected with a buffer column 7. When under pressure, the buffer column 7 moves to the inside of the buffer tube 9. The bottom of the buffer column 7 is fixedly connected with the shock-absorbing spring 8, the outer surface of the buffer column 7 is movably connected with the buffer tube 9, the bottom of the buffer tube 9 is fixedly connected with the chassis 10, and the lower surface of the chassis 10 is fixedly connected with the connecting piece 11 , the outer surface of the connecting piece 11 is movably connected with the rotating rod 12 through the rotating shaft, the rotating rod 12 can be rotated on the surface of the connecting piece 11 through the rotating shaft, and the outer surface of the rotating rod 12 is fixedly connected with the roller 13, and the number of the brackets 1 is Two, the outer surface of the work box 2 is provided with a movable hole 14, the width of the movable hole 14 is adapted to the width of the movable rod 6, the outer surface of the bracket 1 is fixedly connected with a wind panel 15, and the cross section of the wind panel 15 is a triangle. .

As a preferred technical solution of the present invention, the wind panel 15 can reduce wind resistance to a certain extent.

The electrical components appearing in this article are all connected with the external main controller and 220V mains, and the main controller can be a conventional known device controlled by a computer or the like.

To sum up, the UAV uses the landing gear shock absorption structure. When the UAV is in use, when the UAV is landing, the electric motor 3 inside the working box 2 under the bracket 1 starts to work, and the rotating rod is driven by the conducting rod 4 5 is rotated, so that the movable rod 6 rotates, and then the movable rod 6 drives the working assembly below it to rotate from a horizontal state to a vertical state. When the roller 13 touches the ground, the shock-absorbing spring 8 starts to accumulate force to buffer the descending force. , which is convenient for shock absorption. When it needs to be raised, the electric motor 3 inside the work box 2 starts to work, which drives the conduction rod 4 to reverse, and then the rollers are retracted, so as to achieve the purpose of shock absorption and convenient storage.

The above description is only a preferred embodiment of the present invention, but the protection scope of the present invention is not limited to this. Equivalent replacement or modification of the new technical solution and its utility model concept shall be included within the protection scope of the present utility model.

Claims (6)

1. The utility model provides an unmanned aerial vehicle is with landing frame shock-absorbing structure, includes support (1), its characterized in that: the utility model discloses a buffer structure, including support (1), the bottom fixedly connected with work box (2) of support (1), the inside fixedly connected with electric motor (3) of work box (2), the output end fixedly connected with of electric motor (3) conducts stick (4), the one end fixedly connected with dwang (5) of conducting stick (4), the surface fixedly connected with activity stick (6) of dwang (5), the one end fixedly connected with buffering post (7) of activity stick (6), the bottom fixedly connected with damping spring (8) of buffering post (7), the surface swing joint of buffering post (7) has buffer tube (9), the bottom fixedly connected with chassis (10) of buffer tube (9).

2. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the lower surface of the chassis (10) is fixedly connected with a connecting sheet (11), and the outer surface of the connecting sheet (11) is movably connected with a rotating rod (12) through a rotating shaft.

3. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 2, wherein: the outer surface of the rotating rod (12) is fixedly connected with rollers (13), and the number of the brackets (1) is two.

4. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the outer surface of the working box (2) is provided with a movable hole (14), and the width of the movable hole (14) is matched with that of the movable rod (6).

5. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the outer surface fixed connection of support (1) has wind plate (15), the cross section of wind plate (15) is triangle-shaped.

6. The landing frame shock-absorbing structure for unmanned aerial vehicle of claim 1, wherein: the inner wall swing joint of axis of rotation and work box (2) is passed through to the one end of dwang (5), the bottom of damping spring (8) and the interior diapire fixed connection of buffer tube (9).

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