CN216887204U

CN216887204U - Rotor unmanned aerial vehicle undercarriage

Info

Publication number: CN216887204U
Application number: CN202123270788.2U
Authority: CN
Inventors: 刘智深
Original assignee: Shenyang Zhixiang Tongfei General Aviation Technology Co ltd
Current assignee: Shenyang Zhixiang Tongfei General Aviation Technology Co ltd
Priority date: 2021-12-24
Filing date: 2021-12-24
Publication date: 2022-07-05
Anticipated expiration: 2031-12-24

Abstract

The utility model discloses a rotor unmanned aerial vehicle undercarriage which comprises a fixed plate, wherein the top of the fixed plate is fixedly connected with a first damping plate and a second damping plate, two symmetrically arranged damping shafts are arranged between the first damping plate and the second damping plate, a bearing plate is arranged above the damping shafts, two symmetrically arranged fixed plates are arranged on the second damping plate, two symmetrically arranged damping blocks are connected onto the damping shafts in a sliding mode, the top of the bearing plate is provided with a connecting plate, and the top of the connecting plate is provided with a fixing groove for containing feet of an unmanned aerial vehicle. According to the utility model, through the matched use of the damping block, the bearing plate and the connecting plate, the footing of the unmanned aerial vehicle can fall into the fixing groove, then the bearing plate can be integrally pressed down to absorb shock, and the fixing shaft can be fixed in the fixing hole after being pressed down, so that the whole device is in a fixed state to absorb shock for the descending unmanned aerial vehicle, the unmanned aerial vehicle is prevented from being damaged, and the practicability of the device is improved.

Description

Unmanned gyroplane undercarriage

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a rotor unmanned aerial vehicle undercarriage.

Background

Unmanned aerial vehicle is unmanned aerial vehicle and traditional manned aircraft of comparison has advantages such as lightweight, conveniently transports and deposits, and because unmanned driving is less with the size, so the flexible operation can get into dangerous area and shoot, the wide application is in aspects such as taking photo by plane and disaster rescue, and the last mechanical undercarriage of unmanned aerial vehicle receive and releases the structure and then can promote security and stability when unmanned aerial vehicle takes off and lands.

Unmanned aerial vehicle when descending, can make unmanned aerial vehicle take place to bounce back when falling on the ground because of stability, and then make unmanned aerial vehicle take place to damage, to current problem, we propose a rotor unmanned aerial vehicle undercarriage.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the problems in the prior art, and provides a landing gear of a rotor wing unmanned aerial vehicle.

In order to achieve the purpose, the utility model adopts the following technical scheme:

the utility model provides a rotor unmanned aerial vehicle undercarriage, includes the fixed plate, first shock attenuation board of fixed plate top fixedly connected with and second shock attenuation board, be equipped with the damping shaft that two symmetries set up between first shock attenuation board and the second shock attenuation board, the top of damping shaft is equipped with the loading board, be equipped with the backup pad that two symmetries set up on the second shock attenuation board, the epaxial sliding connection of damping has the snubber block that two symmetries set up, the top of loading board is equipped with the connecting plate, the fixed slot that is used for accomodating the unmanned aerial vehicle footing is seted up at the connecting plate top.

Preferably, the damping shaft lateral wall sliding connection has two snubber blocks, damping shaft lateral wall cover is equipped with two damping spring, two damping spring's one end respectively with first shock attenuation board and second shock attenuation board lateral wall fixed connection, two one side mutually back of the body of snubber block respectively with corresponding damping spring's other end fixed connection.

Preferably, the bottom of the bearing plate is connected with two first connecting shafts, two damping block outer side walls are fixedly connected with second connecting shafts, the first connecting shafts are connected with the second connecting shafts through telescopic rods, the telescopic rods are provided with first telescopic blocks and second telescopic blocks, and the first telescopic blocks are inserted in the second telescopic blocks.

Preferably, the first connecting plate of first flexible piece lateral wall fixedly connected with, the flexible piece lateral wall fixedly connected with second connecting plate of second, telescopic link lateral wall cover is equipped with compression spring, the compression spring both ends respectively with first connecting plate lateral wall and second connecting plate lateral wall fixed connection.

Preferably, the top of the bearing plate is provided with a sliding groove, the inner side wall of the sliding groove is fixedly connected with a sliding shaft, the connecting plate is provided with a sliding hole, and the outer side wall of the sliding shaft is in sliding connection with the inner side wall of the sliding hole.

Preferably, a fixed port is formed in the supporting plate, a fixed shaft is fixedly connected to the outer side wall of the connecting plate, and the outer side wall of the fixed shaft is slidably connected with the inner side wall of the fixed port.

Compared with the prior art, the utility model has the following advantages:

the cooperation through snubber block, loading board and connecting plate is used, can fall into the fixed slot at unmanned aerial vehicle's footing in, then can wholly push down the loading board, carry out the shock attenuation to it to can make the fixed axle at fixed orifices internal fixation after pushing down, make whole device be the stationary state from this, carry out the shock attenuation to the unmanned aerial vehicle of descending, prevent that unmanned aerial vehicle from taking place to damage, improved the practicality of device.

Drawings

Fig. 1 is a schematic structural view of a landing gear of a rotorcraft according to the present invention;

FIG. 2 is a schematic structural view of a bearing plate and a connecting plate according to the present invention;

fig. 3 is a schematic structural diagram of a first telescopic block and a second telescopic block according to the present invention.

In the figure: 1. a fixing plate; 2. a first damper plate; 3. a second damper plate; 4. a support plate; 5. a shock-absorbing shaft; 6. a damper block; 7. a carrier plate; 8. a connecting plate; 9. a fixed port; 10. a sliding groove; 11. a first telescopic block; 12. a second telescopic block; 13. and fixing the shaft.

Detailed Description

Referring to fig. 1-3, a landing gear of a rotor wing unmanned aerial vehicle comprises a fixed plate 1, wherein the top of the fixed plate 1 is fixedly connected with a first damping plate 2 and a second damping plate 3, two symmetrically arranged damping shafts 5 are arranged between the first damping plate 2 and the second damping plate 3, the outer side wall of each damping shaft 5 is slidably connected with two damping blocks 6, the outer side wall of each damping shaft 5 is sleeved with two damping springs, one ends of the two damping springs are respectively and fixedly connected with the outer side walls of the first damping plate 2 and the second damping plate 3, and the opposite sides of the two damping blocks 6 are respectively and fixedly connected with the other ends of the corresponding damping springs;

a bearing plate 7 is arranged above the damping shaft 5, two first connecting shafts are connected to the bottom of the bearing plate 7, second connecting shafts are fixedly connected to the outer side walls of the two damping blocks 6, the first connecting shafts are connected with the second connecting shafts through telescopic rods, each telescopic rod is composed of a first telescopic block 11 and a second telescopic block 12, the first telescopic blocks 11 are inserted into the second telescopic blocks 12, the outer side walls of the first telescopic blocks are fixedly connected with first connecting plates, the outer side walls of the second telescopic blocks are fixedly connected with second connecting plates, compression springs are sleeved on the outer side walls of the telescopic rods, two ends of each compression spring are fixedly connected with the outer side walls of the first connecting plates and the outer side walls of the second connecting plates respectively, and downward impact force of the unmanned aerial vehicle can be absorbed through the compression springs and the damping springs;

be equipped with backup pad 4 that two symmetries set up on second shock attenuation board 3, sliding connection has the snubber block 6 that two symmetries set up on damping shaft 5, the top of loading board 7 is equipped with connecting plate 8, loading board 7 top is equipped with sliding tray 10, sliding tray 10 inside wall fixedly connected with sliding shaft, the sliding hole has been seted up on connecting plate 8, sliding shaft lateral wall and the downthehole lateral wall sliding connection of sliding hole, the fixed slot that is used for accomodating the unmanned aerial vehicle footing is seted up at connecting plate 8 top, fixed mouthful 9 has been seted up on

backup pad

4, 8 lateral wall fixedly connected with fixed axles 13 of connecting plate, 13 lateral walls of fixed axle and 9 inside wall sliding connection of fixed mouthful, carry out the back that subtracts shock attenuation to unmanned aerial vehicle from this, make the device wholly be stationary state, can not take place to rock, the practicality of device has been improved.

The specific working principle of the utility model is as follows:

at first, the device under the initial condition can the shock attenuation, but be in the state that can take place to rock, when unmanned aerial vehicle is descending, unmanned aerial vehicle can fall on connecting plate 8, unmanned aerial vehicle's footing can be fixed by the fixed slot, unmanned aerial vehicle can be absorbed by damping spring and compression spring to the decurrent impact force of connecting plate 8, and can make fixed axle 13 take place to remove after pushing down, and then make connecting plate 8 spacing by fixed mouthful 9, make the device can not take place to rock after the unmanned aerial vehicle shock attenuation, the practicality of device has been improved.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and equivalent alternatives or modifications according to the technical solution of the present invention and the inventive concept thereof should be covered by the scope of the present invention.

Claims

1. The utility model provides a rotor unmanned aerial vehicle undercarriage, includes fixed plate (1), its characterized in that, fixed plate (1) top fixedly connected with first shock attenuation board (2) and second shock attenuation board (3), be equipped with damping shaft (5) that two symmetries set up between first shock attenuation board (2) and second shock attenuation board (3), the top of damping shaft (5) is equipped with loading board (7), be equipped with backup pad (4) that two symmetries set up on second shock attenuation board (3), sliding connection has snubber block (6) that two symmetries set up on damping shaft (5), the top of loading board (7) is equipped with connecting plate (8), the fixed slot that is used for accomodating the unmanned aerial vehicle footing is seted up at connecting plate (8) top.

2. A rotary wing unmanned aerial vehicle landing gear according to claim 1, wherein two damping blocks (6) are slidably connected to an outer side wall of the damping shaft (5), two damping springs are sleeved on an outer side wall of the damping shaft (5), one ends of the two damping springs are fixedly connected to outer side walls of the first damping plate (2) and the second damping plate (3), and opposite sides of the two damping blocks (6) are fixedly connected to the other ends of the corresponding damping springs.

3. The landing gear of claim 1, wherein two first connecting shafts are connected to the bottom of the bearing plate (7), a second connecting shaft is fixedly connected to the outer side walls of the two shock-absorbing blocks (6), the first connecting shafts and the second connecting shafts are connected through telescopic rods, each telescopic rod comprises a first telescopic block (11) and a second telescopic block (12), and the first telescopic blocks (11) are inserted into the second telescopic blocks (12).

4. The undercarriage for a rotorcraft according to claim 3, wherein a first connecting plate is fixedly connected to an outer side wall of the first telescoping block, a second connecting plate is fixedly connected to an outer side wall of the second telescoping block, a compression spring is sleeved on an outer side wall of the telescoping rod, and two ends of the compression spring are fixedly connected to an outer side wall of the first connecting plate and an outer side wall of the second connecting plate respectively.

5. The landing gear of claim 1, wherein a sliding groove (10) is formed in the top of the bearing plate (7), a sliding shaft is fixedly connected to the inner side wall of the sliding groove (10), a sliding hole is formed in the connecting plate (8), and the outer side wall of the sliding shaft is slidably connected with the inner side wall of the sliding hole.

6. A landing gear for a rotorcraft according to claim 1, wherein the support plate (4) has a fixing opening (9) formed therein, a fixing shaft (13) is fixedly connected to an outer side wall of the connecting plate (8), and an outer side wall of the fixing shaft (13) is slidably connected to an inner side wall of the fixing opening (9).