CN211810206U

CN211810206U - Unmanned aerial vehicle prevents empting undercarriage

Info

Publication number: CN211810206U
Application number: CN202020052018.7U
Authority: CN
Inventors: 周汉文
Original assignee: Xuzhou Golden Beach Machine Tool Accessories Co Ltd
Current assignee: Xuzhou Golden Beach Machine Tool Accessories Co Ltd
Priority date: 2020-01-10
Filing date: 2020-01-10
Publication date: 2020-10-30
Anticipated expiration: 2030-01-10

Abstract

The utility model relates to an unmanned air vehicle technique field just discloses an unmanned aerial vehicle prevents empting undercarriage, including unmanned aerial vehicle and undercarriage, the undercarriage is hollow structure, fixedly connected with piston box on one side lateral wall of undercarriage, sliding connection has first piston in the piston box, the one end fixedly connected with push rod of first piston, and the push rod runs through the lateral wall setting of piston box, piston box is linked together through first pipeline with the inside of undercarriage, and is provided with the check valve in the first pipeline, is located the downside of first pipeline is provided with the second pipeline, and piston box and undercarriage are linked together through the second pipeline. This kind of undercarriage is prevented empting by unmanned aerial vehicle can reduce the recoil force when buffering, avoids unmanned aerial vehicle to take place to empty.

Description

Unmanned aerial vehicle prevents empting undercarriage

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is an unmanned aerial vehicle prevents empting undercarriage.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar.

Along with the development of science and technology, unmanned aerial vehicle is applied to many fields in the life, current unmanned aerial vehicle undercarriage is mostly through the spring bradyseism or also has some unmanned aerial vehicle undercarriages to carry out the bradyseism through magnetic force, these supports can provide better bradyseism under normal conditions, but when taking place danger, unmanned aerial vehicle probably can't normally descend, the support will bear very big impact force at the in-process of buffering, these supports can be under the very big condition of impact force, can receive great recoil dynamics after accomplishing the bradyseism, can cause to take place to rock at the bradyseism in-process for unmanned aerial vehicle like this, even take place to topple.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

Not enough to prior art, the utility model provides an unmanned aerial vehicle prevents empting undercarriage possesses advantages such as prevent toppling and shock attenuation buffering, has solved the problem that the background art provided.

(II) technical scheme

For the purpose of realizing the aforesaid prevent toppling and shock attenuation buffering, the utility model provides a following technical scheme: an anti-toppling undercarriage of an unmanned aerial vehicle comprises the unmanned aerial vehicle and an undercarriage, wherein the undercarriage is of a hollow structure, a piston box is fixedly connected onto one side wall of the undercarriage, a first piston is connected in the piston box in a sliding mode, one end of the first piston is fixedly connected with a push rod, the push rod penetrates through the side wall of the piston box, the piston box is communicated with the interior of the undercarriage through a first pipeline, a check valve is arranged in the first pipeline, a second pipeline is arranged on the lower side of the first pipeline, the piston box is communicated with the undercarriage through a second pipeline, a first magnet is fixedly connected in the undercarriage, a second piston is arranged in the undercarriage and positioned at the lower end of the first magnet, a second magnet is fixedly connected onto one side wall of the second piston, a partition plate is arranged at the lower end of the second piston, and a plurality of through holes are formed in the, the side wall of the partition plate is provided with an anti-recoil device, a third piston is arranged in the undercarriage positioned on the lower side of the partition plate, and a support rod is fixedly connected to the side wall of one side of the third piston.

Preferably, an anti-collision groove is formed in the side wall of one side of the first magnet, the anti-collision groove is fixedly connected with an anti-collision cushion, the anti-collision cushion is made of rubber, and a plurality of rubber particles are arranged on the side wall of one side of the anti-collision cushion.

Preferably, the anti-recoil device comprises a connecting rod, the connecting rod is fixedly connected to the side wall of the partition plate, a stop block is fixedly connected to one end of the connecting rod, a fourth piston is slidably connected to the side wall of the connecting rod, a plurality of oil passing holes are formed in the side wall of the fourth piston, and the fourth piston is fixedly connected with the partition plate through a compression spring.

Preferably, the thickness of the fourth piston is larger than the diameter of the second pipeline, and the oil passing hole formed in the fourth piston is different from the through hole formed in the partition plate in position.

Preferably, a mounting hole is formed in the side wall of one side of the stop block, an internal thread is arranged in the mounting hole, an external thread is formed in the outer side wall of one end of the connecting rod, and the stop block is connected with the connecting rod through a thread.

Preferably, the one end fixedly connected with push pedal of push rod, the cover is equipped with the rubber pad on the push pedal, and has seted up the bar groove on the rubber pad.

(III) advantageous effects

Compared with the prior art, the utility model discloses possess following beneficial effect:

1. this kind of undercarriage is prevented empting by unmanned aerial vehicle, through parts such as the third piston that sets up and second pipeline, when unmanned aerial vehicle is great at buffering in-process dynamics, set up third piston meeting upward movement in the undercarriage to drive second piston and second magnet upward movement. Magnetic force between two magnets can repel each other, realizes the shock attenuation, and at the in-process of recovering when recoil power is too big, hydraulic oil can extrude the second piston to make the second piston no longer block up the second pipeline, hydraulic oil can enter into the piston box through the second pipeline, reduces the impact force of landing gear in the buffering resumes, avoids unmanned aerial vehicle to take place to topple.

2. This kind of undercarriage is prevented empting by unmanned aerial vehicle can protect second magnet through the crashproof groove of seting up in first magnet, prevents because two magnet clashes each other of too big messenger of impact force, provides further buffering space, has improved the security of undercarriage in buffer process.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

fig. 2 is a schematic cross-sectional structure view of the landing gear and the piston box of the present invention;

FIG. 3 is an enlarged schematic view of the structure at A in FIG. 2;

fig. 4 is an enlarged schematic view of a portion B in fig. 2.

In the figure: 1. an unmanned aerial vehicle; 2. a landing gear; 3. a piston case; 4. a first piston; 5. a push rod; 6. a first magnet; 7. a second magnet; 8. a second piston; 9. a partition plate; 10. a through hole; 11. a third piston; 12. a support bar; 13. a first conduit; 14. a one-way valve; 15. a second conduit; 16. a connecting rod; 17. a stopper; 18. a fourth piston; 19. an oil passing hole; 20. compressing the spring.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Example 1

Referring to fig. 1-3, an anti-toppling undercarriage for an unmanned aerial vehicle comprises an unmanned aerial vehicle 1 and an undercarriage 2, wherein the undercarriage 2 is of a hollow structure, a piston box 3 is fixedly connected to the side wall of one side of the undercarriage 2, hydraulic oil is arranged in the undercarriage 2 and at the lower end of the piston box 3, a first piston 4 is slidably connected in the piston box 3, one end of the first piston 4 is fixedly connected with a push rod 5, and the push rod 5 is arranged by penetrating through the side wall of the piston box, one end of the push rod 5 is fixedly connected with a push plate, a rubber pad is sleeved on the push plate, and the rubber pad is provided with a strip-shaped groove, the push plate and the rubber pad are arranged to facilitate the control of the push rod 5 by an operator, the piston box 3 is communicated with the inner part of the undercarriage 2 through a first pipeline 13, and a check valve 14 is arranged in the first pipeline 13, a second pipeline 15 is arranged at the lower side of the first pipeline 13, and the piston box 3 is communicated with the landing gear 2 through the second pipeline 15.

A first magnet 6 is fixedly connected inside the undercarriage 2, a second piston 8 is arranged in the undercarriage 2 at the lower end of the first magnet 6, a second magnet 7 is fixedly connected on the side wall of one side of the second piston 8, a partition plate 9 is arranged at the lower end of the second piston 8, a plurality of through holes 10 are formed in the partition plate 9, an anti-recoil device is arranged on the side wall of the partition plate 9 and comprises a connecting rod 16, the connecting rod 16 is fixedly connected on the side wall of the partition plate 9, a stop 17 is fixedly connected at one end of the connecting rod 16, a mounting hole is formed in the side wall of one side of the stop 17, an internal thread is arranged in the mounting hole, an external thread is formed in the outer side wall of one end of the connecting rod 16, the stop 17 is connected with the connecting rod 16 through a thread, the arranged thread connection can facilitate the mounting and dismounting between the stop 17 and the connecting, the side wall of the fourth piston 18 is provided with a plurality of oil passing holes 19, the thickness of the fourth piston 18 is larger than the diameter of the pipeline of the second pipeline 15, the oil passing holes 19 formed in the fourth piston 18 are different from the positions of the through holes 10 in the partition plate 9, the thickness of the fourth piston 18 is larger than the diameter of the pipeline of the second pipeline 15, so that the fourth piston 18 can block the second pipeline 15, the flow rate of hydraulic oil can be reduced during recoil when the oil passing holes 19 and the through holes 10 are staggered, the rebound speed of the supporting rod 12 is reduced, overturning is prevented, the fourth piston 18 is fixedly connected with the partition plate 9 through a compression spring 20, the set anti-recoil device can extrude the second piston 8 when the recoil force is too large in the process of recovering the hydraulic oil of the landing gear 2, so that the second pipeline 15 is not blocked by the second piston 8 and enters the piston box through the second pipeline 15, the counter impact force of the landing gear in the buffering recovery process is reduced, the situation that the airplane overturns is avoided, the third piston 11 is arranged in the landing gear 2 on the lower side of the partition plate 9, and the supporting rod 12 is fixedly connected to the side wall of one side of the third piston 11.

Example 2

Based on embodiment 1, as shown in fig. 1-3, a collision avoidance groove has been opened on one side lateral wall of first magnet 6, and collision avoidance groove internal fixation connects collision avoidance cushion, and collision avoidance cushion adopts the rubber material, and is provided with a plurality of rubber particles on one side lateral wall of collision avoidance cushion, can protect second magnet 7 through the collision avoidance groove of seting up in first magnet 6, prevents to make two magnets collide each other because the impact force is too big, has improved undercarriage 2 security in the buffering process.

The working principle is as follows: when needs cushion, bracing piece 12 can extrude third piston 11, make the hydraulic oil extrusion second piston 8 motion in the undercarriage 2, second piston 8 can drive second magnet 7 upward movement, cushion through repulsive magnetic force between second magnet 7 and the first magnet 6, at the in-process that the buffering resumes, when recoil force is too big, hydraulic oil can extrude third piston 11, third piston 11 can the downstream, thereby open second pipeline 15, make hydraulic oil enter into piston box 3, make the speed that bracing piece 12 resumeed the position slow down, unmanned aerial vehicle has been prevented to rock owing to great bounce in the buffering process, lead to the fuselage to damage.

Further, when the impact force exceeded buffering limit, can protect second magnet 7 through the crashproof groove of seting up in first magnet 6, prevent because two magnet of too big messenger of impact force collide each other, provide further buffering space, improved the security of landing gear in the buffering process.

Further, after the buffering, the staff promotes push rod 5 through the operation push pedal, and push rod 5 drives first piston 4 and moves down to make the hydraulic oil of the excess in the piston box 3 pass through first pipeline 13 and check valve 14 and reentry undercarriage 2, let bracing piece 2 resume the normal position through artificial controlling.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An unmanned aerial vehicle anti-overturning undercarriage comprises an unmanned aerial vehicle (1) and an undercarriage (2), wherein the undercarriage (2) is of a hollow structure;

the method is characterized in that:

a piston box (3) is fixedly connected to the side wall of one side of the undercarriage (2), a first piston (4) is connected to the piston box (3) in a sliding mode, a push rod (5) is fixedly connected to one end of the first piston (4), the push rod (5) penetrates through the side wall of the piston box (3), the piston box (3) is communicated with the interior of the undercarriage (2) through a first pipeline (13), a one-way valve (14) is arranged in the first pipeline (13), a second pipeline (15) is arranged on the lower side of the first pipeline (13), the piston box (3) is communicated with the undercarriage (2) through the second pipeline (15), a first magnet (6) is fixedly connected to the interior of the undercarriage (2), a second piston (8) is arranged in the undercarriage (2) at the lower end of the first magnet (6), and a second magnet (7) is fixedly connected to the side wall of one side of the second piston (8), the lower end that is located second piston (8) is provided with baffle (9), and has seted up a plurality of through-holes (10) on baffle (9), be provided with anti-recoil device on the lateral wall of baffle (9), be located be provided with third piston (11) in undercarriage (2) of baffle (9) downside, and one side lateral wall fixedly connected with bracing piece (12) of third piston (11).

2. The unmanned aerial vehicle anti-tip landing gear of claim 1, wherein: the anti-collision device is characterized in that an anti-collision groove is formed in one side wall of the first magnet (6), an anti-collision cushion is fixedly connected in the anti-collision groove and made of rubber, and a plurality of rubber particles are arranged on one side wall of the anti-collision cushion.

3. The unmanned aerial vehicle anti-tip landing gear of claim 1, wherein: the anti-recoil device comprises a connecting rod (16), the connecting rod (16) is fixedly connected to the side wall of the partition plate (9), a stop block (17) is fixedly connected to one end of the connecting rod (16), a fourth piston (18) is slidably connected to the side wall of the connecting rod (16), a plurality of oil passing holes (19) are formed in the side wall of the fourth piston (18), and the fourth piston (18) is fixedly connected with the partition plate (9) through a compression spring (20).

4. The unmanned aerial vehicle anti-tip landing gear of claim 3, wherein: the thickness of the fourth piston (18) is larger than the diameter of the second pipeline (15), and the oil passing hole (19) formed in the fourth piston (18) is different from the position of the through hole (10) formed in the partition plate (9).

5. The unmanned aerial vehicle anti-tip landing gear of claim 3, wherein: the connecting rod is characterized in that a mounting hole is formed in the side wall of one side of the stop block (17), an internal thread is arranged in the mounting hole, an external thread is formed in the outer side wall of one end of the connecting rod (16), and the stop block (17) is connected with the connecting rod (16) through the thread.

6. The unmanned aerial vehicle anti-tip landing gear of claim 1, wherein: the one end fixedly connected with push pedal of push rod (5), the cover is equipped with the rubber pad on the push pedal, and has seted up the bar groove on the rubber pad.