CN218506143U

CN218506143U - Unmanned aerial vehicle shock attenuation fixture

Info

Publication number: CN218506143U
Application number: CN202223171817.4U
Authority: CN
Inventors: 崔亚鹏
Original assignee: China Science Star Control Tianjin Information Technology Co ltd
Current assignee: China Science Star Control Tianjin Information Technology Co ltd
Priority date: 2022-11-29
Filing date: 2022-11-29
Publication date: 2023-02-21
Anticipated expiration: 2032-11-29

Abstract

The utility model provides an unmanned aerial vehicle shock attenuation fixture, including the unmanned aerial vehicle fuselage, four support arms are evenly installed to unmanned aerial vehicle fuselage surface, the support arm is kept away from the one end of unmanned aerial vehicle fuselage and is installed the rotor, unmanned aerial vehicle fuselage lower surface one side is installed second servo motor, second servo motor output and U type frame fixed connection, the both ends of U type frame are all rotated and are installed in unmanned aerial vehicle fuselage bottom, unmanned aerial vehicle fuselage bottom is rotated and is installed two parallel arrangement's straight section of thick bamboo, slidable mounting has the piston in the straight section of thick bamboo, piston one side fixedly connected with connecting rod, the one end that the piston was kept away from to the connecting rod extends to the straight section of thick bamboo outside and rotates with U type frame to be connected, straight section of thick bamboo blind end surface mounting has and the communicating solenoid valve of straight section of thick bamboo, the utility model discloses following beneficial effect has: the effect is that the weight of the article between the two jaws is prevented from acting on the output of the servomotor.

Description

Unmanned aerial vehicle shock attenuation fixture

Technical Field

The utility model relates to an unmanned aerial vehicle shock attenuation fixture belongs to the unmanned aerial vehicle field.

Background

To the place that is not suitable for personnel's work, for example high altitude construction, generally install two clamping jaws on unmanned aerial vehicle, half round gear intermeshing on two clamping jaws, two clamping jaws are closed or expand by a servo motor drive, through two clamping jaw centre gripping article, realize utilizing unmanned aerial vehicle to carry out the high altitude transfer of article, change for the clamping jaw orientation, utilize another servo motor to adjust the orientation of clamping jaw, behind two clamping jaw centre gripping article, the weight of article can be used for adjusting on the servo motor output of clamping jaw orientation, the output that leads to the servo motor who is used for adjusting the clamping jaw orientation bears great load, influence life, consequently, need design an article weight and do not act on the unmanned aerial vehicle shock attenuation fixture on servo motor's output.

SUMMERY OF THE UTILITY MODEL

Not enough to prior art exists, the utility model aims at providing an unmanned aerial vehicle shock attenuation fixture to solve the problem that proposes in the above-mentioned background art, the utility model discloses realize preventing that the weight of the article between two clamping jaws from being used in servo motor's output.

In order to achieve the above purpose, the present invention is realized by the following technical solution: the utility model provides an unmanned aerial vehicle shock attenuation fixture, includes the unmanned aerial vehicle fuselage, four support arms are evenly installed to unmanned aerial vehicle fuselage surface, the rotor is installed to the one end that the unmanned aerial vehicle fuselage was kept away from to the support arm, second servo motor is installed to unmanned aerial vehicle fuselage lower surface one side, second servo motor output and U type frame fixed connection, the both ends of U type frame are all rotated and are installed in unmanned aerial vehicle fuselage bottom, the one side middle part position that U type frame deviates from the unmanned aerial vehicle fuselage installs the holder that is used for centre gripping article, unmanned aerial vehicle fuselage bottom is rotated and is installed two parallel arrangement's straight section of thick bamboo, slidable mounting has the piston in the straight section of thick bamboo, piston one side fixedly connected with connecting rod, the one end that the piston was kept away from to the connecting rod extends to the straight section of thick bamboo outside and is connected with U type frame rotation, the one end that straight section of thick bamboo is close to the unmanned aerial vehicle fuselage is the closed form, straight section of thick bamboo blind end surface mounting has and straight communicating solenoid valve, the shock attenuation piece is installed to one side that the support arm lower surface is close to the rotor.

Further, the holder includes the support plate, the support plate is installed to the one side intermediate position that U type frame deviates from the unmanned aerial vehicle fuselage, the support plate one side is rotated and is installed two semi-circular gears, two semi-circular gear intermeshing, one semi-circular gear and first servo motor output fixed connection, first servo motor is fixed with the support plate connection, two all rotate on the semi-circular gear and be connected with the clamping jaw that is used for centre gripping article, two parallel side intermediate position of clamping jaw all rotate and are connected with the linkage arm, the linkage arm other end rotates with the support plate and is connected.

Furthermore, the shock attenuation piece includes branch, vertical layout's branch is installed to one side that the support arm lower surface is close to the rotor, the branch lower extreme extends to in the barrel casing, one end fixedly connected with compression leg that branch is in the barrel casing, the compression leg downside is equipped with vertical layout's spring, the spring downside is equipped with the end cap, the lower part position in the barrel casing is installed to the end cap.

Furthermore, a blind hole is formed in one surface, facing the spring, of the compression column, and the upper end of the spring extends into the blind hole.

Further, the solenoid valve is kept away from the one end of straight section of thick bamboo and is installed the tube head, the one end threaded connection that the solenoid valve was kept away from to the tube head has the screw cap, keep away from one side of tube head in the screw cap and install the filter screen that is used for filtering the dust.

Further, a locating frame is installed to a side that the unmanned aerial vehicle fuselage is close to U type frame, install the camera through the screw in the locating frame.

The utility model has the advantages that:

1. control the solenoid valve when second servo motor works and open, and then second servo motor work drive U type frame rotates, U type frame this moment drives the connecting rod and removes, the connecting rod drives the piston and slides in straight section of thick bamboo, the air passes through the solenoid valve and gets into or discharge straight section of thick bamboo, the structural length that connecting rod and straight section of thick bamboo formed changes this moment, control the solenoid valve closure when second servo motor stops working, the air no longer passes in and out straight section of thick bamboo, the length of the structure that straight section of thick bamboo and connecting rod formed no longer changes, the structure that straight section of thick bamboo and connecting rod formed, unmanned aerial vehicle fuselage and U type frame form the triangle-shaped structure jointly, make the weight of the article of centre gripping between two clamping jaws act on the unmanned aerial vehicle fuselage, prevent that the weight of the article between two clamping jaws from acting on second servo motor's output, play the effect of protection second servo motor.

2. When the unmanned aerial vehicle fuselage descends, the barrel casing lower extreme at first contacts with ground, along with the continuation descending of unmanned aerial vehicle fuselage, the weight of unmanned aerial vehicle fuselage passes through support arm, branch and acts on the spring, makes the spring produce elastic deformation, realizes buffering absorbing effect.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

fig. 1 is a schematic structural view of the shock-absorbing clamping mechanism of the unmanned aerial vehicle of the present invention;

fig. 2 is an assembly schematic diagram of a second servo motor, a U-shaped frame, a support plate and an unmanned aerial vehicle body in the damping and clamping mechanism of the unmanned aerial vehicle of the present invention;

fig. 3 is an assembly schematic diagram of a U-shaped frame, a connecting rod, a straight cylinder and an unmanned aerial vehicle body in the damping and clamping mechanism for an unmanned aerial vehicle of the present invention;

FIG. 4 is an enlarged view taken at A in FIG. 3;

fig. 5 is an assembly schematic diagram of a piston, a connecting rod and a straight cylinder in the damping and clamping mechanism of the unmanned aerial vehicle of the present invention;

fig. 6 is a schematic view of the assembly of the filter screen and the screw cap in the shock-absorbing clamping mechanism of the unmanned aerial vehicle of the present invention;

fig. 7 is an assembly schematic diagram of the strut, the post rod, the spring and the sleeve in the damping and clamping mechanism of the unmanned aerial vehicle of the present invention;

in the figure: the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, an unmanned aerial vehicle body 2, a support arm 2, a rotor wing 3, a support rod 4, a barrel sleeve 5, a U-shaped frame 6, a first servo motor 7, a clamping jaw 8, a linkage arm 9, a semicircular gear 10, a camera 11, a positioning frame 12, a support plate 13, a second servo motor 14, a connecting rod 15, a straight barrel 16, an electromagnetic valve 17, a pipe head 18, a threaded cover 19, a piston 20, a filter screen 21, a compression column 22, a blind hole 23, a spring 24 and a plug 25.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.

Referring to fig. 1 and 7, the present invention provides a technical solution: the utility model provides an unmanned aerial vehicle shock attenuation fixture, including unmanned aerial vehicle fuselage 1, four support arms 2 of evenly installing at 1 surface of unmanned aerial vehicle fuselage keep away from the one end of unmanned aerial vehicle fuselage 1 and all install rotor 3, provide power for the rising of unmanned aerial vehicle fuselage 1 when blade among the rotor 3 is rotatory, then be close to rotor 3's a side-mounting vertical arrangement's branch 4 at 2 lower surfaces of support arm, make 4 lower extremes of branch extend to in barrel casing 5 and fixed connection compression leg 22, compression leg 22 downside is equipped with vertical arrangement's spring 24, spring 24 downside is equipped with the end cap 25 of installing the lower part position in barrel casing 5, end cap 25 realizes the shutoff to 5 lower extremes of barrel casing, when unmanned aerial vehicle fuselage 1 descends, barrel casing 5 lower extreme at first with ground contact, along with the continuation decline of unmanned aerial vehicle fuselage 1, unmanned aerial vehicle fuselage 1's weight is through support arm 2, branch 4 acts on spring 24, make spring 24 produce elastic deformation, realize buffering absorbing effect, make 24 upper end extend to in the blind hole 23 that compression leg 22 offers towards spring 24, provide the space for the shrink of spring 24, prevention spring 24 is excessively extruded, install camera 11 through the side of screw and gather the camera body 12 a side of unmanned aerial vehicle fuselage and utilize the camera body to be convenient for a side collection clamping jaw 12.

Referring to fig. 1, fig. 2 and fig. 3, a second servo motor 14 is installed on one side of the lower surface of an unmanned aerial vehicle body 1, wherein the output end of the second servo motor 14 is fixedly connected with a U-shaped frame 6, both ends of the U-shaped frame 6 are both rotatably installed at the bottom of the unmanned aerial vehicle body 1, a support plate 13 is installed at the middle position of one side of the U-shaped frame 6, which deviates from the unmanned aerial vehicle body 1, two semicircular gears 10 rotatably installed on the support plate 13 are meshed with each other, one semicircular gear 10 is fixedly connected with the output end of a first servo motor 7 fixed on the support plate 13, a clamping jaw 8 for clamping an article is rotatably connected to the two semicircular gears 10, two parallel side middle positions of the clamping jaw 8 are both rotatably connected with a linkage arm 9, the other end of the linkage arm 9 is rotatably connected with the support plate 13, the linkage arm 9, the clamping jaw 8 and the support plate 13 form a four-bar mechanism, the first servo motor 7 drives the semicircular gear 10 to rotate when in operation, then the two semicircular gears 10 rotate simultaneously, the distance between the two clamping jaws 8 is increased or decreased, and the purpose of clamping an article by using the two clamping jaws 8 is realized.

Referring to fig. 1, 3, 4 and 5, two parallel straight cylinders 16 are rotatably mounted at the bottom of an unmanned aerial vehicle body 1, wherein one end of each straight cylinder 16, which is close to the unmanned aerial vehicle body 1, is closed, one side of a piston 20, which is slidably mounted in each straight cylinder 16, is fixedly connected with a connecting rod 15, one end of each connecting rod 15, which is far away from the piston 20, extends to the outer side of the straight cylinder 16 and is rotatably connected with the corresponding U-shaped frame 6, the second servo motor 14 is controlled to operate, and simultaneously, an electromagnetic valve 17, which is mounted on the outer surface of the closed end of each straight cylinder 16 and is communicated with the straight cylinder 16, is controlled to be opened, so that the second servo motor 14 operates to drive the U-shaped frame 6 to rotate, at this time, the U-shaped frame 6 drives the connecting rod 15 to move, the connecting rod 15 drives the piston 20 to slide in the straight cylinder 16, air enters or exits the straight cylinders 16 through the electromagnetic valve 17, at this time, the structural length formed by the connecting rods 15 and the straight cylinders 16 is changed, when the second servo motor 14 stops operating, the electromagnetic valve 17 is controlled to be closed, air does not enter or exit the straight cylinders 16, the structures formed by the straight cylinders 16, the straight cylinders 16 and the triangular clamping jaws 8 of the unmanned aerial vehicle body 1 and the unmanned aerial vehicle body and the servo motor 14 can protect the unmanned aerial vehicle body from the weight of the second servo motor 14.

Referring to fig. 3, 4 and 6, a pipe head 18 is installed at one end of the solenoid valve 17 far from the straight cylinder 16, a threaded cover 19 is screwed at one end of the pipe head 18 far from the solenoid valve 17, and a filter screen 21 for filtering dust is installed at one side of the threaded cover 19 far from the pipe head 18, so that when air enters the straight cylinder 16 through the solenoid valve 17, the filter screen 21 filters dust in the air flow, and the dust is prevented from entering the straight cylinder 16 at will.

Although the present description is described in terms of embodiments, not every embodiment includes only a single embodiment, and such description is for clarity only, and those skilled in the art should be able to integrate the description as a whole, and the embodiments can be appropriately combined to form other embodiments as will be understood by those skilled in the art.

Claims

1. The utility model provides an unmanned aerial vehicle shock attenuation fixture, includes unmanned aerial vehicle fuselage (1), its characterized in that: unmanned aerial vehicle fuselage (1) surface evenly installs four support arms (2), support arm (2) are kept away from the one end of unmanned aerial vehicle fuselage (1) and are installed rotor (3), second servo motor (14) are installed to unmanned aerial vehicle fuselage (1) lower surface one side, second servo motor (14) output and U type frame (6) fixed connection, the both ends of U type frame (6) are all rotated and are installed in unmanned aerial vehicle fuselage (1) bottom, U type frame (6) deviate from the one side middle part position installation of unmanned aerial vehicle fuselage (1) and are used for the holder of centre gripping article, unmanned aerial vehicle fuselage (1) bottom is rotated and is installed two parallel arrangement's straight section of thick bamboo (16), slidable mounting has piston (20) in straight section of thick bamboo (16), piston (20) one side fixedly connected with connecting rod (15), the one end that piston (20) was kept away from in connecting rod (15) extends to straight section of thick bamboo (16) outside and is connected with U type frame (6) rotation, the one end that straight section of thick bamboo (16) is close to fuselage (1) is the form, straight section of thick bamboo (16) outer surface mounting has the solenoid valve (17) that communicates with straight section of thick bamboo (16), and the solenoid valve (17) that the blind end that the rotor communicates with the blind end of straight section of unmanned aerial vehicle fuselage (2) is close to be close to unmanned aerial vehicle lower surface install.

2. The unmanned aerial vehicle shock attenuation fixture of claim 1, characterized in that: the holder includes support plate (13), support plate (13) are installed to the one side intermediate position that U type frame (6) deviates from unmanned aerial vehicle fuselage (1), support plate (13) one side is rotated and is installed two semicircle gears (10), two semicircle gear (10) intermeshing, one semicircle gear (10) and first servo motor (7) output fixed connection, first servo motor (7) are connected fixedly with support plate (13), two all rotate on semicircle gear (10) and are connected with clamping jaw (8) that are used for centre gripping article, clamping jaw (8) two parallel side intermediate position all rotate and are connected with linkage arm (9), linkage arm (9) other end rotates with support plate (13) and is connected.

3. The unmanned aerial vehicle shock attenuation fixture of claim 1, characterized in that: damping piece includes branch (4), branch (4) of vertical arrangement are installed to one side that support arm (2) lower surface is close to rotor (3), branch (4) lower extreme extends to in barrel casing (5), one end fixedly connected with compression leg (22) that branch (4) are in barrel casing (5), compression leg (22) downside is equipped with spring (24) of vertical arrangement, spring (24) downside is equipped with end cap (25), lower part position in barrel casing (5) is installed in end cap (25).

4. The unmanned aerial vehicle shock attenuation fixture of claim 3, characterized in that: the one side that compression leg (22) faced spring (24) has seted up blind hole (23), spring (24) upper end extends to in blind hole (23).

5. The unmanned aerial vehicle shock attenuation fixture of claim 1, characterized in that: solenoid valve (17) are kept away from the one end of straight section of thick bamboo (16) and are installed tube head (18), the one end threaded connection that solenoid valve (17) were kept away from in tube head (18) has screw cap (19), filter screen (21) that are used for filtering the dust are installed to one side of keeping away from in screw cap (19) tube head (18).

6. The unmanned aerial vehicle shock attenuation fixture of claim 1, characterized in that: unmanned aerial vehicle fuselage (1) is close to a side of U type frame (6) and installs locating frame (12), install camera (11) through the screw in locating frame (12).