CN216401743U - Aircraft loading support with shock attenuation effect - Google Patents
Aircraft loading support with shock attenuation effect Download PDFInfo
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- CN216401743U CN216401743U CN202123111741.1U CN202123111741U CN216401743U CN 216401743 U CN216401743 U CN 216401743U CN 202123111741 U CN202123111741 U CN 202123111741U CN 216401743 U CN216401743 U CN 216401743U
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- pressing block
- spring
- connecting rod
- loading frame
- loading
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Abstract
The utility model belongs to the technical field of aircrafts, in particular to an aircraft loading bracket with a damping effect, which comprises a body and a buffer component arranged at the lower part of the body, wherein the buffer component comprises a loading frame, a transmission rod, a connecting rod, a support leg, a pressing block and a spring, the surface of the body is rotationally connected with one end of the loading frame, the other end of the loading frame is rotationally connected with one end of the transmission rod, the other end of the transmission rod is fixedly connected with the surface of the connecting rod, the device pushes the connecting rod to move by the falling of the loading frame, can indirectly drive the pressing block to slide in the support leg and compress the spring, enables the spring to buffer the loading frame loaded with an instrument, is beneficial to avoiding the instrument from being damaged, can effectively receive the thrust from the pressing block and push a vertebral body to extend out of the pressing block to be connected with the bottom surface by a stress piece arranged on a stabilizing component, the body is more stable when landing.
Description
Technical Field
The utility model belongs to the technical field of aircrafts, and particularly relates to an aircraft loading support with a damping effect.
Background
The aircraft refers to a novel electronic technology, can realize the purpose of unmanned aerial flight to still can play various different effects under the condition of carrying on various instruments, but current aircraft loading support when loading the instrument, the position of instrument does not have the function that can give it enough buffering, just so very probably cause not little impact force to the instrument when the aircraft falls, and influence the normal use of instrument, current aircraft is when landing simultaneously, direct contact between the bottom surface of support and the ground, do not have sufficient frictional force to carry out quick stable problem with the aircraft.
In order to solve the problem, the application provides an aircraft loading bracket with a shock absorption effect.
SUMMERY OF THE UTILITY MODEL
To solve the problems set forth in the background art described above. The utility model provides an aircraft loading bracket with a damping effect, which can indirectly drive a pressing block to slide in a supporting leg and compress a spring by pushing a connecting rod to move through the falling of a loading bracket, so that the spring buffers the loading bracket loaded with an instrument, the instrument is favorably prevented from being damaged, and a stress piece arranged on a stabilizing component can effectively receive the thrust from the pressing block and push a cone to extend out of the pressing block to be connected with the bottom surface, so that the aircraft body is more stable during landing.
In order to achieve the purpose, the utility model provides the following technical scheme: an aircraft loading bracket with a shock absorption effect comprises a machine body and a buffer component arranged at the lower part of the machine body;
the buffering assembly comprises a loading frame, a transmission rod, a connecting rod, support legs, a pressing block and a spring, the surface of the machine body is rotatably connected with one end of the loading frame, the other end of the loading frame is rotatably connected with one end of the transmission rod, the other end of the transmission rod is fixedly connected with the surface of the connecting rod, the two ends of the connecting rod are rotatably connected with the pressing block, the inner surface of each support leg is slidably connected with the surface of the pressing block, and the spring is arranged below the pressing block in the support legs.
Preferably, one side of the support leg, which is close to the loading frame, is provided with a rectangular through groove, and the surface of the support leg, which is far away from the loading frame, is provided with a circular through hole.
The instrument mounting frame for the unmanned aerial vehicle preferably comprises a stabilizing assembly arranged below a machine body, the stabilizing assembly comprises a stress piece and a cone, the surface of the stress piece is connected with the inner surface of the pressing block in a sliding mode, the surface, close to the machine body, of the pressing block is connected with the pressing block in an attaching mode, the surface of the other side of the stress piece is fixedly connected with one end of the spring, and the surface, close to the spring, of the stress piece is fixedly provided with the cone.
Preferably, as an instrument mounting bracket for an unmanned aerial vehicle according to the present invention, a cross-sectional diameter of the tapered body is smaller than a diameter of a hole formed in a bottom surface of the pressing block.
Compared with the prior art, the utility model has the beneficial effects that: promote the connecting rod through loading frame tenesmus and remove, drive briquetting that can be indirect slides and compression spring in the inside of stabilizer blade, makes the spring cushion the loading frame that has the instrument, is favorable to avoiding the instrument impaired, and the atress piece through setting up on the stabilizing component can effectually accept the thrust that comes from the briquetting and promote the centrum and stretch out the briquetting and be connected with the bottom surface, makes more stability of organism when landing.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model and not to limit the utility model. In the drawings:
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a cross-sectional structural view showing a state where a tapered body is extended out from a press block according to the present invention;
FIG. 3 is an exploded view of the buffering assembly and the stabilizing assembly of the present invention;
fig. 4 is a schematic cross-sectional view of the supporting leg of the present invention.
In the figure:
1. a body;
2. a buffer assembly; 21. a loading frame; 22. a transmission rod; 23. a connecting rod; 24. a support leg; 25. briquetting; 26. a spring;
3. a stabilizing assembly; 31. a stress sheet; 32. a vertebral body.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1:
an aircraft loading support with shock absorption effect comprises an airframe (1).
In this embodiment: when the existing aircraft loads the instrument, the position of the instrument does not have the function of giving enough buffering to the instrument, so that when the aircraft falls, the instrument is likely to be subjected to small impact force, the normal use of the instrument is influenced, meanwhile, when the existing aircraft lands, the bottom surface of the support is in direct contact with the ground, and the problem that the aircraft is rapidly stabilized due to insufficient friction force is solved, and in order to solve the problem, the buffering component 2 and the stabilizing component 3 are additionally arranged on the basis.
Further, the method comprises the following steps:
as shown in fig. 1-4:
with the above in mind: the buffer assembly 2 comprises a loading frame 21, a transmission rod 22, a connecting rod 23, a support leg 24, a pressing block 25 and a spring 26, wherein the surface of the machine body 1 is rotatably connected with one end of the loading frame 21, the other end of the loading frame 21 is rotatably connected with one end of the transmission rod 22, the other end of the transmission rod 22 is fixedly connected with the surface of the connecting rod 23, the two ends of the connecting rod 23 are rotatably connected with the pressing block 25, the inner surface of the support leg 24 is slidably connected with the surface of the pressing block 25, and the spring 26 is arranged below the pressing block 25 in the support leg 24.
In this embodiment: when the machine body 1 lands, due to inertia, one end of the loading frame 21 moves downwards, the end of the loading frame 21 connected with the machine body 1 rotates, the loading frame 21 pushes the connecting rod 23 to move through the transmission rod 22, a small-amplitude rotation is generated between the connecting rod 23 and the pressing block 25, the pressing block 25 is pushed to slide inside the supporting leg 24, then the pressing block 25 extrudes the spring 26 through the stress piece 31, the acting force generated by the falling of the loading frame 21 is buffered, and when the acting force buffering is completed, the spring 26 and the loading frame 21 reset.
It should be noted that: the connection point of the machine body 1 and the loading frame 21, the connection point of the loading frame 21 and the transmission rod 22 and the connection point of the connecting rod 23 and the pressing block 25 form a triangle, so that the connection point of the machine body 1 and the loading frame 21 and the side between the connecting rod 23 and the pressing block 25 can be effectively stretched when the loading frame 21 drops and deforms with the transmission rod 22, and the pressing block 25 can effectively extrude the spring 26.
Further, the method comprises the following steps:
in an alternative embodiment, a rectangular through slot is opened at one side of the support leg 24 close to the loading frame 21, and a circular through hole is opened at the surface of the support leg 24 far from the loading frame 21.
In this embodiment: the supporting of the machine body 1 by the supporting legs 24 can be performed while ensuring that the pressing block 25 can have enough movement space when sliding.
Further, the method comprises the following steps:
in an alternative embodiment, the stabilizing assembly 3 is further arranged below the machine body 1, the stabilizing assembly 3 comprises a force-bearing sheet 31 and a cone 32, the surface of the force-bearing sheet 31 is slidably connected with the inner surface of the pressing block 25, the surface of the pressing block 25 close to the machine body 1 is in fit connection with the pressing block 25, the other side surface of the force-bearing sheet 31 is fixedly connected with one end of the spring 26, and the surface of the force-bearing sheet 31 close to the spring 26 is fixedly provided with the cone 32.
In this embodiment: when the loading frame 21 is pressed down to drive the pressing block 25 to slide downwards in the supporting leg 24, the pressing block 25 pushes the connecting rod 23 to move, meanwhile, the connecting rod 23 drives the vertebral body 32 below the connecting rod 23 to move simultaneously, when the end point of the vertebral body 32 is in contact with the ground, the pressure between the vertebral body 32 and the ground is increased, the machine body 1 is more stable, effective stable work is achieved, and the situation that the machine body 1 is toppled due to instability when falling is effectively avoided.
It should be noted that: the stress sheet 31 is in the shape of a cylinder with the same diameter as the cross section of the pressing block 25, and can receive effective thrust through the close connection between the stress sheet 31 and the pressing block 25, and smoothly drive the vertebral body 32 to move and stably work on the machine body 1.
Further, the method comprises the following steps:
in an alternative embodiment, the cross-sectional diameter of the cone 32 is smaller than the diameter of the hole formed in the bottom surface of the compact 25.
In this embodiment: when the pressing block 25 is pressed down, the cone 32 can smoothly extend out of the hole formed in the bottom surface of the pressing block 25, the contact area with soft ground or the pressure and the friction force of the hard bottom surface are increased, and the stability of the aircraft is guaranteed.
It should be noted that: the cross-sectional diameter of the cone 32 is smaller than the minimum diameter of the spring 26, which is beneficial to ensure that the effective damping work of the spring 26 is smooth, and can also provide an effective moving space for the movement of the cone 32.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will understand that various changes, modifications and substitutions can be made without departing from the spirit and scope of the utility model as defined by the appended claims. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. An aircraft loading support with shock absorption effect, comprising a body (1), characterized in that: the device also comprises a buffer component (2) arranged below the machine body (1);
buffer unit (2) including load frame (21), transfer line (22), connecting rod (23), stabilizer blade (24), briquetting (25) and spring (26), the surface of organism (1) with the one end swivelling joint of load frame (21), the other end of load frame (21) with the one end swivelling joint of transfer line (22), the other end of transfer line (22) with the fixed surface of connecting rod (23) is connected, the both ends of connecting rod (23) with briquetting (25) swivelling joint, the internal surface of stabilizer blade (24) with the surface sliding connection of briquetting (25), the below of briquetting (25) is provided with in the inside of stabilizer blade (24) spring (26).
2. An aircraft loading cradle with shock absorbing effect according to claim 1, characterized in that: one side, close to the loading frame (21), of the support leg (24) is provided with a rectangular through groove, and the surface, far away from the loading frame (21), of the support leg (24) is provided with a circular through hole.
3. An aircraft loading cradle with shock absorbing effect according to claim 1, characterized in that: the stabilizing component (3) is arranged below the machine body (1), the stabilizing component (3) comprises a stress sheet (31) and a cone body (32), the surface of the stress sheet (31) is in sliding connection with the inner surface of the pressing block (25), the pressing block (25) is close to the surface of the machine body (1) and is in fit connection with the pressing block (25), the other side surface of the stress sheet (31) is fixedly connected with one end of the spring (26), and meanwhile the stress sheet (31) is close to the surface of the spring (26) and is fixedly provided with the cone body (32).
4. An aircraft loading cradle with shock absorbing effect according to claim 3, characterized in that: the diameter of the section of the cone body (32) is smaller than that of a hole formed in the bottom surface of the pressing block (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123111741.1U CN216401743U (en) | 2021-12-13 | 2021-12-13 | Aircraft loading support with shock attenuation effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123111741.1U CN216401743U (en) | 2021-12-13 | 2021-12-13 | Aircraft loading support with shock attenuation effect |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216401743U true CN216401743U (en) | 2022-04-29 |
Family
ID=81283690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123111741.1U Active CN216401743U (en) | 2021-12-13 | 2021-12-13 | Aircraft loading support with shock attenuation effect |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216401743U (en) |
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2021
- 2021-12-13 CN CN202123111741.1U patent/CN216401743U/en active Active
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