CN217893217U - Integrated undercarriage for unmanned aerial vehicle - Google Patents
Integrated undercarriage for unmanned aerial vehicle Download PDFInfo
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- CN217893217U CN217893217U CN202222503715.1U CN202222503715U CN217893217U CN 217893217 U CN217893217 U CN 217893217U CN 202222503715 U CN202222503715 U CN 202222503715U CN 217893217 U CN217893217 U CN 217893217U
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- aerial vehicle
- unmanned aerial
- undercarriage
- connecting frame
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Abstract
The utility model discloses an integrated undercarriage for unmanned aerial vehicle, including the unmanned aerial vehicle body, the unmanned aerial vehicle body evenly is provided with a plurality of horn all around, unmanned aerial vehicle body bottom is connected with the undercarriage through the connecting plate; the undercarriage includes the link, the link four corners all is provided with the side bolster, side bolster one end is passed through buffer spring cooperation locating piece and is connected in the link surface, and the other end is connected in the link surface through the pivot, link center department still is provided with middle bolster. The lateral buffering parts are matched with the buffering springs, the positioning blocks and the rotating shaft, so that the stability of four corners can be adjusted simultaneously or a certain angle can be adjusted independently according to the field condition when the unmanned aerial vehicle takes off and lands, and rubber layers are arranged on the surfaces of the lateral buffering parts and the middle buffering parts; when descending, can also effectively cooperate cushion column and shock pad to carry out the shock attenuation work. The device has the advantages of high overall structural strength, high stability and difficult forward tilting and side turning.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is an integral type undercarriage for unmanned aerial vehicle.
Background
The fixed wing VTOL unmanned aerial vehicle takes off and land, and it is big to take off weight, and the performance that bears and keep the aircraft stable to the undercarriage when descending requires highly. Especially under the abominable condition of environment of taking off and land, the possibility that unmanned aerial vehicle takes place to turn on one's side greatly increased. The mode of two poles on both sides is adopted mostly to rotor unmanned aerial vehicle undercarriage, and this kind of common structure can satisfy small-size many rotor unmanned aerial vehicle's take off and land performance requirement basically, nevertheless has single structure, supports intensity poor, poor stability's problem, and the easy emergence is leaned forward and is turned on one's side.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an integral type undercarriage for unmanned aerial vehicle to it has single structure to provide current unmanned aerial vehicle undercarriage in solving above-mentioned background art, supports intensity difference, and poor stability's problem takes place easily to lean forward and the problem of turning on one's side.
In order to achieve the above object, the utility model provides a following technical scheme:
an integrated undercarriage for an unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein a plurality of arms are uniformly arranged on the periphery of the unmanned aerial vehicle body, and the bottom of the unmanned aerial vehicle body is connected with the undercarriage through a connecting plate;
the undercarriage includes the link, the link four corners all is provided with the side bolster, side bolster one end is passed through buffer spring cooperation locating piece and is connected in the link surface, and the other end is connected in the link surface through the pivot, link center department still is provided with middle bolster.
Further preferably, the side bumper surface is provided with a slider, and the slider is in sliding connection with the bottom of the connecting plate through the sliding groove in a matched manner.
Further preferably, the connecting frame is integrally of an I-shaped structure, the side buffer pieces are respectively provided with four corners of the connecting frame, and the middle buffer piece is connected to the center of the connecting frame through a fastening nut.
Further preferably, a plurality of buffer columns are further uniformly distributed at the bottom of the connecting frame of the landing gear, and shock absorption pads are arranged at the tail ends of the buffer columns.
Further preferably, rubber layers are arranged on the surfaces of the side buffers and the surfaces of the middle buffers.
Further preferably, the joints of the interior of the buffer spring, the positioning block and the side buffer piece are provided with guide posts.
Compared with the prior art, the beneficial effects of the utility model are that:
the connecting frame is integrally in an I-shaped structure, the side buffer pieces are respectively provided with four corners of the connecting frame, and the middle buffer piece is connected to the center of the connecting frame through a fastening nut; one end of the side buffer piece is connected to the surface of the connecting frame through the buffer spring matched with the positioning block, and the other end of the side buffer piece is connected to the surface of the connecting frame through the rotating shaft. The lateral buffering parts are matched with the buffering springs, the positioning blocks and the rotating shaft, so that the stability of four corners can be adjusted simultaneously or a certain angle can be adjusted independently according to the field condition when the unmanned aerial vehicle takes off and lands, and rubber layers are arranged on the surfaces of the lateral buffering parts and the middle buffering parts; when descending, can also effectively cooperate cushion column and shock pad to carry out the shock attenuation work.
In conclusion, the device has the advantages of high overall structural strength, high supporting strength, high stability and low probability of forward tilting and side turning.
Drawings
Fig. 1 is a schematic front view of the overall structure of the present invention;
FIG. 2 is a side view of the overall structure of the present invention;
fig. 3 is a top view of the landing gear structure of the present invention;
fig. 4 is a structural bottom view of the landing gear of the present invention;
in the figure: the unmanned aerial vehicle comprises an unmanned aerial vehicle body, 2 connecting plates, 3 arms, 4 side buffer parts, 5 sliding grooves, 6 sliding blocks, 7 buffer springs, 8 rotating shafts, 9 positioning blocks, 10 middle buffer parts, 11 connecting frames, 12 buffer columns and 13 shock pads.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the 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 efforts all belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution:
an integrated undercarriage for an unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, a plurality of arms 3 are uniformly arranged on the periphery of the unmanned aerial vehicle body 1, and the bottom of the unmanned aerial vehicle body 1 is connected with the undercarriage through a connecting plate 2;
the undercarriage includes link 11, and 11 four corners of link all are provided with side bolster 4, and 4 one end of side bolster are passed through buffer spring 7 cooperation locating piece 9 and are connected in link 11 surfaces, and the other end is connected in link 11 surfaces through pivot 8, and 11 center departments of link still are provided with middle bolster 10.
The utility model discloses in, side bolster 4 surfaces are provided with slider 6, and slider 6 cooperates sliding connection in connecting plate 2 bottoms through spout 5. Through sliding connection's side bolster 4 and connecting plate 2, can adjust the stability of supporting under the effect of gravity according to real-time condition is automatic when using.
In the utility model, the connecting frame 11 is integrally in an I-shaped structure, the side buffer pieces 4 are respectively provided with four corners of the connecting frame 11, and the middle buffer piece 10 is connected to the center of the connecting frame 11 through the fastening nut; the side buffers 4 and the middle buffer 10 are provided with rubber layers on the surfaces. A plurality of buffer columns 12 are uniformly distributed at the bottom of the connecting frame 11 of the landing gear, and shock pads 13 are arranged at the tail ends of the buffer columns 12; when the landing is performed, the damping operation can be performed by effectively matching the damping columns 12 and the damping cushions 13.
The utility model discloses in, buffer spring 7 is inside all to be provided with the guide post with locating piece 9 and side bolster 4 junction. The guide post can guarantee that the buffer spring 7 can buffer and does not deform, such as fracture.
The working principle is as follows:
at first with the undercarriage through the spout 5 of 2 bottoms of slider 6 cooperation connecting plate on side bolster 4 surface, carry out sliding connection, in unmanned aerial vehicle take off and land, the shock attenuation and the good support performance to unmanned aerial vehicle body 1 can be realized to the middle bolster 10 and the cushion 12 of the 11 cooperation four corners settings of link of I shape and center department, 7 cooperation locating pieces 9 of buffer spring are passed through to side bolster 4 one end and are connected in link 11 surfaces, the other end is connected in link 11 surfaces through pivot 8, can cushion work in the cooperation of slider 6 and spout 5. The stability of the entire connecting frame 11 is ensured. Rubber layers are arranged on the surfaces of the side buffer piece 4 and the middle buffer piece 10; when the landing is performed, the damping operation can be performed by effectively matching the damping columns 12 and the damping cushions 13. And guide posts are arranged at the joints of the inside of the buffer spring 7, the positioning block 9 and the side buffer piece 4. The guide post can guarantee that the buffer spring 7 can buffer and does not deform, such as fracture.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.
The above, only be the embodiment of the preferred of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, which are designed to be replaced or changed equally, all should be covered within the protection scope of the present invention.
Claims (6)
1. The utility model provides an integral type undercarriage for unmanned aerial vehicle, includes unmanned aerial vehicle body (1), unmanned aerial vehicle body (1) evenly is provided with a plurality of horn (3) all around, its characterized in that: the bottom of the unmanned aerial vehicle body (1) is connected with an undercarriage through a connecting plate (2);
the undercarriage comprises a connecting frame (11), side buffer pieces (4) are arranged at four corners of the connecting frame (11), one ends of the side buffer pieces (4) are connected to the surface of the connecting frame (11) through buffer springs (7) and matched with positioning blocks (9), the other ends of the side buffer pieces are connected to the surface of the connecting frame (11) through rotating shafts (8), and middle buffer pieces (10) are further arranged at the center of the connecting frame (11).
2. An integrated undercarriage for an unmanned aerial vehicle according to claim 1 wherein: side bolster (4) surface is provided with slider (6), just slider (6) through spout (5) cooperation sliding connection in connecting plate (2) bottom.
3. An integrated undercarriage for an unmanned aerial vehicle according to claim 1 wherein: the connecting frame (11) is integrally of an I-shaped structure, the side buffer pieces (4) are respectively provided with four corners of the connecting frame (11), and the middle buffer piece (10) is connected to the center of the connecting frame (11) through fastening nuts.
4. An integrated undercarriage for an unmanned aerial vehicle according to claim 1 wherein: a plurality of buffer columns (12) are further uniformly distributed at the bottom of the connecting frame (11) of the landing gear, and shock pads (13) are arranged at the tail ends of the buffer columns (12).
5. An integrated undercarriage for an unmanned aerial vehicle according to claim 1 wherein: the surfaces of the side buffer piece (4) and the middle buffer piece (10) are both provided with rubber layers.
6. An integrated undercarriage for an unmanned aerial vehicle according to claim 1 wherein: and guide posts are arranged at the joints of the interior of the buffer spring (7) and the positioning block (9) and the side buffer piece (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222503715.1U CN217893217U (en) | 2022-09-21 | 2022-09-21 | Integrated undercarriage for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222503715.1U CN217893217U (en) | 2022-09-21 | 2022-09-21 | Integrated undercarriage for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217893217U true CN217893217U (en) | 2022-11-25 |
Family
ID=84109190
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222503715.1U Active CN217893217U (en) | 2022-09-21 | 2022-09-21 | Integrated undercarriage for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217893217U (en) |
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2022
- 2022-09-21 CN CN202222503715.1U patent/CN217893217U/en active Active
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