CN216070497U - Unmanned aerial vehicle vibration damper - Google Patents
Unmanned aerial vehicle vibration damper Download PDFInfo
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- CN216070497U CN216070497U CN202122200956.4U CN202122200956U CN216070497U CN 216070497 U CN216070497 U CN 216070497U CN 202122200956 U CN202122200956 U CN 202122200956U CN 216070497 U CN216070497 U CN 216070497U
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- 238000013016 damping Methods 0.000 claims abstract description 36
- 230000003139 buffering effect Effects 0.000 claims abstract description 17
- 230000000712 assembly Effects 0.000 claims abstract description 7
- 238000000429 assembly Methods 0.000 claims abstract description 7
- 230000007704 transition Effects 0.000 claims description 5
- 230000001737 promoting effect Effects 0.000 abstract 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
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Abstract
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle vibration damper, which comprises an undercarriage, wherein the undercarriage comprises a fixed seat and two groups of supporting columns, the fixed seat is used for being connected with an unmanned aerial vehicle body, the two groups of supporting columns are symmetrically arranged on two sides of the fixed seat, the lower end of each group of supporting columns is connected with a horizontal supporting beam extending along the length direction of the unmanned aerial vehicle body, the two horizontal supporting beams are parallel to each other and have consistent height, and the technical key points are as follows: the front portion and the rear portion of the lower surface of the horizontal supporting beam are symmetrically provided with buffering assemblies, the middle portion of the lower surface of the horizontal supporting beam is provided with a horizontal supporting tube, the lower surface of the horizontal supporting tube is provided with a vibration damping pad, the front end and the rear end of the horizontal supporting tube are respectively provided with a plugging plate, a buffering spring is arranged between each buffering assembly and the plugging plate on the corresponding side, and the bottom surface of each buffering assembly is lower than the bottom surface of the vibration damping pad. The problem that current damping device damping capacity is poor has been solved to this device, and small, light in weight are showing and are promoting unmanned aerial vehicle damping capacity.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle vibration damper.
Background
At present, unmanned aerial vehicles in various industries in China are more and more widely applied, and can be used for aerial photography, reconnaissance, resource exploration, search and rescue, biological control, chemical control and the like. And according to its function difference, need carry on devices such as photoelectricity platform, dispenser on the unmanned aerial vehicle. The built-in equipment of unmanned aerial vehicle and the precision of carrying on equipment are stronger, therefore, unmanned aerial vehicle need keep stronger stationarity when falling to the ground, otherwise if the impact force with ground is great, will lead to equipment impaired.
Therefore, the unmanned aerial vehicle is usually equipped with vibration damper to reduce the vibration influence that ground impact force brought, and current vibration damper has following problem in the use: receive the restriction of unmanned aerial vehicle small, light in weight's design requirement, current damping device mainly comprises undercarriage, the damping pad of locating the undercarriage bottom, and the damping ability of damping pad is limited, falls to the ground earlier when the unmanned aerial vehicle front end falls to the ground earlier or the rear end falls to the ground earlier, still produces very big impact force to the organism, is unfavorable for the organism steadily to fall to the ground.
Disclosure of Invention
The utility model aims to provide the vibration damping device of the unmanned aerial vehicle, which is reasonable in structure and reliable in use, solves the problem of poor vibration damping capacity of the existing vibration damping device, is small in size and light in weight, and remarkably improves the vibration damping capacity of the unmanned aerial vehicle.
The technical scheme of the utility model is as follows:
the utility model provides an unmanned aerial vehicle vibration damper, includes the undercarriage, two sets of pillars of fixing base both sides are located by fixing base, the symmetry that is used for being connected with the unmanned aerial vehicle fuselage to the undercarriage, and the lower extreme of every group pillar is connected with the horizontal support beam who extends along fuselage length direction, and two horizontal support beams are parallel to each other and highly uniform, and its technical essential is: the front part and the rear part of the lower surface of the horizontal supporting beam are symmetrically provided with buffering assemblies, the middle part of the lower surface of the horizontal supporting beam is provided with a horizontal supporting tube, the lower surface of the horizontal supporting tube is provided with a damping pad, the front end and the rear end of the horizontal supporting tube are respectively provided with a plugging plate, a buffering spring is arranged between the buffering assemblies and the plugging plate on the corresponding side, and the bottom surface of the buffering assemblies is lower than that of the damping pad.
Foretell unmanned aerial vehicle vibration damper, the buffering subassembly includes one end perk and the buffer board of the fixed vertical push pedal of other end, be fixed in a plurality of lower engaging lugs of buffer board upper surface, be fixed in horizontal support beam lower surface and with the last engaging lug of engaging lug one-to-one down, connect the connecting rod between last engaging lug and the lower engaging lug that corresponds, the axial lead in the articulated shaft hole of each last engaging lug, each lower engaging lug is parallel to each other and perpendicular with horizontal support beam, the bottom surface of buffer board is less than the bottom surface of damping pad, is located the perk end of the anterior buffer board of horizontal support beam towards the fuselage front portion, is located the perk end of the buffer board at horizontal support beam rear portion towards the fuselage rear portion, buffer spring is located between the shutoff board of vertical push pedal and horizontal support pipe.
Foretell unmanned aerial vehicle vibration damper, the quantity of engaging lug and last engaging lug is three respectively down, is triangular distribution respectively.
Foretell unmanned aerial vehicle vibration damper, the pillar comprises the horizontal segment of being connected with the fixing base, the vertical section of being connected with horizontal support beam, the changeover portion of connecting between horizontal segment and vertical section, the changeover portion middle part is equipped with the buffering inflection point.
Foretell unmanned aerial vehicle vibration damper, the quantity of buffer spring between vertical push pedal and the shutoff board that corresponds the side is two and buffer spring's axial lead is parallel to each other.
The utility model has the beneficial effects that:
1. through being equipped with the buffering subassembly respectively at horizontal support beam's anterior and rear portion, when the unmanned aerial vehicle front end falls to the ground earlier or the rear end falls to the ground earlier, the buffering subassembly of anterior or rear portion plays the cushioning effect earlier, makes the damping pad of horizontal support pipe bottom surface land again, the secondary damping to very big reduction the influence of ground impact force to the organism, be favorable to the organism steadily to fall to the ground.
2. The horizontal supporting beam of the original undercarriage is as long as the horizontal supporting tube, and the vibration damping pad on the bottom surface of the horizontal supporting tube plays a vibration damping role.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a left side view of FIG. 1;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a schematic diagram of the front end of the present invention landing first and then;
fig. 5 is a schematic view of the present invention after both ends are grounded following the state of fig. 4.
In the figure: 1. the unmanned aerial vehicle comprises an unmanned aerial vehicle body, 2. pillars, 201. horizontal sections, 202. buffer inflection points, 203. transition sections, 204. vertical sections, 3. horizontal supporting beams, 4. plugging plates, 5. buffer plates, 6. fixed seats, 7. upper connecting lugs, 8. connecting rods, 9. lower connecting lugs, 10. buffer springs, 11. vertical push plates, 12. horizontal supporting tubes and 13. damping pads.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and reference numerals.
As shown in fig. 1-5, this unmanned aerial vehicle vibration damper, including the undercarriage, the undercarriage is located two sets of pillars 2 of 6 both sides of fixing base by the fixing base 6, the symmetry that are used for being connected with unmanned aerial vehicle fuselage 1, and the lower extreme of every group pillar 2 is connected with the horizontal support beam 3 that extends along fuselage length direction, and two horizontal support beam 3 are parallel to each other and highly uniform.
Wherein, the front part and the rear part of the lower surface of the horizontal supporting beam 3 are symmetrically provided with a buffer component, and the middle part of the lower surface of the horizontal supporting beam 3 is provided with a horizontal supporting tube 12. The lower surface of the horizontal supporting pipe 12 is provided with a damping pad 13, and the front end and the rear end of the horizontal supporting pipe 12 are respectively provided with a plugging plate 4. And a buffer spring 10 is arranged between the buffer assembly and the plugging plate 4 on the corresponding side, and the bottom surface of the buffer assembly is lower than that of the damping pad 13.
In this embodiment, the buffer assembly includes one end perk and buffer board 5 of the fixed vertical push pedal 11 of other end, be fixed in three engaging lug 9 down of buffer board 5 upper surface, be fixed in horizontal support beam 3 lower surface and with the last engaging lug 7 of lower engaging lug 9 one-to-one, connect in last engaging lug 7 and the connecting rod 8 between the lower engaging lug 9 that corresponds. The lower connecting lug 9 and the upper connecting lug 7 are respectively distributed in a triangular shape. The axes of the hinge shaft holes of the upper connecting lugs 7 and the lower connecting lugs 9 are parallel to each other and are perpendicular to the horizontal support beam 3. The bottom surface of the cushion plate 5 is lower than the bottom surface of the vibration damping pad 13. The tilting end of the buffer plate 5 positioned at the front part of the horizontal support beam 3 faces the front part of the body, and the tilting end of the buffer plate 5 positioned at the rear part of the horizontal support beam 3 faces the rear part of the body. The buffer spring 10 is positioned between the vertical push plate 11 and the plugging plate 4 of the horizontal support pipe 12. The number of the buffer springs 10 between the vertical push plate 11 and the corresponding side blocking plate 4 is two, and the axial leads of the buffer springs 10 are parallel to each other.
The supporting column 2 is composed of a horizontal section 201 connected with the fixed seat 6, a vertical section 204 connected with the horizontal supporting beam 3, and a transition section 203 connected between the horizontal section 201 and the vertical section 204, wherein a buffer inflection point 202 is arranged in the middle of the transition section 203.
When the unmanned aerial vehicle flies in the sky, the bottom surface of the buffer plate 5 is lower than the bottom surface of the damping pad 13 under the action of the buffer spring 10 of the buffer component, see fig. 2. When the front or rear buffer component of the fuselage is firstly contacted with the ground, the buffer spring 10 is compressed, in the process, the impact force of a part of the ground is buffered, and then the damping pad 13 at the bottom surface of the horizontal supporting tube 12 is contacted with the ground to carry out secondary damping, which is shown in fig. 4; finally, the rear or front damping assembly of the fuselage is in contact with the ground, and the damping spring 10 on this side is stretched, see fig. 5.
The embodiments of the present invention have been described in detail, but the description is only for the preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention. All equivalent changes and modifications made within the scope of the utility model are also within the scope of the present patent.
Claims (5)
1. The utility model provides an unmanned aerial vehicle vibration damper, includes the undercarriage, two sets of pillars of fixing base both sides are located by fixing base, the symmetry that is used for being connected with the unmanned aerial vehicle fuselage to the undercarriage, and the lower extreme of every group pillar is connected with the horizontal support beam who extends along fuselage length direction, and two horizontal support beams are parallel to each other and highly uniform, its characterized in that: the front part and the rear part of the lower surface of the horizontal supporting beam are symmetrically provided with buffering assemblies, the middle part of the lower surface of the horizontal supporting beam is provided with a horizontal supporting tube, the lower surface of the horizontal supporting tube is provided with a damping pad, the front end and the rear end of the horizontal supporting tube are respectively provided with a plugging plate, a buffering spring is arranged between the buffering assemblies and the plugging plate on the corresponding side, and the bottom surface of the buffering assemblies is lower than that of the damping pad.
2. The vibration damping device for unmanned aerial vehicles according to claim 1, wherein: the buffer assembly comprises a buffer plate with one end tilted and the other end fixed with a vertical push plate, a plurality of lower connecting lugs fixed on the upper surface of the buffer plate, an upper connecting lug fixed on the lower surface of a horizontal support beam and corresponding to the lower connecting lug one by one, and a connecting rod connected between the upper connecting lug and the corresponding lower connecting lug, wherein the axial leads of the hinged shaft holes of the upper connecting lugs and the lower connecting lugs are parallel to each other and perpendicular to the horizontal support beam, the bottom surface of the buffer plate is lower than the bottom surface of a damping pad, the tilted end of the buffer plate positioned at the front part of the horizontal support beam faces the front part of the machine body, the tilted end of the buffer plate positioned at the rear part of the horizontal support beam faces the rear part of the machine body, and a buffer spring is positioned between the vertical push plate and the plugging plate of the horizontal support tube.
3. The vibration damping device for unmanned aerial vehicles according to claim 1, wherein: the support column is composed of a horizontal section connected with the fixed seat, a vertical section connected with the horizontal supporting beam and a transition section connected between the horizontal section and the vertical section, and a buffering inflection point is arranged in the middle of the transition section.
4. The vibration damping device for unmanned aerial vehicles according to claim 2, wherein: the number of the lower connecting lugs and the number of the upper connecting lugs are three respectively and are distributed in a triangular shape respectively.
5. The vibration damping device for unmanned aerial vehicles according to claim 2, wherein: the number of the buffer springs between the vertical push plate and the plugging plate on the corresponding side is two, and the axial leads of the buffer springs are parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122200956.4U CN216070497U (en) | 2021-09-13 | 2021-09-13 | Unmanned aerial vehicle vibration damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122200956.4U CN216070497U (en) | 2021-09-13 | 2021-09-13 | Unmanned aerial vehicle vibration damper |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216070497U true CN216070497U (en) | 2022-03-18 |
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ID=80675848
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122200956.4U Active CN216070497U (en) | 2021-09-13 | 2021-09-13 | Unmanned aerial vehicle vibration damper |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216070497U (en) |
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2021
- 2021-09-13 CN CN202122200956.4U patent/CN216070497U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: SHENYANG SAISI ENVIRONMENTAL ENGINEERING DESIGN & RESEARCH CENTER CO.,LTD. Assignor: Panjin Zhongkai Technology Co.,Ltd. Contract record no.: X2023210000066 Denomination of utility model: Drone damping device Granted publication date: 20220318 License type: Common License Record date: 20230721 |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231208 Address after: Room 409, Intelligent Unmanned System Industrial Park, Kaiyuan Avenue, High tech Industrial Park, Yulin City, Shaanxi Province, 719000 Patentee after: Shaanxi Zhuofan Xinchuang Intelligent Technology Co.,Ltd. Address before: 124000 Room 301, floor 3, science and technology incubator, high tech Industrial Development Zone, No. 30, Xingye street, Xinglongtai District, Panjin City, Liaoning Province Patentee before: Panjin Zhongkai Technology Co.,Ltd. |