CN211685654U - Unmanned aerial vehicle descending damping device - Google Patents
Unmanned aerial vehicle descending damping device Download PDFInfo
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- CN211685654U CN211685654U CN201922295374.1U CN201922295374U CN211685654U CN 211685654 U CN211685654 U CN 211685654U CN 201922295374 U CN201922295374 U CN 201922295374U CN 211685654 U CN211685654 U CN 211685654U
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- aerial vehicle
- unmanned aerial
- sleeve
- spring
- damping device
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- 238000013016 damping Methods 0.000 title claims abstract description 21
- 230000035939 shock Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle descending damping device relates to the damping device field, does not have better shock attenuation equipment to current unmanned aerial vehicle descending, is vulnerable to the problem of the accurate photographic equipment that the machine carried, now proposes following scheme, and it includes unmanned aerial vehicle body, machine equipment's the first sleeve of bottom fixedly connected with, the interior diapire fixedly connected with second sleeve of unmanned aerial vehicle body, be provided with first spring between first sleeve and the second sleeve, the spacing groove has all been seted up to the left and right both sides of unmanned aerial vehicle body, sliding connection has T type gag lever post in the spacing groove, be connected with the second spring between the upper end of T type gag lever post and the last inner wall of spacing groove, slide, every have all been seted up to preceding, the back both sides of unmanned aerial vehicle body bottom the equal fixedly connected with slide bar of the left and right both sides inner wall of slide. The device has the characteristics of good damping effect, and capability of better protecting airborne equipment, so that the service life of the device is prolonged.
Description
Technical Field
The utility model relates to a damping device field especially relates to an unmanned aerial vehicle descending damping device.
Background
Along with the improvement of unmanned aerial vehicle load capacity, unmanned aerial vehicle's cost of manufacture also increases thereupon, and on the one hand, the unmanned aerial vehicle that has damping device that has now is bulky, very inconvenient when the transportation, and on the other hand, unmanned aerial vehicle's cost of manufacture also increases thereupon high.
How to improve the shock-absorbing capacity when unmanned aerial vehicle descends on the basis of reducing unmanned aerial vehicle volume is the present urgent solution that awaits the solution. And present small-size unmanned aerial vehicle generally carries some important accurate shooting equipment, does not have the life that good damping device will be great reduction equipment on it when taking off and land. Therefore, an unmanned aerial vehicle descending damping device is provided.
SUMMERY OF THE UTILITY MODEL
The utility model provides a pair of unmanned aerial vehicle descending damping device has solved current unmanned aerial vehicle descending and has not better shock-absorbing equipment, the problem of the accurate photography equipment of vulnerable machine year.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an unmanned aerial vehicle landing damping device comprises an unmanned aerial vehicle body and airborne equipment, wherein the bottom of the airborne equipment is fixedly connected with a first sleeve, a second sleeve is fixedly connected with the inner bottom wall of the unmanned aerial vehicle body, a first spring is arranged between the first sleeve and the second sleeve, the left side and the right side of the unmanned aerial vehicle body are both provided with limiting grooves, T-shaped limiting rods are connected in the limiting grooves in a sliding manner, a second spring is connected between the upper end of the T-shaped limiting rod and the upper inner wall of the limiting groove, slide ways are respectively arranged on the front side and the rear side of the bottom of the unmanned aerial vehicle body, slide rods are fixedly connected with the inner walls of the left side and the right side of each slide way, the left end and the right end of the sliding rod are movably sleeved with sliding blocks, the two sliding blocks on the surface of the sliding rod are connected with a third spring, and the two sliding blocks on the same side of the left end and the right end are movably connected with a supporting plate.
Preferably, the first sleeve is sleeved in the second sleeve in a sliding manner, one end of the first spring is fixedly connected to the inner wall of the first sleeve, and the other end of the first spring is fixedly connected to the inner wall of the second sleeve.
Preferably, the T-shaped end of the T-shaped limiting rod is connected in the limiting groove in a sliding mode, and a second spring is connected between the upper end face of the T-shaped end and the upper inner wall of the limiting groove.
Preferably, the lower end of the T-shaped limiting rod penetrates through the limiting groove, extends below the limiting groove, and is movably connected to the upper surface of the supporting plate through a hinge.
Preferably, two ends of the third spring are respectively and fixedly connected to one side face, close to each other, of the sliding blocks on the left side and the right side, and the third spring is sleeved on the surface of the sliding rod.
Preferably, the front end and the rear end of the supporting plate are respectively and movably connected to the sliding blocks on the respective sides through hinges.
Compared with the prior art, the beneficial effects of the utility model are that:
through a human body, airborne equipment, a first sleeve, a second sleeve, a first spring, a limiting groove, a T-shaped limiting rod, a second spring, a slide way, a slide rod, a slide block, a third spring and a support plate, the device can pass through a movable connector on the upper surfaces of the T-shaped limiting rod and the support plate, the T-shaped limiting plate is connected in the limiting groove in a sliding manner, and the second spring is connected between the T-shaped limiting plate and the inner wall of the limiting groove, so that in the descending process, the support plate can rotate and push the T-shaped limiting rod to slide in the limiting groove, then, as the front end and the rear end of the support plate are movably connected on the slide blocks on the front side and the rear side through hinges, and the slide blocks are sleeved on the surface of the slide rod in a sliding manner, when the support plate rotates, the slide blocks on the left side and the right side can be compressed, the third spring can be, and a first spring is connected between the two springs, so that the airborne equipment can be well damped.
Make this device have the shock attenuation effectual, and the protection airborne equipment that can be better for the characteristics of the life increase of device.
Drawings
Fig. 1 is the utility model discloses a cross-sectional view of unmanned aerial vehicle descending damping device's structure.
Fig. 2 is the utility model discloses an unmanned aerial vehicle descending damping device overlook the cross-sectional view of structure.
Reference numbers in the figures: the device comprises a human body 1, an airborne device 2, a first sleeve 3, a second sleeve 4, a first spring 5, a limiting groove 6, a 7T-shaped limiting rod, a second spring 8, a slideway 9, a sliding rod 10, a sliding block 11, a third spring 12 and a supporting plate 13.
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.
Referring to fig. 1-2, an unmanned aerial vehicle landing damping device comprises an unmanned aerial vehicle body 1 and an airborne device 2, wherein the bottom of the airborne device 2 is fixedly connected with a first sleeve 3, the inner bottom wall of the unmanned aerial vehicle body 1 is fixedly connected with a second sleeve 4, a first spring 5 is arranged between the first sleeve 3 and the second sleeve 4, the left side and the right side of the unmanned aerial vehicle body 1 are respectively provided with a limiting groove 6, the limiting grooves 6 are internally and slidably connected with a T-shaped limiting rod 7, a second spring 8 is connected between the upper end of the T-shaped limiting rod 7 and the upper inner wall of the limiting groove 6, the front side and the rear side of the bottom of the unmanned aerial vehicle body 1 are respectively provided with a slide 9, the left side of, the inner walls of the right two sides are fixedly connected with a slide bar 10, the left and right ends of the slide bar 10 are movably sleeved with slide blocks 11, a third spring 12 is connected between the two slide blocks 11 on the surface of the same slide bar 10, and a support plate 13 is movably connected between the two slide blocks 11 on the same side of the left and right sides.
In this embodiment, first sleeve 3 slides and cup joints in second sleeve 4, and the one end fixed connection of first spring 5 is at the inner wall of first sleeve 3, and other end fixed connection is at the inner wall of second sleeve 4, and airborne equipment is current airborne photography equipment.
In this embodiment, the T-shaped end of the T-shaped limiting rod 7 is slidably connected in the limiting groove 6, and a second spring 8 is connected between the upper end surface of the T-shaped end and the upper inner wall of the limiting groove 6.
In this embodiment, the lower end of the T-shaped limiting rod 7 passes through the limiting groove 6 and extends below the limiting groove 6, and is movably connected to the upper surface of the supporting plate 13 through a hinge.
In this embodiment, two ends of the third spring 12 are respectively fixedly connected to a side surface of the left and right side sliders 11 close to each other, and the third spring 12 is sleeved on the surface of the slide bar 10.
In this embodiment, the front and rear ends of the supporting plate 13 are respectively movably connected to the respective sliders 11 through hinges.
The working principle is as follows: when in use, the T-shaped limiting rod 7 and the movable connector on the upper surface of the supporting plate 13 can be connected, and the T-shaped limit plate 7 is connected in the limit groove 6 in a sliding way, and a second spring 5 is connected between the T-shaped limit plate and the inner wall of the limit groove 6, so that in the descending process, then, as the T-shaped limiting rod 7 is connected in the limiting groove 6 in an up-and-down sliding manner, the supporting plate can rotate, and pushes the T-shaped limiting rod 7 to slide in the limiting groove 6, the front end and the rear end of the supporting plate 13 are movably connected on the sliding blocks 11 at the front side and the rear side through hinges, and the sliding blocks 11 are sleeved on the surface of the sliding rod 10 in a sliding way, so that when the supporting plate 13 rotates, the sliding blocks 11 on the left side and the right side are compressed, and then compress third spring 12, reach vertical and horizontal absorbing effect, and first sleeve 3 slides and cup joints in second sleeve 4, and is connected with first spring 5 between for airborne equipment 2 can carry out better shock attenuation.
The above, only be the concrete implementation of the preferred embodiment 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, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (6)
1. An unmanned aerial vehicle descending damping device comprises an unmanned aerial vehicle body (1) and an airborne device (2), and is characterized in that the bottom of the airborne device (2) is fixedly connected with a first sleeve (3), the inner bottom wall of the unmanned aerial vehicle body (1) is fixedly connected with a second sleeve (4), a first spring (5) is arranged between the first sleeve (3) and the second sleeve (4), limiting grooves (6) are respectively formed in the left side and the right side of the unmanned aerial vehicle body (1), T-shaped limiting rods (7) are slidably connected in the limiting grooves (6), second springs (8) are connected between the upper ends of the T-shaped limiting rods (7) and the upper inner walls of the limiting grooves (6), slide ways (9) are respectively formed in the front side and the rear side of the bottom of the unmanned aerial vehicle body (1), and slide bars (10) are respectively fixedly connected to the inner walls of the left side and the right side of each slide way (9), the left end and the right end of the sliding rod (10) are movably sleeved with sliding blocks (11), a third spring (12) is connected between the two sliding blocks (11) on the surface of the same sliding rod (10), and a supporting plate (13) is movably connected between the two sliding blocks (11) on the same side.
2. An unmanned aerial vehicle landing damping device according to claim 1, characterized in that, first sleeve (3) slip cup joints in second sleeve (4), the one end fixed connection of first spring (5) is at the inner wall of first sleeve (3), and other end fixed connection is at the inner wall of second sleeve (4).
3. An unmanned aerial vehicle landing damping device according to claim 1, wherein the T-shaped end of the T-shaped limiting rod (7) is slidably connected in the limiting groove (6), and a second spring (8) is connected between the upper end face of the T-shaped end and the upper inner wall of the limiting groove (6).
4. An unmanned aerial vehicle landing damping device according to claim 1, wherein the lower end of the T-shaped limiting rod (7) passes through the limiting groove (6) and extends below the limiting groove (6), and is movably connected to the upper surface of the support plate (13) through a hinge.
5. The unmanned aerial vehicle landing damping device of claim 1, wherein the two ends of the third spring (12) are respectively fixedly connected to a side face of the left and right sides, which is close to the slide blocks (11), and the third spring (12) is sleeved on the surface of the slide rod (10).
6. An unmanned aerial vehicle landing damping device according to claim 1, wherein the front and rear ends of the support plate (13) are respectively movably connected to the slide block (11) on each side through hinges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922295374.1U CN211685654U (en) | 2019-12-19 | 2019-12-19 | Unmanned aerial vehicle descending damping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922295374.1U CN211685654U (en) | 2019-12-19 | 2019-12-19 | Unmanned aerial vehicle descending damping device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211685654U true CN211685654U (en) | 2020-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922295374.1U Expired - Fee Related CN211685654U (en) | 2019-12-19 | 2019-12-19 | Unmanned aerial vehicle descending damping device |
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| CN (1) | CN211685654U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148121A (en) * | 2021-03-25 | 2021-07-23 | 杭州科技职业技术学院 | Unmanned aerial vehicle undercarriage structure |
-
2019
- 2019-12-19 CN CN201922295374.1U patent/CN211685654U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148121A (en) * | 2021-03-25 | 2021-07-23 | 杭州科技职业技术学院 | Unmanned aerial vehicle undercarriage structure |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201016 |