CN211033001U - Light-duty rotor unmanned aerial vehicle shock attenuation undercarriage - Google Patents
Light-duty rotor unmanned aerial vehicle shock attenuation undercarriage Download PDFInfo
- Publication number
- CN211033001U CN211033001U CN201922253172.0U CN201922253172U CN211033001U CN 211033001 U CN211033001 U CN 211033001U CN 201922253172 U CN201922253172 U CN 201922253172U CN 211033001 U CN211033001 U CN 211033001U
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- pulley
- connecting block
- rotary
- fixing
- damping spring
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- 230000035939 shock Effects 0.000 title claims abstract description 19
- 229910001294 Reinforcing steel Inorganic materials 0.000 claims abstract description 14
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 5
- 239000010959 steel Substances 0.000 claims abstract description 5
- 238000013016 damping Methods 0.000 claims description 24
- 238000012423 maintenance Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 5
- 230000002035 prolonged effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
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Abstract
The utility model discloses a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage, including unable adjustment base, swivelling joint piece and pulley, unable adjustment base's inside all is provided with the reinforcement steel sheet, and the outside of unable adjustment base, reinforcement steel sheet all is provided with fixation nut, unable adjustment base's inboard is provided with fixed diaphragm, and the below of fixed diaphragm all is provided with fixed connection piece, connect buckle is all installed to fixed connection piece's inboard, swivelling joint piece all installs in unable adjustment base's below, and swivelling joint piece's below is provided with the rotary rod, the standpipe is all installed to the below of rotary rod, and the outside of standpipe all is provided with rubber cushion, the below of standpipe all is provided with the telescopic bracket. The utility model provides a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage, consolidates the steel sheet through setting up, can consolidate the device like this, increases the hardness of the device's self, increases the device's life, reduces the device's maintenance cost.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle correlation technique field specifically is a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage.
Background
In recent years, there has been a rapid development of unmanned aerial vehicle technology. Because of the advantages of low cost, good maneuvering performance, strong survival ability, no casualty risk and the like, the unmanned aerial vehicle occupies an extremely important position in modern military wars and has very wide prospect in the civil field.
Traditional unmanned aerial vehicle shock attenuation undercarriage, outside exhibition is bulky, does not have the shrink function, at the in-process of aircraft operation, because the volume is too big, receives the wind-force influence, can lead to the aircraft to rock at the in-process production of flight.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage to the outside exhibition that provides in solving above-mentioned background is bulky, does not have the shrink function, at the in-process of aircraft operation, because the volume is too big, receives the wind-force influence, can lead to the aircraft to produce the problem of rocking at the in-process of flight.
In order to achieve the above object, the utility model provides a following technical scheme: a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage, includes unable adjustment base, swivelling joint piece and pulley, unable adjustment base's inside all is provided with the reinforcement steel sheet, and unable adjustment base, the outside of reinforcement steel sheet all is provided with fixation nut, unable adjustment base's inboard is provided with fixed diaphragm, and the below of fixed diaphragm all is provided with the fixed connection piece, the inboard of fixed connection piece all is installed and is connected the buckle, the swivelling joint piece all is installed in the below of unable adjustment base, and the below of swivelling joint piece is provided with the rotary rod, the below of rotary rod all is installed the standpipe, and the outside of standpipe all is provided with the rubber cushion, the below of standpipe all is provided with telescopic bracket, and the below of telescopic bracket all welds damping spring, the below of damping spring all is provided with the pulley connecting block, and the below of pulley connecting block all is installed the pulley, the inner sides of the pulley shields are provided with pulleys.
Preferably, the reinforcing steel plate is tightly attached to the fixed base, and the outer diameter of the reinforcing steel plate is the same as the inner diameter of the fixed base.
Preferably, the upper end of standpipe constitutes swivelling joint through the outer wall of rotary rod and the lower extreme of swivelling joint piece, and the standpipe is connected for the draw-in groove with connecting the buckle.
Preferably, the rubber cushion is tightly attached to the vertical pipe, and the inner diameter of the rubber cushion is the same as the outer diameter of the vertical pipe.
Preferably, the outer wall of the telescopic support forms a telescopic structure with the lower end of the rotary connecting block through the inner wall of the vertical pipe, and the telescopic support is symmetrically arranged about the central axis of the fixed transverse plate.
Preferably, the damping spring and the telescopic support are welded, and the width of the damping spring is larger than that of the telescopic support.
Preferably, the pulley connecting block and the damping spring are welded, and the width of the pulley connecting block is smaller than that of the damping spring.
Compared with the prior art, the beneficial effects of the utility model are that:
1. according to the light rotor unmanned aerial vehicle damping undercarriage, the reinforcing steel plate is arranged, so that the device can be reinforced, the hardness of the device is increased, the service life of the device is prolonged, and the maintenance cost of the device is reduced;
2. according to the light rotor unmanned aerial vehicle damping undercarriage, the vertical pipe can be rotated to a state that the vertical pipe is connected with the connecting buckle clamping groove through the rotating rod, so that the device can be folded, and the vertical pipe of the device can be conveniently fixed;
3. this light-duty rotor unmanned aerial vehicle shock attenuation undercarriage through setting up the rubber cushion, can play the guard action to the device like this, and the device can produce certain friction with ground when falling to the ground, can reduce like this because the loss that the friction produced the device.
Drawings
FIG. 1 is a schematic view of the front view of the internal structure of the present invention;
FIG. 2 is a schematic front view of the present invention;
FIG. 3 is a schematic left-view internal structure of the present invention;
fig. 4 is an enlarged schematic view of a portion a in fig. 1.
In the figure: 1. a fixed base; 2. reinforcing the steel plate; 3. fixing a nut; 4. fixing the transverse plate; 5. fixing a connecting block; 6. connecting a buckle; 7. rotating the connecting block; 8. rotating the rod; 9. a vertical tube; 10. a rubber cushion; 11. a telescopic bracket; 12. a damping spring; 13. a pulley connecting block; 14. a pulley shroud; 15. a pulley.
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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage, including unable adjustment base 1, swivel joint block 7 and pulley 15, the inside of unable adjustment base 1 all is provided with reinforcement steel sheet 2, and the outside of unable adjustment base 1, reinforcement steel sheet 2 all is provided with fixation nut 3, the inboard of unable adjustment base 1 is provided with fixed diaphragm 4, and the below of fixed diaphragm 4 all is provided with fixed joint block 5, the inboard of fixed joint block 5 all is installed and connected the buckle 6, swivel joint block 7 all is installed under unable adjustment base 1, and the below of swivel joint block 7 is provided with rotary rod 8, the below of rotary rod 8 all is installed standpipe 9, and the outside of standpipe 9 all is provided with rubber cushion 10, the below of standpipe 9 all is provided with telescopic bracket 11, and the below of telescopic bracket 11 all welds damping spring 12, the below of damping spring 12 all is provided with pulley connecting block 13, and the below of pulley connecting block 13 all is installed with pulley 14, the inside of the pulley shroud 14 is provided with pulleys 15.
The reinforcing steel plate 2 is tightly attached to the fixing base 1, the outer diameter of the reinforcing steel plate 2 is the same as the inner diameter of the fixing base 1, and the reinforcing steel plate 2 is arranged, so that the device can be reinforced, the hardness of the device is increased, the service life of the device is prolonged, and the maintenance cost of the device is reduced.
The outer wall that the upper end of standpipe 9 passes through rotary rod 8 constitutes swivelling joint with the lower extreme of swivelling joint piece 7, and standpipe 9 is connected for the draw-in groove with connect buckle 6, through setting up rotary rod 8, can be rotatory to standpipe 9 and connect buckle 6 draw-in groove connected state through rotary rod 8 with standpipe 9 like this, can fold the device like this, the device standpipe 9 of being convenient for is fixed.
Closely laminate between rubber cushion 10 and the standpipe 9, and the internal diameter of rubber cushion 10 is the same with the external diameter of standpipe 9, through setting up rubber cushion 10, can play the guard action to the device like this, the device can produce certain friction with ground when falling to the ground, can reduce like this because the loss that the friction produced the device.
The outer wall of telescopic bracket 11 constitutes extending structure with the lower extreme of swivelling joint piece 7 through the inner wall of standpipe 9, and telescopic bracket 11 sets up about the axis symmetry of fixed diaphragm 4, through setting up telescopic bracket 11, can stretch out and draw back telescopic bracket 11 to suitable position through standpipe 9 like this, can reduce the device volume that exposes outside like this, reduces the resistance of the device in the air.
For the welding between damping spring 12 and telescopic bracket 11, and damping spring 12's width is greater than telescopic bracket 11's width, through setting up damping spring 12, can handle the device shock attenuation like this, reduce rocking that produces when the device falls to the ground to improve the device's life.
For the welding between pulley connecting block 13 and damping spring 12, and the width of pulley connecting block 13 is less than damping spring 12's width, through setting up pulley connecting block 13, can take off at the device like this, inside pulley 15 can play the run-up effect, and when the device falls to the ground, can play the cushioning effect to the device, makes the device steadily fall to the ground.
The working principle is as follows: firstly, the device is connected with an unmanned aerial vehicle needing to be docked through a fixed base 1, a reinforced steel plate 2 is arranged, so that the device can be reinforced, the hardness of the device is increased, the service life of the device is prolonged, the maintenance cost of the device is reduced, then when the unmanned aerial vehicle flies, a telescopic bracket 11 is stretched to a proper position through a vertical pipe 9, so that the exposed volume of the device can be reduced, the resistance of the device in the air is reduced, then, the vertical pipe 9 is rotated to the clamping groove connection state of the vertical pipe 9 and a connecting buckle 6 through a rotary rod 8, so that the device can be folded, the vertical pipe 9 of the device is convenient to fix, through arranging a damping spring 12, so that the damping treatment can be carried out on the device, the shaking generated when the device falls to the ground is reduced, the service life of the device is prolonged, through arranging a rubber cushion 10, can play the guard action to the device like this, the device can produce certain friction with ground when falling to the ground, can reduce like this because the loss that the friction produced to the device, at last when unmanned aerial vehicle needs descend with telescopic bracket 11 through standpipe 9 flexible to suitable position, again with standpipe 9 through the rotatory to standpipe 9 of rotary rod 8 and 6 draw-in grooves of connecting buckle state that drops, has accomplished with the use of such light-duty rotor unmanned aerial vehicle shock attenuation undercarriage.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides a light-duty rotor unmanned aerial vehicle shock attenuation undercarriage, includes unable adjustment base (1), swivelling joint piece (7) and pulley (15), its characterized in that: the fixing device is characterized in that a reinforcing steel plate (2) is arranged inside the fixing base (1), fixing nuts (3) are arranged on the outer sides of the fixing base (1) and the reinforcing steel plate (2), a fixing transverse plate (4) is arranged on the inner side of the fixing base (1), a fixing connecting block (5) is arranged below the fixing transverse plate (4), connecting buckles (6) are arranged on the inner side of the fixing connecting block (5), rotary connecting blocks (7) are arranged below the fixing base (1), rotary rods (8) are arranged below the rotary connecting blocks (7), vertical pipes (9) are arranged below the rotary rods (8), rubber cushions (10) are arranged on the outer sides of the vertical pipes (9), telescopic supports (11) are arranged below the vertical pipes (9), and damping springs (12) are welded below the telescopic supports (11), damping spring (12)'s below all is provided with pulley connecting block (13), and pulley guard shield (14) are all installed to the below of pulley connecting block (13), the inboard of pulley guard shield (14) all is provided with pulley (15).
2. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the reinforced steel plate (2) is tightly attached to the fixed base (1), and the outer diameter of the reinforced steel plate (2) is the same as the inner diameter of the fixed base (1).
3. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the upper end of the vertical pipe (9) forms rotary connection with the lower end of the rotary connecting block (7) through the outer wall of the rotary rod (8), and the vertical pipe (9) is connected with the connecting buckle (6) through a clamping groove.
4. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the rubber soft cushion (10) is tightly attached to the vertical pipe (9), and the inner diameter of the rubber soft cushion (10) is the same as the outer diameter of the vertical pipe (9).
5. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the outer wall of the telescopic support (11) forms a telescopic structure with the lower end of the rotary connecting block (7) through the inner wall of the vertical pipe (9), and the telescopic support (11) is symmetrically arranged relative to the central axis of the fixed transverse plate (4).
6. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the damping spring (12) and the telescopic support (11) are welded, and the width of the damping spring (12) is larger than that of the telescopic support (11).
7. A light weight rotary wing drone shock absorbing landing gear according to claim 1, characterized in that: the pulley connecting block (13) and the damping spring (12) are welded, and the width of the pulley connecting block (13) is smaller than that of the damping spring (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922253172.0U CN211033001U (en) | 2019-12-13 | 2019-12-13 | Light-duty rotor unmanned aerial vehicle shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922253172.0U CN211033001U (en) | 2019-12-13 | 2019-12-13 | Light-duty rotor unmanned aerial vehicle shock attenuation undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211033001U true CN211033001U (en) | 2020-07-17 |
Family
ID=71539495
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922253172.0U Expired - Fee Related CN211033001U (en) | 2019-12-13 | 2019-12-13 | Light-duty rotor unmanned aerial vehicle shock attenuation undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211033001U (en) |
-
2019
- 2019-12-13 CN CN201922253172.0U patent/CN211033001U/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200717 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |