CN212448058U - Small low-altitude unmanned aerial vehicle - Google Patents
Small low-altitude unmanned aerial vehicle Download PDFInfo
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- CN212448058U CN212448058U CN202021313217.5U CN202021313217U CN212448058U CN 212448058 U CN212448058 U CN 212448058U CN 202021313217 U CN202021313217 U CN 202021313217U CN 212448058 U CN212448058 U CN 212448058U
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- aerial vehicle
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Abstract
The utility model discloses a small-size low latitude unmanned aerial vehicle, including low latitude unmanned aerial vehicle main part with fix the mounting panel in low latitude unmanned aerial vehicle main part bottom, the below of mounting panel is equipped with four supporting legs, and the gyro wheel is installed in the bottom rotation of supporting leg, four first grooves have been seted up to the bottom of mounting panel, and fixed mounting has same locating lever between the both sides inner wall in first groove, and the movable sleeve is equipped with the bracing piece that the slope set up on the locating lever, and two relative bracing piece symmetries set up, controls that one side that two relative bracing pieces are close to each other respectively with the one side inner wall in the first groove that corresponds between the same first spring of. The utility model relates to a rationally, the collision impact force when being convenient for alleviate the descending of low latitude unmanned aerial vehicle main part avoids because of the great risk that causes the damage of low latitude unmanned aerial vehicle main part of collision impact force, and is convenient for adjust buffer spring's elasticity size according to actual need, improves buffering effect, prolongs buffer spring's life, is favorable to using.
Description
Technical Field
The utility model relates to a small-size low latitude unmanned machine technical field especially relates to small-size low latitude unmanned machine.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by an on-board computer, along with the continuous development of the technical field of the unmanned aerial vehicle, small low-altitude unmanned aerial vehicles gradually appear, can realize real-time image transmission and aerial photography by carrying various sensors, and is powerful supplement of satellite remote sensing and traditional aerial remote sensing;
the buffering effect of current small-size low latitude unmanned machine when falling to the ground is poor, and it falls down from the sky, because height is higher relatively ground, when receiving the effect of gravity and when colliding with ground, if the impact is great, causes small-size low latitude unmanned machine to damage very easily, can not satisfy the user demand, therefore we have proposed small-size low latitude unmanned machine and have been used for solving above-mentioned problem.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the defects existing in the prior art and providing a small low-altitude unmanned machine.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a small-sized low-altitude unmanned aerial vehicle comprises a low-altitude unmanned aerial vehicle main body and a mounting plate fixed at the bottom of the low-altitude unmanned aerial vehicle main body, wherein four supporting legs are arranged below the mounting plate, rollers are rotatably arranged at the bottom ends of the supporting legs, four first grooves are formed in the bottom of the mounting plate, the same positioning rod is fixedly arranged between the inner walls of the two sides of each first groove, supporting rods which are obliquely arranged are movably sleeved on the positioning rods, the two opposite supporting rods are symmetrically arranged, the same first spring is fixedly arranged between the side, close to each other, of the two opposite supporting rods on the left side and the right side and the inner wall of one side of the corresponding first groove respectively, the first spring is movably sleeved on the corresponding positioning rod, the bottom ends of the supporting rods extend to the lower part of the mounting plate, the supporting legs are slidably sleeved on the corresponding supporting rods, the supporting leg top is equipped with the rectangular block, first rectangular hole has been seted up at the top of rectangular block, the rectangular block cover is established on the bracing piece that corresponds, the bracing piece is located corresponding first rectangular hole, fixed mounting has same buffer spring between the bottom of rectangular block and the top of the supporting leg that corresponds, buffer spring movable sleeve is established on the bracing piece that corresponds, rotate between the both sides inner wall of first rectangular hole and install the same sleeve pipe that is located corresponding first through-hole, the sleeve pipe thread cover is established on the corresponding screw rod, fixed cover is equipped with first bevel gear on the sleeve pipe, the meshing of bottom one side of first bevel gear has the second bevel gear, one side fixed mounting that corresponding screw rod was kept away from to the second bevel gear has the pivot, the one end that corresponding second bevel gear was kept away from in the pivot extends to the rectangular block outside and fixed mounting has the rocking disc, the rectangular block rotates the cover and establishes.
Preferably, the rectangular channel has been seted up on the top of supporting leg, the inner wall of rectangular channel and the outside sliding connection of the bracing piece that corresponds, all seted up the spacing groove on the both sides inner wall of rectangular channel, the equal fixed mounting in both sides of bracing piece has the stopper, stopper and the spacing groove sliding connection that corresponds, the top of stopper and the top inner wall movable contact of the spacing groove that corresponds.
Preferably, the inner side of the sleeve is provided with internal threads, and the internal threads are in threaded connection with the corresponding screw rods.
Preferably, two first bearings are fixedly installed between the inner walls of the two sides of the first rectangular hole, and inner rings of the first bearings are fixedly sleeved with the outer sides of the corresponding sleeves.
Preferably, a circular hole is formed in the inner wall, close to each other, of the two first rectangular holes opposite to each other in the left and right direction, a second bearing is sleeved in the circular hole in a fixed mode, and the inner ring of the second bearing is sleeved with the outer side of the corresponding rotating shaft in a fixed mode.
Preferably, the outer side of each of the first bevel gears and the outer side of the corresponding second bevel gear are not in contact with the inner wall of the first rectangular hole.
Preferably, the bottom of supporting leg is seted up the rotation groove that both sides are the opening setting, and fixed mounting has same round pin axle between the front side inner wall in rotation groove and the rear side inner wall, and the front side of gyro wheel is opened and is equipped with the perforation, and the perforation internal fixation cover is equipped with the third bearing, the fixed suit in the outer side of the inner circle of third bearing and the round pin axle that corresponds.
Preferably, a second rectangular hole is formed in one side of the supporting rod, the positioning rod is located in the corresponding second rectangular hole, balls are embedded in the inner walls of the four sides of the second rectangular hole, the positioning rod is located between the corresponding eight balls, and the balls are in rolling contact with the outer side of the corresponding positioning rod.
Compared with the prior art, the beneficial effects of the utility model are that:
through the low-altitude unmanned aerial vehicle main body, the mounting plate, the support rods, the support legs, the rollers, the first through hole, the buffer spring, the screw rod, the rectangular block, the first rectangular hole, the sleeve, the first bevel gear, the second bevel gear, the rocking disc, the rotating shaft, the rectangular groove and the first spring, when the low-altitude unmanned aerial vehicle main body descends, the four rollers are firstly contacted with the ground, the falling gravity drives the mounting plate to downwards extrude the four support rods, so that the support rods slide in the corresponding rectangular grooves, the left support rod and the right support rod which are opposite drive the corresponding balls to move in the direction away from each other on the positioning rod respectively and stretch the first spring, the support rods drive the sleeve to downwards move through the screw rod, the sleeve drives the rectangular block to downwards move through the corresponding first bearing and compress the buffer spring, and under the elastic force of the buffer spring, the collision impact force when the low-altitude unmanned aerial vehicle main body falls is relieved, when the buffer spring is used for a long time and the phenomenon of elastic fatigue occurs, four rocking discs are rotated in the forward direction, the rocking discs drive a second bevel gear to rotate through corresponding rotating shafts, the second bevel gear drives a sleeve to rotate through a first bevel gear meshed with the second bevel gear, the sleeve rotates and drives a rectangular block to compress the buffer spring downwards through a corresponding first bearing, the buffer spring is in a slightly compressed or semi-compressed state before buffering is not performed on the buffer spring, the buffering force can be adjusted according to the compression degree of the buffer spring, the mode can also be adjusted when the elastic force of the buffer spring is weakened after the buffer spring is used for a long time, the buffering effect is improved, and the service life of the buffer spring is prolonged.
The utility model relates to a rationally, the collision impact force when being convenient for alleviate the descending of low latitude unmanned aerial vehicle main part avoids because of the great risk that causes the damage of low latitude unmanned aerial vehicle main part of collision impact force, and is convenient for adjust buffer spring's elasticity size according to actual need, improves buffering effect, prolongs buffer spring's life, is favorable to using.
Drawings
Fig. 1 is a schematic sectional structure view of a small-sized low-altitude unmanned aerial vehicle provided by the present invention;
fig. 2 is an enlarged schematic view of a portion a in fig. 1.
In the figure: the automatic lifting device comprises a low-altitude unmanned aerial vehicle main body 1, a mounting plate 2, a support rod 3, support legs 4, rollers 5, a first through hole 6, a buffer spring 7, a screw rod 8, a rectangular block 9, a first rectangular hole 10, a sleeve 11, a first bevel gear 12, a second bevel gear 13, a rocking disc 14, a rotating shaft 15, a rectangular groove 16, a first spring 17 and a positioning rod 18.
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, a small-sized low-altitude unmanned aerial vehicle comprises a low-altitude unmanned aerial vehicle main body 1 and a mounting plate 2 fixed at the bottom of the low-altitude unmanned aerial vehicle main body 1, four supporting legs 4 are arranged below the mounting plate 2, rollers 5 are rotatably arranged at the bottom ends of the supporting legs 4, four first grooves are formed at the bottom of the mounting plate 2, the same positioning rod 18 is fixedly arranged between the inner walls of the two sides of the first groove, the supporting rods 3 are obliquely arranged and movably sleeved on the positioning rod 18, the two opposite supporting rods 3 are symmetrically arranged, the same first spring 17 is fixedly arranged between the side, close to each other, of the two left and right opposite supporting rods 3 and the inner wall of one side of the corresponding first groove, the first spring 17 is movably sleeved on the corresponding positioning rod 18, the bottom ends of the supporting rods 3 extend to the lower part of the mounting plate 2, the supporting legs 4 are, a same screw 8 is fixedly arranged between the top inner wall and the bottom inner wall of the first through hole 6, a rectangular block 9 is arranged above the supporting leg 4, a first rectangular hole 10 is arranged at the top of the rectangular block 9, the rectangular block 9 is sleeved on the corresponding supporting rod 3, the supporting rod 3 is positioned in the corresponding first rectangular hole 10, a same buffer spring 7 is fixedly arranged between the bottom of the rectangular block 9 and the top end of the corresponding supporting leg 4, the buffer spring 7 is movably sleeved on the corresponding supporting rod 3, a same sleeve 11 positioned in the corresponding first through hole 6 is rotatably arranged between the inner walls at two sides of the first rectangular hole 10, the sleeve 11 is in threaded sleeve on the corresponding screw 8, a first bevel gear 12 is fixedly sleeved on the sleeve 11, a second bevel gear 13 is meshed at one side of the bottom of the first bevel gear 12, and a rotating shaft 15 is fixedly arranged at one side of the second bevel gear 13 far away from the corresponding screw 8, the one end that pivot 15 kept away from corresponding second bevel gear 13 extends to outside rectangular block 9 and fixed mounting has rocking disc 14, and rectangular block 9 rotates the cover and establishes in corresponding pivot 15, the utility model relates to a rationally, be convenient for alleviate the collision impact force when low latitude unmanned aerial vehicle main part 1 descends, avoid causing the risk of low latitude unmanned aerial vehicle main part 1 damage because of the collision impact force is great, and be convenient for adjust buffer spring 7's elasticity size according to actual need, improve buffering effect, extension buffer spring 7's life is favorable to using.
In the utility model, the top end of the supporting leg 4 is provided with a rectangular groove 16, the inner wall of the rectangular groove 16 is connected with the outer side of the corresponding supporting rod 3 in a sliding way, the inner walls of the two sides of the rectangular groove 16 are provided with limit grooves, the two sides of the supporting rod 3 are fixedly provided with limit blocks, the limit blocks are connected with the corresponding limit grooves in a sliding way, the top parts of the limit blocks are in movable contact with the inner walls of the top parts of the corresponding limit grooves, the inner side of the sleeve 11 is provided with internal threads which are connected with the corresponding screw rods 8 in a threaded way, two first bearings are fixedly arranged between the inner walls of the two sides of the first rectangular holes 10, the inner ring of each first bearing is fixedly sleeved with the outer side of the corresponding sleeve 11, the inner wall of one side, which is close to each other, of the two first rectangular holes 10 which are opposite from left to, the outer side of the first bevel gear 12 and the outer side of the corresponding second bevel gear 13 are not in contact with the inner wall of the first rectangular hole 10, the bottom end of the supporting leg 4 is provided with a rotating groove with two sides being provided with openings, the same pin shaft is fixedly installed between the front inner wall and the rear inner wall of the rotating groove, the front side of the roller 5 is provided with a through hole, the through hole is internally and fixedly sleeved with a third bearing, the inner ring of the third bearing is fixedly sleeved with the outer side of the corresponding pin shaft, one side of the supporting rod 3 is provided with a second rectangular hole, the positioning rod 18 is positioned in the corresponding second rectangular hole, the four side inner walls of the second rectangular hole are all embedded with balls, the positioning rod 18 is positioned between the corresponding eight balls, and the balls are in rolling contact with the outer side of the corresponding positioning rod 18, the utility model has reasonable design, is convenient for relieving the collision impact force when the low-altitude unmanned main body 1 is landed, and avoids the, and the elasticity of the buffer spring 7 can be conveniently adjusted according to actual needs, the buffering effect is improved, the service life of the buffer spring 7 is prolonged, and the use is facilitated.
The working principle is as follows: when the low-altitude unmanned aerial vehicle main body 1 is used, when the low-altitude unmanned aerial vehicle main body 1 descends, the four rollers 5 firstly contact the ground, and further can limit the four supporting legs 4 to continuously move, at the moment, the falling gravity drives the mounting plate 2 to downwards extrude the four supporting rods 3, so that the supporting rods 3 slide in the corresponding rectangular grooves 16, because the inclination angles of the supporting rods 3 are unchanged, the mounting plate 2 drives the four T-shaped sliding rails to downwards move while vertically downwards moving, so that the left and right opposite supporting rods 3 drive the corresponding balls to move in the directions away from each other on the positioning rods 18, the supporting rods 3 stretch the corresponding first springs 17 while moving, meanwhile, the supporting rods 3 drive the sleeves 11 to downwards move through the screw rods 8, the sleeves 11 drive the rectangular blocks 9 to downwards move through the corresponding first bearings, and the corresponding buffer springs 7 are compressed while the rectangular blocks 9 downwards move, under the elastic force action of the buffer spring 7, the collision impact force generated when the low-altitude unmanned aerial vehicle main body 1 falls is relieved, and the risk that the low-altitude unmanned aerial vehicle main body 1 is damaged due to large collision impact force is avoided;
when the buffer spring 7 is used for a long time and the phenomenon of weakened elastic fatigue elasticity occurs, the four rocking discs 14 are rotated in the forward direction, the rocking discs 14 rotate and simultaneously drive the corresponding rotating shafts 15 to rotate, the rotating shafts 15 drive the corresponding second bevel gears 13 to rotate, the second bevel gears 13 rotate and simultaneously drive the first bevel gears 12 meshed with the second bevel gears to rotate, the first bevel gears 12 drive the corresponding sleeves 11 to rotate, under the action that the internal threads are meshed with the corresponding screw rods 8, the sleeves 11 rotate and simultaneously move downwards, the sleeves 11 drive the rectangular blocks 9 to move downwards through the corresponding first bearings, the corresponding buffer springs 7 are compressed while the rectangular blocks 9 move downwards, the buffer springs 7 are in a slightly compressed or semi-compressed state before being buffered, the buffer springs are compressed to be shortened, and the elastic damping of the buffer springs 7 in the compressed state on the mounting plate 2 is obviously increased, can adjust the buffering dynamics according to the compression degree adjustment buffer spring 7, this mode also can be adjusted when buffer spring 7 uses elasticity weak for a long time, improves buffering effect, prolongs buffer spring 7's life.
In the description of the present application, it should be further noted that, unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may include, for example, a fixed connection, a detachable connection, an integral connection, a mechanical connection, an electrical connection, a direct connection, a connection through an intermediate medium, and a connection between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to specific circumstances.
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 (8)
1. The small-sized low-altitude unmanned aerial vehicle comprises a low-altitude unmanned aerial vehicle main body (1) and a mounting plate (2) fixed at the bottom of the low-altitude unmanned aerial vehicle main body (1), wherein four supporting legs (4) are arranged below the mounting plate (2), and rollers (5) are rotatably arranged at the bottom ends of the supporting legs (4), and is characterized in that four first grooves are formed in the bottom of the mounting plate (2), a same positioning rod (18) is fixedly arranged between the inner walls of the two sides of each first groove, the positioning rod (18) is movably sleeved with supporting rods (3) which are obliquely arranged, the two opposite supporting rods (3) are symmetrically arranged, a same first spring (17) is fixedly arranged between one side, close to each other, of the two opposite supporting rods (3) at the left side and the right side and the inner wall of one side of the corresponding first groove respectively, the first spring (17) is movably sleeved on the corresponding positioning rod (18), and, the supporting legs (4) are sleeved on the corresponding supporting rods (3) in a sliding manner, one side of each supporting rod (3) is provided with a first through hole (6), a same screw rod (8) is fixedly arranged between the inner wall of the top part and the inner wall of the bottom part of each first through hole (6), a rectangular block (9) is arranged above each supporting leg (4), the top part of each rectangular block (9) is provided with a first rectangular hole (10), each rectangular block (9) is sleeved on the corresponding supporting rod (3), each supporting rod (3) is positioned in the corresponding first rectangular hole (10), a same buffer spring (7) is fixedly arranged between the bottom part of each rectangular block (9) and the top end of the corresponding supporting leg (4), each buffer spring (7) is movably sleeved on the corresponding supporting rod (3), and a same sleeve (11) positioned in the corresponding first through hole (6) is rotatably arranged between the inner walls on the two sides of each first rectangular hole (, the screw sleeve (11) is sleeved on the corresponding screw rod (8) in a threaded manner, a first bevel gear (12) is fixedly sleeved on the sleeve (11), a second bevel gear (13) is meshed on one side of the bottom of the first bevel gear (12), a rotating shaft (15) is fixedly installed on one side, away from the corresponding screw rod (8), of the second bevel gear (13), one end, away from the corresponding second bevel gear (13), of the rotating shaft (15) extends to the outside of the rectangular block (9) and is fixedly provided with a rocking disc (14), and the rectangular block (9) is rotatably sleeved on the corresponding rotating shaft (15).
2. The small-sized low-altitude unmanned aerial vehicle as claimed in claim 1, wherein a rectangular groove (16) is formed in the top end of the supporting leg (4), the inner wall of the rectangular groove (16) is in sliding connection with the outer side of the corresponding supporting rod (3), limiting grooves are formed in the inner walls of the two sides of the rectangular groove (16), limiting blocks are fixedly mounted on the two sides of the supporting rod (3), the limiting blocks are in sliding connection with the corresponding limiting grooves, and the tops of the limiting blocks are in movable contact with the inner walls of the tops of the corresponding limiting grooves.
3. The small-sized low-altitude unmanned aerial vehicle according to claim 1, wherein the inner side of the sleeve (11) is provided with an internal thread, and the internal thread is in threaded connection with the corresponding screw (8).
4. The small-sized low-altitude unmanned aerial vehicle according to claim 1, wherein two first bearings are fixedly installed between the inner walls of the two sides of the first rectangular hole (10), and the inner rings of the first bearings are fixedly sleeved with the outer sides of the corresponding sleeves (11).
5. The small-sized low-altitude unmanned aerial vehicle as claimed in claim 1, wherein circular holes are formed in the inner walls of the two first rectangular holes (10) which are opposite from each other at the left and right sides, the inner walls of the two first rectangular holes are close to each other, second bearings are fixedly sleeved in the circular holes, and inner rings of the second bearings are fixedly sleeved with the outer sides of the corresponding rotating shafts (15).
6. The small-sized low-altitude drone according to claim 1, characterized in that both the outer side of the first bevel gear (12) and the outer side of the corresponding second bevel gear (13) are not in contact with the inner wall of the first rectangular hole (10).
7. The small-sized low-altitude unmanned aerial vehicle according to claim 1, wherein the bottom end of the support leg (4) is provided with a rotating groove with two sides provided with openings, the same pin shaft is fixedly installed between the front inner wall and the rear inner wall of the rotating groove, the front side of the roller (5) is provided with a through hole, a third bearing is fixedly sleeved in the through hole, and the inner ring of the third bearing is fixedly sleeved with the outer side of the corresponding pin shaft.
8. The small-sized low-altitude unmanned aerial vehicle according to claim 1, wherein one side of the support rod (3) is provided with a second rectangular hole, the positioning rods (18) are located in the corresponding second rectangular holes, balls are embedded in the inner walls of the four sides of each second rectangular hole, the positioning rods (18) are located between the corresponding eight balls, and the balls are in rolling contact with the outer side of the corresponding positioning rods (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021313217.5U CN212448058U (en) | 2020-07-07 | 2020-07-07 | Small low-altitude unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021313217.5U CN212448058U (en) | 2020-07-07 | 2020-07-07 | Small low-altitude unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212448058U true CN212448058U (en) | 2021-02-02 |
Family
ID=74484134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021313217.5U Expired - Fee Related CN212448058U (en) | 2020-07-07 | 2020-07-07 | Small low-altitude unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212448058U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619783A (en) * | 2021-08-05 | 2021-11-09 | 湖南久正环保科技有限公司 | Remote control strain feeding flying device for black and odorous water treatment |
| CN113895607A (en) * | 2021-11-11 | 2022-01-07 | 北京卓翼智能科技有限公司 | Unmanned aerial vehicle undercarriage buffer structure |
| CN114030614A (en) * | 2021-12-22 | 2022-02-11 | 六安市空间数据应用有限公司 | Remote sensing image collection equipment for high-standard farmland assessment |
-
2020
- 2020-07-07 CN CN202021313217.5U patent/CN212448058U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113619783A (en) * | 2021-08-05 | 2021-11-09 | 湖南久正环保科技有限公司 | Remote control strain feeding flying device for black and odorous water treatment |
| CN113895607A (en) * | 2021-11-11 | 2022-01-07 | 北京卓翼智能科技有限公司 | Unmanned aerial vehicle undercarriage buffer structure |
| CN114030614A (en) * | 2021-12-22 | 2022-02-11 | 六安市空间数据应用有限公司 | Remote sensing image collection equipment for high-standard farmland assessment |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210202 Termination date: 20210707 |