CN211685633U - Landing gear of many rotor unmanned aerial vehicle - Google Patents
Landing gear of many rotor unmanned aerial vehicle Download PDFInfo
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- CN211685633U CN211685633U CN202020270134.6U CN202020270134U CN211685633U CN 211685633 U CN211685633 U CN 211685633U CN 202020270134 U CN202020270134 U CN 202020270134U CN 211685633 U CN211685633 U CN 211685633U
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- 230000000670 limiting effect Effects 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 3
- 241000561734 Celosia cristata Species 0.000 claims description 2
- 210000001520 comb Anatomy 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 230000003139 buffering effect Effects 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 3
- 230000002159 abnormal effect Effects 0.000 abstract 1
- 238000003466 welding Methods 0.000 abstract 1
- 230000005489 elastic deformation Effects 0.000 description 5
- 230000035939 shock Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000001595 contractor effect Effects 0.000 description 1
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Abstract
The utility model discloses a many rotor unmanned aerial vehicle's landing gear, which comprises a bod, the all fixed mounting in organism bottom both sides has the surge bin, and is two sets of second loop bar, four groups have all been welded in fixed block top both sides first loop bar top welding is on the inside top of surge bin, and all twines in the first loop bar outside has the third spring, and is two sets of the fixed block bottom rotates through pivot and the support body that rises and falls to be connected, the slide rail has all been seted up to organism both sides bottom, and is two sets of second push rod bottom all rotates through pivot and the support body that rises and falls to be connected. The utility model discloses when unmanned aerial vehicle takes place abnormal descending, extrude the cushion rubber piece inwards through the bottom slide bar, prevent that the damage is received to the support body and the organism that rise and fall, avoided under the not enough condition of unmanned aerial vehicle electric quantity, the in-process bottom that descends does not play the effect of buffering with ground, leads to the machine to receive the damage, has influenced the problem of normal use.
Description
Technical Field
The utility model relates to a landing gear technical field specifically is a many rotor unmanned aerial vehicle's landing gear.
Background
The landing gear of the multi-rotor unmanned aerial vehicle is mainly used for protecting the body of the unmanned aerial vehicle and preventing the body from being damaged by removing the ground, the landing gear of the existing multi-rotor unmanned aerial vehicle has various functions so as to meet various requirements of the unmanned aerial vehicle and realize diversification, for example, the landing gear of the unmanned aerial vehicle disclosed by the publication No. CN209719901U relates to the field of the unmanned aerial vehicle and has the advantages of increasing the stress area of a foot rest and increasing the bearing capacity of the foot rest, the landing gear of the unmanned aerial vehicle comprises a left frame leg and a right frame leg which are arranged on the body, the left frame leg comprises a first U-shaped rod, both sides of the upper end of the first U-shaped rod are provided with a first horizontal rod vertical to a horizontal extension rod in the first U-shaped rod, the right frame leg comprises a second U-shaped rod, both sides of the upper end of the second U-shaped rod are provided with a second horizontal rod vertical to a horizontal extension rod, first horizon bar and second horizon bar set up relatively and connect through the connecting piece that sets up on first horizon bar, the embedded groove of placing first horizon bar and second horizon bar is seted up to the fuselage bottom, and is equipped with the mounting of fixed first horizon bar and second horizon bar position in the embedded groove on the fuselage, consequently can know that current many rotor unmanned aerial vehicle's landing gear has satisfied people's user demand, still has following problem.
Problem 1: current many rotor unmanned aerial vehicle's landing gear generally is fixed design, under the not enough condition of unmanned aerial vehicle electric quantity, descends and mostly sets up damping device because of the bottom, and the in-process bottom that descends does not play the effect of buffering with ground, leads to the machine to receive the damage, has influenced normal use.
Problem 2: when current many rotor unmanned aerial vehicle's landing gear is generally accomodate and is placed, because of the bottom support is fixed installation, can't accomodate foldingly mostly, has taken great storage space, and current device accomodates comparatively troublesome, complex operation, therefore need a neotype many rotor unmanned aerial vehicle's landing gear to solve above-mentioned problem urgently.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a many rotor unmanned aerial vehicle's landing gear to what provide among the above-mentioned background art is solved and is leaded to the machine to damage and can't accomodate folding great storage space's problem of occuping because of the bottom does not set up buffer.
In order to achieve the above object, the utility model provides a following technical scheme: a landing device of a multi-rotor unmanned aerial vehicle comprises a body, wherein two sides of the bottom end of the body are fixedly provided with buffer bins, fixed blocks are sleeved in the buffer bins, two groups of fixed blocks are welded on two sides of the top ends of the fixed blocks, second sleeve rods are sleeved in the first sleeve rods, the top ends of the first sleeve rods are welded on the top ends of the interior of the buffer bins, third springs are wound on the outer sides of the first sleeve rods, the bottom ends of the two groups of fixed blocks are rotatably connected with a landing frame body through rotating shafts, slide rails are arranged at the bottom ends of the two sides of the body, slide blocks are arranged in the slide rails, the bottom ends of the two groups of slide blocks are rotatably connected with first push rods through rotating shafts, the bottom ends of the first push rods are sleeved in second push rods, two groups of first push rods are fixedly provided with second springs, and the bottom ends of the second springs, and the bottom ends of the two groups of second push rods are rotatably connected with the landing gear body through rotating shafts.
Preferably, two sets of fixed block top is fixed mounting all has the slide bar, and is two sets of the spout of mutually supporting with the slide bar is all seted up to the surge bin both sides, and the inside top of spout all is provided with the cushion rubber piece, four groups the cushion rubber piece is soft rubber material.
Preferably, the inside locking levers that are close to the organism outside of two sets of slider all are provided with, and the locking lever is the cockscomb structure design, two sets of locking lever bottom all fixed mounting have the pull ring, and the locking lever outside all twines first spring.
Preferably, the top ends of the two sets of slide rails are fixedly provided with toothed belts, and the toothed belts on the slide rails are mutually clamped with the locking rods.
Preferably, both sides of the bottom end of the machine body are provided with notches, the top ends of the inner portions of the notches on the machine body are fixedly provided with fourth springs, the bottom ends of the two groups of fourth springs are fixedly arranged at the top ends of the limiting clamping plates, and the limiting clamping plates are designed to be in a structure like a Chinese character 'ji'.
Preferably, the two groups of fixed blocks and the bottom sliding rod form a T-shaped design, and the outer diameter of each fixed block is smaller than the inner diameter of the buffer bin.
Compared with the prior art, the beneficial effects of the utility model are that:
1. the landing gear of the multi-rotor unmanned aerial vehicle is provided with a body, a first push rod, a second spring, a landing gear body, a buffer bin, a fixed block, a first loop bar, a second loop bar, a third spring and a buffer rubber block, through the design, when the unmanned aerial vehicle abnormally lands, the landing gear body is contacted with the ground, the buffer rubber block is inwards extruded through a bottom slide bar under the action of the fixed block inside the buffer bin, the force borne by the landing gear body is buffered for the first step under the action of the buffer rubber block, the third spring is inwards elastically deformed under the action of the first loop bar, the second loop bar and the third spring, the fixed block is slowly contracted inwards to perform the second buffering action, the body is prevented from being damaged, the landing gear body is supported and damped under the action of the inner second spring through the arranged first push rod and the second push rod, carry out tertiary shock attenuation with the power that the landing gear body received, prevent that landing gear body and organism from receiving the damage, avoided under the not enough condition of unmanned aerial vehicle electric quantity, descend and mostly do not set up damping device because of the bottom, the in-process bottom that descends does not play the effect of buffering with ground, leads to the machine to receive the damage, has influenced normal use's problem.
2. The landing gear of the multi-rotor unmanned aerial vehicle is provided with a slide rail, a slide block, a locking rod, a first spring, a first push rod, a second push rod, a landing gear body, a fourth spring and a limiting clamp plate, when the device is to be stored, the limiting function of the slide block is relieved by pulling the locking rod under the elastic deformation of the first spring, so that the slide block slides in the slide rail, the landing gear body rotates at the bottom end of the second push rod under the action of a rotating shaft, the first push rod rotates at the bottom end of the slide block, so that the landing gear body is folded, the landing gear body is put in by pulling the limiting clamp plate under the elastic deformation state of the fourth spring, the landing gear body is clamped and stored under the contraction action of the fourth spring, the situation that the landing gear body cannot be stored and folded due to the fixed installation of a bottom end support is avoided, occupy great storage space, and the current device accomodates comparatively trouble complex operation's problem.
Drawings
Fig. 1 is a schematic front view of a cross-sectional structure of the present invention;
FIG. 2 is a schematic side view of the stop plate of the present invention;
fig. 3 is an enlarged schematic view of the structure at a in fig. 1 according to the present invention;
fig. 4 is an enlarged schematic view of the structure at B in fig. 3 according to the present invention.
In the figure: 1. a body; 2. a slide rail; 3. a slider; 4. a locking lever; 5. a first spring; 6. a first push rod; 7. a second push rod; 8. a second spring; 9. a landing gear body; 10. a buffer bin; 11. a fixed block; 12. a first loop bar; 13. a second loop bar; 14. a third spring; 15. a buffer rubber block; 16. a fourth spring; 17. a limiting splint.
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 an embodiment:
a landing device of a multi-rotor unmanned aerial vehicle comprises a machine body 1, wherein buffer bins 10 are fixedly arranged on two sides of the bottom end of the machine body 1, fixed blocks 11 are sleeved inside the buffer bins 10, two groups of fixed blocks 11 and bottom end sliding rods form a T-shaped design, the outer diameter of each fixed block 11 is smaller than the inner diameter of each buffer bin 10, sliding rods are fixedly arranged at the top ends of the two groups of fixed blocks 11, sliding grooves matched with the sliding rods are formed in two sides of each buffer bin 10, buffer rubber blocks 15 are arranged at the top ends inside the sliding grooves, the four groups of buffer rubber blocks 15 are made of soft rubber materials, the landing device can buffer through the design when descending, the device is prevented from being damaged, second loop bars 13 are welded on two sides of the top ends of the two groups of fixed blocks 11, the second loop bars 13 are sleeved inside first loop bars 12, and the top ends of the four groups of first loop bars, and the third spring 14 has all been twined in the first loop bar 12 outside, and two sets of fixed block 11 bottoms rotate with the landing gear body 9 through the pivot and be connected, and slide rail 2 has all been seted up to 1 both sides bottom of organism, and slide rail 2 is inside all to be provided with slider 3.
The inner parts of the two groups of sliders 3 close to the outer side of the machine body 1 are respectively provided with a locking rod 4, the top ends of the two groups of sliding rails 2 are respectively fixedly provided with a toothed belt, the toothed belt on the sliding rail 2 is mutually clamped with the locking rod 4, the locking rods 4 are in a zigzag design, the bottom ends of the two groups of locking rods 4 are respectively fixedly provided with a pull ring, the outer parts of the locking rods 4 are respectively wound with a first spring 5, the design can ensure that the device can be better pulled by pulling through the pull rings, the two sides of the bottom end of the machine body 1 are respectively provided with a notch, the top ends of the inner parts of the notches on the machine body 1 are respectively fixed with a fourth spring 16, the bottom ends of the two groups of fourth springs 16 are respectively fixed at the top ends of limiting splints 17, the limiting splints 17 are in a zigzag structural design, the design can ensure that the device can be fixed through the, the 6 bottom of two sets of first push rods all fixed mounting have the second spring 8, and the 8 bottom of second spring all fixed mounting in the inside bottom of second spring 8, and 7 bottoms of two sets of second push rods all rotate with the landing gear body 9 through the pivot and be connected.
The working principle is as follows: when unmanned aerial vehicle takes place not normally to descend, through playing support body 9 and ground contact, under the effect of buffering storehouse 10 inside fixed block 11 with the dynamics, extrude cushion rubber piece 15 inwards through the bottom slide bar, the power that makes support body 9 receive through cushion rubber piece 15 effect carries out the first step and cushions, effect through first loop bar 12 and second loop bar 13 makes outside third spring 14 inwards carry out elastic deformation, make fixed block 11 carry out the cushioning effect of second time to inside slow shrink, prevent that organism 1 from taking place the damage, first push rod 6 and second push rod 7 through the setting support the shock attenuation to support body 9 under the effect of inside second spring 8, carry out tertiary shock attenuation with the power that support body 9 received, prevent support body 9 and organism 1 from receiving the damage.
When the device is to be stored, under the effect of elastic deformation of the first spring 5, the limiting effect of the sliding block 3 is removed by pulling the locking rod 4, the sliding block 3 slides inside the sliding rail 2, under the effect of the rotating shaft, the landing gear body 9 rotates at the bottom end of the second push rod 7, the first push rod 6 rotates at the bottom end of the sliding block 3, the landing gear body 9 is enabled to be folded, the landing gear body 9 is placed in the elastic deformation state of the fourth spring 16 by pulling the limiting clamping plate 17, the landing gear body 9 is clamped and stored under the contracting effect of the fourth spring 16, and the operation is finished.
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. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. The utility model provides a many rotor unmanned aerial vehicle's landing gear, includes organism (1), its characterized in that: the two sides of the bottom end of the machine body (1) are fixedly provided with buffer bins (10), fixed blocks (11) are sleeved inside the buffer bins (10), two groups of fixed blocks (11) are welded on two sides of the top end of each second loop bar (13), the second loop bars (13) are sleeved inside the first loop bars (12), four groups of first loop bars (12) are welded on the top end inside the buffer bins (10), third springs (14) are wound outside the first loop bars (12), the bottom ends of the two groups of fixed blocks (11) are rotatably connected with a lifting frame body (9) through rotating shafts, the bottom ends of the two sides of the machine body (1) are provided with slide rails (2), slide blocks (3) are arranged inside the slide rails (2), the bottom ends of the two groups of slide blocks (3) are rotatably connected with first push rods (6) through rotating shafts, and the bottom ends of the first push rods (6) are sleeved inside second push rods (7), two sets of all fixed mounting in first push rod (6) bottom has second spring (8), and all fixed mounting in the inside bottom of second spring (8) in second spring (8) bottom, and is two sets of second push rod (7) bottom all rotates through pivot and landing gear body (9) and is connected.
2. A landing gear for a multi-rotor drone according to claim 1, characterized in that: two sets of fixed block (11) top is fixed mounting all has the slide bar, and is two sets of surge bin (10) both sides all offer the spout of mutually supporting with the slide bar, and the inside top of spout all is provided with cushion rubber piece (15), four groups cushion rubber piece (15) are soft rubber material.
3. A landing gear for a multi-rotor drone according to claim 1, characterized in that: two sets of slider (3) inside is close to organism (1) outside and all is provided with locking lever (4), and locking lever (4) are the cockscomb structure design, and two sets of locking lever (4) bottom all fixed mounting have the pull ring, and locking lever (4) outside all twines first spring (5).
4. A landing gear for a multi-rotor drone according to claim 3, characterized in that: the top ends of the two groups of slide rails (2) are fixedly provided with toothed belts, and the toothed belts on the slide rails (2) are mutually clamped with the locking rods (4).
5. A landing gear for a multi-rotor drone according to claim 1, characterized in that: the novel engine body is characterized in that notches are formed in two sides of the bottom end of the engine body (1), fourth springs (16) are fixed to the top ends of the inner portions of the notches of the engine body (1), the bottom ends of the two groups of fourth springs (16) are fixed to the top end of a limiting clamping plate (17), and the limiting clamping plate (17) is of a structure in a shape like a Chinese character 'ji'.
6. A landing gear for a multi-rotor drone according to claim 1, characterized in that: the two groups of fixed blocks (11) and the bottom sliding rods form a T-shaped design, and the outer diameter of each fixed block (11) is smaller than the inner diameter of the buffer bin (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020270134.6U CN211685633U (en) | 2020-03-07 | 2020-03-07 | Landing gear of many rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020270134.6U CN211685633U (en) | 2020-03-07 | 2020-03-07 | Landing gear of many rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211685633U true CN211685633U (en) | 2020-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020270134.6U Expired - Fee Related CN211685633U (en) | 2020-03-07 | 2020-03-07 | Landing gear of many rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN211685633U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353248A (en) * | 2021-07-27 | 2021-09-07 | 宁波阿瑞斯自动化技术有限公司 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
| CN114489145A (en) * | 2022-04-13 | 2022-05-13 | 山东亿华天产业发展集团有限公司 | Unmanned aerial vehicle photogrammetry path planning method and low-altitude flight unmanned aerial vehicle system |
-
2020
- 2020-03-07 CN CN202020270134.6U patent/CN211685633U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113353248A (en) * | 2021-07-27 | 2021-09-07 | 宁波阿瑞斯自动化技术有限公司 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
| CN114489145A (en) * | 2022-04-13 | 2022-05-13 | 山东亿华天产业发展集团有限公司 | Unmanned aerial vehicle photogrammetry path planning method and low-altitude flight unmanned aerial vehicle system |
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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: 20201016 |