CN211766248U - Novel double-blade quick-dismantling type unmanned aerial vehicle rotor wing - Google Patents
Novel double-blade quick-dismantling type unmanned aerial vehicle rotor wing Download PDFInfo
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- CN211766248U CN211766248U CN201922352062.XU CN201922352062U CN211766248U CN 211766248 U CN211766248 U CN 211766248U CN 201922352062 U CN201922352062 U CN 201922352062U CN 211766248 U CN211766248 U CN 211766248U
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- 230000005611 electricity Effects 0.000 claims abstract description 6
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 4
- 239000008141 laxative Substances 0.000 description 3
- 230000002475 laxative effect Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 206010019345 Heat stroke Diseases 0.000 description 1
- 241000238631 Hexapoda Species 0.000 description 1
- 241000607479 Yersinia pestis Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 201000010099 disease Diseases 0.000 description 1
- 208000037265 diseases, disorders, signs and symptoms Diseases 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses a novel two blade quick detach formula unmanned aerial vehicle rotors, including last rotor subassembly, lower rotor subassembly, supporting seat, go up the rotor subassembly and install the both sides at the supporting seat with lower rotor, go up rotor subassembly and include first rotor, second on rotor, go up oar clamp group, go up the motor, go up the electricity and transfer the ware, lower rotor subassembly includes rotor, second down rotor, oar clamp group, lower motor, electricity transfer the ware down, the utility model discloses an unmanned aerial vehicle wing is equipped with two sets of blades from top to bottom, and it is more stable to compare in the unmanned aerial vehicle that the wing only is equipped with a set of blade, meets resistance still can the stable flight, has guaranteed unmanned aerial vehicle's work efficiency, reduces the damage, practices thrift cost of maintenance. And this unmanned aerial vehicle wing is dismantled easily, realizes connecting the function at each position through the connecting piece, reaches the purpose of quick detach fast-assembling. The unmanned aerial vehicle after the dismantlement is small, easily accomodates and easily carries, practices thrift the space.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle rotor, especially a two-blade type unmanned aerial vehicle rotor.
Background
In recent years, drones have no longer just circle-in-picture and circle-of-the-great games, thanks to the advancement of materials, the development of mobile networks and the encouragement of policies. The shadow of the unmanned aerial vehicle walking on the route of the parent people appears in more and more fields, and the aerial 'big bird' can do more and more things for people. Wherein, in agriculture, unmanned aerial vehicle can carry the medical kit for dying the regional laxative of plant diseases and insect pests, not only is higher than artifical laxative speed a lot, and dose, the water yield that use are but less than artifical laxative a lot, and can adapt to various operational environment high-efficiently to reduce and exempt from the harm such as heatstroke that bring to people.
However, current unmanned aerial vehicle is limited to power and equipment convenience that the wing can provide, makes unmanned aerial vehicle comparatively inconvenient when using, and this is the problem that the practitioner in unmanned aerial vehicle field waited to solve urgently.
Disclosure of Invention
In order to solve the technical problem, the utility model provides a novel two-blade quick detach formula unmanned aerial vehicle rotor, including a novel two-blade quick detach formula unmanned aerial vehicle rotor, its characterized in that: including last rotor subassembly, lower rotor subassembly, supporting seat, go up rotor subassembly and lower rotor subassembly and install the both sides at the supporting seat, go up the rotor subassembly and include first rotor, second upper rotor, go up oar clamp group, go up the motor, go up the electric adjuster, lower rotor subassembly includes rotor, second lower rotor, lower oar clamp group, lower motor, electric adjuster down, the supporting seat sets up the mounting groove, goes up the electric adjuster and is located this mounting groove with electric adjuster down, first upper rotor sets up with second upper rotor relatively, first lower rotor sets up with second lower rotor relatively, and first upper rotor passes through with second upper rotor the oar clamp group is fixed, and first lower rotor passes through with second lower rotor down the oar clamp group is fixed, and first upper rotor and second upper rotor form an upper mounting hole around forming between the wing, the motor spindle of going up the motor stretches into in the upper mounting hole drive first upper rotor and second upper rotor rotate, the utility model discloses a rotor, including first rotor and second, upper oar clamp group and upper motor, the first rotor of lower motor is connected fixedly between upper oar clamp group and the lower motor, be connected fixedly between lower oar clamp group and the lower motor respectively between lower rotor and the lower motor, between lower motor and the supporting seat respectively.
Further, rotor, first rotor, second down all have one with the last oar clamp group that corresponds or the link of oar clamp group connection down, the link all sets up the arc wall, forms respectively between the arc wall that corresponds go up mounting hole and mounting hole down on the first rotor, the second.
Further, the connecting end is towards the convex arc of the corresponding mounting hole.
Further, go up oar and press from both sides group and include first clamping piece and the first clamping piece that falls, the link of rotor is pressed from both sides tightly the location on first rotor and the second between the first clamping piece that goes up, and first clamping piece and the first clamping piece that falls run through and set up the mounting hole on first rotor and the second rotor is in corresponding the position of mounting hole sets up the connecting hole, the mounting hole has the connecting piece with the downthehole interlude of connecting hole.
Further, the connecting piece is a bolt.
Further, the supporting seat includes last supporting seat, under bracing seat, the pedestal by last under to interconnect, the pedestal sets up the opening formation in the face of the one end of under bracing seat the mounting groove goes up installing of electricity modulator and lower electricity modulator buckle in the mounting groove and through the under bracing seat compresses tightly spacingly.
The beneficial effects of the utility model reside in that: the wing of the unmanned aerial vehicle is provided with the upper and lower groups of blades, so that the unmanned aerial vehicle is more stable compared with an unmanned aerial vehicle with only one group of blades on the wing, can stably fly when meeting resistance, is high in balance, ensures the working efficiency of the unmanned aerial vehicle, reduces damage and saves maintenance cost; the wing of the unmanned aerial vehicle is provided with the double-layer rotor wing assemblies, the double-layer rotor wing assemblies are connected through sharing one supporting seat, the wing is easy to disassemble, the function of connecting each part is realized through the connecting piece, and the purposes of quick disassembly and quick assembly are achieved; can fold unmanned aerial vehicle through rotatory each rotor, and can not mutual interference when rotating and folding up between the relative rotor, folding back is small, easily accomodates and easily carries, practices thrift the space.
Drawings
Figure 1 is the novel biplate quick detach formula unmanned aerial vehicle rotor's stereogram.
Figure 2 is the novel three-dimensional exploded view of two blade quick detach formula unmanned aerial vehicle rotors.
Figure 3 is the novel partial enlargements of A department in two blade quick detach formula unmanned aerial vehicle rotor drawings 2.
Reference numerals:
1. the upper rotor assembly, 101, the first upper rotor, 102, the second upper rotor, 103, the upper paddle clamp group, 104, the upper motor, 106, the upper adjuster 2, the lower rotor assembly, 201, the first lower rotor, 202, the second lower rotor, 203, the lower paddle clamp group, 204, the lower motor, 205, the lower adjuster, 3, the support base, 301, the upper support base, 302, the lower support base, 303, the base, 304, the mounting groove, 401, the first upper clip, 402, the first lower clip, 501, the second upper clip, 502, the second lower clip, 6, the mounting hole, 601, the connecting hole, 602, the connecting piece, 602' connecting piece (bolt), 7, the motor spindle, 8, the connecting end, 801, the arc-shaped groove, 802, the upper mounting hole, 803, the lower mounting hole.
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.
The invention will be further described with reference to the accompanying drawings.
In order to solve the technical problem, the utility model provides a novel two blade quick detach formula unmanned aerial vehicle rotors is in order to solve a great deal of problems of prior art.
Referring to fig. 1 to 3, the novel dual-blade fast-detachable drone rotor includes an upper rotor assembly 1, a lower rotor assembly 2, and a support base 3, where the upper rotor assembly 1 and the lower rotor assembly 2 are installed on two sides of the support base 3, the upper rotor assembly 1 includes a first upper rotor 101, a second upper rotor 102, an upper paddle clamp group 103, an upper motor 104, and an upper regulator 106, the lower rotor assembly 2 includes a first lower rotor 201, a second lower rotor 202, a lower paddle clamp group 203, a lower motor 204, and a lower regulator 205, the support base 3 is provided with a mounting groove 304, the upper regulator 106 and the lower regulator 205 are located in the mounting groove 304, the first upper rotor 101 and the second upper rotor 102 are arranged opposite to each other, the first lower rotor 201 and the second lower rotor 202 are arranged opposite to each other, the first upper rotor 101 and the second upper rotor 102 are fixed by the upper paddle clamp group 103, and the first lower rotor 201 and the second lower rotor 202 are fixed by the lower paddle clamp group 203, go up between rotor 101 and the second upper rotor 102 around forming an last mounting hole 802, the motor spindle 7 of going up motor 104 stretches into go up rotor 101 and second upper rotor 102 rotation in the mounting hole 802 of driving, around forming a lower mounting hole 803 between first lower rotor 201 and the second lower rotor 202, motor spindle 7 of lower motor 204 stretches into drive first lower rotor 201 and second lower rotor 202 rotation in the mounting hole 803, go up between oar clamp group 103 and the last motor 104, go up between motor 104 and the supporting seat 3 and be connected fixedly respectively, between lower oar clamp group 203 and lower motor 204, be connected fixedly between lower motor 204 and the supporting seat 3 respectively.
Specifically, first upper rotor wing 101, second upper rotor wing 102, first rotor wing 201, second lower rotor wing 202 all have one with the corresponding link 8 that goes up oar clamp group 103 or lower oar clamp group 203 and connect, link 8 all sets up arc-shaped groove 801, forms respectively between the corresponding arc-shaped groove 801 go up mounting hole 802 and mounting hole 803 down.
Specifically, the connecting end 8 is in an arc shape protruding towards the corresponding upper mounting hole or the corresponding lower mounting hole. The end edges of the two connecting ends 8 are arc-shaped, so that the connecting ends 8 cannot interfere with each other at the edges when rotating during folding the rotor wing.
Specifically, the upper paddle clamp group 103 includes a first upper clamp piece 401 and a first lower clamp piece 402, the connecting end 8 of the first upper rotor 101 and the second upper rotor 102 is clamped and positioned between the first upper clamp piece 401 and the first lower clamp piece 402, the first upper clamp piece 401 and the first lower clamp piece 402 are provided with an installation hole 6 in a penetrating manner, the first upper rotor 101 and the second upper rotor 102 are provided with a connection hole 601 at a position corresponding to the installation hole 6, and a connection piece 602 is inserted in the installation hole 6 and the connection hole 601 in a penetrating manner. Specifically, in this embodiment, the connecting member 602 is a bolt 602'. The corresponding first upper jaw 401 and the first lower jaw 402 are fixed by bolts 602'.
Lower oar press from both sides the structure of group 203 with go up oar press from both sides the setting of group 103 the same, it is specific, lower oar press from both sides the group 203 and includes that clamping piece 501 and second lower clamping piece 502 under the second, first rotor 201 is pressed from both sides tightly the location with the link of second lower rotor 202 under the second between clamping piece 501 and the second lower clamping piece 502, and is same, clamping piece 501 and second lower clamping piece 502 run through and set up the mounting hole under the second, first rotor 201 is corresponding under first lower rotor and the 201 second the position of mounting hole sets up the connecting hole, it will to have worn to insert the bolt in mounting hole and the connecting hole clamp on the second clamping piece 501 and second lower clamping piece 502 dead center is fixed.
Unmanned aerial vehicle wing be equipped with about two sets of blades, compare in that the wing only is equipped with the unmanned aerial vehicle of a set of blade more stable, when unmanned aerial vehicle meets air resistance at the flight in-process, still can stably fly, the equilibrium is high, has guaranteed unmanned aerial vehicle's work efficiency, reduces the damage, practices thrift cost of maintenance.
Specifically, supporting seat 3 includes by last upper supporting seat 301, lower supporting seat 302, the pedestal 303 of interconnect under to, pedestal 303 sets up the opening formation to the one end of lower supporting seat 302 mounting groove 304, the installation of going up electric accent ware 106 and electric accent ware 205 buckle in the mounting groove 304 and through lower supporting seat 302 compresses tightly spacingly. The side wall of the mounting groove 304 is flexible, the size of the upper electronic regulator 106 and the size of the lower electronic regulator 205 are slightly larger than the size of the mounting groove 304, and after the arrangement, the upper electronic regulator 106 and the lower electronic regulator 205 are limited in the mounting groove 304 and further form a relatively fixed connecting body with the supporting seat 3, so that the influence on balance caused by the slight change of the center of gravity in the flying process of the unmanned aerial vehicle is ensured. The self-adaptive capacity of the unmanned aerial vehicle in the flight process is improved. The wing of the unmanned aerial vehicle is provided with the double-layer rotor wing assembly, and the double-layer rotor wing assembly is connected through the shared supporting seat 3, so that the wing is easy to disassemble; the function of connecting each part is realized through the connecting piece 602, and the purposes of quick disassembly and quick assembly are achieved; loosen soon connecting piece 602 later can fold unmanned aerial vehicle through rotatory each rotor, and can not mutual interference when rotating to fold up between the relative rotor, folding back is small, easily accomodates portable, practices thrift the space.
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 (6)
1. The utility model provides a novel two blade quick detach formula unmanned aerial vehicle rotors which characterized in that: including last rotor subassembly, lower rotor subassembly, supporting seat, go up rotor subassembly and lower rotor subassembly and install the both sides at the supporting seat, go up the rotor subassembly and include first rotor, second upper rotor, go up oar clamp group, go up the motor, go up the electric adjuster, lower rotor subassembly includes rotor, second lower rotor, lower oar clamp group, lower motor, electric adjuster down, the supporting seat sets up the mounting groove, goes up the electric adjuster and is located this mounting groove with electric adjuster down, first upper rotor sets up with second upper rotor relatively, first lower rotor sets up with second lower rotor relatively, and first upper rotor passes through with second upper rotor the oar clamp group is fixed, and first lower rotor passes through with second lower rotor down the oar clamp group is fixed, and first upper rotor and second upper rotor form an upper mounting hole around forming between the wing, the motor spindle of going up the motor stretches into in the upper mounting hole drive first upper rotor and second upper rotor rotate, the utility model discloses a rotor, including first rotor and second, upper oar clamp group and upper motor, the first rotor of lower motor is connected fixedly between upper oar clamp group and the lower motor, be connected fixedly between lower oar clamp group and the lower motor respectively between lower rotor and the lower motor, between lower motor and the supporting seat respectively.
2. The novel two-bladed quick detach formula unmanned aerial vehicle rotor of claim 1 characterized in that: rotor, first rotor, second down in rotor all have one with the last oar clamp group that corresponds or the link of oar clamp group connection down on first rotor, the second, the link all sets up the arc wall, forms respectively between the arc wall that corresponds go up mounting hole and mounting hole down.
3. The novel two-bladed quick detach formula unmanned aerial vehicle rotor of claim 2 characterized in that: the connecting end is towards the convex arc of the corresponding mounting hole.
4. The novel two-bladed quick detach formula unmanned aerial vehicle rotor of claim 1 characterized in that: go up oar and press from both sides group and include first clamping piece and first clamping piece down, the link of rotor is pressed from both sides tightly the location on first last rotor and the second between clamping piece and the first clamping piece down, and first last clamping piece runs through with first clamping piece and sets up the mounting hole, rotor is corresponding on first last rotor and the second the position of mounting hole sets up the connecting hole, the mounting hole has the connecting piece with the downthehole interlude of connecting.
5. Novel two-blade quick detach formula unmanned aerial vehicle rotor of claim 4 characterized in that: the connecting piece is a bolt.
6. The novel two-bladed quick detach formula unmanned aerial vehicle rotor of claim 1 characterized in that: the supporting seat includes last supporting seat, under bracing seat, pedestal by last under to interconnect, the pedestal sets up the opening formation in the face of the one end of under bracing seat the mounting groove is gone up installing of electricity modulator and electricity modulator buckle down in the mounting groove and through the under bracing seat compresses tightly spacingly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922352062.XU CN211766248U (en) | 2019-12-24 | 2019-12-24 | Novel double-blade quick-dismantling type unmanned aerial vehicle rotor wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922352062.XU CN211766248U (en) | 2019-12-24 | 2019-12-24 | Novel double-blade quick-dismantling type unmanned aerial vehicle rotor wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211766248U true CN211766248U (en) | 2020-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922352062.XU Expired - Fee Related CN211766248U (en) | 2019-12-24 | 2019-12-24 | Novel double-blade quick-dismantling type unmanned aerial vehicle rotor wing |
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| Country | Link |
|---|---|
| CN (1) | CN211766248U (en) |
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2019
- 2019-12-24 CN CN201922352062.XU patent/CN211766248U/en not_active Expired - Fee Related
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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: 20201027 |