CN209972770U - Many rotor unmanned aerial vehicle folding mechanism - Google Patents
Many rotor unmanned aerial vehicle folding mechanism Download PDFInfo
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- CN209972770U CN209972770U CN201920290481.2U CN201920290481U CN209972770U CN 209972770 U CN209972770 U CN 209972770U CN 201920290481 U CN201920290481 U CN 201920290481U CN 209972770 U CN209972770 U CN 209972770U
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- unmanned aerial
- aerial vehicle
- mounting seat
- side fixing
- horn
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- 230000007246 mechanism Effects 0.000 title claims abstract description 20
- 238000009434 installation Methods 0.000 claims description 12
- 125000006850 spacer group Chemical group 0.000 claims description 2
- 230000032258 transport Effects 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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Abstract
The utility model relates to a multi-rotor unmanned aerial vehicle folding mechanism, which comprises a horn mounting seat and side fixing pieces connected with the two sides of the horn mounting seat, wherein the left side and the right side of the horn mounting seat are respectively provided with a concentric cylindrical pin, one end of each side fixing piece is provided with a through hole, and the connection of the horn mounting seat and the side fixing pieces is realized through the matching connection of the concentric cylindrical pins and the through holes; the arm mounting base rotates by taking the concentric cylindrical pin as an axis, so that the folding function of the unmanned aerial vehicle is realized; a limiting pin is arranged above the through hole and used for limiting the arm mounting base when the unmanned aerial vehicle is unfolded; a threaded gasket is arranged above the side fixing piece and is detachably connected and fixed with the machine arm mounting seat; a plurality of screw holes are all opened at both ends about the side stationary blade, connect and fixed unmanned aerial vehicle fuselage through the screw hole. The utility model has the advantages that, guarantee that the folding convenient while of unmanned aerial vehicle transportation can reliably firmly launch the flight again, make unmanned aerial vehicle organism rigidity and flight performance not receive or reduce folding mechanism's influence, it is safe convenient again.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to many rotor unmanned aerial vehicle folding mechanism.
Background
At present, the unmanned aerial vehicle technology develops more and more rapidly, and its application in aspects such as take photo by plane, monitoring and reconnaissance is more general and urgent, and many rotor unmanned aerial vehicle rely on its advantages such as can suspend and stop, take off and land convenient and fast and flight stability receives more developers' attention. To facilitate transport, multi-rotor drones are usually designed in a collapsible form. However, the existing folding mechanism has certain risks, and the rigidity of a part of the machine body is also lost. Some of the wings can be loosened during the unfolding flight, and some of the wings can not be loosened but have certain swinging gaps.
Present chinese patent document CN201820586170.6 discloses a joint formula unmanned aerial vehicle folding arm mechanism, its main technical scheme is: the utility model provides a folding arm mechanism of joint formula unmanned aerial vehicle, the folding arm mechanism of joint formula unmanned aerial vehicle includes: fuselage cantilever arm, horn and buckle sleeve, the horn is articulated extremely the fuselage cantilever arm, buckle sleeve cover is established the horn with on one in the fuselage cantilever arm, be provided with first joint portion on the buckle sleeve, the horn with be provided with second joint portion on another in the fuselage cantilever arm, under the horn stretches out the arm for the fuselage and opens the condition, first joint portion and the mutual joint of second joint portion. The problem of its solution is mainly the inconvenient problem of the folding wall connected mode of current unmanned aerial vehicle, with the utility model discloses the scheme is different.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the above problem, a folding convenient many rotor unmanned aerial vehicle folding mechanism who has firm reliable is provided.
In order to achieve the above object, the utility model provides a following technical scheme:
a folding mechanism of a multi-rotor unmanned aerial vehicle comprises a horn installation seat and side fixing pieces connected with the two sides of the horn installation seat, wherein concentric cylindrical pins are respectively arranged on the left side and the right side of the horn installation seat, a through hole is formed in one end of each side fixing piece, and the horn installation seat and the side fixing pieces are connected through the fit connection of the concentric cylindrical pins and the through holes;
the arm mounting base rotates by taking the concentric cylindrical pin as an axis, so that the folding function of the unmanned aerial vehicle is realized; a limiting pin is arranged above the through hole and used for limiting the arm mounting seat when the unmanned aerial vehicle is unfolded;
a threaded gasket is arranged above the side fixing piece and detachably connected and fixed with the machine arm mounting seat; a plurality of screw holes are all opened at both ends about the side stationary blade, connect and fixed unmanned aerial vehicle fuselage through the screw hole.
Preferably, the threaded gasket is fixed to the horn attachment base by a fixing bolt.
Preferably, the threaded holes are respectively provided with three upper threaded holes and three lower threaded holes.
The beneficial effects of the utility model reside in that:
the utility model discloses an arm mount pad uses concentric cylindric lock as the axle center rotation, realizes unmanned aerial vehicle's folding function, sets up the spacer pin through the through-hole junction top at concentric cylindric lock and side stationary blade, carries on spacingly to the unmanned aerial vehicle arm mount pad when expanding, has guaranteed that unmanned aerial vehicle transports folding convenient while can reliably firmly expand the flight again, makes unmanned aerial vehicle organism rigidity and flight performance not receive or reduce folding mechanism's influence, and is safe convenient again.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only for the purpose of more clearly illustrating the embodiments of the present invention or the technical solutions in the prior art, and for those skilled in the art, other drawings can be obtained according to these drawings without any creative efforts.
FIG. 1 is a schematic view of the main structure of the present invention;
fig. 2 is a schematic structural view of the boom mount of the present invention when it is unfolded;
fig. 3 is a schematic structural view of the arm mounting base of the present invention when folded.
Detailed Description
In order to make the technical solution of the present invention better understood by those skilled in the art, the present invention will be further described with reference to the following specific embodiments, which are not intended to limit the present invention.
As shown in fig. 1-3, the folding mechanism of the multi-rotor unmanned aerial vehicle comprises a horn installation base 1 and side fixing pieces 2 connected to two sides of the horn installation base 1, wherein concentric cylindrical pins 11 are respectively arranged on the left side and the right side of the horn installation base 1, a through hole 21 is formed in one end of each side fixing piece 2, and the connection between the horn installation base 1 and the side fixing pieces 2 is realized through the matching connection between the concentric cylindrical pins 11 and the through holes 21;
the arm mounting base 1 rotates by taking the concentric cylindrical pin 11 as an axis, so that the folding function of the unmanned aerial vehicle is realized; a limiting pin 22 is arranged above the through hole 21, and the limiting pin 22 is used for limiting the arm mounting base 1 when the unmanned aerial vehicle is unfolded;
a threaded gasket 3 is arranged above the side fixing piece 2, and the threaded gasket 3 is detachably connected and fixed with the machine arm mounting seat 1; a plurality of threaded holes 23 are all opened at both ends about the side stationary blade 2, connect and fixed unmanned aerial vehicle fuselage through threaded holes 23.
Preferably, the threaded washer 3 is fixed to the horn attachment base 1 by a fixing bolt 31.
Preferably, the threaded holes 23 are opened three at the top and three at the bottom.
The folding and unfolding functions of the folding mechanism of the multi-rotor unmanned aerial vehicle are realized by rotating the horn mounting seat 1 by taking the concentric cylindrical pin 11 as the axis; it is fixed through fixing bolt 31 when folding, and spacing round pin 22 through the through-hole 21 junction top setting at concentric cylindric lock 11 and side stationary blade carries on spacingly to unmanned aerial vehicle horn mount pad 1 when expanding.
The utility model provides a risk, organism rigidity loss, the folding mechanism pine that unmanned aerial vehicle folding mechanism exists among the prior art take off or have the problem of rocking the clearance, guaranteed that unmanned aerial vehicle transportation folding convenient while can reliably firmly launch the flight again, make unmanned aerial vehicle organism rigidity and flight performance not receive or reduce folding mechanism's influence, it is safe convenient again.
The present invention is not described in detail in the prior art.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The folding mechanism of the multi-rotor unmanned aerial vehicle is characterized by comprising a horn installation seat (1) and side fixing pieces (2) connected with the horn installation seat at two sides, wherein concentric cylindrical pins (11) are respectively arranged at the left side and the right side of the horn installation seat (1), one ends of the side fixing pieces (2) are provided with through holes (21), and the connection of the horn installation seat (1) and the side fixing pieces (2) is realized through the matching connection of the concentric cylindrical pins (11) and the through holes (21);
the arm mounting seat (1) rotates by taking the concentric cylindrical pin (11) as an axis, so that the folding function of the unmanned aerial vehicle is realized; a limiting pin (22) is arranged above the through hole (21), and the limiting pin (22) is used for limiting the arm mounting seat (1) when the unmanned aerial vehicle is unfolded;
a threaded gasket (3) is arranged above the side fixing piece (2), and the threaded gasket (3) is detachably connected and fixed with the machine arm mounting seat (1); both ends all opened a plurality of screw holes (23) about side stationary blade (2), connect and fixed unmanned aerial vehicle fuselage through screw hole (23).
2. A folding mechanism for multi-rotor unmanned aerial vehicles according to claim 1, wherein the threaded spacer (3) is fixed to the horn mount (1) by a fixing bolt (31).
3. A folding mechanism for a multi-rotor drone according to claim 1 or 2, characterised in that the threaded holes (23) are respectively opened three above and three below.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920290481.2U CN209972770U (en) | 2019-03-07 | 2019-03-07 | Many rotor unmanned aerial vehicle folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920290481.2U CN209972770U (en) | 2019-03-07 | 2019-03-07 | Many rotor unmanned aerial vehicle folding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209972770U true CN209972770U (en) | 2020-01-21 |
Family
ID=69254148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920290481.2U Expired - Fee Related CN209972770U (en) | 2019-03-07 | 2019-03-07 | Many rotor unmanned aerial vehicle folding mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209972770U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021196135A1 (en) * | 2020-03-30 | 2021-10-07 | 南京达索航空科技有限公司 | Unmanned aerial vehicle folding mechanism |
-
2019
- 2019-03-07 CN CN201920290481.2U patent/CN209972770U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021196135A1 (en) * | 2020-03-30 | 2021-10-07 | 南京达索航空科技有限公司 | Unmanned aerial vehicle folding mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20200121 |