CN214648991U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN214648991U CN214648991U CN202120649904.2U CN202120649904U CN214648991U CN 214648991 U CN214648991 U CN 214648991U CN 202120649904 U CN202120649904 U CN 202120649904U CN 214648991 U CN214648991 U CN 214648991U
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- Prior art keywords
- rotating shaft
- base
- aerial vehicle
- unmanned aerial
- horn
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- Expired - Fee Related
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- 239000007787 solid Substances 0.000 claims description 3
- 238000012856 packing Methods 0.000 abstract description 5
- 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 abstract 1
- 230000020347 spindle assembly Effects 0.000 description 5
- 238000010079 rubber tapping Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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Abstract
The utility model discloses an unmanned aerial vehicle, it includes fuselage, pivot subassembly and horn, the pivot unit mount is in the fuselage, the horn is installed in the pivot subassembly, the horn can revolute the pivot subassembly and expand the position and rotate between the folding position, the pivot subassembly includes base, pivot and elastic component, pedestal mounting is in the fuselage, the pivot is rotatable to be installed in the base, the horn is connected with the pivot, the pivot is located to the elastic component cover for provide the frictional force between pivot and the base, wherein, the elastic component includes the wave form packing ring of a plurality of range upon range of settings. The utility model discloses an unmanned aerial vehicle sets up to the wave washer through the elastic component with the pivot subassembly, and for the mode of current adoption cylindrical spring, the elastic component that the wave washer formed, length is littleer, can effectively reduce the length of pivot subassembly to reduce the length of horn root, and then reduce unmanned aerial vehicle complete machine width, make unmanned aerial vehicle light small and exquisite more.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to an unmanned aerial vehicle.
Background
Through setting up the pivot subassembly between current unmanned aerial vehicle's the fuselage and the horn, the pivot subassembly is connected with the fuselage, and the horn is connected with the pivot subassembly, and the horn can be around the pivot subassembly rotatory between expansion position and folding position, and during the use, the horn is rotatory to expansion position, and when not needing the use, the horn is rotatory to folding position to in accomodate and carry.
Present unmanned aerial vehicle, the pivot subassembly size is longer for the root that horn and pivot subassembly are connected is longer, leads to unmanned aerial vehicle complete machine width great, can't accomplish the light weight small and exquisite.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides an unmanned aerial vehicle.
The utility model provides an unmanned aerial vehicle, including fuselage, pivot subassembly and horn, the pivot unit mount in the fuselage, the horn install in the pivot subassembly, the horn can wind the pivot subassembly is rotatory between expansion position and folding position, the pivot subassembly includes:
a base mounted to the body;
the rotating shaft is rotatably arranged on the base, and the machine arm is connected with the rotating shaft;
the elastic piece is sleeved on the rotating shaft and used for providing friction force between the rotating shaft and the base;
wherein the elastic member includes a plurality of wave washers stacked one on another.
According to the technical scheme, the utility model provides an unmanned aerial vehicle sets up the elastic component through with the pivot subassembly into the wave form packing ring, and for the mode of current adoption cylindrical spring, the elastic component that the wave form packing ring formed, length is littleer, can effectively reduce the length of pivot subassembly to reduce the length of horn root, and then reduce unmanned aerial vehicle complete machine width, make unmanned aerial vehicle light small and exquisite more.
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 some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without any creative effort.
Fig. 1 is a schematic view of a partial structure cross section of an unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 2 is an enlarged partial schematic view at A of FIG. 1;
fig. 3 is a schematic structural view of a rotating shaft assembly according to another embodiment of the present invention;
FIG. 4 is a schematic structural view of a wave washer of the spindle assembly shown in FIG. 3;
FIG. 5 is a schematic view of the spindle assembly of FIG. 1;
FIG. 6 is a top schematic view of the spindle assembly of FIG. 1;
fig. 7 is a schematic view of a cross-sectional view of a part of an unmanned aerial vehicle according to another embodiment of the present invention;
FIG. 8 is an enlarged partial schematic view at B of FIG. 7;
FIG. 9 is a schematic structural view of the spindle assembly shown in FIG. 7;
FIG. 10 is a top schematic view of the spindle assembly of FIG. 7;
fig. 11 is a schematic structural view of the end face of the arm root of the drone shown in fig. 7.
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 some, not all, of the embodiments of the present invention. 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.
It is also to be understood that the terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
It should be further understood that the term "and/or" as used in the specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes such combinations.
As shown in fig. 1 and fig. 2, an embodiment of the present invention provides an unmanned aerial vehicle, which includes a body 11, a rotating shaft assembly 12 and a boom 13, wherein the rotating shaft assembly 12 is installed on the body 11, the boom 13 is installed on the rotating shaft assembly 12, and the boom 13 can rotate around the rotating shaft assembly 12 between an unfolding position and a folding position.
The rotating shaft assembly 12 includes a base 121, a rotating shaft 122 and an elastic member 123, the base 121 is mounted on the body 11, the rotating shaft 122 is rotatably mounted on the base 121, the arm 13 is connected to the rotating shaft 122, the rotating shaft 122 is sleeved with the elastic member 123, and the elastic member 123 is used for providing a friction force between the rotating shaft 122 and the base 121. When the arm 13 is rotated, the arm 13 drives the shaft 122 to rotate relative to the base 121.
As shown in fig. 3 and 4, in some embodiments, the resilient member 123 'includes a plurality of wave washers 1231' arranged in a stack. Through setting up the elastic component 123 'with pivot subassembly 12' into the wave form packing ring 1231 'of a plurality of range upon range of settings, for current adoption cylindrical spring's mode, the elastic component 123 'that wave form packing ring 1231' formed, length is littleer, can effectively reduce pivot subassembly 12 ''s length to reduce the length of horn root, and then reduce unmanned aerial vehicle complete machine width, make unmanned aerial vehicle light and small and exquisite more.
As shown in fig. 2 and 5, the base 121 illustratively includes a bottom plate 1211 and a boss 1212 protruding from the bottom plate 1211, the bottom plate 1211 is used for connecting with the body 11, and the base 121 is provided with a through hole 1213 extending through the bottom plate 1211 and the boss 1212. The rotating shaft 122 includes a shaft portion 1221 and a retaining portion 1222, the shaft portion 1221 includes a first end 1221a and a second end 1221b, the shaft portion 1221 is rotatably disposed through the through hole 1213, and the retaining portion 1222 is mounted at the first end 1221a of the shaft portion 1221 and is clamped at a side of the bottom plate 1211 opposite to the boss 1212. One end of the elastic member 123 abuts against the boss 1212, the other end of the elastic member 123 abuts against the second end 1221b of the shaft portion 1221, and the elastic member 123 is in a compressed state, so that there is a friction force between the bottom plate 1211 and the catch 1222, and the rotating shaft 122 and the base 121 can smoothly rotate, that is, the arm 13 can smoothly rotate.
In some embodiments, the rotating shaft assembly 12 further includes a sleeve 124, the sleeve 124 is sleeved outside the rotating shaft 122, the elastic member 123 is received inside the sleeve 124, one end of the sleeve 124 away from the base 121 abuts against the second end 1221b of the rotating shaft 122, and one end of the elastic member 123 away from the base 121 abuts against the sleeve 124.
Optionally, the unmanned aerial vehicle further comprises a first fastener 14, the rotating shaft assembly 12 is provided with a first locking portion 1214, and the first fastener 14 penetrates through the fuselage 11 and is connected with the first locking portion 1214 to fasten the rotating shaft assembly 12 to the fuselage 11. Present unmanned aerial vehicle adopts self tapping screw fastening's mode to fasten pivot subassembly 12 on fuselage 11 more, and this design need set up great wall thickness cooperation self tapping screw fastening on fuselage 11, leads to unmanned aerial vehicle's size great, and weight is big. In this embodiment, through set up first locking portion 1214 on pivot subassembly 12, first fastener 14 passes fuselage 11 and is connected with first locking portion 1214, and like this, fuselage 11 need not to set up great wall thickness, can effectively reduce unmanned aerial vehicle size, reduces unmanned aerial vehicle's weight simultaneously.
Optionally, the first fastener 14 is a machine-threaded screw.
As shown in fig. 2 and 5, the first locking portion 1214 is optionally a first screw hole 1214 formed in the base 121, and the first fastening member 14 passes through the body 11 and is threadedly coupled to the first screw hole 1214.
Optionally, the base 121 further includes a first protrusion 1215 disposed on a side of the bottom plate 1211 away from the body 11, and the first screw hole 1214 extends through the first protrusion 1215, and this embodiment is intended to provide a longer first screw hole 1214 on the base 121, so that the first fastening member 14 can be stably connected with the base 121. By providing the first protrusion 1215, the base 1211 having a large thickness does not need to be designed, so that the weight of the rotating shaft assembly 12 can be reduced, and the weight of the unmanned aerial vehicle can be reduced. Of course, the base 121 is not provided with the first projection 1215, but it is possible to provide the bottom plate 1211 with a thicker thickness, depending on the actual design requirements.
Alternatively, the first locking portion is a first nut (not shown) disposed on a side of the base 121 opposite to the body 11, and the first fastening member 14 passes through the body 11 and the base 121 and is screwed with the first nut. It should be noted that the first nut may also be disposed on a side of the body 11 opposite to the base 121, and the first fastening member 14 passes through the base 121 and the body 11 and is in threaded connection with the first nut. This embodiment does not need fuselage 11 to set up great wall thickness equally, can effectively alleviate the weight of fuselage 11 and reduce unmanned aerial vehicle's width.
As shown in fig. 2, 5 and 6, optionally, the rotating shaft 122 further includes a connecting portion 1223, the connecting portion 1223 includes a first extending portion 1224 and a second extending portion 1225, the first extending portion 1224 is connected to the shaft portion 1223, the second extending portion 1225 extends from the first extending portion 1224 toward the base 121, and the arm 13 is sleeved outside the rotating shaft 122 and connected to the second extending portion 1225. Through setting up second extension 1225 to extend towards base 121, set up second extension 1225 relatively to the mode that extends towards keeping away from base 121 direction, can shorten the length of pivot subassembly 12 to can shorten the length of horn 13 root, make the width of unmanned aerial vehicle complete machine littleer. An end of the sleeve 124 remote from the base 121 abuts the connection 1223.
Illustratively, the number of the second extending portions 1225 is two, two second extending portions 1225 are disposed on two opposite sides of the shaft portion 1221, and the arm 13 is sleeved outside the rotating shaft 122 and connected to the two second extending portions 1225. The number of the second extending portions 1225 is two, so that the connection strength between the horn 13 and the rotating shaft 122 can be improved, stress on the rotating shaft 122 is balanced when the horn 13 rotates, and the service life of the rotating shaft 122 can be prolonged. The number of the second extension portions 1225 is not limited to two, and may be one or more than two.
Optionally, the drone further comprises a second fastener (not shown), and the second extension 1225 is provided with a second locking portion 1226, and the second fastener passes through the horn 13 and is connected with the second locking portion 1226 to fasten the horn 13 to the second extension 1225.
Alternatively, the second locking portion 1226 is a second screw hole 1226 provided in the second extension 1225, and the second fastening member passes through the second extension 1225 and is threadedly coupled to the second screw hole 1226.
Optionally, the connecting portion 1223 further includes a second protrusion 1227 disposed on a side of the second extending portion 1225 opposite to the horn 13, and the second screw hole 1226 extends through the second extending portion 1225 and the second protrusion 1227, and this embodiment is intended to provide a longer second screw hole 1226 on the second extending portion 1225, so that the second fastening member and the base 121 can be stably connected. It should be noted that the second projection 1227 may be provided on the side of the second extension 1225 facing the horn 13. Of course, the second extension 1225 is not provided with the second projection 1227, and it is also possible to provide the second extension 1225 with a thicker thickness, depending on the actual design requirement.
Optionally, the rotating shaft 122 is a hollow structure for the cable 200 to pass through. The cable 200 inside the body 11 can pass through the rotating shaft 122 and then be connected with the motor mounted with the arm 13.
As shown in fig. 7 and 8, another embodiment of the present invention provides an unmanned aerial vehicle, which includes a body 21, a rotating shaft assembly 22 and a boom 23, wherein the rotating shaft assembly 22 is installed on the body 21, the boom 23 is installed on the rotating shaft assembly 22, and the boom 23 can rotate around the rotating shaft assembly 22 between an unfolded position and a folded position.
The rotating shaft assembly 22 includes a base 221, a rotating shaft 222 and an elastic member 223, the base 221 is mounted on the body 21, the rotating shaft 222 is rotatably mounted on the base 221, the arm 23 is connected to the rotating shaft 222, the elastic member 123 is sleeved on the rotating shaft 222, and the elastic member 223 is used for providing a friction force between the rotating shaft 222 and the base 221. When the arm 23 is rotated, the arm 23 drives the shaft 222 to rotate relative to the base 221.
In some embodiments, the resilient member 223 comprises a plurality of wave washers arranged in a stack. Through setting up the elastic component 223 with pivot subassembly 22 into wave washer, for the mode of current adoption cylindrical spring, the elastic component 223 that wave washer formed, length is littleer, can effectively reduce pivot subassembly 22's length to reduce the length of horn 23 root, reduce unmanned aerial vehicle complete machine width, make unmanned aerial vehicle light small and exquisite more.
As shown in fig. 8 and 9, the base 221 illustratively includes a bottom plate 2211 and a boss 2212 protruding from the bottom plate 2211, the bottom plate 2211 is used for connecting to the body 21, and the base 221 is provided with a through hole 2213 penetrating through the bottom plate 2211 and the boss 2212. The rotating shaft 222 includes a shaft portion 2221 and a retaining portion 2222, the shaft portion 2221 includes a first end 2221a and a second end 2221b, the shaft portion 2221 is rotatably disposed through the through hole 2213, and the retaining portion 2222 is mounted at the first end 2221a of the shaft portion 2221 and is clamped at one side of the bottom plate 2211 opposite to the boss 2212. One end of the elastic member 223 abuts against the boss 2212, the other end of the elastic member 223 abuts against the second end 2221b of the shaft portion 2221, and the elastic member 223 is in a compressed state, so that friction force exists between the bottom plate 2211 and the holding portion 2222, and the rotating shaft 222 and the base 221 can rotate smoothly, that is, the machine arm 23 can rotate smoothly.
In some embodiments, the rotating shaft assembly 22 further includes a sleeve 224, the sleeve 224 is sleeved outside the rotating shaft 222, the elastic member 223 is received inside the sleeve 224, one end of the sleeve 224 away from the base 221 abuts against the second end 2221b of the rotating shaft 222, and one end of the elastic member 223 away from the base 221 abuts against the sleeve 224.
Optionally, the unmanned aerial vehicle further comprises a first fastener 24, the rotating shaft assembly 22 is provided with a first locking portion 2214, and the first fastener 24 penetrates through the body 21 and is connected with the first locking portion 2214 to fasten the rotating shaft assembly 22 to the body 21. Present unmanned aerial vehicle adopts self tapping screw fastening's mode to fasten pivot subassembly 22 on fuselage 21 more, and this design need set up great wall thickness cooperation self tapping screw fastening on fuselage 21, leads to unmanned aerial vehicle's size great, and weight is big. In this embodiment, through set up first locking portion 2214 on pivot subassembly 22, first fastener 24 passes fuselage 21 and is connected with first locking portion 2214, and like this, fuselage 21 need not to set up great wall thickness, can effectively reduce unmanned aerial vehicle size, reduces unmanned aerial vehicle's weight simultaneously.
Optionally, the first fastener 24 is a machine-threaded screw.
As shown in fig. 8 and 9, the first locking portion 2214 is a first screw hole 2214 provided on the base 221, and the first fastening member 24 passes through the body 21 and is screwed with the first screw hole 2214.
Alternatively, the first locking portion 2214 is a first nut (not shown) disposed on a side of the base 221 opposite to the body 21, and the first fastening member 24 passes through the body 21 and the base 221 and is screwed with the first nut. It should be noted that the first nut may also be disposed on a side of the body 21 opposite to the base 221, and the first fastening member 24 passes through the base 221 and the body 21 and is screwed with the first nut. This embodiment does not need fuselage 21 to set up great wall thickness equally, can effectively alleviate the weight of fuselage 21 and reduce unmanned aerial vehicle's width.
As shown in fig. 8 to 10, optionally, the rotating shaft 222 further includes a connecting portion 2223, the connecting portion 2223 includes a first extending portion 2224 and a second extending portion 2225, the first extending portion 2224 is connected with the shaft portion 2221, the second extending portion 2225 extends from the first extending portion 2224 toward the base 221, and the arm 23 is sleeved outside the rotating shaft 222 and connected with the second extending portion 2225. Through setting up second extension 2225 to extending towards base 221, set up second extension 2225 to the mode that extends towards keeping away from base 221 direction, can shorten the length of pivot subassembly 22 relatively to can shorten the length of horn 23 root, make the width of unmanned aerial vehicle complete machine littleer, unmanned aerial vehicle is more small and exquisite. An end of the sleeve 224 remote from the base 221 abuts the connection portion 2223.
For example, the number of the second extending portions 2225 is one, and the arm 23 is sleeved outside the rotating shaft 222 and connected to the second extending portions 2225. It should be noted that the number of the second extending portions 2225 is not limited to one, and may be more than one.
Optionally, the drone further includes a second fastener (not shown), and the second extending portion 2225 is provided with a second locking portion 2226, and the second fastener passes through the horn 23 and is connected to the second locking portion 2226 to lock the horn 23 to the second extending portion 2225.
Alternatively, the second locking portion 2226 is a second screw hole 2226 formed in the second extending portion 2225, and a second fastening member is inserted through the second extending portion 2225 and threadedly coupled to the second screw hole 2226.
Optionally, the connecting portion 2223 further includes a second protrusion 2227 disposed on a side of the second extending portion 2225 facing the horn 23, and a second screw hole 2226 extends through the second extending portion 2225 and the second protrusion 2227, and this embodiment aims to provide a longer second screw hole 2226 on the second extending portion 2225, so that the second fastening member and the base 221 can be stably connected. It should be noted that the second projection 2227 may be disposed on a side of the second extending portion 2225 opposite to the horn 23. Of course, the second extension 2225 is not provided with the second projection 2227, and it is also possible to provide the second extension 2225 with a thicker thickness, depending on the actual design requirements.
As shown in fig. 8 and 11, optionally, the rotating shaft 222 is a solid structure, and the arm 23 includes a connecting end 231 connected to the rotating shaft 222, and the connecting end 231 is provided with a wire hole 232 for the cable 200 to pass through. Through setting up pivot 222 to solid construction, satisfying under the condition of intensity, can effectively reduce the external diameter of pivot 222 subassembly, and then reduce the diameter of horn 23 root, reduce unmanned aerial vehicle's size and weight.
Alternatively, a wire hole 232 is formed in an end surface 233 of the connection end 231, and the wire hole 232 has an arc shape disposed around the rotation axis of the horn 23. By providing the routing hole 232 in the shape of an arc surrounding the rotation axis of the horn 23, in this embodiment, a sufficient space is formed to avoid the cable 200, and the horn 23 is prevented from pulling the cable 200 during the rotation process.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical scope of the present invention, and these modifications or replacements should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides an unmanned aerial vehicle, its characterized in that, includes fuselage, pivot subassembly and horn, the pivot subassembly install in the fuselage, the horn install in the pivot subassembly, the horn can wind the pivot subassembly is rotatory between expansion position and folding position, the pivot subassembly includes:
a base mounted to the body;
the rotating shaft is rotatably arranged on the base, and the machine arm is connected with the rotating shaft;
the elastic piece is sleeved on the rotating shaft and used for providing friction force between the rotating shaft and the base;
wherein the elastic member includes a plurality of wave washers stacked one on another.
2. The drone of claim 1, further comprising a first fastener, the shaft assembly being provided with a first locking portion, the first fastener passing through the fuselage and being connected with the first locking portion to fasten the shaft assembly to the fuselage.
3. The unmanned aerial vehicle of claim 2, wherein the first locking portion is a first screw hole formed in the base, and the first fastener passes through the fuselage and is in threaded connection with the first screw hole.
4. The unmanned aerial vehicle of claim 2, wherein the first locking portion is a first nut disposed on a side of the base opposite to the fuselage, and the first fastener passes through the fuselage and the base and is in threaded connection with the first nut.
5. The drone of claim 1, wherein the shaft includes:
the shaft part is rotatably connected with the base;
the connecting part comprises a first extending part and a second extending part, the first extending part is connected with the shaft part, the second extending part extends from the first extending part towards the base, and the machine arm is sleeved outside the rotating shaft and is connected with the second extending part.
6. The drone of claim 5, further comprising a second fastener, the second extension being provided with a second locking portion, the second fastener passing through the horn and being connectively connected to the second locking portion to secure the horn to the second extension.
7. The unmanned aerial vehicle of claim 6, wherein the second locking portion is a second screw hole provided in the second extension portion, and the second fastener passes through the second extension portion and is in threaded connection with the second screw hole.
8. The unmanned aerial vehicle of claim 1, wherein the rotating shaft is a hollow structure for a cable to pass through.
9. The unmanned aerial vehicle of claim 1, wherein the rotating shaft is a solid structure, the arm includes a connecting end connected with the rotating shaft assembly, and the connecting end is provided with a wire hole for a cable to pass through.
10. An unmanned aerial vehicle as defined in claim 9, wherein the wire hole is formed in an end surface of the connecting end, and the wire hole is shaped as an arc surrounding the rotating shaft of the arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120649904.2U CN214648991U (en) | 2021-03-29 | 2021-03-29 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120649904.2U CN214648991U (en) | 2021-03-29 | 2021-03-29 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214648991U true CN214648991U (en) | 2021-11-09 |
Family
ID=78457578
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120649904.2U Expired - Fee Related CN214648991U (en) | 2021-03-29 | 2021-03-29 | Unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214648991U (en) |
-
2021
- 2021-03-29 CN CN202120649904.2U patent/CN214648991U/en not_active Expired - Fee Related
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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 |
Granted publication date: 20211109 |
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| CF01 | Termination of patent right due to non-payment of annual fee |