CN112339985A - Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle Download PDFInfo
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- CN112339985A CN112339985A CN202011333304.1A CN202011333304A CN112339985A CN 112339985 A CN112339985 A CN 112339985A CN 202011333304 A CN202011333304 A CN 202011333304A CN 112339985 A CN112339985 A CN 112339985A
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- aerial vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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Abstract
The utility model provides an unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle, unmanned aerial vehicle power horn rapid disassembly structure includes: the machine arm connecting component is used for installing the socket component; the machine arm assembly is used for mounting the plug assembly; the first end of the horn assembly is mounted with the first end of the horn connecting assembly in a matched manner; the disassembling and assembling assembly is used for disassembling and assembling the machine arm connecting assembly and the machine arm assembly; the disassembling and assembling component is sleeved at the first end of the machine arm component and the first end of the machine arm connecting component; the socket assembly is used for being plugged with the plug assembly; the socket assembly is arranged at the first end of the horn connecting assembly; the plug assembly is used for being plugged with the socket assembly; the plug assembly is arranged at the first end of the horn assembly. This application can realize the horn simultaneously and be connected the axial, radial and the circumference location of position with the fuselage, even cup joint the nut and have some screw thread pine to take off, whole connection structure's axial positioning, radial location and circumference location are still effective.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a quick-release structure of a power arm of an unmanned aerial vehicle and the unmanned aerial vehicle.
Background
The unmanned aerial vehicle power horn is one of main structure spare on the unmanned aerial vehicle flight platform, and the mounted position that provides the motor generally has the overall arrangement of four groups, six groups or even 8 groups, distributes at fuselage four-axis, is connected with the fuselage. Generally, due to the rotating space requirement of the rotor, the power horn must have a certain length so that the rotor does not interfere with the fuselage or other structural members when rotating. The development of the unmanned aerial vehicle industry has higher and higher requirements on products, and one of the most important is to pursue the portability of the products. The relatively long size of the power arm assembly seriously affects the portability of the product.
In view of the above problems, one of the current methods is to make the power arm foldable, but this method has the following disadvantages: (1) the folding horn form usually can not carry on the axial and radial positioning at the same time, lead to the structural stability is not good, can cause the horn to shake while flying in great maneuvering, influence the flight safety; (2) the folding horn form can only realize the folding of horn structure, and inside electrical signal still uses cable wire to connect, and the pleasing to the eye degree is relatively poor. Meanwhile, if the machine arm is damaged and needs to be maintained, the internal connecting line of the machine body needs to be detached, which is very inconvenient.
Alternatively, the power horn is connected to the fuselage using a screw structure and the electrical signal connection is connected using a connector to achieve both structural and electrical synchronization of the connection and disconnection, but this method has the following disadvantages: the axial positioning of this kind of design is realized through outside cup joint nut, and radial positioning is realized through horn face of cylinder and fuselage face of cylinder, and both realize alone, and the cup joint nut when the outside loosens a bit a little slightly, and axial positioning will lose efficacy to lead to electrical connection to become invalid, and then influence flight safety.
Disclosure of Invention
In view of the above problems, the present invention provides a quick release structure of a power arm of an unmanned aerial vehicle and an unmanned aerial vehicle, which overcomes or at least partially solves the above problems.
In order to solve the technical problem, the invention provides a quick-release structure of a power arm of an unmanned aerial vehicle, which comprises:
the machine arm connecting component is used for installing the socket component;
the machine arm assembly is used for mounting the plug assembly; the first end of the horn assembly is mounted with the first end of the horn connecting assembly in a matched manner;
the disassembling and assembling assembly is used for disassembling and assembling the machine arm connecting assembly and the machine arm assembly; the disassembling and assembling component is sleeved at the first end of the machine arm component and the first end of the machine arm connecting component;
the socket assembly is used for being plugged with the plug assembly; the socket assembly is arranged at the first end of the horn connecting assembly;
the plug assembly is used for being plugged with the socket assembly; the plug assembly is arranged at the first end of the horn assembly;
wherein, work as the first end of horn subassembly with during the first end adaptation installation of horn coupling assembling, dismouting subassembly cover is located the first end of horn subassembly with the first end of horn coupling assembling, just socket component correspond with plug subassembly connects.
Preferably, the horn connecting assembly is fixed to the body.
Preferably, the horn connecting assembly comprises: the connecting pipe is arranged on the outer side wall of the machine body, the pressing plate is arranged on the inner side wall of the machine body, and the fastening screws are sequentially screwed on the connecting pipe, the machine body and the pressing plate.
Preferably, a sealing ring is arranged between the connecting pipe and the machine body in a sealing manner.
Preferably, the horn assembly comprises: the horn comprises a horn carbon tube and a horn, wherein the horn carbon tube is inserted in the horn.
Preferably, the disassembling and assembling assembly comprises: and the sleeve nut is screwed on the connecting pipe in the machine arm connecting component and the machine arm carbon tube in the machine arm component.
Preferably, an internal thread is arranged on the inner wall of the socket nut, a first external thread is arranged on the outer wall of the connecting pipe, a second external thread is arranged on the outer wall of the horn carbon tube, when the socket nut is sleeved on the connecting pipe, the internal thread is meshed with the first external thread, and when the socket nut is sleeved on the horn carbon tube, the internal thread is meshed with the second external thread.
Preferably, the socket assembly comprises: first circuit board and female head, wherein, first circuit board set up in horn coupling assembling's the connecting pipe, female head set up in on the first circuit board.
Preferably, the plug assembly comprises: the second circuit board is arranged in the horn carbon tube of the horn component, and the male head is arranged on the second circuit board.
The invention also provides an unmanned aerial vehicle which comprises the unmanned aerial vehicle power arm quick-release structure.
One or more technical solutions in the embodiments of the present invention have at least the following technical effects or advantages: the application provides a pair of unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle have following advantage:
(1) the axial, radial and circumferential positioning of the connecting part of the horn and the fuselage can be realized simultaneously, even if a part of threads of the sleeve nut with the fastening effect are loosened under the conditions of large overload and large vibration, the axial positioning, the radial positioning and the circumferential positioning of the whole connecting structure are still effective, the electric connection is not loosened, and the reliability of structural connection and the safety of flight are ensured;
(2) the modularization degree of the unmanned aerial vehicle product is improved;
(3) the reliability of the connection between the machine arm and the machine body is improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed 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 it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
Fig. 1 is a schematic overall structural diagram of a carbon tube structure of a power arm of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic diagram of an explosion structure of a carbon tube structure of a power arm of an unmanned aerial vehicle according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail below with reference to specific embodiments and examples, and the advantages and various effects of the present invention will be more clearly apparent therefrom. It will be understood by those skilled in the art that these specific embodiments and examples are for the purpose of illustrating the invention and are not to be construed as limiting the invention.
Throughout the specification, unless otherwise specifically noted, terms used herein should be understood as having meanings as commonly used in the art. Accordingly, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. If there is a conflict, the present specification will control.
Unless otherwise specifically stated, various raw materials, reagents, instruments, equipment and the like used in the present invention are commercially available or can be prepared by existing methods.
As shown in fig. 1-2, in the embodiment of the present application, the present invention provides a carbon tube structure of a power arm of an unmanned aerial vehicle, including:
a horn connecting assembly 10 for mounting a socket assembly 40;
a horn assembly 20 for mounting a plug assembly 50; the first end of the horn assembly 20 is fittingly mounted with the first end of the horn connecting assembly 10;
the disassembling and assembling assembly 30 is used for disassembling and assembling the horn connecting assembly 10 and the horn assembly 20; the disassembling and assembling component 30 is sleeved at the first end of the horn component 20 and the first end of the horn connecting component 10;
a receptacle assembly 40 for mating with the plug assembly 50; the socket assembly 40 is disposed at a first end of the horn connecting assembly 10;
a plug assembly 50 for mating with the receptacle assembly 40; the plug assembly 50 is disposed at a first end of the horn assembly 20;
wherein, when the first end of horn subassembly 20 with the first end adaptation installation of horn coupling assembling 10, dismouting subassembly 30 cover is located the first end of horn subassembly 20 with the first end of horn coupling assembling 10, just socket component 40 correspond with plug component 50 is connected.
When the unmanned aerial vehicle power horn carbon tube structure is used, firstly, the horn connecting assembly 10 is arranged on the unmanned aerial vehicle, the socket assembly 40 is arranged at the first end of the horn connecting assembly 10, the socket assembly 40 is connected with the unmanned aerial vehicle, then, the plug assembly 50 is arranged at the first end of the horn assembly 20, then, the dismounting assembly 30 is sleeved on the first end of the horn assembly 20 and the first end of the horn connecting assembly 10, the first end of the horn assembly 20 is matched and installed with the first end of the horn connecting assembly 10, at the moment, the socket assembly 40 is correspondingly connected with the plug assembly 50, and stable mechanical connection and electric connection are achieved between the horn assembly 20 and the unmanned aerial vehicle.
In the present embodiment, the horn linkage assembly 10 is secured to a fuselage 11, as shown in fig. 1-2. The horn linkage assembly 10 may be fastened to the body 11 by screws.
As shown in fig. 1-2, in the embodiment of the present application, the horn linkage assembly 10 includes: connecting pipe 12, clamp plate 13 and fastening screw 14, wherein, connecting pipe 12 set up in on the lateral wall of fuselage 11 and clamp plate 13 set up in on the inside wall of fuselage 11, fastening screw 14 screws in proper order connecting pipe 12 fuselage 11 with clamp plate 13. The pressing plate 13 is arranged inside the unmanned aerial vehicle and is tightly attached to the inner side wall of the body 11; the connecting pipe 12 is arranged outside the unmanned aerial vehicle and is tightly attached to the outer side wall of the body 11; the connecting pipe 12, the pressure plate 13 and the body 11 are fastened and connected through a fastening screw 14.
In the embodiment of the present application, as shown in fig. 1-2, a sealing ring 15 is sealingly disposed between the connecting pipe 12 and the body 11. The sealing ring 15 is tightly attached to the side walls of the body 11 and the connecting pipe 12, thereby enhancing the sealing between them.
As shown in fig. 1-2, in the embodiment of the present application, the horn assembly 20 includes: the horn comprises a horn carbon tube 21 and a horn 22, wherein the horn carbon tube 21 is inserted into the horn 22. The horn carbon tube 21 is inserted into the horn 22, and the two are screwed together by a screw.
As shown in fig. 1-2, in the embodiment of the present application, the dismounting assembly 30 includes: and the sleeve nut 31 is screwed on the connecting pipe 12 in the horn connecting assembly 10 and the horn carbon tube 21 in the horn assembly 20 by the sleeve nut 31. The inner diameter of the coupling nut 31 is the same as the outer diameter of the connecting pipe 12 and the outer diameter of the horn carbon tube 21, and the connecting pipe 12 and the horn carbon tube 21 are inserted into the coupling nut 31.
As shown in fig. 1-2, in the embodiment of the present application, an inner thread 32 is disposed on an inner wall of the union nut 31, a first outer thread 16 is disposed on an outer wall of the connecting pipe 12, and a second outer thread 23 is disposed on an outer wall of the horn carbon tube 21, wherein when the union nut 31 is sleeved on the connecting pipe 12, the inner thread 32 is engaged with the first outer thread 16, and when the union nut 31 is sleeved on the horn carbon tube 21, the inner thread 32 is engaged with the second outer thread 23. Coupling nut 31 and connecting pipe 12 are connected through the intermeshing cooperation between internal thread 32 and the first external screw thread 16 of screwing, and coupling nut 31 and horn carbon pipe 21 are connected through the intermeshing cooperation between internal thread 32 and the second external screw thread 23 of screwing to realize stable mechanical connection between unmanned aerial vehicle and the horn subassembly 20.
As shown in fig. 1-2, in the present embodiment, the socket assembly 40 includes: a first circuit board 41 and a female head 42, wherein the first circuit board 41 is disposed in the connecting pipe 12 of the horn connecting assembly 10, and the female head 42 is disposed on the first circuit board 41.
As shown in fig. 1-2, in the present embodiment, the plug assembly 50 includes: a second circuit board 51 and a male terminal 52, wherein the second circuit board 51 is disposed in the horn carbon tube 21 of the horn assembly 20, and the male terminal 52 is disposed on the second circuit board 51.
In the embodiment of the present application, when the plug assembly 50 is correspondingly plugged onto the socket assembly 40, the male connector 52 is correspondingly plugged onto the female connector 42, so as to realize the electrical connection between the first circuit board 41 and the second circuit board 51, and further realize the stable electrical connection between the unmanned aerial vehicle and the horn assembly 20.
The application provides a pair of unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle have following advantage:
(1) the axial, radial and circumferential positioning of the connecting part of the horn and the fuselage can be realized simultaneously, even if a part of threads of the sleeve nut with the fastening effect are loosened under the conditions of large overload and large vibration, the axial positioning, the radial positioning and the circumferential positioning of the whole connecting structure are still effective, the electric connection is not loosened, and the reliability of structural connection and the safety of flight are ensured;
(2) the modularization degree of the unmanned aerial vehicle product is improved;
(3) the reliability of the connection between the machine arm and the machine body is improved.
Finally, it should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. The terms "first" and "second" in this application are to be understood as terms.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. The utility model provides an unmanned aerial vehicle power horn rapid disassembly structure which characterized in that includes:
the machine arm connecting component is used for installing the socket component;
the machine arm assembly is used for mounting the plug assembly; the first end of the horn assembly is mounted with the first end of the horn connecting assembly in a matched manner;
the disassembling and assembling assembly is used for disassembling and assembling the machine arm connecting assembly and the machine arm assembly; the disassembling and assembling component is sleeved at the first end of the machine arm component and the first end of the machine arm connecting component;
the socket assembly is used for being plugged with the plug assembly; the socket assembly is arranged at the first end of the horn connecting assembly;
the plug assembly is used for being plugged with the socket assembly; the plug assembly is arranged at the first end of the horn assembly;
wherein, work as the first end of horn subassembly with during the first end adaptation installation of horn coupling assembling, dismouting subassembly cover is located the first end of horn subassembly with the first end of horn coupling assembling, just socket component correspond with plug subassembly connects.
2. The unmanned aerial vehicle power horn quick detach structure of claim 1, wherein the horn attachment assembly is fixed to a fuselage.
3. The unmanned aerial vehicle power horn quick detach structure of claim 2, characterized in that the horn connection assembly includes: the connecting pipe is arranged on the outer side wall of the machine body, the pressing plate is arranged on the inner side wall of the machine body, and the fastening screws are sequentially screwed on the connecting pipe, the machine body and the pressing plate.
4. The unmanned aerial vehicle power arm quick detach structure of claim 3, characterized in that a sealing ring is arranged between the connecting pipe and the fuselage in a sealing manner.
5. The unmanned aerial vehicle power horn quick detach structure of claim 1, characterized in that the horn assembly comprises: the horn comprises a horn carbon tube and a horn, wherein the horn carbon tube is inserted in the horn.
6. The unmanned aerial vehicle power horn quick detach structure of claim 1, characterized in that the dismouting subassembly includes: and the sleeve nut is screwed on the connecting pipe in the machine arm connecting component and the machine arm carbon tube in the machine arm component.
7. The unmanned aerial vehicle horn rapid disassembly structure of claim 6, wherein an inner thread is provided on an inner wall of the union nut, a first outer thread is provided on an outer wall of the connecting pipe, a second outer thread is provided on an outer wall of the horn carbon tube, the inner thread meshes with the first outer thread when the union nut is fitted on the connecting pipe, and the inner thread meshes with the second outer thread when the union nut is fitted on the horn carbon tube.
8. The unmanned aerial vehicle arm quick release structure of claim 1, wherein the receptacle assembly comprises: first circuit board and female head, wherein, first circuit board set up in horn coupling assembling's the connecting pipe, female head set up in on the first circuit board.
9. The unmanned aerial vehicle arm quick release structure of claim 1, wherein the plug assembly comprises: the second circuit board is arranged in the horn carbon tube of the horn component, and the male head is arranged on the second circuit board.
10. An unmanned aerial vehicle comprising the unmanned aerial vehicle power arm quick release structure of any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011333304.1A CN112339985A (en) | 2020-11-24 | 2020-11-24 | Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011333304.1A CN112339985A (en) | 2020-11-24 | 2020-11-24 | Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN112339985A true CN112339985A (en) | 2021-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011333304.1A Pending CN112339985A (en) | 2020-11-24 | 2020-11-24 | Unmanned aerial vehicle power horn rapid disassembly structure and unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021093904A3 (en) * | 2021-02-24 | 2021-12-09 | 郑州航空工业管理学院 | Easy-to-assemble unmanned aerial vehicle |
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| CN206466158U (en) * | 2016-12-21 | 2017-09-05 | 深圳市道通智能航空技术有限公司 | Detachable horn component and aircraft |
| CN207157489U (en) * | 2017-09-01 | 2018-03-30 | 陕西土豆数据科技有限公司 | A kind of horizontal folding mechanism applied to aircraft |
| CN208760906U (en) * | 2018-09-03 | 2019-04-19 | 深圳市富籁科技有限公司 | Agricultural plant protection unmanned plane |
| CN209553471U (en) * | 2019-01-23 | 2019-10-29 | 常熟市翼天航空技术有限公司 | A kind of unmanned plane horn connector |
| KR102134473B1 (en) * | 2019-07-16 | 2020-07-16 | 주식회사 올뉴텍 | Folding joint of drone blade |
| CN211139648U (en) * | 2019-08-09 | 2020-07-31 | 武汉天易航科技有限公司 | Plug locking structure of unmanned aerial vehicle horn |
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2020
- 2020-11-24 CN CN202011333304.1A patent/CN112339985A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206466158U (en) * | 2016-12-21 | 2017-09-05 | 深圳市道通智能航空技术有限公司 | Detachable horn component and aircraft |
| CN207157489U (en) * | 2017-09-01 | 2018-03-30 | 陕西土豆数据科技有限公司 | A kind of horizontal folding mechanism applied to aircraft |
| CN208760906U (en) * | 2018-09-03 | 2019-04-19 | 深圳市富籁科技有限公司 | Agricultural plant protection unmanned plane |
| CN209553471U (en) * | 2019-01-23 | 2019-10-29 | 常熟市翼天航空技术有限公司 | A kind of unmanned plane horn connector |
| KR102134473B1 (en) * | 2019-07-16 | 2020-07-16 | 주식회사 올뉴텍 | Folding joint of drone blade |
| CN211139648U (en) * | 2019-08-09 | 2020-07-31 | 武汉天易航科技有限公司 | Plug locking structure of unmanned aerial vehicle horn |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021093904A3 (en) * | 2021-02-24 | 2021-12-09 | 郑州航空工业管理学院 | Easy-to-assemble unmanned aerial vehicle |
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Application publication date: 20210209 |
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