CN114455064A - Locking device and unmanned aerial vehicle - Google Patents
Locking device and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN114455064A CN114455064A CN202210089619.9A CN202210089619A CN114455064A CN 114455064 A CN114455064 A CN 114455064A CN 202210089619 A CN202210089619 A CN 202210089619A CN 114455064 A CN114455064 A CN 114455064A
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- Prior art keywords
- fuselage
- wing
- main
- release pin
- locking device
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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
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention relates to a locking device and an unmanned aerial vehicle, wherein the locking device is used for wings and a fuselage of the unmanned aerial vehicle, and comprises at least two first connecting pieces and at least two corresponding second connecting pieces; wherein the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage; correspondingly, the at least two second connecting pieces are arranged on the fuselage/wing, and the at least two first connecting pieces are respectively and correspondingly connected with the at least two second connecting pieces. The locking device can realize convenient disassembly and assembly of the wings and the fuselage without tools, and has simple operation and reliable locking.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a locking device and an unmanned aerial vehicle.
Background
At present most unmanned aerial vehicle all adopts each part with unmanned aerial vehicle to dismantle for satisfying the road transportation condition, and the part of will dismantling is boxed respectively and is transported to transport unmanned aerial vehicle to the place of needs. When unmanned aerial vehicle need carry out the task, through the mode of equipment, with each part of the unmanned aerial vehicle of vanning, accomplish the assembly of each subassembly of unmanned aerial vehicle according to unmanned aerial vehicle's design, with the complete back of each part assembly of these vanning, unmanned aerial vehicle just can fly to carry out predetermined task. Wing and fuselage docking mechanism wide application have the unmanned aerial vehicle of stationary vane, and the wing of conventional unmanned aerial vehicle and fuselage generally directly link firmly with the bolt, but this kind of connected mode is more troublesome when carrying out the dismouting to wing and fuselage in assembly and transportation, and frequent dismouting causes the harm to the wing easily moreover, influences the structure of wing, and also can bring certain influence to the flight performance of unmanned aerial vehicle after wing and fuselage dress together. Therefore, the research on a connection locking device suitable for wings and fuselages of various unmanned aerial vehicles becomes a problem to be solved urgently at present.
Disclosure of Invention
The invention aims to solve the defects in the prior art, and provides a locking device and an unmanned aerial vehicle, which are used for solving the problems in the prior art.
The above technical object of the present invention will be achieved by the following technical solutions.
A locking device for connecting a wing and a fuselage of a drone, the locking device comprising: the connecting structure comprises at least two first connecting pieces and at least two corresponding second connecting pieces;
wherein the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage;
correspondingly, the at least two second connecting pieces are arranged on the fuselage/wing,
the at least two first connecting pieces are respectively and correspondingly connected with the at least two second connecting pieces.
There is further provided in accordance with the above-described aspect and any possible implementation, an implementation in which the at least two first connectors include a wing/fuselage main plug and a wing/fuselage secondary plug.
The above aspects and any possible implementations further provide an implementation in which the at least two second connectors include a fuselage/wing main box corresponding to the wing/fuselage main pin, and a fuselage/wing sublance box corresponding to the wing/fuselage sublance pin.
The above aspects and any possible implementations further provide an implementation, where the locking device further includes a main quick-release pin and an auxiliary quick-release pin, where the main quick-release pin connects the main bolt and the main trunk; the auxiliary quick-release pin is connected with the auxiliary bolt and the auxiliary sleeve box.
In accordance with the above aspect and any possible implementation manner, there is further provided an implementation manner, wherein circular bosses are disposed at upper ends of the main quick-release pin and the auxiliary quick-release pin, through holes are disposed at lower ends of the main quick-release pin and the auxiliary quick-release pin, and a distance from each circular boss to each through hole is the same as a thickness of the wing at a mounting position of the main quick-release pin and the auxiliary quick-release pin.
In accordance with the above aspect and any possible implementation manner, there is further provided an implementation manner, wherein the main bolt and the auxiliary bolt are both provided with a cylindrical hole, and correspondingly, the main casing and the auxiliary casing are both provided with a circular hole corresponding to the cylindrical hole.
The above aspects and any possible implementation manners further provide an implementation manner, and further include two spring bayonet locks, where the two spring bayonet locks are respectively inserted into the through holes at the lower ends of the main quick-release pin and the auxiliary quick-release pin.
The above aspects and any possible implementation further provide an implementation in which the main quick-release pin and the auxiliary quick-release pin have lengths longer than heights of the wings at positions where the main bolt and the main trunk, and the auxiliary bolt and the auxiliary trunk are located.
The invention also provides an unmanned aerial vehicle, which comprises the locking device, wings and a fuselage, wherein the locking device is used for connecting the wings and the fuselage.
As for the aspects and any possible implementation manners described above, an implementation manner is further provided, where the locking device includes at least two sets, and the two sets are respectively disposed between the fuselage of the unmanned aerial vehicle and the wings on the left and right sides.
The invention has the beneficial technical effects
The locking device provided by the embodiment of the invention is used for connecting the wings and the fuselage of the unmanned aerial vehicle, and comprises at least two first connecting pieces and at least two corresponding second connecting pieces; wherein the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage; correspondingly, the at least two second connecting pieces are arranged on the fuselage/wing, and the at least two first connecting pieces are respectively and correspondingly connected with the at least two second connecting pieces. The locking device can realize convenient and fast disassembly and assembly of the wing and the fuselage without tools, and has simple operation and reliable locking.
Drawings
Embodiments of the invention are described in detail below with reference to the attached drawing figures, wherein:
FIG. 1 is an exploded view of a locking device in an embodiment of the invention;
FIG. 2 is a schematic view of a wing to fuselage interface process according to an embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating the upper surface effect of a butt joint of a wing and a fuselage according to an embodiment of the present invention;
FIG. 4 is a schematic diagram illustrating the effect of the lower surface of the wing after the wing is butted with the fuselage in the embodiment of the invention.
Detailed Description
In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following detailed description is made with reference to the accompanying drawings and specific examples, but the embodiments of the present invention are not limited thereto.
As shown in fig. 1, the locking device of the present invention is used for wings and a fuselage of an unmanned aerial vehicle, and the locking device includes at least two first connecting members and at least two corresponding second connecting members; wherein the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage; correspondingly, the at least two second connecting pieces are arranged on the fuselage/wing, and the at least two first connecting pieces are respectively and correspondingly connected with the at least two second connecting pieces.
Specifically, the locking device in the embodiment of the present invention includes a wing main bolt 1, a fuselage main casing 2, a wing auxiliary bolt 3, a fuselage auxiliary casing 4, a main quick release pin 5, an auxiliary quick release pin 6, and a spring bayonet 7, where the positions of the bolt and the casing are not limited, and the main bolt 1 and the auxiliary bolt 3 may be provided on the fuselage, and the wing main casing 2 and the auxiliary casing 4 are provided on the wing correspondingly.
Preferably, the main bolt 1 and the auxiliary bolt 3 in the embodiment of the invention are telescopically/rotatably arranged on the wing/fuselage, specifically, a cavity is arranged on the corresponding wing/fuselage, and when the wing and the fuselage are separated, the main bolt 1 and the auxiliary bolt 3 are contracted into the corresponding cavity, so that the wing and the fuselage are convenient to respectively carry out boxing and transportation; or a rotating shaft is arranged between the main bolt 1 and the auxiliary bolt 3 and the wing/fuselage, and when the locking is not needed, the main bolt 1 and the auxiliary bolt 3 are rotated to the side edge of the wing/fuselage, so that the wing/fuselage is convenient to place or transport.
Preferably, in the embodiment of the present invention, the main quick release pin 5 connects the main bolt 1 and the main sleeve 2; the auxiliary quick-release pin 6 is connected with the auxiliary bolt 3 and the auxiliary sleeve box 4, when the aircraft is locked, the wing main bolt 1 is inserted into the airframe main sleeve box 2, the wing auxiliary bolt 3 is inserted into the airframe auxiliary sleeve box 4, the two actions are carried out simultaneously, the end surface of the airframe and the end surface of the wing are aligned after the actions are finished, and the assembling process is shown in figure 2; the upper ends of the main quick-release pin 5 and the auxiliary quick-release pin 6 are provided with circular bosses, the lower ends of the main quick-release pin 5 and the auxiliary quick-release pin 6 are provided with through holes, the through holes can be circular, square or oval and the like, the shapes of the through holes are not limited, and the distance between each circular boss and each through hole is the same as the thickness of the wing at the installation position of the main quick-release pin 5 and the corresponding auxiliary quick-release pin 6.
Preferably, in the embodiment of the present invention, cylindrical holes are respectively formed in the main bolt 1 and the auxiliary bolt 3, the cylindrical holes are in a vertical direction, correspondingly, circular holes are formed in corresponding positions on the main casing 2 and the auxiliary casing 4, and also in a vertical direction, when the wing and the fuselage are installed, after the main bolt 1 is inserted into the fuselage main casing 2, the cylindrical holes in the main bolt 1 are aligned with the circular holes in the main casing 2; similarly, the auxiliary bolt 3 is inserted into the auxiliary casing 4 of the body so that the cylindrical hole on the auxiliary bolt 3 is aligned with the circular hole on the auxiliary casing 4. That is to say, when the main bolt 1 is inserted into and connected with the main jacket case 2 and the auxiliary bolt 3 is inserted into and connected with the auxiliary jacket case 4, the cylindrical holes and the circular holes are in a superposed and aligned state, in this case, the main quick release pin 5 and the auxiliary quick release pin 6 respectively penetrate through the superposed and aligned cylindrical holes and the circular holes, so that the quick disassembly and assembly are convenient, and the effect after the installation is finished is as shown in fig. 3.
Preferably, the length of the main quick-release pin 5 and the auxiliary quick-release pin 6 in the embodiment of the invention is greater than the height of the wing where the main bolt 1 and the main jacket box 2, and the auxiliary bolt 3 and the auxiliary jacket box 4 are located, so as to ensure the complete alignment and locking of the wing and the fuselage, the surfaces of the wing and the fuselage are the same plane after the locking, the lower ends of the main quick-release pin 5 and the auxiliary quick-release pin 6 are provided with through holes, and the axes of the two through holes are respectively perpendicular to the axes of the main quick-release pin 5 and the auxiliary quick-release pin 6; two spring bayonet locks 7 are also arranged in the locking device of the invention, after the main quick-release pin 5 and the auxiliary quick-release pin 6 pass through the overlapped and aligned cylindrical hole and the circular hole, the lower end of the through hole is extended out of the lower surface of the machine body at the corresponding connection part, the two spring bayonet locks 7 respectively pass through the through hole to complete locking and installation, and the effect after installation is shown in figure 4.
The process of disassembling one wing by the locking device comprises the following steps: firstly, the spring bayonet pins 7 are sequentially and respectively drawn out from the through holes of the main quick-assembly pin 5 and the auxiliary quick-assembly pin 6, so that the unlocking of the main quick-assembly pin 5 and the auxiliary quick-assembly pin 6 is completed; then the main quick-assembly pin 5 and the auxiliary quick-assembly pin 6 are sequentially and respectively pulled out of the fuselage to unlock the wing main bolt 1 and the fuselage main sleeve 2, the wing auxiliary bolt 3 and the fuselage auxiliary sleeve 4, and simultaneously the main bolt 1 and the auxiliary bolt 3 are contracted or rotated; and finally, the wings are pulled out of the fuselage to complete the separation and disassembly of the wings and the fuselage, and another wing is quickly disassembled and unlocked in the same way.
The invention also provides the unmanned aerial vehicle which comprises at least two locking devices, wings and a body, wherein the two locking devices are respectively arranged between the body of the unmanned aerial vehicle and the wings on two sides of the body.
While the foregoing description shows and describes several preferred embodiments of the invention, it is to be understood, as noted above, that the invention is not limited to the forms disclosed herein, but is not intended to be exhaustive or to exclude other embodiments and may be used in various other combinations, modifications, and environments and is capable of changes within the scope of the invention as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A locking device is used for connecting wings and a fuselage of an unmanned aerial vehicle and is characterized by comprising at least two first connecting pieces and at least two corresponding second connecting pieces;
wherein the at least two first connectors are telescopically/rotatably arranged on the wing/fuselage;
correspondingly, the at least two second connecting pieces are arranged on the fuselage/wing,
the at least two first connecting pieces are respectively and correspondingly connected with the at least two second connecting pieces.
2. The locking device of claim 1, wherein the at least two first connectors comprise a wing/fuselage main latch and a wing/fuselage secondary latch.
3. The locking device of claim 2, wherein the at least two second connectors comprise a fuselage/wing main box corresponding to the wing/fuselage main pin and a fuselage/wing sub box corresponding to the wing/fuselage sub pin.
4. The locking device of claim 3, further comprising a primary quick release pin and a secondary quick release pin, the primary quick release pin connecting the primary latch and the primary nest; the auxiliary quick-release pin is connected with the auxiliary bolt and the auxiliary sleeve box.
5. The locking device according to claim 4, characterized in that the upper ends of the main quick release pin and the auxiliary quick release pin are provided with circular bosses, the lower ends are provided with through holes, and the distance from the circular bosses to the through holes is the same as the thickness of the wing at the installation position of the main quick release pin and the auxiliary quick release pin.
6. A locking arrangement as claimed in claim 4, wherein cylindrical holes are provided in both the main bolt and the secondary bolt, and correspondingly circular holes corresponding to the cylindrical holes are provided in both the main and secondary casings.
7. The locking device according to claim 5, further comprising two spring pins, wherein the two spring pins are respectively arranged on the through holes at the lower ends of the main quick-release pin and the auxiliary quick-release pin in a penetrating way.
8. The locking device of claim 7, wherein the main quick release pin and the secondary quick release pin are longer than the height of the wing at the location of the main bolt and the main casing box and the secondary bolt and the secondary casing box, respectively.
9. An unmanned aerial vehicle comprising the locking device of any one of claims 1-8, a wing, and a fuselage, the locking device for connecting the wing to the fuselage.
10. The unmanned aerial vehicle of claim 9, wherein the locking device comprises at least two sets of locking devices respectively arranged between the fuselage of the unmanned aerial vehicle and the wings on the left and right sides.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210089619.9A CN114455064A (en) | 2022-01-25 | 2022-01-25 | Locking device and unmanned aerial vehicle |
| PCT/CN2022/137318 WO2023142702A1 (en) | 2022-01-25 | 2022-12-07 | Locking device and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210089619.9A CN114455064A (en) | 2022-01-25 | 2022-01-25 | Locking device and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114455064A true CN114455064A (en) | 2022-05-10 |
Family
ID=81411792
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210089619.9A Pending CN114455064A (en) | 2022-01-25 | 2022-01-25 | Locking device and unmanned aerial vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN114455064A (en) |
| WO (1) | WO2023142702A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023142702A1 (en) * | 2022-01-25 | 2023-08-03 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
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| US20060091258A1 (en) * | 2004-10-29 | 2006-05-04 | Chiu Tien S | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) |
| US20090146007A1 (en) * | 2007-12-05 | 2009-06-11 | The Boeing Company | Methods and Systems for Attaching Aircraft Wings to Fuselages |
| CN106275385A (en) * | 2016-08-31 | 2017-01-04 | 河南翱翔航空科技有限公司 | Unmanned plane wing aileron bindiny mechanism |
| US20180057136A1 (en) * | 2016-09-01 | 2018-03-01 | Horizon Hobby, LLC | Wing lock and disconnect mechanisms for a rc aircraft |
| CN207450221U (en) * | 2017-10-27 | 2018-06-05 | 华南农业大学 | A kind of unmanned plane of variable aerodynamic arrangement |
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| CN208897306U (en) * | 2018-09-29 | 2019-05-24 | 四川长虹电器股份有限公司 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
| CN213414200U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle ready-package wing |
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| GB201209697D0 (en) * | 2012-05-31 | 2012-07-18 | Airbus Uk Ltd | Method of coupling aerofoil surface structures and an aerofoil assembly |
| CN204368408U (en) * | 2014-09-12 | 2015-06-03 | 深圳市艾特航空科技股份有限公司 | For being fixedly connected with the mounting structure of model plane fuselage and wing |
| CN213323644U (en) * | 2020-09-30 | 2021-06-01 | 天津飞眼无人机科技有限公司 | Unmanned aerial vehicle fixing device and use this fixing device's unmanned aerial vehicle |
| CN114455064A (en) * | 2022-01-25 | 2022-05-10 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
-
2022
- 2022-01-25 CN CN202210089619.9A patent/CN114455064A/en active Pending
- 2022-12-07 WO PCT/CN2022/137318 patent/WO2023142702A1/en unknown
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060091258A1 (en) * | 2004-10-29 | 2006-05-04 | Chiu Tien S | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) |
| US20090146007A1 (en) * | 2007-12-05 | 2009-06-11 | The Boeing Company | Methods and Systems for Attaching Aircraft Wings to Fuselages |
| CN106275385A (en) * | 2016-08-31 | 2017-01-04 | 河南翱翔航空科技有限公司 | Unmanned plane wing aileron bindiny mechanism |
| US20180057136A1 (en) * | 2016-09-01 | 2018-03-01 | Horizon Hobby, LLC | Wing lock and disconnect mechanisms for a rc aircraft |
| CN207450221U (en) * | 2017-10-27 | 2018-06-05 | 华南农业大学 | A kind of unmanned plane of variable aerodynamic arrangement |
| CN108438200A (en) * | 2018-05-11 | 2018-08-24 | 南京航天猎鹰飞行器技术有限公司 | A kind of fixed-wing unmanned plane of fast demountable wing |
| CN208897306U (en) * | 2018-09-29 | 2019-05-24 | 四川长虹电器股份有限公司 | Unmanned aerial vehicle body and wing fast assembling-disassembling connection structure |
| CN213414200U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle ready-package wing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023142702A1 (en) * | 2022-01-25 | 2023-08-03 | 航天时代飞鸿技术有限公司 | Locking device and unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2023142702A1 (en) | 2023-08-03 |
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