CN111605698A - Wing folding structure of small unmanned aerial vehicle - Google Patents
Wing folding structure of small unmanned aerial vehicle Download PDFInfo
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- CN111605698A CN111605698A CN202010395174.8A CN202010395174A CN111605698A CN 111605698 A CN111605698 A CN 111605698A CN 202010395174 A CN202010395174 A CN 202010395174A CN 111605698 A CN111605698 A CN 111605698A
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- wing
- fixedly connected
- aerial vehicle
- unmanned aerial
- main wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The invention provides a wing folding structure of a small unmanned aerial vehicle, which comprises: a main wing, an auxiliary wing, and a folding connection device; the main wing is fixedly connected with the unmanned aerial vehicle body, and the auxiliary wing is connected with the main wing through the folding connection device; the folding connection device comprises a first connection piece fixedly connected with one end of the main wing, a second connection piece fixedly connected with one end of the auxiliary wing, and a plurality of elastic bulges fixedly connected with the first connection piece and the second connection piece respectively. The invention has the beneficial effects that: the integral wing of the unmanned aerial vehicle can be formed by the arranged main wing and the auxiliary wing; through the arranged folding connecting device, the main wing and the auxiliary wing can be fixedly connected together when in use, and the main wing and the auxiliary wing can be folded together when not in use.
Description
Technical Field
The invention relates to the technical field of aviation aircrafts and mechanical designs, in particular to a wing folding structure of a small unmanned aerial vehicle.
Background
Unmanned aerial vehicle and light aircraft's pneumatic overall arrangement has always been the problem that must consider in aircraft design and the manufacturing, simultaneously for the sake of the better carrying of unmanned vehicles, more and more unmanned aerial vehicle adopts the structure of folding wing, consequently folding mechanism's design not only will consider the influence to the pneumatic overall arrangement of unmanned aerial vehicle, still consider the pleasing to the eye of the whole appearance of unmanned aerial vehicle, folding mechanism in the existing market is mostly direct to expose in the outside, so that there are some gaps in the wing junction as to cause, both influence unmanned aerial vehicle's whole pneumatic overall arrangement, also cause certain potential safety hazard to the aircraft.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a wing folding structure of a small unmanned aerial vehicle.
The problem of unmanned aerial vehicle's folding mechanism mostly all directly expose outside in the existing market to cause the wing junction to have some gaps, both influenced unmanned aerial vehicle's whole aerodynamic layout, also cause certain potential safety hazard to the aircraft is solved.
The invention is realized by the following technical scheme:
the invention provides a wing folding structure of a small unmanned aerial vehicle, which comprises: a main wing, an auxiliary wing, and a folding connection device;
the main wing is fixedly connected with the unmanned aerial vehicle body, and the auxiliary wing is connected with the main wing through the folding connection device;
the folding connection device comprises a first connection piece fixedly connected with one end of the main wing, a second connection piece fixedly connected with one end of the auxiliary wing, and a plurality of elastic bulges fixedly connected with the first connection piece and the second connection piece respectively; the lower part of the first connecting piece is provided with a first sliding groove along the length direction, a first sliding block is connected in the first sliding groove in a sliding mode, the first sliding block is fixedly connected with a limiting rod, and one end of the limiting rod is fixedly connected with the second connecting piece.
Preferably, one end of the first sliding groove extends into the main wing.
Preferably, one end of the main wing is provided with a first accommodating cavity matched with the second connecting sheet, and one end of the auxiliary wing is provided with a second accommodating cavity matched with the first connecting sheet.
Preferably, the upper side wall and the lower side wall of the first accommodating cavity and the second accommodating cavity are respectively provided with a groove corresponding to the elastic bulges one to one.
Preferably, the elastic protrusion comprises a mounting hole formed on the first connecting sheet or the second connecting sheet, a plurality of second sliding grooves formed in the mounting hole, a second sliding block connected with each second sliding groove in a sliding manner, a sliding plate fixedly connected with the second sliding block, and a protrusion fixedly connected with one side of the sliding plate; one end of the mounting hole is fixedly connected with a baffle, and the other side of the sliding plate is fixedly connected with a plurality of compression springs.
Preferably, a first threaded hole communicated with the second accommodating cavity is formed in the auxiliary wing, and a second threaded hole matched with the first threaded hole is formed in the first connecting piece.
The invention has the beneficial effects that: the integral wing of the unmanned aerial vehicle can be formed by the arranged main wing and the auxiliary wing; through the arranged folding connecting device, the main wing and the auxiliary wing can be fixedly connected together when in use, and the main wing and the auxiliary wing can be folded together when not in use.
Drawings
Fig. 1 is a schematic structural diagram of wings of a wing folding structure of a small unmanned aerial vehicle provided in an embodiment of the present invention when the wings are connected together;
fig. 2 is a schematic structural diagram of a folded wing of a wing folding structure of a small unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an elastic protrusion of a wing folding structure of a small unmanned aerial vehicle according to an embodiment of the present invention.
Detailed Description
The following detailed description of specific embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
Firstly, in order to facilitate understanding of the wing folding structure of the small unmanned aerial vehicle provided by the embodiment of the application, an application scene of the wing folding structure is explained, and the wing folding structure of the small unmanned aerial vehicle provided by the embodiment of the application is used for seamlessly connecting folded wings together; and unmanned aerial vehicle's folding mechanism is most all directly exposed in the market now to cause the wing junction to have some gaps, both influenced unmanned aerial vehicle's whole aerodynamic layout, also caused certain potential safety hazard to the aircraft. The wing folding structure of the small unmanned aerial vehicle provided by the embodiment of the application is described below with reference to the accompanying drawings.
The invention provides a wing folding structure of a small unmanned aerial vehicle, which comprises a main wing 1, an aileron 2 and a folding connecting device, wherein the main wing 1 and the aileron 2 are fixedly connected with the small unmanned aerial vehicle, and the folding connecting device is used for connecting the main wing 1 and the aileron 2.
Fig. 1 is a schematic structural view of the wings of the wing folding structure of the unmanned aerial vehicle provided by the embodiment of the invention when connected together, and fig. 2 is a schematic structural view of the wings of the wing folding structure of the unmanned aerial vehicle provided by the embodiment of the invention when folded. As can be seen from fig. 2, the folding attachment means comprise a first attachment tab 3 fixedly connected to the main wing 1, and a second attachment tab 4 fixedly connected to the auxiliary wing 2; and a first containing cavity 9 matched with the second connecting sheet 4 is arranged on the main wing 1, and a second containing cavity 10 matched with the first connecting sheet 3 is arranged on the auxiliary wing 2. As can be seen from fig. 1, when the main wing 1 and the sub-wing 2 are coupled together, the first connecting piece 3 is inserted into the corresponding second receiving cavity 10, and the second connecting piece 4 is inserted into the corresponding first receiving cavity 9, thereby seamlessly coupling the main wing 1 and the sub-wing 2 together. In order to make the connection between the main wing 1 and the auxiliary wing 2 more compact, referring to fig. 2, it can be seen from fig. 2 that the upper and lower sides of the first connecting piece 3 and the second connecting piece 4 are respectively and fixedly connected with a plurality of elastic protrusions 5, and the upper and lower inner walls of the first accommodating cavity 9 and the second accommodating cavity 10 are respectively provided with a groove 11 corresponding to the plurality of elastic protrusions 5 one by one; with continued reference to fig. 1, when the first connecting piece 3 is inserted into the corresponding second accommodating cavity 10, the elastic protrusion 5 on the first connecting piece 3 is engaged with the corresponding groove 11, and when the second connecting piece 4 is inserted into the corresponding first accommodating cavity 9, the elastic protrusion 5 on the second connecting piece 4 is engaged with the corresponding groove 11, so as to fixedly connect the first connecting piece 3 and the auxiliary wing 2 together, and fixedly connect the second connecting piece 3 and the main wing 1 together, so as to more firmly connect the main wing 1 and the auxiliary wing 2 together in a seamless manner.
Fig. 3 can be referred to when the elastic protrusion 5 is specifically arranged, and fig. 3 is a schematic structural diagram of the elastic protrusion of the wing folding structure of the unmanned aerial vehicle provided in the embodiment of the present invention. As can be seen from fig. 3, the elastic protrusion 5 includes a plurality of mounting holes 12 formed in the first connecting plate 3 or the second connecting plate 4, a plurality of parallel second sliding grooves 13 are formed in an inner wall of each mounting hole 12, 2 to 4 second sliding grooves 13 may be specifically formed in each second sliding groove 13, and a second sliding block 14 is slidably connected in each second sliding groove 13; all the second sliding blocks 14 are fixedly connected with the same sliding plate 15, one side of the sliding plate 15, which faces the outside of the mounting hole 12, is fixedly connected with a protrusion 16, the other side of the sliding plate 15 is fixedly connected with a plurality of compression springs 18, and one ends of the compression springs 18, which are far away from the sliding plate 15, are fixedly connected with the inner wall of the mounting hole 12; to prevent the slide 15 from sliding out of the mounting hole 12, with continued reference to fig. 3, one end of the mounting hole 12 is fixedly connected to a stop 17. When the first connecting piece 3 is inserted into the second accommodating cavity 10 or the second connecting piece 4 is inserted into the first accommodating cavity 9, the side wall of the first accommodating cavity 9 or the second accommodating cavity 10 extrudes the protrusion 16 inwards, so that the sliding plate 15 slides into the mounting hole 12, when the protrusion 16 and the corresponding groove 11 are positioned on the same straight line, the sliding plate 15 slides outwards towards the mounting hole 12 under the action of the compression spring 18, so that the protrusion 16 slides outwards towards the mounting hole 12 until the protrusion 16 and the corresponding groove 11 are matched together, and at the moment, the first connecting piece 3 and the second accommodating cavity 10, the second connecting piece 4 and the first accommodating cavity 9 are clamped together.
In order to prevent the aileron 2 from being detached from the main wing 1 under the influence of centrifugal force when using the drone, reference is continued to figures 1 and 2. As can be seen from fig. 1 and 2, the sub-wing 2 is provided with a first threaded hole 19 communicated with the second accommodating cavity 10, and the first connecting plate 3 is provided with a second threaded hole 20 corresponding to the first threaded hole 19; when the main wing 1 and the aileron 2 are seamlessly joined together, bolts may be threadedly coupled within the first threaded hole 19 and the second threaded hole 20 to fixedly couple the aileron 2 and the first coupling tab 3 together, thereby preventing the aileron 2 from being separated from the main wing 1 by centrifugal force. Meanwhile, when the first threaded hole 19 and the second threaded hole 20 are screwed with bolts, the top ends of the bolts are flush with the upper surface of the auxiliary wing 2, thereby preventing the first threaded hole 19 from damaging the aerodynamic layout of the whole unmanned aerial vehicle when flying.
Continuing to refer to fig. 1 and 2, first spout 6 has been seted up to the lower part of first connection piece 3, and in first spout 6 extended to main wing 1, the intercommunication had the bar hole between first spout 6 and the first chamber 9 that holds, and second connection piece 4 fixedly connected with gag lever post 8, and the top fixedly connected with first slider 7 of gag lever post 8, and first slider 7 is in the same place with first spout 6 sliding connection. Wherein, gag lever post 8 is the telescopic link commonly used among the prior art. When the main wing 1 and the auxiliary wing 2 are connected together in a seamless manner, when the second connecting piece 3 enters the first accommodating cavity 9, the first sliding block 7 can slide into the first sliding groove 6 in the main wing 1, and meanwhile, the limiting rod 8 can move into the strip-shaped hole; when the main wing 1 and the aileron 2 are folded, the bolts in the first threaded hole 19 and the second threaded hole 20 can be taken out, then the aileron 2 is pulled outwards, so that the first connecting piece 3, the second accommodating cavity 10, the second connecting piece 4 and the first accommodating cavity 9 are separated until the limiting rod 8 and the first sliding block 7 move to the outside of the main wing 1, then the limiting rod 8 extends downwards until the aileron 2 is positioned below the main wing 1, then the aileron 2 is rotated, so that the aileron 2 is positioned right below the main wing 1, and the main wing 1 and the aileron 2 in the invention are folded together.
In the above-mentioned embodiment, the wing beta structure of a small unmanned aerial vehicle that this application embodiment provided can be in the same place unmanned aerial vehicle's main wing and aileron seamless fixed connection to can fold main wing and aileron together.
The above-described embodiments are merely illustrative of the preferred embodiments of the present invention and do not limit the spirit and scope of the present invention. Various modifications and improvements of the technical solutions of the present invention may be made by those skilled in the art without departing from the design concept of the present invention, and the technical contents of the present invention are all described in the claims.
Claims (6)
1. A unmanned aerial vehicle's wing beta structure, its characterized in that includes: a main wing, an auxiliary wing, and a folding connection device;
the main wing is fixedly connected with the unmanned aerial vehicle body, and the auxiliary wing is connected with the main wing through the folding connection device;
the folding connection device comprises a first connection piece fixedly connected with one end of the main wing, a second connection piece fixedly connected with one end of the auxiliary wing, and a plurality of elastic bulges fixedly connected with the first connection piece and the second connection piece respectively; the lower part of the first connecting piece is provided with a first sliding groove along the length direction, a first sliding block is connected in the first sliding groove in a sliding mode, the first sliding block is fixedly connected with a limiting rod, and one end of the limiting rod is fixedly connected with the second connecting piece.
2. The wing-folding structure of a small unmanned aerial vehicle as claimed in claim 1, wherein one end of the first chute extends into the main wing.
3. The wing folding structure of a small unmanned aerial vehicle as claimed in claim 1, wherein one end of the main wing is provided with a first accommodating cavity matched with the second connecting piece, and one end of the auxiliary wing is provided with a second accommodating cavity matched with the first connecting piece.
4. The wing folding structure of a small unmanned aerial vehicle as claimed in claim 3, wherein the upper and lower sidewalls of the first and second accommodating chambers are respectively provided with a groove corresponding to the elastic protrusions.
5. The wing folding structure of a small unmanned aerial vehicle as claimed in claim 1, wherein the elastic protrusion comprises a mounting hole formed on the first connecting plate or the second connecting plate, a plurality of second sliding grooves formed in the mounting hole, a second sliding block slidably connected with each second sliding groove, a sliding plate fixedly connected with the second sliding block, and a protrusion fixedly connected with one side of the sliding plate; one end of the mounting hole is fixedly connected with a baffle, and the other side of the sliding plate is fixedly connected with a plurality of compression springs.
6. The wing folding structure of a small unmanned aerial vehicle as claimed in claim 1, wherein the aileron is provided with a first threaded hole communicated with the second accommodating cavity, and the first connecting piece is provided with a second threaded hole matched with the first threaded hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010395174.8A CN111605698A (en) | 2020-05-12 | 2020-05-12 | Wing folding structure of small unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010395174.8A CN111605698A (en) | 2020-05-12 | 2020-05-12 | Wing folding structure of small unmanned aerial vehicle |
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| CN111605698A true CN111605698A (en) | 2020-09-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010395174.8A Pending CN111605698A (en) | 2020-05-12 | 2020-05-12 | Wing folding structure of small unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112046730A (en) * | 2020-09-17 | 2020-12-08 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203681865U (en) * | 2014-01-23 | 2014-07-02 | 西安交通大学 | Foldable miniature unmanned aerial vehicle |
| CN106741849A (en) * | 2017-03-09 | 2017-05-31 | 北京奇正数元科技股份有限公司 | A kind of foldable folding and unfolding wing of SUAV |
| CN208963301U (en) * | 2018-10-26 | 2019-06-11 | 山西恒赫贸易有限责任公司 | A kind of unmanned plane folding wing |
| CN209581847U (en) * | 2019-02-16 | 2019-11-05 | 安徽安飞智能科技有限公司 | A kind of unmanned plane wing-folding structure |
-
2020
- 2020-05-12 CN CN202010395174.8A patent/CN111605698A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203681865U (en) * | 2014-01-23 | 2014-07-02 | 西安交通大学 | Foldable miniature unmanned aerial vehicle |
| CN106741849A (en) * | 2017-03-09 | 2017-05-31 | 北京奇正数元科技股份有限公司 | A kind of foldable folding and unfolding wing of SUAV |
| CN208963301U (en) * | 2018-10-26 | 2019-06-11 | 山西恒赫贸易有限责任公司 | A kind of unmanned plane folding wing |
| CN209581847U (en) * | 2019-02-16 | 2019-11-05 | 安徽安飞智能科技有限公司 | A kind of unmanned plane wing-folding structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112046730A (en) * | 2020-09-17 | 2020-12-08 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| CN112046730B (en) * | 2020-09-17 | 2022-01-04 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
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Application publication date: 20200901 |