CN205366049U - Unmanned aerial vehicle's wing beta structure - Google Patents
Unmanned aerial vehicle's wing beta structure Download PDFInfo
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- CN205366049U CN205366049U CN201620136034.8U CN201620136034U CN205366049U CN 205366049 U CN205366049 U CN 205366049U CN 201620136034 U CN201620136034 U CN 201620136034U CN 205366049 U CN205366049 U CN 205366049U
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- connecting rod
- wing
- axle
- folding
- folding hinge
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Abstract
The utility model discloses an unmanned aerial vehicle's wing beta structure, unmanned aerial vehicle's wing beta structure includes: folding page or leaf piece, axis of rotation, connecting rod, spout and sliding shaft, folding page or leaf piece is including first folding page or leaf piece and the folding page or leaf piece of second, first folding page or leaf piece and the folding page or leaf piece of second be fixed two interior lateral sections to the wing respectively, the axis of rotation includes first axis of rotation and second axis of rotation, first axis of rotation and second axis of rotation set up respectively in first folding page or leaf piece and the folding page or leaf piece of second, the connecting rod is connected respectively first axis of rotation and second axis of rotation, and pass through first axis of rotation and second axis of rotation are rotated, the spout sets up respectively the inside of first folding page or leaf piece and the folding page or leaf piece of second, and the below of first axis of rotation and second axis of rotation, the sliding shaft runs through the connecting rod sets up, the sliding shaft passes through the spout slides, realizes that the connecting rod is in removal in the spout.
Description
Technical field
This utility model relates to the wing-folding structure of a kind of aviation aircraft technical field, particularly a kind of SUAV.
Background technology
The problem that the aerodynamic arrangement of SUAV and light aerocraft have to consider in being always up airplane design and manufacturing, better carry for the ease of unmanned vehicle simultaneously, increasing unmanned plane adopts the structure of folded wing, and unmanned plane is typically all and improves power by the high speed rotating of propeller, flight efficiency own is had a great impact by aircraft skin structure, therefore the design of fold mechanism not only to consider the impact on UAV aerodynamic layout, it is also contemplated that the attractive in appearance of unmanned plane monnolithic case, now fold mechanism in the market mostly all directly exposed outside, to such an extent as to cause wing junction to there are some gaps, both the overall aerodynamic arrangement of unmanned plane had been affected, also aircraft is caused certain potential safety hazard.
Traditional fold mechanism adopts two page of one axle construction, although structure is simple, but to do manual work also relatively rough comparatively speaking simultaneously, nor can ensure the problem that folding angles is fixed at any time.
Thus, it is desirable to have the wing-folding structure of a kind of SUAV can overcome or at least alleviate the drawbacks described above of prior art.
Utility model content
Technical problem to be solved in the utility model is in that to overcome the defect existed in above-mentioned prior art, and provides the wing-folding structure of a kind of SUAV.
For solving above-mentioned technical problem, the wing-folding structure of a kind of SUAV of the present utility model, including: folding hinge, rotation axle, connecting rod, chute and sliding axle；
Folding hinge, described folding hinge includes the first folding hinge and the second folding hinge, the described first folding hinge and the second folding hinge and is individually secured to two inside cross-sectional of wing；
Rotating axle, described rotation axle includes the first rotation axle and second and rotates axle, and described first rotation axle and second rotates axle and is separately positioned in the described first folding hinge and the second folding hinge；
Connecting rod, described connecting rod connects described first respectively and rotates axle and the second rotation axle, and is rotated by described first rotation axle and the second rotation axle；
Chute, described chute is separately positioned on the described first folding hinge and the inside of the second folding hinge, and in the lower section that described first rotates axle and the second rotation axle；
Sliding axle, described sliding axle runs through described connecting rod and arranges, and described sliding axle is slided by described chute, it is achieved connecting rod movement in described chute.
Preferably, being provided with screw counterbore and screw hole in described folding hinge, screw passes sequentially through the burst that described folding hinge is fixed on the wing of SUAV by described screw counterbore and screw hole.
Preferably, described connecting rod includes first connecting rod, second connecting rod, third connecting rod and fourth link, described first connecting rod and third connecting rod and connects described first rotation axle, and described second connecting rod and fourth link connect described second and rotate axle.
Preferably, when expansion wing, the described first folding hinge and second folds hinge rotary folding, and described connecting rod is rotated by described rotation axle, described sliding axle slide in described chute drive described connecting rod move make fold mechanism change angle so that wing realize stretch；When folded wing, by the reciprocal stress of wing, and the reciprocal motion of fold mechanism realizes the folding of wing.
This utility model provides the wing-folding structure of a kind of SUAV, and the wing-folding structure of described SUAV has the advantages that
1) first optimize installation operation, be a kind of good method of convenient installation
2) secondly, in appearance, traditional mechanism of comparing is more attractive in appearance, and it is more novel to design.
3) when two panels hinge closes time, middle connecting rod can be completely hidden in inside hinge, will not be exposed at fuselage outer surface, due to accomplishing without any letup of unmanned plane surface structure so that the unmanned vehicle flight time under the same conditions is longer, and flight efficiency is higher.
4) being greatly improved comparing traditional scheme efficiency for the folding spacing of wing, be relatively easy to achieve the location of folded wing part, rotation, stability and the reliability of system are also ensured.
Accompanying drawing illustrates:
Fig. 1 is the schematic front view of the wing-folding structure of this utility model SUAV.
Fig. 2 is another structural representation of the wing-folding structure of this utility model SUAV
Fig. 3 is the generalized section of the wing-folding structure of this utility model SUAV.
Detailed description of the invention:
For the purpose making this utility model implement, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish.Described embodiment is a part of embodiment of this utility model, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of this utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, it is for only for ease of description this utility model and simplifies description, rather than the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that restriction to this utility model protection domain
The wing-folding structure of a kind of SUAV according to this utility model one broad embodiment includes: folding hinge, rotation axle, connecting rod, chute and sliding axle；Folding hinge, described folding hinge includes the first folding hinge and the second folding hinge, the described first folding hinge and the second folding hinge and is individually secured to two inside cross-sectional of wing；Rotating axle, described rotation axle includes the first rotation axle and second and rotates axle, and described first rotation axle and second rotates axle and is separately positioned in the described first folding hinge and the second folding hinge；Connecting rod, described connecting rod connects described first respectively and rotates axle and the second rotation axle, and is rotated by described first rotation axle and the second rotation axle；Chute, described chute is separately positioned on the described first folding hinge and the inside of the second folding hinge, and in the lower section that described first rotates axle and the second rotation axle；Sliding axle, described sliding axle is arranged on described connecting rod, and described sliding axle is slided by described chute, it is achieved connecting rod movement in described chute.
As Figure 1-3, the wing-folding structure of SUAV includes: the first folding hinge 2, first of folding hinge 1, second rotates axle 3, second and rotates axle 4, first connecting rod 5, second connecting rod 6, third connecting rod 7, fourth link 8, chute the 9, first sliding axle 10 and the second sliding axle 11.
Being provided with screw counterbore 12 and screw hole 13 in described first folding hinge 1 and the second folding hinge 2, screw passes sequentially through described screw counterbore 12 and screw hole 13 and described first folding hinge 1 and the second folding hinge 2 is individually secured to two inside cross-sectional of wing.
Described first rotation axle 3 and the second rotation axle 4 are separately positioned in the described first folding hinge 1 and the second folding hinge 2.
Described first connecting rod 5 and third connecting rod 7 connect described first and rotate axle 3, described second connecting rod 6 and fourth link 8 connect described second and rotate axle 4, and described first connecting rod 5, second connecting rod 6, third connecting rod 7 and fourth link 8 rotate axle 3 by described first and the second rotation axle 4 rotates.But it is understood that, described connecting rod is not necessarily first connecting rod, second connecting rod, third connecting rod and fourth link, and in a not shown embodiment, described connecting rod is first connecting rod and second connecting rod.
Described chute 9 is respectively perpendicular the inside being arranged on the described first folding hinge 1 and the second folding hinge 2, and described chute 9 is arranged on the described first lower section rotating axle 3 and the second rotation axle 4, and the quantity of described chute 9 is two.
Described first sliding axle 10 runs through described first connecting rod 5 and third connecting rod 7 is arranged, second sliding axle 11 runs through described second connecting rod 6 and fourth link 8 is arranged, described first sliding axle 10 and the second sliding axle 11 are slided by described chute 9, it is achieved the movement in described chute 9 of described first connecting rod 5, second connecting rod 6, third connecting rod 7 and fourth link 8.
When expansion wing, described first folding hinge 1 and the second folding hinge 2 rotary folding, described first connecting rod 5, second connecting rod 6, third connecting rod 7 and fourth link 8 rotate axle 3 by described first and the second rotation axle 4 rotates, described first sliding axle 10 and the second sliding axle 11 slide in described the chute 9 described first connecting rod 5 of drive, second connecting rod 6, third connecting rod 7 and fourth link 8 move and make fold mechanism change angle, so that wing realizes stretching；When folded wing, by the reciprocal stress of wing, and the reciprocal motion of fold mechanism realizes the folding of wing.
For the problem solving overall aerodynamic arrangement better, the wingfold mechanism of SUAV of the present utility model adopts the mode installing pivot link additional, hinge connecting rod adopt embedded, Guan Bi after is completely hidden in inside, it is to avoid exposing of fold mechanism and affect aerodynamic arrangement.The hinge being simultaneously connected with wing has less fastening point, although fixing point tails off, but by selecting thicker screw and counter bore structure also to solve this drawback, traditional exposed fold mechanism of comparing, security performance is more reliable.
For installing the wingfold mechanism of SUAV of the present utility model, each folding hinge only has two screw holes, and adopt the mode of counter sink, fixed by the installation of flat head screw Yu Airfoil Sections, make hinge outer surface concordant with flat head screw, do not only reach effect attractive in appearance, and hinge does not expose wing and makes the aerodynamic arrangement of aircraft better, additionally, mechanism rotates the fixing friction only relying between connecting rod, frictional force is bigger, therefore wing can rely on him to rest on Anywhere, also have, mechanism have employed two each and every one rotating shafts, wherein, two modes adopting fixed rotating shaft, the two outer modes adopting rotation of sliding.
In small-sized unmanned aircraft designs, apply the technology of the wingfold mechanism of SUAV of the present utility model, making the folded wing in this aircraft install making to be greatly simplified than ever, manufacturing process and installation process can shorten, and matching relationship is simply easier to assemble.In full machine so that aircraft outward appearance is more attractive in appearance, have better aerodynamic arrangement.In the process of working service, it is more convenient that such design replacing is got up, it is necessary to the place of cutting amendment significantly reduces, performance optimization, and reliability strengthens.
Above embodiment of the present utility model is described in detail, but described content has been only preferred embodiment of the present utility model, it is impossible to be considered for limiting practical range of the present utility model.All equalizations made according to this utility model application range change and improvement etc., all should still belong within patent covering scope of the present utility model.
Claims (4)
1. the wing-folding structure of a SUAV, it is characterised in that including: folding hinge, rotation axle, connecting rod, chute and sliding axle；
Folding hinge, described folding hinge includes the first folding hinge and the second folding hinge, the described first folding hinge and the second folding hinge and is individually secured to two inside cross-sectional of wing；
Rotating axle, described rotation axle includes the first rotation axle and second and rotates axle, and described first rotation axle and second rotates axle and is separately positioned in the described first folding hinge and the second folding hinge；
Connecting rod, described connecting rod connects described first respectively and rotates axle and the second rotation axle, and is rotated by described first rotation axle and the second rotation axle；
Chute, described chute is separately positioned on the described first folding hinge and the inside of the second folding hinge, and in the lower section that described first rotates axle and the second rotation axle；
Sliding axle, described sliding axle runs through described connecting rod and arranges, and described sliding axle is slided by described chute, it is achieved connecting rod movement in described chute.
2. the wing-folding structure of the SUAV according to claim 1, it is characterized in that: be provided with screw counterbore and screw hole in described folding hinge, screw passes sequentially through the burst that described folding hinge is fixed on the wing of SUAV by described screw counterbore and screw hole.
3. the wing-folding structure of the SUAV according to claim 1, it is characterized in that: described connecting rod includes first connecting rod, second connecting rod, third connecting rod and fourth link, described first connecting rod and third connecting rod connect described first and rotate the described second rotation axle of axle, described second connecting rod and fourth link connection.
4. the wing-folding structure of the SUAV according to claim 1, it is characterized in that: when expansion wing, described first folding hinge and the second folding hinge rotary folding, described connecting rod is rotated by described rotation axle, described sliding axle slide in described chute drive described connecting rod move make fold mechanism change angle so that wing realize stretch；When folded wing, by the reciprocal stress of wing, and the reciprocal motion of fold mechanism realizes the folding of wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620136034.8U CN205366049U (en) | 2016-02-23 | 2016-02-23 | Unmanned aerial vehicle's wing beta structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620136034.8U CN205366049U (en) | 2016-02-23 | 2016-02-23 | Unmanned aerial vehicle's wing beta structure |
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| CN205366049U true CN205366049U (en) | 2016-07-06 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105584622A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Wing folding structure of small unmanned air vehicle |
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- 2016-02-23 CN CN201620136034.8U patent/CN205366049U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105584622A (en) * | 2016-02-23 | 2016-05-18 | 天峋创新（北京）科技有限公司 | Wing folding structure of small unmanned air vehicle |
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