CN213620211U - Unmanned aerial vehicle folding wing - Google Patents
Unmanned aerial vehicle folding wing Download PDFInfo
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- CN213620211U CN213620211U CN202022287066.7U CN202022287066U CN213620211U CN 213620211 U CN213620211 U CN 213620211U CN 202022287066 U CN202022287066 U CN 202022287066U CN 213620211 U CN213620211 U CN 213620211U
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- 238000009434 installation Methods 0.000 claims description 12
- 238000003780 insertion Methods 0.000 description 4
- 230000037431 insertion Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
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Abstract
The utility model provides an unmanned aerial vehicle folding wing, which comprises a first wing and a rotating assembly, wherein one end of the first wing is provided with a rotating shaft, the rotating shaft penetrates through the first wing, one side of the first wing is provided with a holding tank, the rotating shaft is sleeved with a second wing on the holding tank area, the end of the second wing is connected with a propeller inserting block, the other end of the first wing is provided with a mounting groove, a fixing bolt is arranged on the outer side of the first wing, and the fixing bolt penetrates through the first wing into the mounting groove; a bearing groove and a fixing groove are formed in the rotating shaft, and the fixing groove penetrates through the second wing; the rotating assembly is including the axis of rotation, and the axis of rotation upper end is provided with the dwang, and the end of dwang is run through by the restriction bolt, and restriction bolt size and fixed slot diameter coincide mutually, and this utility model discloses a foldable design of first wing and second wing to be convenient for accomodate and carry, and through the design of rotatory subassembly, fixed when having realized first wing and second wing expansion.
Description
Technical Field
The utility model discloses a mainly relate to unmanned aerial vehicle wing technical field specifically is an unmanned aerial vehicle folds wing.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. Ground, on the naval vessel or mother's aircraft remote control station personnel pass through equipment such as radar, track it, the location, the remote control, telemetering measurement and digital transmission, and unmanned aerial vehicle need use the wing, for example, the patent number is CN 201210581497.1's patent number, this patent can let the wing expand fast in unmanned aerial vehicle ballistic section, and lock the wing when arriving the position of expandeing completely, moreover, the steam generator is simple in structure, the realization is convenient, the time is fast, the synchronism is good, but present unmanned aerial vehicle wing can not fold the shrink, area is big when not using, and portable not.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle folds wing to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
an unmanned aerial vehicle folding wing comprises a first wing and a rotating assembly, wherein a rotating shaft is arranged at one end of the first wing, the rotating shaft penetrates through the first wing, a containing groove is formed in one side of the first wing, a second wing is sleeved on a containing groove area of the rotating shaft, the tail end of the second wing is connected with a propeller inserting block, a mounting groove is formed in the other end of the first wing, a fixing bolt is arranged on the outer side of the first wing, and the fixing bolt penetrates through the first wing and is arranged in the mounting groove; the rotating shaft is provided with a bearing groove and a fixing groove, and the fixing groove penetrates through the second wing; the rotating assembly comprises a rotating shaft, a rotating rod is arranged at the upper end of the rotating shaft, the tail end of the rotating rod is penetrated through by a limiting bolt, and the size of the limiting bolt is matched with the diameter of a fixing groove.
Furthermore, the rubber pad is pasted to the mounting groove inner wall to can realize the mounting groove and other inseparabler laminating of part.
Furthermore, the bottom end of the limiting bolt is slightly wider than the upper end, and the diameter of the tail end of the limiting bolt is larger than that of the groove hole in the rotating rod, so that the limiting bolt cannot be separated from the rotating rod.
Furthermore, the tail end of the second wing is provided with a cavity groove, a spring is fixed at the bottom of the cavity groove, an installation block is fixed at the other end of the spring, and an installation slot for inserting the propeller insertion block is formed in the installation block, so that the propeller insertion block can be conveniently installed and detached.
Furthermore, the blind groove is formed above the tail end of the accommodating groove, so that the first wing and the second wing can be accommodated and folded without completely accommodating the mounting block into the accommodating groove.
Furthermore, the two sides of the propeller inserting block are provided with empty grooves, the bottom of each empty groove is fixedly provided with a pushing spring, the other end of each pushing spring is fixedly provided with a clamping block, and the mounting block is provided with a clamping groove for clamping the clamping blocks, so that the simple and convenient mounting and fixing of the propeller inserting block can be realized.
Furthermore, the clamping block is sleeved with a rubber ring, so that the clamping block can be tightly attached to the clamping groove, and the firmness is improved.
Furthermore, the screw inserting block is detachably inserted into the screw to be connected with the screw, so that the screw can be conveniently detached and installed.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model discloses a through the foldable design of first wing and second wing to be convenient for accomodate and carry, and through the cooperation of mounting groove and fixing bolt, the convenient installation of the wing of also realizing, through the design of rotatory subassembly, fixed when having realized first wing and second wing expansion.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is an enlarged view of area A of FIG. 1;
FIG. 3 is an enlarged view of area B of FIG. 1;
FIG. 4 is a cut-off sectional view of the propeller mounting block of the present invention;
in the figure: 1. a rotating shaft; 2. a first airfoil; 3. a second airfoil; 4. fixing the bolt; 5. A rotating assembly; 6. a restraining bolt; 7. mounting blocks; 8. a propeller mounting block; 11. a bearing groove; 12. fixing grooves; 21. accommodating grooves; 22. a hidden groove; 23. mounting grooves; 31. a cavity groove; 51. a rotating shaft; 52. rotating the rod; 71. inserting a slot; 72. a clamping groove; 81. an empty groove; 82. A clamping block; 83. pushing the spring.
Detailed Description
In order to facilitate understanding of the present invention, the present invention will be described more fully with reference to the accompanying drawings, in which several embodiments of the present invention are shown, but the present invention can be implemented in different forms, and is not limited to the embodiments described in the text, but rather, these embodiments are provided to make the disclosure of the present invention more thorough and comprehensive.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may be present, and when an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present, as the terms "vertical", "horizontal", "left", "right" and the like are used herein for descriptive purposes only.
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, and the use of the term knowledge in the specification of the present invention is for the purpose of describing particular embodiments and is not intended to limit the present invention, and the term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.
Referring to fig. 1-4, the present invention provides a technical solution: an unmanned aerial vehicle folding wing comprises a first wing 2 and a rotating assembly 5, wherein a rotating shaft 1 is arranged at one end of the first wing 2, the rotating shaft 1 penetrates through the first wing 2, an accommodating groove 21 is formed in one side of the first wing 2, a second wing 3 is sleeved on the area of the accommodating groove 21 of the rotating shaft 1, the tail end of the second wing 3 is connected with a propeller mounting and inserting block 8, a mounting groove 23 is formed in the other end of the first wing 2, a fixing bolt 4 is arranged on the outer side of the first wing 2, and the fixing bolt 4 penetrates through the first wing 2 to the mounting groove 23; the rotating shaft 1 is provided with a bearing groove 11 and a fixing groove 12, and the fixing groove 12 penetrates through the second wing 3; the rotating assembly 5 comprises a rotating shaft 51, a rotating rod 52 is arranged at the upper end of the rotating shaft 51, the tail end of the rotating rod 52 is penetrated through by a limiting bolt 6, and the size of the limiting bolt 6 is matched with the diameter of the fixing groove 12, in the embodiment, the first wing 2 and the second wing 3 are folded, so that the wing is convenient to store and carry, and the convenient installation of the wing is realized through the matching of the mounting groove 23 and the fixing bolt 4; through the design of the rotating assembly 5, the first wing 2 and the second wing 3 are fixed when being unfolded.
Please refer to fig. 1 and fig. 2, a rubber pad is adhered to an inner wall of the mounting groove 23, a bottom end of the limiting bolt 6 is slightly wider than an upper end, a diameter of the end is larger than a groove hole on the rotating rod 52, and a blind groove 22 is arranged above an end of the receiving groove 21.
Referring to fig. 3 and 4 again, the end of the second wing 3 is provided with a cavity groove 31, a spring is fixed at the bottom of the cavity containing groove 31, a mounting block 7 is fixed at the other end of the spring, an inserting groove 71 for inserting the propeller inserting block 8 is arranged on the mounting block 7, two sides of the propeller mounting block 8 are provided with empty slots 81, the bottom of the empty slot 81 is fixed with a pushing spring 83, an engaging block 82 is fixed to the other end of the pushing spring 83, an engaging groove 72 for engaging the engaging block 82 is formed in the mounting block 7, the clamping block 82 is sleeved with a rubber ring, the propeller mounting and inserting block 8 is detachably connected with the propeller in a mounting and inserting way, in this embodiment, through the design of the cavity groove 31, the installation of the installation block 7 is convenient, and through the design of the propeller installation and insertion block 8, the installation can be completed only by pressing the clamping block 82 and inserting the propeller installation and insertion block 8 into the installation block 7.
The utility model discloses a concrete operation as follows:
when the wing needs to be used, the second wing 3 is firstly pulled out from the accommodating groove 21 of the first wing 2, when the first wing 2 is parallel to the second wing 3, the first wing 2 is rotated into the fixing groove 12 through rotating the limiting bolt 6 to complete fixing, then the propeller mounting and inserting block 8 is inserted into the mounting block 7 through pressing the clamping block 82 to complete mounting, finally the mounting groove 23 is aligned to a part needing to be mounted, and the mounting is supported through rotating the fixing bolt 4, so that mounting is completed.
The above description of the present invention is made in conjunction with the accompanying drawings, and it is obvious that the present invention is not limited by the above embodiments, and the method and the technical solution of the present invention are not substantially improved or directly applied to other occasions without improvement, and are all within the protection scope of the present invention.
Claims (8)
1. The folding wing of the unmanned aerial vehicle comprises a first wing (2) and a rotating assembly (5), and is characterized in that one end of the first wing (2) is provided with a rotating shaft (1), the rotating shaft (1) penetrates through the first wing (2), a containing groove (21) is formed in one side of the first wing (2), a second wing (3) is sleeved on the area of the containing groove (21) of the rotating shaft (1), the tail end of the second wing (3) is connected with a propeller mounting and inserting block (8), a mounting groove (23) is formed in the other end of the first wing (2), a fixing bolt (4) is arranged on the outer side of the first wing (2), and the fixing bolt (4) penetrates through the first wing (2) to the mounting groove (23); a bearing groove (11) and a fixing groove (12) are formed in the rotating shaft (1), and the fixing groove (12) penetrates through the second wing (3);
rotating assembly (5) are including axis of rotation (51), axis of rotation (51) upper end is provided with dwang (52), the end of dwang (52) is run through by restriction bolt (6), just restriction bolt (6) size and fixed slot (12) diameter coincide mutually.
2. The folding wing of unmanned aerial vehicle of claim 1, characterized in that the inner wall of the installation groove (23) is pasted with a rubber pad.
3. The folding wing of unmanned aerial vehicle of claim 1, characterized in that the bottom end of the limiting bolt (6) is slightly wider than the upper end, and the diameter of the end is larger than the slot hole on the rotating rod (52).
4. The folding wing of unmanned aerial vehicle of claim 1, characterized in that the end of the second wing (3) is provided with a cavity groove (31), a spring is fixed at the bottom of the cavity groove (31), a mounting block (7) is fixed at the other end of the spring, and a mounting slot (71) for inserting the propeller mounting block (8) is arranged on the mounting block (7).
5. Unmanned folding wing according to claim 1, characterized in that a blind groove (22) is provided above the end of the receiving groove (21).
6. The folding wing of unmanned aerial vehicle of claim 4, wherein two sides of the propeller mounting and inserting block (8) are provided with empty slots (81), the bottom of the empty slot (81) is fixed with a pushing spring (83), the other end of the pushing spring (83) is fixed with a clamping block (82), and the mounting block (7) is provided with a clamping slot (72) for clamping the clamping block (82).
7. The folding wing of unmanned aerial vehicle of claim 6, characterized in that the block (82) is sleeved with a rubber ring.
8. The folding wing of unmanned aerial vehicle of claim 1, characterized in that the propeller mounting block (8) is detachably mounted and connected with the propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022287066.7U CN213620211U (en) | 2020-10-14 | 2020-10-14 | Unmanned aerial vehicle folding wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022287066.7U CN213620211U (en) | 2020-10-14 | 2020-10-14 | Unmanned aerial vehicle folding wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213620211U true CN213620211U (en) | 2021-07-06 |
Family
ID=76660450
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022287066.7U Active CN213620211U (en) | 2020-10-14 | 2020-10-14 | Unmanned aerial vehicle folding wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213620211U (en) |
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2020
- 2020-10-14 CN CN202022287066.7U patent/CN213620211U/en active Active
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