CN218431713U - Hide beta structure's collapsible unmanned aerial vehicle wing - Google Patents
Hide beta structure's collapsible unmanned aerial vehicle wing Download PDFInfo
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- CN218431713U CN218431713U CN202222501966.6U CN202222501966U CN218431713U CN 218431713 U CN218431713 U CN 218431713U CN 202222501966 U CN202222501966 U CN 202222501966U CN 218431713 U CN218431713 U CN 218431713U
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- connecting rod
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- spout
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Abstract
The utility model relates to a foldable unmanned aerial vehicle wing with a hidden folding structure, which comprises a wing body and a wing tail rotationally connected with the tail end of the wing body; the wing is provided with the spout along its length direction in the wing body, is provided with the gliding slewing mechanism of length direction that can follow the spout in the spout, and slewing mechanism includes first connecting rod, second connecting rod and the third connecting rod that mutual rotation connects in proper order, and the one end and the wing tail of third connecting rod are close to wing body one side fixed connection, are provided with locking mechanism on the wing body to make slewing mechanism slide or fixed in the spout, and the outer wall radian of locking mechanism outer wall and wing body is unanimous. Unblock locking mechanism, pulling wing tail make first connecting rod, second connecting rod and the outside roll-off of third connecting rod, after the spout is drawn out to second connecting rod and third connecting rod, rotatable in order folding wing tail, through hiding slewing mechanism in the wing body, locking mechanism hides in wing body outer wall, and keeps unanimous with the radian of wing body, does not influence the air current of flight in-process.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle equipment technical field, concretely relates to hide beta structure's collapsible unmanned aerial vehicle wing.
Background
The conventional unmanned aerial vehicle has two types of wings, one type of wing cannot be folded, and the wing occupies a large space in the packaging, transporting or storing process, needs a larger storage box for storage and has higher cost; the other is foldable (for example, the method disclosed in chinese patent No. cn201811359890.X for operating an aircraft wing including a foldable wing tip portion), in such a way that the wing tail portion of the wing is folded, and the folded structure is exposed, which changes the original profile of the wing and easily causes an undesirable influence on the airflow during the flight.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve is: how to realize the folding of wing to the space that occupies when reducing to accomodate can not produce improper influence to the air current again at the flight in-process simultaneously.
The utility model provides an above-mentioned technical problem's technical scheme as follows: a foldable unmanned aerial vehicle wing with a hidden folding structure comprises a wing body and a wing tail which is rotatably connected to the tail end of the wing body; the wing is provided with the spout along its length direction in the wing body, is provided with the gliding slewing mechanism of length direction that can follow the spout in the spout, and slewing mechanism includes first connecting rod, second connecting rod and the third connecting rod that mutual rotation connects in proper order, and the one end and the wing tail of third connecting rod are close to wing body one side fixed connection, are provided with locking mechanism on the wing body to make slewing mechanism slide or fixed in the spout, and the outer wall radian of locking mechanism outer wall and wing body is unanimous.
The beneficial effects of the utility model are that: unblock locking mechanism, pulling wing tail make first connecting rod, second connecting rod and the outside roll-off of third connecting rod, after the spout is drawn out to second connecting rod and third connecting rod, rotatable in order folding wing tail, through hiding slewing mechanism in the wing body, locking mechanism hides in wing body outer wall, and keeps unanimous with the radian of wing body, does not influence the air current of flight in-process.
On the basis of the technical scheme, the utility model discloses can also do following improvement.
Further, locking mechanism is including setting up first spring locating pin, the second spring locating pin in first connecting rod and setting up in the button of wing body outer wall, and the outer wall of button is unanimous with the outer wall radian of wing body, and the button is connected with the ejector pin, and the ejector pin can be dismantled with the round pin head of first spring locating pin, second spring locating pin and be connected.
Furthermore, a button hole is formed in the outer wall of the wing body, the button is arranged in the button hole, a reset spring is sleeved outside the ejector rod, a positioning hole is formed in the peripheral wall of the sliding groove, and the ejector rod stretches into the positioning hole and is detachably connected with the pin heads of the first spring positioning pin and the second spring positioning pin.
Further, the cross-section of the chute is of a non-circular structure.
Drawings
Fig. 1 is a schematic view of a wing folding structure of the present invention;
fig. 2 is a schematic view of the wing unfolding structure of the present invention;
fig. 3 is a schematic view of a partial cross-sectional structure of the present invention;
fig. 4 is a schematic view of a partial cross-sectional structure of the present invention;
fig. 5 is an enlarged view of the structure a in fig. 1 according to the present invention;
fig. 6 is an enlarged view of the structure at B in fig. 3 according to the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. the wing body 11, the sliding chute 2, the wing tail 3, the rotating mechanism 31, the first connecting rod 311, the first spring positioning pin 312, the second spring positioning pin 32, the second connecting rod 33, the third connecting rod 4, the locking mechanism 41, the button 42, the ejector rod 43, the button hole 44, the reset spring 45 and the positioning hole.
Detailed Description
The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.
Unblock locking mechanical system 4, pulling wing tail 2 makes first connecting rod 31, second connecting rod 32 and third connecting rod 33 outwards roll-off, and after second connecting rod 32 and third connecting rod 33 drawn spout 11, rotatable with folding wing tail 2, through hiding slewing mechanism 3 in wing body 1, locking mechanical system 4 hides in wing body 1 outer wall, and keeps unanimous with the radian of wing body 1, does not influence the air current of flight in-process.
Example 2, as shown in fig. 1 to 6, this example is a further improvement on example 1, and specifically includes the following steps:
the locking mechanism 4 comprises a first spring positioning pin 311 and a second spring positioning pin 312 which are arranged in the first connecting rod 31, and a button 41 which is arranged on the outer wall of the wing body 1, the radian of the outer wall of the button 41 is consistent with that of the outer wall of the wing body 1, the button 41 is connected with a push rod 42, and the push rod 42 is detachably connected with the pin heads of the first spring positioning pin 311 and the second spring positioning pin 312.
The pin head of the first spring positioning pin 311 or the second spring positioning pin 312 is retracted by pressing the button 41 to unlock; in the concrete operation process, when the wing is completely unfolded, the first spring positioning pin 311 positions the locking, when needs are folded, the locking mechanism 4 is unlocked, after the rotating mechanism 3 is pulled out, the second spring positioning pin 312 positions the locking, the rotating mechanism 3 is prevented from being completely pulled out, in addition, when the wing tail 2 is required to be completely disassembled and stored, only the button 41 needs to be pressed again to enable the pin head of the second spring positioning pin 312 to retract, and the rotating mechanism 3 can be completely pulled out from the wing body 1 so as to detach the wing tail 2.
the outer wall of the wing body 1 is provided with a button hole 43, the button 41 is arranged in the button hole 43, the ejector rod 42 is sleeved with a return spring 44, the peripheral wall of the sliding chute 11 is provided with a positioning hole 45, and the ejector rod 42 extends into the positioning hole 45 and is detachably connected with the pin heads of the first spring positioning pin 311 and the second spring positioning pin 312.
When the button is pressed, the ejector rod 42 pushes the pin head of the first spring positioning pin 311 or the second spring positioning pin 312 out of the positioning hole 45, and simultaneously pulls the wing tail 2 outwards to realize unlocking, and after the button is pressed, the button 41 is reset and keeps consistent with the radian of the outer wall of the wing body 1 again, so that the airflow is not influenced; in the specific implementation process, the button 41 is arranged in a T shape, and the button hole 43 extends inwards to form a skirt, so that the button 41 is prevented from being separated from the button hole 43.
the cross-section of the chute 11 is of non-circular configuration. So that the first link 31, the second link 32 and the third link 33 will not rotate during the sliding process, thereby avoiding the situation that the folding device is not easy to reset after being folded.
While embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the present invention.
Claims (4)
1. The foldable unmanned aerial vehicle wing with the hidden folding structure is characterized by comprising a wing body (1) and a wing tail (2) rotatably connected to the tail end of the wing body (1); be provided with spout (11) along its length direction in wing body (1), be provided with in spout (11) and follow the gliding slewing mechanism (3) of length direction of spout (11), slewing mechanism (3) are including first connecting rod (31), second connecting rod (32) and third connecting rod (33) that rotate each other in proper order and connect, the one end of third connecting rod (33) with wing tail (2) are close to wing body (1) one side fixed connection, be provided with locking mechanism (4) on wing body (1), so that slewing mechanism (3) are in slide or fixed in spout (11), just locking mechanism (4) outer wall with the outer wall radian of wing body (1) is unanimous.
2. The foldable unmanned aerial vehicle wing with the hidden folding structure is characterized in that the locking mechanism (4) comprises a first spring positioning pin (311) and a second spring positioning pin (312) which are arranged in the first connecting rod (31) and a button (41) which is arranged on the outer wall of the wing body (1), the radian of the outer wall of the button (41) is consistent with that of the outer wall of the wing body (1), the button (41) is connected with a push rod (42), and the push rod (42) is detachably connected with pin heads of the first spring positioning pin (311) and the second spring positioning pin (312).
3. The foldable unmanned aerial vehicle wing with the hidden folding structure is characterized in that a button hole (43) is formed in the outer wall of the wing body (1), the button (41) is arranged in the button hole (43), a return spring (44) is sleeved outside the ejector rod (42), a positioning hole (45) is formed in the peripheral wall of the sliding groove (11), and the ejector rod (42) extends into the positioning hole (45) and is detachably connected with the pin heads of the first spring positioning pin (311) and the second spring positioning pin (312).
4. The foldable unmanned aerial vehicle wing of hidden folding structure of any of claims 1 to 3, characterized in that the cross section of the chute (11) is non-circular structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222501966.6U CN218431713U (en) | 2022-09-21 | 2022-09-21 | Hide beta structure's collapsible unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222501966.6U CN218431713U (en) | 2022-09-21 | 2022-09-21 | Hide beta structure's collapsible unmanned aerial vehicle wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218431713U true CN218431713U (en) | 2023-02-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222501966.6U Active CN218431713U (en) | 2022-09-21 | 2022-09-21 | Hide beta structure's collapsible unmanned aerial vehicle wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218431713U (en) |
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2022
- 2022-09-21 CN CN202222501966.6U patent/CN218431713U/en active Active
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