CN213036065U - Unmanned aerial vehicle wingtip winglet folding and locking structure - Google Patents
Unmanned aerial vehicle wingtip winglet folding and locking structure Download PDFInfo
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- CN213036065U CN213036065U CN202021535143.XU CN202021535143U CN213036065U CN 213036065 U CN213036065 U CN 213036065U CN 202021535143 U CN202021535143 U CN 202021535143U CN 213036065 U CN213036065 U CN 213036065U
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- wingtip winglet
- locking
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- folding
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Abstract
The utility model provides an unmanned aerial vehicle wingtip winglet folding locking structure, includes the elastic pin that stretches out unmanned aerial vehicle main wing bottom, establishes at the pivot at the top of main wing tip and winds the rotatory rotor of pivot, the lateral surface of rotor forms wingtip winglet installation face, and the rotor is kept away from and is equipped with the locking piece of inside extension with pivot swivelling joint one end, be equipped with on the locking piece and supply the locking hole that the elastic pin inserted and locked under the wingtip winglet expandes the state. By adopting the technical scheme, the folding and unfolding operations of the wingtip winglet are quick, simple and reliable.
Description
Technical Field
The utility model belongs to the technical field of the folding locking technique of unmanned aerial vehicle wingtip winglet, and specifically relates to a folding locking structure of unmanned aerial vehicle wingtip winglet.
Background
Along with the development of the unmanned aerial vehicle pneumatic design technology, in order to reduce wing tip vortex resistance and improve the endurance time of the unmanned aerial vehicle, wingtips winglets are additionally arranged on more and more main wings of the unmanned aerial vehicle. When unmanned aerial vehicle transport state, for reducing the transport case volume, generally need dismantle wingtip winglet, conventional unmanned aerial vehicle majority adopts the screw connection mode. This connection method requires a long time for disassembly and assembly and has low reliability, and thus needs improvement.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a folding locking structure of unmanned aerial vehicle wingtip winglet has reduced wingtip winglet takedown time, has improved the reliability of wingtip winglet installation. In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides an unmanned aerial vehicle wingtip winglet folding locking structure, includes the elastic pin that stretches out unmanned aerial vehicle main wing bottom, establishes at the pivot at the top of main wing tip and winds the rotatory rotor of pivot, the lateral surface of rotor forms wingtip winglet installation face, and the rotor is kept away from and is equipped with the locking piece of inside extension with pivot swivelling joint one end, be equipped with on the locking piece and supply the locking hole that the elastic pin inserted and locked under the wingtip winglet expandes the state.
Further, the rotating piece and the locking piece are integrally formed and form an L-shaped locking piece.
Furthermore, the end part of the main wing is fixedly provided with a hinged plate, the top of the hinged plate is hinged with the rotating sheet through a rotating shaft, and the outer side surface of the hinged plate forms a supporting surface for supporting the wingtip winglet in the unfolding state of the wingtip winglet.
Furthermore, the outer side surface of the hinged plate supports the inner side surface of the rotary sheet in the unfolding state of the wingtip winglet.
Further, be equipped with the uide bushing in the main wing, the bottom of uide bushing is equipped with the block, is equipped with the through-hole on the block, is equipped with the spring in the uide bushing, the elastic pin includes the spring mounting section, establishes at the spacing section of spring mounting section one end, establishes the locking section of keeping away from spring mounting section one end in spacing section, the cover of spring is on the spring mounting section, the one end and the spring contact of spacing section, the other end of spacing section is suppressed on the block by the spring, and the locking section stretches out the outside of block through the through-hole.
Furthermore, the main wing is internally provided with an accommodating cavity, the guide sleeve is arranged in the accommodating cavity, and the part of the main wing, which is positioned at the bottom of the guide sleeve, forms the blocking.
By adopting the technical scheme, the wingtip winglet is unfolded, the locking sheet moves along with the wingtip winglet to turn downwards, and finally the locking hole on the locking sheet is sleeved on the elastic pin below the main wing to complete the unfolding and fixing of the wingtip winglet.
When the unfolding state needs to be unlocked, the elastic pin is jacked up manually to be moved out of the locking hole, then the wingtip winglets are folded, and are folded and stacked above the main wing, so that the wingtip winglets are folded.
Therefore, by adopting the technical scheme, the folding and unfolding operations are quick, simple and reliable.
Drawings
FIG. 1 is a schematic perspective view of a main wing and winglet attachment.
Figure 2 is a schematic view of a winglet in a deployed condition.
Figure 3 is a schematic view of a winglet in a folded state.
Detailed Description
The present invention will be described with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1-3, a wingtip winglet folding and locking structure for an unmanned aerial vehicle comprises an elastic pin 2 extending out of the bottom of a main wing 1 of the unmanned aerial vehicle, a hinged plate 3 fixedly arranged at the end part of the main wing 1, a rotating shaft 4 arranged at the top of the hinged plate 3, a rotating plate 5 rotating around the rotating shaft 4, and a locking plate 6 arranged at one end of the rotating plate 5 far away from the rotating shaft 4 and extending inwards, wherein the top of the hinged plate 3 is hinged with the rotating plate 5 through the rotating shaft 4, the outer side surface of the rotating plate 5 forms a mounting surface for a wingtip winglet 7, the outer side surface of the hinged plate 3 supports the inner side surface of the rotating plate 5 in the unfolding, therefore, the wingtip winglet 7 in the unfolding state can be effectively supported, the rotating sheet 5 and the locking sheet 6 are integrally formed to form an L-shaped locking sheet, and the locking sheet 6 is provided with a locking hole 8 for the elastic pin 2 to be inserted and locked in the unfolding state of the wingtip winglet 7.
The specific mounting of the spring pin 2 is as follows:
be equipped with in the main wing 1 and hold chamber 9, hold and be equipped with uide bushing 10 in the chamber 9, the bottom part that the main wing 1 is located uide bushing 10 forms and blocks 11, be equipped with the through-hole on the block 11, be equipped with spring 13 in the uide bushing 10, the elastic pin 2 includes spring mounting section 14, establish the spacing section 15 in spring mounting section 14 one end, establish the locking section 16 of keeping away from 14 one end of spring mounting section in spacing section 15, the cover of spring 13 is on spring mounting section 14, spacing 15 one end and the contact of spring 13, spacing 15 other end is suppressed on block 11 by spring 13, locking section 16 stretches out the outside of block 11 through the through-hole. The force is applied to the extending end of the locking section 16, the elastic pin 2 overcomes the spring 13 to move upwards, and in the locking state of the wingtip winglet 7, the elastic pin 2 moves upwards to move out of the locking hole 8, so that the locking state is removed, and the wingtip winglet 7 can be folded conveniently.
By adopting the technical scheme, the wingtip winglet 7 is unfolded, the locking sheet 6 moves along with the wingtip winglet 7 and turns downwards, and finally the locking hole 8 on the locking sheet is sleeved on the elastic pin 2 below the main wing 1 to complete the unfolding and fixing of the wingtip winglet 7.
When the unfolding state needs to be unlocked, the elastic pin 2 is jacked up manually, so that the elastic pin 2 is moved out of the locking hole 8, then the wingtip winglet 7 is folded, the wingtip winglet 7 is folded over and is folded above the main wing 1, and the folding of the wingtip winglet 7 is completed.
Therefore, by adopting the technical scheme, the folding and unfolding operations are quick, simple and reliable.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not intended to limit the present invention, which may be modified, combined, and varied by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.
Claims (6)
1. The utility model provides a folding locking structure of unmanned aerial vehicle wingtip winglet which characterized in that: including stretching out the elastic pin of unmanned aerial vehicle main wing bottom, establishing the pivot at the top of main wing tip and winding the rotatory rotor of pivot, the lateral surface of rotor forms the wingtip winglet installation face, and the rotor is kept away from and is equipped with the locking piece of inside extension with pivot swivelling joint one end, be equipped with on the locking piece and supply the elastic pin to insert and the locking hole under the wingtip winglet expandes the state.
2. The unmanned aerial vehicle wingtip winglet folding and locking structure of claim 1, wherein: the rotating piece and the locking piece are integrally formed and form an L-shaped locking plate.
3. The unmanned aerial vehicle wingtip winglet folding and locking structure of claim 1, wherein: the end part of the main wing is fixedly provided with a hinged plate, the top of the hinged plate is hinged with the rotating sheet through a rotating shaft, and the outer side surface of the hinged plate forms a supporting surface which supports the wingtip winglet in the wingtip winglet unfolding state.
4. The unmanned aerial vehicle wingtip winglet folding and locking structure of claim 3, wherein: the outer side surface of the hinged plate supports the inner side surface of the rotary sheet in the unfolding state of the wingtip winglet.
5. The unmanned aerial vehicle wingtip winglet folding and locking structure of claim 3, wherein: the novel spring pin is characterized in that a guide sleeve is arranged in the main wing, a block is arranged at the bottom end of the guide sleeve, a through hole is formed in the block, a spring is arranged in the guide sleeve, the spring pin comprises a spring installation section, a limiting section arranged at one end of the spring installation section and a locking section arranged at one end of the limiting section and far away from one end of the spring installation section, the spring is sleeved on the spring installation section, one end of the limiting section is in contact with the spring, the other end of the limiting section is pressed on the block by the spring, and the locking section extends out of the block through the through hole.
6. The unmanned aerial vehicle wingtip winglet folding and locking structure of claim 5, wherein: the main wing is internally provided with an accommodating cavity, the guide sleeve is arranged in the accommodating cavity, and the part of the main wing, which is positioned at the bottom of the guide sleeve, forms the blocking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021535143.XU CN213036065U (en) | 2020-07-29 | 2020-07-29 | Unmanned aerial vehicle wingtip winglet folding and locking structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021535143.XU CN213036065U (en) | 2020-07-29 | 2020-07-29 | Unmanned aerial vehicle wingtip winglet folding and locking structure |
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| Publication Number | Publication Date |
|---|---|
| CN213036065U true CN213036065U (en) | 2021-04-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021535143.XU Active CN213036065U (en) | 2020-07-29 | 2020-07-29 | Unmanned aerial vehicle wingtip winglet folding and locking structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
-
2020
- 2020-07-29 CN CN202021535143.XU patent/CN213036065U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
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