CN114394223A - Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle Download PDFInfo
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- CN114394223A CN114394223A CN202111632320.5A CN202111632320A CN114394223A CN 114394223 A CN114394223 A CN 114394223A CN 202111632320 A CN202111632320 A CN 202111632320A CN 114394223 A CN114394223 A CN 114394223A
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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
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
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Abstract
The invention discloses a wing folding mechanism of an unmanned aerial vehicle, which comprises: a mandrel; the first rotating part and the second rotating part are respectively used for connecting two folding parts of a foldable wing of the unmanned aerial vehicle, one end of the first rotating part and one end of the second rotating part are respectively provided with a first rotating ring and a second rotating ring, and the first rotating ring and the second rotating ring are sleeved on the mandrel in a rotating mode; the first elastic component is connected with the first rotating part and the second rotating part and can drive the first rotating part and the second rotating part to rotate around the axial direction of the core in opposite directions; the self-locking structure is arranged between the first rotating part and the second rotating part and can lock the relative positions of the first rotating part and the second rotating part when the first rotating part and the second rotating part rotate to a set position; the foldable wing can be folded for use, and the self-locking structure can realize the locking of the unfolded state after the foldable wing is unfolded.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle wing folding mechanism and an unmanned aerial vehicle.
Background
The aerospace technology has been rapidly developed at the present stage, and in order to meet the flight efficiency of an aircraft and the space limitation of a launching device, new requirements are provided for a deformable unmanned aerial vehicle so as to realize launching the unmanned aerial vehicle in a limited space, so that the unmanned aerial vehicle can be used under different environmental conditions and has the capability of multiple tasks. The demand of the unmanned aerial vehicle greatly promotes scholars in related fields at home and abroad to research the deformable aircraft, wherein the mechanism for folding and unfolding the wings is the key point of research.
Disclosure of Invention
The invention aims to provide a wing folding mechanism of an unmanned aerial vehicle and the unmanned aerial vehicle aiming at the blank research of the wing folding and unfolding mechanism, the mechanism is provided with a first rotating part and a second rotating part which are connected with two folding parts of a foldable wing, the folding use of the foldable wing can be met, the automatic unfolding of the foldable wing can be realized under the action of a first elastic part, and the locking of the unfolding state is realized by a self-locking structure after the folding.
In order to achieve the above object, the present invention provides a wing folding mechanism of an unmanned aerial vehicle, the mechanism comprising:
a mandrel;
the first rotating part and the second rotating part are respectively used for connecting two folding parts of a foldable wing of the unmanned aerial vehicle, one end of the first rotating part and one end of the second rotating part are respectively provided with a first rotating ring and a second rotating ring, and the first rotating ring and the second rotating part are sleeved on the mandrel in a rotating mode;
a first elastic member connected to the first rotating portion and the second rotating portion, the first elastic member being capable of driving the first rotating portion and the second rotating portion to rotate in opposite directions in an axial direction of the core;
and the self-locking structure is arranged between the first rotating part and the second rotating part and can lock the relative positions of the first rotating part and the second rotating part when the first rotating part and the second rotating part rotate to a set position.
Optionally, the first rotating portion and the second rotating portion are both plate-shaped, the first rotating portion and the second rotating portion are tangent to the first rotating ring and the second rotating ring, respectively, and the first rotating portion and the second rotating portion are in the same plane when the position is set.
Optionally, one end of the first rotating portion is provided with two first rotating rings, a first gap is formed between the two first rotating rings, one end of the second rotating portion is provided with two second rotating rings, and the two second rotating rings are respectively arranged on one sides, away from each other, of the two first rotating rings.
Optionally, the first elastic component is a torsion spring, the core shaft is sleeved with the torsion spring, and the torsion spring is located in the first gap.
Optionally, two ends of the torsion spring are respectively embedded in the first rotating portion and the second rotating portion.
Optionally, the self-locking structure comprises:
the pin hole is formed in one end, close to the second rotating ring, of the first rotating ring;
the sliding groove is arranged in the second rotating ring;
the positioning pin is arranged in the sliding groove in a sliding manner;
and a second elastic member disposed in the sliding groove, the second elastic member being capable of driving the positioning pin to be inserted into the pin hole when the first rotating portion and the second rotating portion rotate to a set position.
Optionally, one side of the pin hole is provided with a guide groove, one end of the guide groove is communicated with the pin hole, the guide groove is gradually shallower from the end close to the pin control to the end far away from the pin hole, and the positioning pin can slide in the guide groove.
Optionally, the first rotating ring and the second rotating ring are detachably connected to the mandrel, the plug is used for limiting the first rotating ring and the second rotating ring to fall off from the mandrel, the chute penetrates through the second rotating portion, and the second elastic component is plugged in the chute by the plug.
Optionally, the first limiting block and the second limiting block are respectively disposed on the first rotating portion and the second rotating portion, and when the first rotating portion and the second rotating portion rotate to a set position, the first limiting block and the second limiting block are close to and contact with each other.
The present invention also provides an unmanned aerial vehicle, comprising:
a foldable wing;
foretell unmanned aerial vehicle wing folding mechanism.
The invention provides an unmanned aerial vehicle wing folding mechanism and an unmanned aerial vehicle, which have the beneficial effects that:
1. the mechanism is provided with a first rotating part and a second rotating part which are connected with two folding parts of the foldable wing, can meet the folding use of the foldable wing, can realize the automatic unfolding of the foldable wing under the action of a first elastic part, and can realize the locking of the unfolding state by a self-locking structure after the foldable wing is unfolded;
2. the mechanism is provided with a bolt type self-locking structure formed by a positioning pin and a butt joint type limiting structure formed by a first limiting block and a second limiting block, and the bolt type self-locking structure and the butt joint type limiting structure respectively realize positioning of the foldable wing after automatic unfolding from two aspects of shearing force and forward pressure.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows a schematic structural diagram of a wing folding mechanism of a drone in a foldable wing folded state according to one embodiment of the present invention.
Fig. 2 shows a schematic structural diagram of a wing folding mechanism of a drone in a foldable wing folded state according to an embodiment of the present invention.
Fig. 3 shows a schematic structural diagram of a wing folding mechanism of an unmanned aerial vehicle after automatic unfolding of a foldable wing according to an embodiment of the invention.
Fig. 4 shows a schematic structural diagram of a wing folding mechanism of an unmanned aerial vehicle after automatic unfolding of a foldable wing according to an embodiment of the invention.
Fig. 5 shows a front view structural diagram of a wing folding mechanism of a drone in a foldable wing folding state according to an embodiment of the invention.
Fig. 6 shows a schematic side view of a wing folding mechanism of a drone in a foldable wing folded state according to an embodiment of the invention.
Fig. 7 shows a schematic bottom view of a wing folding mechanism of a drone in a foldable wing folded state according to an embodiment of the present invention.
Description of reference numerals:
1. a mandrel; 2. a first rotating section; 3. a second rotating part; 4. a first rotating ring; 5. a second rotating ring; 6. a torsion spring; 7. a pin hole; 8. a chute; 9. positioning pins; 10. a pressure spring; 11. a guide groove; 12. a plug; 13. a first stopper; 14. and a second limiting block.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
As shown in fig. 1 to 7, the present invention provides a wing folding mechanism for an unmanned aerial vehicle, the mechanism comprising:
a mandrel 1;
the unmanned aerial vehicle comprises a first rotating part 2 and a second rotating part 3, wherein the first rotating part 2 and the second rotating part 3 are respectively used for connecting two folding parts of a foldable wing of the unmanned aerial vehicle, one end of the first rotating part 2 and one end of the second rotating part 3 are respectively provided with a first rotating ring 4 and a second rotating ring 5, and the first rotating ring 4 and the second rotating ring are sleeved on a mandrel 1 in a rotating mode;
a first elastic member connected to the first rotating part 2 and the second rotating part 3, the first elastic member being capable of driving the first rotating part 2 and the second rotating part 3 to rotate in opposite directions around the spindle 1;
and the self-locking structure is arranged between the first rotating part 2 and the second rotating part 3 and can lock the relative positions of the first rotating part 2 and the second rotating part 3 when the first rotating part 2 and the second rotating part 3 rotate to a set position.
Specifically, the first rotating part 2 and the second rotating part 3 are rotationally connected to the mandrel 1, so that the two folding parts of the foldable wing can be folded, and the size of the wing in a launching state is reduced; the first rotating part 2 and the second rotating part 3 can drive two folding parts of the foldable wing to automatically unfold under the driving of the first elastic component, so that the function of the variable wing is realized; when the self-locking structure is unfolded, the self-locking of the wing is completed, and the reliability is improved.
Optionally, the first rotating portion 2 and the second rotating portion 3 are both plate-shaped, the first rotating portion 2 and the second rotating portion 3 are tangent to the first rotating ring 4 and the second rotating ring 5, respectively, and the first rotating portion 2 and the second rotating portion 3 are in the same plane when the position is set.
Specifically, when the first rotating part 2 and the second rotating part 3 rotate and unfold to the set position, as shown in fig. 1-2, the first rotating part 2 and the second rotating part 3 are in the same plane, and two folding parts of the foldable wing can be respectively installed on the first rotating part 2 and the second rotating part 3 to complete the butt-type unfolding.
Optionally, one end of the first rotating portion 2 is provided with two first rotating rings 4, a first gap is provided between the two first rotating rings 4, one end of the second rotating portion 3 is provided with two second rotating rings 5, and the two second rotating rings 5 are respectively disposed on one sides of the two first rotating rings 4, which are away from each other.
Specifically, the first rotating ring 4 and the second rotating ring 5 are in sliding fit.
Optionally, the first elastic component is a torsion spring 6, the torsion spring 6 is sleeved on the spindle 1, and the torsion spring 6 is located in the first gap.
Specifically, the first gap may serve as a receiving groove for the torsion spring 6, and in the present embodiment, the diameter of the wire of the torsion spring 6 is not greater than the thickness of the annular wall of the first rotating ring 4 and the second rotating ring 5.
Alternatively, both ends of the torsion spring 6 are embedded inside the first and second rotating parts 2 and 3, respectively.
Specifically, can insert the inside of first rotation portion 2 and second rotation portion 3 respectively with the both ends of torsional spring 6, realize hidden arranging, avoid occupying exterior space.
Optionally, the self-locking structure comprises:
the pin hole 7 is formed in one end, close to the second rotating ring 5, of the first rotating ring 4;
the chute 8 is arranged in the second rotating ring 5;
the positioning pin 9 is arranged in the sliding groove 8 in a sliding manner;
and a second elastic member provided in the slide groove 8 and capable of driving the insertion of the positioning pin 9 into the pin hole 7 when the first and second rotating portions 2 and 3 rotate to the set position.
Specifically, the second elastic member applies elastic force to the positioning pin 9 to move in the pin hole 7, and the positioning pin 9 is automatically inserted into the pin hole 7 to realize self-locking when the first rotating part 2 and the second rotating part 3 rotate to the set position.
Optionally, one side of the pin hole 7 is provided with a guide groove 11, one end of the guide groove 11 is communicated with the pin hole 7, the guide groove 11 becomes gradually shallower from the end close to the pin controller to the end far away from the pin hole 7, and the positioning pin 9 can slide in the guide groove 11.
Specifically, the guide groove 11 is formed in a slope-type structure, and guides the positioning pin 9, thereby ensuring that the positioning pin 9 ejected by the second elastic member can smoothly slide into the pin hole 7.
In the present embodiment, the second elastic member is a compression spring 10.
Optionally, the mandrel further comprises a plug 12, the plug 12 is detachably connected with the mandrel 1, the plug 12 is used for limiting the first rotating ring 4 and the second rotating ring 5 from falling off from the mandrel 1, the sliding groove 8 penetrates through the second rotating portion 3, and the plug 12 plugs the second elastic component in the sliding groove 8.
Specifically, the plug 12 can block the second rotating ring 5 to prevent the first rotating ring 4 and the second rotating ring 5 from falling off from the mandrel 1, and on the other hand, the second elastic component can be taken down after the plug 12 is removed, and the unfolded foldable wing is folded again for the next use.
Optionally, a first stopper 13 and a second stopper 14 are further included, the first stopper 13 and the second stopper 14 are respectively disposed on the first rotating portion 2 and the second rotating portion 3, and the first stopper 13 and the second stopper 14 approach and contact each other when the first rotating portion 2 and the second rotating portion 3 rotate to a set position.
Specifically, the first stopper 13 and the second stopper 14 are in butt-joint contact with each other after the foldable wing is unfolded and are subjected to positive pressure, so that the function of limiting and preventing torsional impact is achieved.
The present invention also provides an unmanned aerial vehicle, comprising:
a foldable wing;
foretell unmanned aerial vehicle wing folding mechanism.
In conclusion, when the wing folding mechanism of the unmanned aerial vehicle provided by the invention is used, two folding parts of the foldable wing are respectively arranged on the first rotating part 2 and the second rotating part 3; when the mechanism is in a folded state, as shown in FIGS. 1-2 and 5-7, two folded parts of the foldable wing are also in a folded state; after the mechanism is released, the first rotating part 2 and the second rotating part 3 rotate under the driving of the torsion spring 6 to drive the foldable wing to automatically unfold; in the rotating process of the first rotating part 2 and the second rotating part 3, the positioning pin 9 moves to the positioning groove in the sliding groove 8 under the action of the second elastic component; when the foldable wing is automatically unfolded in place, the first limiting block 13 is in butt contact with the second limiting block 14, the first rotating portion 2 and the second rotating portion 3 stop rotating, and the positioning pin 9 is inserted into the pin hole 7 to realize self-locking. The mechanism adopts a torsion spring 6 to realize the automatic unfolding of the foldable wing; the foldable wing has a self-locking function, and can realize self-locking after being unfolded in place, so that the reliability of the folding mechanism of the unmanned aerial vehicle is met; have the limit function that first stopper 13 and second stopper 14 formed, can avoid the wing to expand to strike too big when targetting in place, cause the damage to locating pin 9, improve unmanned aerial vehicle folding mechanism's reliability. The folding mechanism realizes wing folding, can reduce the wing volume in a launching state, and can meet the use requirements of unmanned aerial vehicles such as a barrel shooting unmanned aerial vehicle, a flying bomb patrol unmanned aerial vehicle and the like.
The wing folding mechanism can increase the wing aspect ratio, improve the lift-drag ratio of the whole unmanned aerial vehicle, improve the endurance performance of the unmanned aerial vehicle and improve the multitask capability of the unmanned aerial vehicle.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The utility model provides an unmanned aerial vehicle wing folding mechanism which characterized in that, this mechanism includes:
a mandrel;
the first rotating part and the second rotating part are respectively used for connecting two folding parts of a foldable wing of the unmanned aerial vehicle, one end of the first rotating part and one end of the second rotating part are respectively provided with a first rotating ring and a second rotating ring, and the first rotating ring and the second rotating part are sleeved on the mandrel in a rotating mode;
a first elastic member connected to the first rotating portion and the second rotating portion, the first elastic member being capable of driving the first rotating portion and the second rotating portion to rotate in opposite directions in an axial direction of the core;
and the self-locking structure is arranged between the first rotating part and the second rotating part and can lock the relative positions of the first rotating part and the second rotating part when the first rotating part and the second rotating part rotate to a set position.
2. The unmanned aerial vehicle wing folding mechanism of claim 1, wherein the first rotating portion and the second rotating portion are both plate-shaped, the first rotating portion and the second rotating portion are tangent to the first rotating ring and the second rotating ring, respectively, and the first rotating portion and the second rotating portion are in a same plane when in the set position.
3. The wing folding mechanism of unmanned aerial vehicle as claimed in claim 1, wherein one end of first rotation portion is provided with two first rotation rings, a first gap is provided between the two first rotation rings, one end of second rotation portion is provided with two second rotation rings, and the two second rotation rings are respectively provided at a side where the two first rotation rings are far away from each other.
4. The unmanned aerial vehicle wing folding mechanism of claim 3, wherein the first elastic component is a torsion spring, the torsion spring is sleeved on the mandrel, and the torsion spring is located in the first gap.
5. The unmanned aerial vehicle wing folding mechanism of claim 4, wherein both ends of the torsion spring are respectively embedded inside the first rotating portion and the second rotating portion.
6. The unmanned aerial vehicle wing folding mechanism of claim 1, wherein the self-locking structure comprises:
the pin hole is formed in one end, close to the second rotating ring, of the first rotating ring;
the sliding groove is arranged in the second rotating ring;
the positioning pin is arranged in the sliding groove in a sliding manner;
and a second elastic member disposed in the sliding groove, the second elastic member being capable of driving the positioning pin to be inserted into the pin hole when the first rotating portion and the second rotating portion rotate to a set position.
7. The wing folding mechanism of unmanned aerial vehicle as claimed in claim 6, wherein one side of pinhole is provided with a guide way, one end of guide way communicates with the pinhole, the guide way becomes shallow gradually from the end that is close to the round pin accuse to the end that is far away from the pinhole, the locating pin can slide in the guide way.
8. The wing folding mechanism of an unmanned aerial vehicle as claimed in claim 7, further comprising a plug detachably connected to the mandrel, wherein the plug is configured to limit the first rotating ring and the second rotating ring from falling off the mandrel, the sliding groove passes through the second rotating portion, and the plug plugs the second elastic member in the sliding groove.
9. The unmanned aerial vehicle wing folding mechanism of claim 3, further comprising a first stopper and a second stopper, the first stopper and the second stopper are respectively disposed on the first rotating portion and the second rotating portion, and the first stopper and the second stopper are close to and contact each other when the first rotating portion and the second rotating portion rotate to a set position.
10. An unmanned aerial vehicle, its characterized in that, this unmanned aerial vehicle includes:
a foldable wing;
the unmanned aerial vehicle wing fold mechanism of any of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111632320.5A CN114394223A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111632320.5A CN114394223A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle |
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| CN114394223A true CN114394223A (en) | 2022-04-26 |
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| CN202111632320.5A Pending CN114394223A (en) | 2021-12-28 | 2021-12-28 | Unmanned aerial vehicle wing folding mechanism and unmanned aerial vehicle |
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| CN111332456A (en) * | 2020-04-14 | 2020-06-26 | 北京远度互联科技有限公司 | Solid locking structure and unmanned aerial vehicle |
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2021
- 2021-12-28 CN CN202111632320.5A patent/CN114394223A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2011014106A1 (en) * | 2009-07-31 | 2011-02-03 | Общество С Ограниченной Ответственностью "Научно-Производственная Фирма "Сигма-Тс" | Airplane with folding wings and device for folding the wings of an airplane |
| CN105000168A (en) * | 2014-04-25 | 2015-10-28 | 波音公司 | System for latching and locking a foldable airfoil |
| CN105840647A (en) * | 2016-05-31 | 2016-08-10 | 南京理工大学 | Self-locking type hinge and cubic star battery array adopting self-locking type hinge |
| CN209506061U (en) * | 2018-11-08 | 2019-10-18 | 彩虹无人机科技有限公司 | A kind of small-sized hinge-type fold mechanism, folding wings unmanned plane and emission system |
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