CN112407239A - Folding wing unmanned aerial vehicle's fin folding mechanism - Google Patents
Folding wing unmanned aerial vehicle's fin folding mechanism Download PDFInfo
- Publication number
- CN112407239A CN112407239A CN202011419471.8A CN202011419471A CN112407239A CN 112407239 A CN112407239 A CN 112407239A CN 202011419471 A CN202011419471 A CN 202011419471A CN 112407239 A CN112407239 A CN 112407239A
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- CN
- China
- Prior art keywords
- fixing piece
- gland
- moving part
- torsion spring
- torsion
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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
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
Abstract
The invention discloses an empennage folding mechanism of a folding wing unmanned aerial vehicle, which comprises a fixing piece, a torsional spring, a fixing piece gland and a rotary moving piece, wherein the rotary moving piece is sleeved and connected inside the fixing piece, the torsional spring is sleeved and connected inside the rotary moving piece, one end of the torsional spring is fixedly connected with the middle part of the fixing piece, and one end of the rotary moving piece is inserted and connected with the middle part of the fixing piece gland. The invention has simple structure, convenient installation and small occupied space, can be used when the empennage rotates and folds along a certain rotating shaft of any plane of the fuselage, has wider application range, can be quickly unfolded under the torsion action of the torsion spring in the use process, effectively improves the unfolding efficiency of the empennage, and has no extra electric loss.
Description
Technical Field
The invention relates to an empennage folding mechanism of an unmanned aerial vehicle, in particular to an empennage folding mechanism of a folding wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.
Background
The application of current society unmanned aerial vehicle is more and more extensive, and the mode of taking off is also more and more diversified, because the rolloff take off and land unmanned aerial vehicle is higher to the place requirement of taking off, has developed the unmanned aerial vehicle of multiple take off and land modes such as VTOL, launch, a section of thick bamboo penetrate, air jettison afterwards.
Many times, single aircraft can't independently accomplish when carrying out complicated task, and the thought in coordination of cluster unmanned aerial vehicle comes to bear, and many options section of thick bamboo of cluster unmanned aerial vehicle launching mode are penetrated, are thrown in the air, and this kind of launching mode just requires that unmanned aerial vehicle occupation space is little, and each wing all can be folded, and the wing is expanded fast and targets in place after the transmission. The folding and unfolding driving modes are generally electrically driven and mechanically driven: the electric drive can drive the airfoil to move by controlling a steering engine or a motor, but has obvious defects that the unfolding speed is slow, and extra electric quantity is required to be lost in the flying process; the mechanical drive is generally driven by the elastic force of a spring, and the mode has a simple structure, high unfolding speed and no additional electric loss.
Disclosure of Invention
The invention aims to provide a tail folding mechanism of a folding wing unmanned aerial vehicle, which aims to solve the problems that the electric drive provided by the background technology can drive the wing surface to move by controlling a steering engine or a motor, but the defects are obvious, the unfolding speed is slow, and extra electric quantity is required to be lost in the flying process.
In order to achieve the purpose, the invention provides the following technical scheme: including mounting, torsional spring, mounting gland and rotatory moving part, the inside cover of mounting is established and is connected with rotatory moving part, the inside cover of rotatory moving part is established and is connected with the torsional spring, the one end of torsional spring and the middle part fixed connection of mounting, the one end of rotatory moving part alternates with the middle part of mounting gland and is connected.
According to a preferable technical scheme, the fixing piece comprises a fixing piece torsional spring mounting hole, a fixing piece limiting groove and a fixing piece mounting hole, the fixing piece torsional spring mounting hole is formed in the middle of one end of the fixing piece, the fixing piece limiting grooves are formed in two sides of one end of the fixing piece, and four fixing piece mounting holes are formed in the side of the fixing piece at equal intervals.
According to a preferred technical scheme, the torsion spring comprises a torsion spring fixed end torsion arm and a torsion spring movable end torsion arm, wherein the torsion spring fixed end torsion arm is fixedly arranged at one end of the torsion spring, the torsion spring movable end torsion arm is fixedly arranged at the other end of the torsion spring, and the torsion spring movable end torsion arm is connected with the fixing piece torsion spring mounting hole in an inserting mode.
As a preferred technical scheme of the present invention, the fixing member gland includes a fixing member gland mounting hole, a circular hole is formed at the center of the fixing member gland, and fixing member gland mounting holes are formed at four sides of the fixing member gland.
According to a preferred technical scheme, the rotary moving part comprises a moving part torsional spring clamping groove, a moving part limiting lug and a moving part tail wing installation end, the center of the moving part is provided with the moving part torsional spring clamping groove, the moving part torsional spring clamping groove is connected with a torsional spring fixed end in an embedded mode, two moving part limiting lugs are symmetrically and fixedly arranged on two sides of one end of the moving part, the two moving part limiting lugs are connected with a fixing part limiting groove in an inserting mode, the center of the other end of the moving part is fixedly provided with the moving part tail wing installation end, and the moving part tail wing installation end is connected with a round hole formed in the center of a fixing part.
As a preferred technical solution of the present invention, the inner diameter of the fixing member mounting hole is aligned with the position of the fixing member gland mounting hole, and the inner diameter of the fixing member mounting hole is matched with the inner diameter of the fixing member gland mounting hole.
As a preferred technical scheme of the invention, the inner diameter of the mounting hole of the fixing piece torsion spring is matched with the size of the end head of the torsion arm at the movable end of the torsion spring.
As a preferred technical solution of the present invention, the size of the inside of the fixed member matches the size of the rotating movable member.
Compared with the prior art, the invention has the beneficial effects that:
the tail wing folding mechanism of the folding wing unmanned aerial vehicle is simple in structure, convenient to install, small in occupied space, capable of being used when the tail wing rotates and folds along a certain rotating shaft on any plane of a machine body, wide in application range, capable of being unfolded rapidly under the torsion of the torsion spring in the using process, capable of effectively improving the unfolding efficiency of the tail wing, and free of extra electric loss.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the assembled structure of the present invention;
fig. 3 is a schematic view of the torsion spring structure of the present invention.
In the figure: 1. a fixing member; 1-1, a fixing piece torsion spring mounting hole; 1-2, fixing piece limiting grooves; 1-3, fixing piece mounting holes; 2. a torsion spring; 2-1, fixing a torsion arm at the end of the torsion spring; 2-2, torsion arms at the movable ends of the torsion springs; 3. a fixing piece gland; 3-1, pressing a cover mounting hole of the fixing piece; 4. a rotating movable member; 4-1, a torsion spring clamping groove of the movable part; 4-2, limiting by the movable piece; 4-3, movable part empennage installation end.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-3, the present invention provides a technical solution of a tail folding mechanism of a folding wing drone:
according to fig. 1-3, including mounting 1, torsional spring 2, mounting gland 3 and rotating movable part 4, the rotating movable part 4 is established and connected to the inside cover of mounting 1, and the torsional spring 2 is established and connected to the inside cover of rotating movable part 4, and the one end of torsional spring 2 and the middle part fixed connection of mounting 1, the one end of rotating movable part 4 and the middle part of mounting gland 3 alternate and are connected.
According to the drawings of fig. 1 and 2, the fixing member 1 comprises a fixing member torsional spring mounting hole 1-1, a fixing member limiting groove 1-2 and a fixing member mounting hole 1-3, the fixing member torsional spring mounting hole 1-1 is formed in the middle of one end of the fixing member 1, so that one end of the torsional spring 2 can be conveniently fixed, the fixing member limiting grooves 1-2 are formed in two sides of one end of the fixing member 1, the rotating movable member 4 is limited, and the four fixing member mounting holes 1-3 are formed in the side of the fixing member 1 at equal intervals, so that the fixing member 1 can be conveniently.
The torsion spring 2 comprises a torsion spring fixed end torsion arm 2-1 and a torsion spring movable end torsion arm 2-2, one end of the torsion spring 2 is fixedly provided with the torsion spring fixed end torsion arm 2-1, the other end of the torsion spring 2 is fixedly provided with the torsion spring movable end torsion arm 2-2, and the torsion spring movable end torsion arm 2-2 is connected with the fixing piece torsion spring mounting hole 1-1 in an inserting mode.
The fixing part gland 3 comprises fixing part gland mounting holes 3-1, a round hole is formed in the center of the fixing part gland 3, and fixing part gland mounting holes 3-1 are formed in four side edges of the fixing part gland 3, so that the fixing part gland 3 can be conveniently mounted.
The rotary moving part 4 comprises a moving part torsional spring clamping groove 4-1, a moving part limiting lug 4-2 and a moving part tail wing installation end 4-3, the center of the moving part 4 is provided with the moving part torsional spring clamping groove 4-1, the moving part torsional spring clamping groove 4-1 is connected with a torsional spring fixed end torsion arm 2-1 in an embedding manner, two moving part limiting lugs 4-2 are symmetrically and fixedly arranged on two sides of one end of the moving part 4, the two moving part limiting lugs 4-2 are alternately connected with a fixing part limiting groove 1-2, the center of the other end of the moving part 4 is fixedly provided with the moving part tail wing installation end 4-3, and the moving part tail wing installation end 4-3 is alternately connected with a round.
The inner diameter of the fixing piece mounting hole 1-3 is aligned with the position of the fixing piece gland mounting hole 3-1, the inner diameter of the fixing piece mounting hole 1-3 is matched with the inner diameter of the fixing piece gland mounting hole 3-1, the embedding of the fixing piece gland mounting hole 3-1 is ensured, the inner diameter of the fixing piece torsion spring mounting hole 1-1 is matched with the size of the end of the torsion arm 2-2 at the movable end of the torsion spring, and the size of the inside of the fixing piece 1 is matched with the size of the rotary moving piece 4.
When the tail folding mechanism of the folding wing unmanned aerial vehicle is used, firstly, a torsion arm 2-1 at the fixed end of a torsion spring 2 is inserted into a mounting hole 1-1 of a fixed part torsion spring, a torsion arm 2-2 at the movable end of the torsion spring 2 is clamped into a clamping groove 4-1 of a movable part torsion spring of a rotary movable part 4, an intermediate shaft of the rotary movable part 4 passes through the torsion spring 2 and is arranged into the fixed part 1, at the moment, the movable part limit 4-2 of the rotary movable part 4 is just clamped into a fixing part limit groove 1-2 on the fixed part 1, the movable part limit 4-2 is matched with the fixing part limit groove 1-2 to limit the rotating angle of the folding and unfolding of the tail, the design is 90-degree limit, and the mounting end 4-3 of the movable part tail is connected with the tail through a through hole at the center of a fixing, the rotating movable part 4 can drive the empennage to rotate and fold together when rotating, then the folding mechanism is installed on the empennage fitting plane through the fixing part gland installation hole 3-1 and the fixing part installation hole 1-3 of the fixing part 1 by screws, at the moment, the fixing part gland 3 can axially limit the rotating movable part 4, meanwhile, the rotating movable part 4 is prevented from rubbing the machine body when rotating, when the unmanned aerial vehicle is not launched, the empennage is in a folded state and clings to the inner wall of a launching tube, the empennage is limited to be unfolded through the inner wall of the tube, at the moment, the torsion spring 2 is in a torsion limit compression state, the torsion of two torsion arms is also maximum, after the unmanned aerial vehicle is launched, the empennage does not have limit restraint of the tube wall, the empennage can be rapidly unfolded.
In the description of the present invention, it is to be understood that the indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings and are only for convenience in describing the present invention and simplifying the description, but are not intended to indicate or imply that the indicated devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be construed as limiting the present invention.
In the present invention, unless otherwise explicitly specified or limited, for example, it may be fixedly attached, detachably attached, or integrated; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate, and may be communication between two elements or interaction relationship between two elements, unless otherwise specifically limited, and the specific meaning of the terms in the present invention will be understood by those skilled in the art according to specific situations.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides a folding wing unmanned aerial vehicle's fin folding mechanism, includes mounting (1), torsional spring (2), mounting gland (3) and rotating movement part (4), its characterized in that, the inside cover of mounting (1) is established and is connected with rotating movement part (4), the inside cover of rotating movement part (4) is established and is connected with torsional spring (2), the middle part fixed connection of the one end of torsional spring (2) and mounting (1), the one end of rotating movement part (4) alternates with the middle part of mounting gland (3) and is connected.
2. The tail folding mechanism of folding wing drone according to claim 1, characterized in that: the fixing piece (1) comprises a fixing piece torsional spring mounting hole (1-1), a fixing piece limiting groove (1-2) and a fixing piece mounting hole (1-3), the fixing piece torsional spring mounting hole (1-1) is formed in the middle of one end of the fixing piece (1), the fixing piece limiting grooves (1-2) are formed in two sides of one end of the fixing piece (1), and four fixing piece mounting holes (1-3) are formed in the side of the fixing piece (1) in an equidistant mode.
3. The tail folding mechanism of folding wing drone according to claim 1, characterized in that: the torsion spring (2) comprises a torsion spring fixed end torsion arm (2-1) and a torsion spring movable end torsion arm (2-2), wherein the torsion spring fixed end torsion arm (2-1) is fixedly arranged at one end of the torsion spring (2), the torsion spring movable end torsion arm (2-2) is fixedly arranged at the other end of the torsion spring (2), and the torsion spring movable end torsion arm (2-2) is connected with the fixing piece torsion spring mounting hole (1-1) in a penetrating manner.
4. The tail folding mechanism of folding wing drone according to claim 1, characterized in that: the fixing part gland (3) comprises fixing part gland mounting holes (3-1), a round hole is formed in the center of the fixing part gland (3), and the fixing part gland mounting holes (3-1) are formed in four side edges of the fixing part gland (3).
5. The tail folding mechanism of folding wing drone according to claim 1, characterized in that: the rotary moving part (4) comprises a moving part torsional spring clamping groove (4-1), a moving part limiting convex block (4-2) and a moving part tail wing installation end (4-3), a moving part torsional spring clamping groove (4-1) is arranged at the center of the moving part (4), the moving part torsional spring clamping groove (4-1) is connected with a torsional arm (2-1) at the fixed end of the torsional spring in an embedding way, two moving part limiting lugs (4-2) are symmetrically and fixedly arranged on two sides of one end of the moving part (4), the two moving part limiting lugs (4-2) are connected with the fixed part limiting grooves (1-2) in an inserting manner, the center of the other end of the moving part (4) is fixedly provided with a moving part tail wing installation end (4-3), the movable part tail wing mounting end (4-3) is connected with a round hole arranged in the center of the fixed part gland (3) in an inserting manner.
6. The tail folding mechanism of folding wing drone according to claim 2, characterized in that: the inner diameter of the fixing piece mounting hole (1-3) is aligned with the position of the fixing piece gland mounting hole (3-1), and the inner diameter of the fixing piece mounting hole (1-3) is matched with the inner diameter of the fixing piece gland mounting hole (3-1).
7. The tail folding mechanism of folding wing drone according to claim 2, characterized in that: the inner diameter of the mounting hole (1-1) of the fixed part torsion spring is matched with the size of the end of the torsion arm (2-2) at the movable end of the torsion spring.
8. The tail folding mechanism of folding wing drone according to claim 1, characterized in that: the size of the inside of the fixed piece (1) is matched with the size of the rotary movable piece (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419471.8A CN112407239A (en) | 2020-12-06 | 2020-12-06 | Folding wing unmanned aerial vehicle's fin folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419471.8A CN112407239A (en) | 2020-12-06 | 2020-12-06 | Folding wing unmanned aerial vehicle's fin folding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112407239A true CN112407239A (en) | 2021-02-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011419471.8A Pending CN112407239A (en) | 2020-12-06 | 2020-12-06 | Folding wing unmanned aerial vehicle's fin folding mechanism |
Country Status (1)
| Country | Link |
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| CN (1) | CN112407239A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117125248A (en) * | 2023-10-24 | 2023-11-28 | 西安羚控电子科技有限公司 | Wing of flying device and V-tail flying device |
| CN117585215A (en) * | 2024-01-18 | 2024-02-23 | 成都金支点科技有限公司 | Folding wing of small unmanned aerial vehicle expands and locking mechanism and unmanned aerial vehicle |
-
2020
- 2020-12-06 CN CN202011419471.8A patent/CN112407239A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117125248A (en) * | 2023-10-24 | 2023-11-28 | 西安羚控电子科技有限公司 | Wing of flying device and V-tail flying device |
| CN117585215A (en) * | 2024-01-18 | 2024-02-23 | 成都金支点科技有限公司 | Folding wing of small unmanned aerial vehicle expands and locking mechanism and unmanned aerial vehicle |
| CN117585215B (en) * | 2024-01-18 | 2024-03-26 | 成都金支点科技有限公司 | Folding wing of small unmanned aerial vehicle expands and locking mechanism and unmanned aerial vehicle |
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