CN112407240A - Rotatory locking mechanism of section of thick bamboo shooting formula unmanned aerial vehicle wing - Google Patents
Rotatory locking mechanism of section of thick bamboo shooting formula unmanned aerial vehicle wing Download PDFInfo
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- CN112407240A CN112407240A CN202011419898.8A CN202011419898A CN112407240A CN 112407240 A CN112407240 A CN 112407240A CN 202011419898 A CN202011419898 A CN 202011419898A CN 112407240 A CN112407240 A CN 112407240A
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- torsion spring
- locking pin
- driving torsion
- rotary
- wing
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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
-
- 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
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a wing rotary locking mechanism of a barrel-jet type unmanned aerial vehicle, which comprises a base, a driving torsion spring, a locking pin pressure spring, a vibration-stopping rubber pad, a rotary wing joint and a cover plate, wherein the driving torsion spring is arranged in a mounting groove of the driving torsion spring, the locking pin is arranged in a limiting hole of the locking pin, the locking pin pressure spring is sleeved at the upper end part of the locking pin, the rotary wing joint is arranged on the upper surface of the base, the driving torsion spring mounting groove is arranged on the edge side at the top end of the rotary wing joint, and the locking pin limiting hole is arranged on the edge side at the top end of a rotary drum sleeve. The locking is firm, and when the wing is completely unfolded, the locking pin is pressed into the locking pin limiting hole by the locking pin pressure spring to lock the wing.
Description
Technical Field
The invention relates to an unmanned aerial vehicle locking structure, in particular to a cylinder jet type unmanned aerial vehicle wing rotary locking mechanism, and belongs to the technical field of unmanned aerial vehicles.
Background
The cylinder-shooting type unmanned aerial vehicle is folded through the folding mechanism, the space size is effectively reduced, the shooting mode of cylinder shooting is adopted, and the cylinder-shooting type unmanned aerial vehicle has the characteristics of low cost, high cost ratio, small size and the like. And the flexible maneuverability and the regional adaptability of the cylinder-jet unmanned aerial vehicle attract a large number of domestic and foreign experts to carry out deep research on the cylinder-jet unmanned aerial vehicle.
The wing folding mechanism generally comprises two parts, namely a folding and unfolding mechanism and a limiting and locking mechanism. The wing folding and unfolding mechanism is divided into an electric driving type and a spring driving type. Electric drive type: the motor is used as power to drive the wings to move through the transmission mechanism, is convenient to control, can be actively folded after being unfolded, and has the defects of low unfolding speed, complex structure and need of an additional driving motor. Spring elastic force drive type: the wing is driven by the spring to move, the unfolding speed is high, the structure is simple, and an additional power device is not needed.
To section of thick bamboo formula unmanned aerial vehicle, the spring drive mode is more suitable, and present majority's research is concentrated on two torsional springs to two wing independent drive forms, but the ubiquitous structure is complicated, the installation is inconvenient, occupation space is big scheduling problem, and the spacing locking mechanism of folding mechanism has slider formula, fixture block formula, bulb round pin formula etc. has shortcomings such as structural volume is big, the lock is unstable usually.
Disclosure of Invention
The invention aims to provide a wing rotating locking mechanism of a barrel-shooting type unmanned aerial vehicle, which aims to solve the problems that two torsion springs are provided to independently drive two wings in the background technology, but the wing rotating locking mechanism is complex in structure, inconvenient to install, large in occupied space and the like. The limit locking mechanism of the folding mechanism has the defects of a sliding block type, a clamping block type, a ball pin type and the like, and generally has the defects of large structure volume, unstable locking and the like.
In order to achieve the purpose, the invention provides the following technical scheme: a wing rotary locking mechanism of a barrel-jet type unmanned aerial vehicle comprises a base, a driving torsion spring, a locking pin pressure spring, a vibration-stopping rubber pad, a rotary wing joint and a cover plate, wherein a driving torsion spring mounting groove is formed in the side of the top end of the base, a rotating shaft is fixedly mounted in the middle of the top end of the base, rotating lug limiting grooves which are symmetrically arranged are formed in two sides of the rotating shaft, a base mounting hole penetrating through the base is formed in the bottom end of the driving torsion spring mounting groove, the base is fixed on the body of the unmanned aerial vehicle through a screw thread mounting screw in the inner part of the base mounting hole, a driving torsion spring is placed in the driving torsion spring mounting groove, a locking pin limiting hole is formed in the side of the rotating shaft, a locking pin is arranged in the locking pin limiting hole, the locking pin pressure spring is, the avris on rotary wing joint top has seted up the drive torsional spring mounting groove, the communicating drive torsional spring horizontal spacing groove with the drive torsional spring mounting groove is seted up to one side of drive torsional spring mounting groove, middle part fixed mounting in the drive torsional spring mounting groove has the rotary drum sleeve, the both sides fixed mounting on rotary drum sleeve top has the rotatory lug that two symmetries set up, the spacing hole of locking round pin has been seted up to the avris on rotary drum sleeve top, the drive torsional spring is placed in the drive torsional spring mounting groove, and the drive torsional spring horizontal spacing end of drive torsional spring places in the drive torsional spring horizontal spacing groove, rotatory lug is arranged in rotatory lug spacing groove, the pivot muffjoint is in the pivot, the upper end of locking round pin passes the spacing hole of locking round.
As a preferred technical scheme of the present invention, a driving torsion spring vertical limiting hole is formed in the driving torsion spring mounting groove, wherein the vertical limiting end of the driving torsion spring is inserted into the driving torsion spring vertical limiting hole for limiting the shaking of the driving torsion spring.
As a preferable technical scheme of the invention, the vibration-stopping rubber pads are arranged at the centers of two ends in the rotating lug limiting groove symmetrically, and when the wing is unfolded, the vibration-stopping rubber pads can effectively reduce the vibration caused by the collision of the rotating lug and the rotating lug limiting groove.
According to a preferable technical scheme of the invention, a lock pin pulling hole is formed in the top of the lock pin, the inner part of the lock pin pulling hole penetrates through the pull ring, and at the moment, the lock pin is pressed in the lock pin limiting hole by a lock pin pressure spring.
As a preferred technical scheme of the invention, two ends of the rotary wing joint are respectively provided with two wing installation limiting holes, and wings are fixedly installed in the wing installation limiting holes.
As a preferable technical scheme of the invention, the top of the rotating shaft sleeve is fixedly provided with a cover plate, and the cover plate is fixed by a cover plate mounting hole and a screw to prevent the rotary wing joint from loosening up and down.
Compared with the prior art, the invention has the beneficial effects that:
the wing rotary locking mechanism of the barrel-injection type unmanned aerial vehicle can realize rapid unfolding of wings, accurate positioning and reliable locking, is reasonable in design, simple, convenient and rapid to implement and regular in appearance, the thickness of the whole rotary locking mechanism is effectively reduced by the design concept of a single torsion spring, the effective use space of the unmanned aerial vehicle is increased, the limiting locking mechanism occupies a small space and is firm in locking, when the wings are completely unfolded, the locking pin is pressed into the locking pin limiting hole by the locking pin pressure spring to lock the wings, and the vibration caused by collision when the wings are unfolded is effectively reduced by the vibration-stopping rubber pad arranged in the rotary locking mechanism.
Drawings
FIG. 1 is an exploded view of the assembly of the present invention;
FIG. 2 is an assembly view of the present invention;
FIG. 3 is a schematic partial cross-sectional view of the present invention;
FIG. 4 is a schematic rotation diagram of the present invention;
FIG. 5 is a schematic view of a base structure according to the present invention;
FIG. 6 is a schematic view of the driving torsion spring according to the present invention;
FIG. 7 is a schematic view of the locking structure of the present invention;
FIG. 8 is a schematic view of the shock-stopping rubber pad of the present invention;
FIG. 9 is a schematic view of the upper surface configuration of a rotary wing joint of the present invention;
FIG. 10 is a schematic view of the lower surface configuration of a rotary wing joint according to the present invention;
fig. 11 is a schematic view of a cover plate.
In the figure: 1. a base; 1-1, base mounting holes; 1-2, cover plate mounting holes; 1-3, driving the torsion spring to vertically limit the hole; 1-4, locking pin limiting holes; 1-5, rotating the bump limiting groove; 1-6, driving the torsion spring mounting groove; 1-7, a rotating shaft; 2. a drive torsion spring; 2-1, driving the vertical limiting end of the torsion spring; 2-2, driving the horizontal limiting end of the torsion spring; 3. a locking pin; 3-1, locking pin pulling up holes; 4. a locking pin pressure spring; 5. a vibration-proof rubber pad; 6. a rotary wing joint; 6-1, locking pin limiting holes; 6-2, mounting a limiting hole on the wing; 6-3, wing joint; 6-4 rotating the lug; 6-5, driving the horizontal limiting groove of the torsion spring; 6-6, a rotating shaft sleeve; 6-7, a driving torsion spring mounting groove 7 and a cover plate; 7-1, a cover plate mounting hole, 8 and a machine body; 9. an airfoil.
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 to 11, the present invention provides a technical solution of a wing rotation locking mechanism of a tube-jet type unmanned aerial vehicle: a wing rotary locking mechanism of a barrel-shooting type unmanned aerial vehicle comprises a base 1, a driving torsion spring 2, a locking pin 3, a locking pin pressure spring 4, a vibration-stopping rubber pad 5, a rotary wing joint 6 and a cover plate 7, wherein the side edge of the top end of the base 1 is provided with driving torsion spring mounting grooves 1-6, the middle part of the top end of the base 1 is fixedly provided with rotating shafts 1-7, two sides of each rotating shaft 1-7 are respectively provided with symmetrically arranged rotating lug limiting grooves 1-5, the bottom end of each driving torsion spring mounting groove 1-6 is provided with a base mounting hole 1-1 penetrating through the base 1, the base 1 is fixed on a body 8 of the unmanned aerial vehicle through a screw thread mounting screw in the base mounting hole 1-1, the driving torsion spring 2 is placed in the driving torsion spring mounting grooves 1-6, the side edge of the rotating shafts 1-7 is provided with locking pin limiting holes 1-, the upper end part of the locking pin 3 is sleeved with a locking pin pressure spring 4, the upper surface of the base 1 is provided with a rotary wing joint 6, the edge side of the top end of the rotary wing joint 6 is provided with a driving torsion spring installation groove 6-7, one side of the driving torsion spring installation groove 6-7 is provided with a driving torsion spring horizontal limiting groove 6-5 communicated with the driving torsion spring installation groove 6-7, the middle part in the driving torsion spring installation groove 6-7 is fixedly provided with a rotary drum sleeve 6-6, two sides of the top end of the rotary drum sleeve 6-6 are fixedly provided with two symmetrically arranged rotary lugs 6-4, the edge side of the top end of the rotary drum sleeve 6-6 is provided with a locking pin limiting hole 6-1, the driving torsion spring 2 is placed in the driving torsion spring installation groove 6-7, and the driving torsion spring horizontal limiting end 2-2, the rotating lug 6-4 is arranged in the rotating lug limiting groove 1-5, the rotating shaft sleeve 6-6 is sleeved on the rotating shaft 1-7, and the upper end of the locking pin 3 penetrates through the locking pin limiting hole 6-1.
The driving torsion spring mounting grooves 1-6 are internally provided with driving torsion spring vertical limiting holes 1-3, wherein the vertical limiting end 2-1 of the driving torsion spring 2 is inserted into the driving torsion spring vertical limiting holes 1-3 and used for limiting the shaking of the driving torsion spring 2.
The anti-vibration rubber pads 5 are arranged at the centers of two ends in the rotating lug limiting grooves 1-5 in a symmetrical mode, and when the wings 9 are unfolded, the anti-vibration rubber pads 5 can effectively reduce vibration caused by collision of the rotating lugs 6-4 and the rotating lug limiting grooves 1-5.
The top of the locking pin 3 is provided with a locking pin pulling hole 3-1, the inside of the locking pin pulling hole 3-1 penetrates through the pull ring, and at the moment, the locking pin 3 is pressed in the locking pin limiting hole 1-4 by the locking pin pressure spring 4.
Two ends of the rotary wing joint 6 are respectively provided with two wing installation limiting holes 6-2, and wings 9 are fixedly installed in the wing installation limiting holes 6-2.
The top of the rotating shaft sleeve 6-6 is fixedly provided with a cover plate 7 which is fixed by screws through cover plate mounting holes 7-1 and 1-2 and is used for preventing the rotary wing joint 6 from loosening up and down.
According to fig. 1-3, specifically, base 1, lock round pin 3, rotary wing joint 6, apron 7 all adopt 7075 aviation aluminum alloy of reference numeral, satisfy sufficient use intensity to make this mechanism weight lighter, be favorable to reducing unmanned aerial vehicle's weight, drive torsional spring 2 and lock round pin pressure spring 4 adopt the SWPB spring steel of reference numeral, and end and shake rubber pad 5 adopts vulcanized rubber.
Referring to fig. 1-9, in particular, the rotary locking mechanism can rotate the wing 9 by 90 °, and when the wing 9 is retracted, the wing 9 is parallel to the fuselage 8; the driving torsion spring 2 adopts a single torsion spring, and the driving torsion spring 2 is provided with a limit in the vertical direction and the horizontal direction.
When the wing 9 is unfolded, the wing 9 is perpendicular to the fuselage 8, the locking pin 3 is pressed in the locking pin limiting holes 1-4 by the locking pin pressure spring 4 to complete locking of the wing 9, the locking pin 3 is pulled up by a string or a metal ring penetrating through the locking pin pulling-up hole 3-1 to be separated from the locking pin limiting holes 1-4, and the wing 9 is rotated clockwise to complete rotary folding of the wing 9.
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 (6)
1. A wing rotary locking mechanism of a barrel-shooting type unmanned aerial vehicle comprises a base (1), a driving torsion spring (2), a locking pin (3), a locking pin pressure spring (4), a vibration-stopping rubber pad (5), a rotary wing joint (6) and a cover plate (7), and is characterized in that a driving torsion spring mounting groove (1-6) is formed in the side of the top end of the base (1), a rotating shaft (1-7) is fixedly mounted in the middle of the top end of the base (1), two sides of the rotating shaft (1-7) are respectively provided with a rotary lug limiting groove (1-5) which are symmetrically arranged, a base mounting hole (1-1) penetrating through the base (1) is formed in the bottom end of the driving torsion spring mounting groove (1-6), the base (1) is fixed on an unmanned aerial vehicle body (8) through a screw thread mounting screw in the base mounting hole (1-, the driving torsion spring (2) is placed in the driving torsion spring mounting groove (1-6), a locking pin limiting hole (1-4) is formed in the side of the rotating shaft (1-7), a locking pin (3) is arranged in the locking pin limiting hole (1-4), a locking pin pressure spring (4) is sleeved at the upper end of the locking pin (3), a rotary wing joint (6) is arranged on the upper surface of the base (1), a driving torsion spring mounting groove (6-7) is formed in the side of the top end of the rotary wing joint (6), a driving torsion spring horizontal limiting groove (6-5) communicated with the driving torsion spring mounting groove (6-7) is formed in one side of the driving torsion spring mounting groove (6-7), and a rotary drum sleeve (6-6) is fixedly mounted in the middle of the driving torsion spring mounting groove (6-7), two symmetrical rotary lugs (6-4) are fixedly mounted on two sides of the top end of the rotary drum sleeve (6-6), a lock pin limiting hole (6-1) is formed in the side edge of the top end of the rotary drum sleeve (6-6), the driving torsion spring (2) is placed in the driving torsion spring mounting groove (6-7), the horizontal limiting end (2-2) of the driving torsion spring (2) is placed in the horizontal limiting groove (6-5) of the driving torsion spring, the rotary lug (6-4) is placed in the rotary lug limiting groove (1-5), the rotary shaft sleeve (6-6) is sleeved on the rotary shaft (1-7), and the upper end of the lock pin (3) penetrates through the lock pin limiting hole (6-1).
2. The wing rotation locking mechanism of the cylinder-shooting type unmanned aerial vehicle as claimed in claim 1, wherein: and a vertical limiting hole (1-3) of the driving torsion spring is formed in the mounting groove (1-6) of the driving torsion spring, wherein the vertical limiting end (2-1) of the driving torsion spring (2) is inserted into the vertical limiting hole (1-3) of the driving torsion spring and used for limiting the shaking of the driving torsion spring (2).
3. The wing rotation locking mechanism of the cylinder-shooting type unmanned aerial vehicle as claimed in claim 1, wherein: the anti-vibration rubber pads (5) are symmetrically arranged at the centers of the two ends in the rotating lug limiting grooves (1-5), and when the wings (9) are unfolded, the anti-vibration rubber pads (5) can effectively reduce vibration caused by collision of the rotating lugs (6-4) and the rotating lug limiting grooves (1-5).
4. The wing rotation locking mechanism of the cylinder-shooting type unmanned aerial vehicle as claimed in claim 1, wherein: the top of the locking pin (3) is provided with a locking pin pulling hole (3-1), the inside of the locking pin pulling hole (3-1) penetrates through the pull ring, and the locking pin pressure spring (4) presses the locking pin (3) in the locking pin limiting hole (1-4).
5. The wing rotation locking mechanism of the cylinder-shooting type unmanned aerial vehicle as claimed in claim 1, wherein: two wing installation limiting holes (6-2) are formed in two ends of the rotary wing joint (6), and wings (9) are fixedly installed inside the wing installation limiting holes (6-2).
6. The wing rotation locking mechanism of the cylinder-shooting type unmanned aerial vehicle as claimed in claim 1, wherein: the top of the rotating shaft sleeve (6-6) is fixedly provided with a cover plate (7) which is fixed through cover plate mounting holes (7-1), (1-2) and screws and used for preventing the rotary wing joint (6) from loosening up and down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419898.8A CN112407240A (en) | 2020-12-06 | 2020-12-06 | Rotatory locking mechanism of section of thick bamboo shooting formula unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419898.8A CN112407240A (en) | 2020-12-06 | 2020-12-06 | Rotatory locking mechanism of section of thick bamboo shooting formula unmanned aerial vehicle wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112407240A true CN112407240A (en) | 2021-02-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011419898.8A Pending CN112407240A (en) | 2020-12-06 | 2020-12-06 | Rotatory locking mechanism of section of thick bamboo shooting formula unmanned aerial vehicle wing |
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| CN (1) | CN112407240A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113320681A (en) * | 2021-06-30 | 2021-08-31 | 沃飞长空科技(成都)有限公司 | Rotary unfolding device and unmanned aerial vehicle 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 CN202011419898.8A patent/CN112407240A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113320681A (en) * | 2021-06-30 | 2021-08-31 | 沃飞长空科技(成都)有限公司 | Rotary unfolding device and unmanned aerial vehicle 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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