CN214729606U - Wing and fuselage fast-assembling locking mechanism of fixed-wing unmanned aerial vehicle - Google Patents
Wing and fuselage fast-assembling locking mechanism of fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN214729606U CN214729606U CN202022459198.3U CN202022459198U CN214729606U CN 214729606 U CN214729606 U CN 214729606U CN 202022459198 U CN202022459198 U CN 202022459198U CN 214729606 U CN214729606 U CN 214729606U
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Abstract
The utility model provides a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism, including handle, pivot, the solid subassembly of card, fixture block, the handle sets up in unmanned aerial vehicle's wing upper portion, and the handle is installed at the pivot top, and the through-hole that the wing was reserved is run through in the wing to the pivot bottom, rotates with the wing to be connected, the solid subassembly of card is including the solid pole of card, and the solid pole of card is installed at the pivot lower extreme, and the fixture block is installed on unmanned aerial vehicle's fuselage for block the solid pole of card. A fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism solved the problem that the unmanned aerial vehicle wing installation is complicated, the installation part loses easily.
Description
Technical Field
The utility model belongs to the unmanned aerial vehicle field especially relates to a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism.
Background
The fixed wing unmanned aerial vehicle is outdoor flight, because its volume is great, is inconvenient to take to the field to go the flight after accomplishing the concatenation installation indoor. When the installation is finished in the field, a plurality of tools are needed, and due to the complex structure of the fixed-wing unmanned aerial vehicle, installation parts and installation tools are easy to be omitted and lost after the installation is finished; if not use tools, connect insecurely, cause unmanned aerial vehicle's part to connect danger such as not hard up droing easily, cause unmanned aerial vehicle's unbalance, finally lead to danger such as out of control.
Disclosure of Invention
In view of this, the utility model provides a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism is complicated in order to solve the problem that the unmanned aerial vehicle wing installation is complicated, the installation part loses easily.
In order to achieve the above purpose, the technical scheme of the utility model is realized like this:
the utility model provides a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism, includes handle, pivot, the solid subassembly of card, fixture block, and the handle sets up in unmanned aerial vehicle's wing upper portion, and the handle is installed at the pivot top, and the through-hole that the pivot bottom was reserved through the wing runs through in the wing, rotates with the wing to be connected, the solid subassembly of card is including the solid pole of card, and the solid pole of card is installed at the pivot lower extreme, and the fixture block is installed on unmanned aerial vehicle's fuselage for block the solid pole of card.
Furthermore, the handle includes the setting aside board, installation piece, the installation piece is fixed in the bottom of setting aside board one end, and it has the opening that corresponds with the pivot to open on the installation piece, and the locating pin is installed through the through-hole of reserving to the installation piece, and the installation piece passes through the locating pin and is connected with the pivot rotation.
Further, installation piece bottom is provided with the arc arch, and the bellied bottom of arc sets up with unmanned aerial vehicle's wing laminating.
Furthermore, the clamping component further comprises a sleeve and a special-shaped nut, a clamping ring is fixed on the rotating shaft positioned on the upper portion of the clamping rod, a threaded portion is arranged at the lower end of the clamping rod, the special-shaped nut is in threaded connection with the threaded portion, the sleeve is sleeved on the clamping rod positioned between the clamping ring and the special-shaped nut, the clamping rod is fixed on the outer side of the sleeve, and the clamping rod is perpendicular to the rotating shaft.
Furthermore, the clamping and fixing rods are two and are respectively fixed on two sides of the sleeve, the clamping blocks are two, an arc-shaped portion is arranged on one side of each clamping block, the arc-shaped portions of the two clamping blocks are arranged oppositely, a gap corresponding to the clamping and fixing rods is reserved between the two clamping blocks, the two clamping and fixing rods are fixed on the mounting frame, and the mounting frame is fixed on the machine body.
The wing fixing device further comprises a mounting plate, the mounting plate is arranged on a rotating shaft between the wing and the clamping rod and fixedly connected with the wing, the mounting plate is slidably connected with the rotating shaft through a reserved through hole, and an elastic piece is sleeved on the rotating shaft between the mounting plate and the clamping ring.
Further, still be connected with the connecting rod between screw thread portion and the pivot, the cross section of connecting rod is the polygon, still installs the baffle on the connecting rod between mounting panel and the elastic component, and the baffle is through the polygon through-hole and the connecting rod sliding connection that the reservation corresponds with the connecting rod, and the mounting panel bottom still is equipped with the dysmorphism recess that corresponds with the baffle, and dysmorphism recess is used for spacing the rotation angle of baffle.
Compared with the prior art, the utility model discloses following advantage has:
(1) the utility model provides a fixed wing unmanned aerial vehicle wing can be fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism fast, and easy operation is swift, connects reliable and stable, has avoided the problem appearance that loses easily when the installation part is dismantled when guaranteeing unmanned aerial vehicle's safe flight.
(2) The opposite sex recess can restrict the baffle clockwise, two anticlockwise directions all can only rotate 90 degrees to can make the card that two card solid poles are accurate under the fixture block, play the fixed action to the pivot simultaneously, prevent that the pivot activity from making the rotation of card solid pole, influence the solid effect of card.
Drawings
The accompanying drawings, which form a part hereof, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without undue limitation. In the drawings:
fig. 1 is a schematic view of a wing and body quick-assembly locking mechanism of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic cross-sectional view of a wing and body quick-assembly locking mechanism of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic view of a local enlarged view of a wing and body quick-assembly locking mechanism of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention;
fig. 4 is a schematic view of the mounting plate and the irregular groove according to the embodiment of the present invention;
fig. 5 is the embodiment of the utility model provides a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism mounted position sketch map.
Description of reference numerals:
1-a handle; 2-a rotating shaft; 3-top thread; 4-positioning pins; 5-arc-shaped bulge; 7-mounting a plate; 71-special-shaped grooves; 8-an elastic member; 9-a fixture block; 91-an arc-shaped portion; 10-a mounting frame; 11-a mounting block; 12-a baffle plate; 13-a connecting rod; 14-a snap ring; 15-a threaded portion; 16-special-shaped nuts; 17-a sleeve; 18-a clamping rod; 19-a baffle ring; 20-wing.
Detailed Description
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1, a fast-assembling locking mechanism for wings and a fuselage of a fixed-wing unmanned aerial vehicle comprises a handle 1, a rotating shaft 2, a clamping component and a clamping block 9, wherein the handle 1 is arranged on the upper portion of the wing 20 of the unmanned aerial vehicle, the handle 1 is arranged at the top of the rotating shaft 2, the bottom of the rotating shaft 2 penetrates through the wing 20 through a through hole reserved in the wing 20 and is rotatably connected with the wing 20, the clamping component comprises a clamping rod 18, the clamping rod 18 is arranged at the lower end of the rotating shaft 2, and the clamping block 9 is arranged on the fuselage of the unmanned aerial vehicle and used for clamping the clamping rod 18.
As shown in fig. 1 and 2, the handle 1 includes a toggle plate and a mounting block 11, the mounting block 11 is fixed at the bottom of one end of the toggle plate, an opening corresponding to the rotating shaft 2 is opened on the mounting block 11, a positioning pin 4 is installed on the mounting block 11 through a reserved through hole, and the mounting block 11 is rotatably connected with the rotating shaft 2 through the positioning pin 4.
As shown in fig. 1 and 2, the bottom of the mounting block 11 is provided with an arc-shaped protrusion 5, and the bottom of the arc-shaped protrusion 5 is attached to the wing 20 of the unmanned aerial vehicle. The arc-shaped protrusions 5 enable the distance from the positioning pin 4 to the outer edge of the mounting block 11 to be different in length, the distance from the position provided with the arc-shaped protrusions 5 is longer, and the distance from the position to the two sides of the mounting block 11 is shorter. When the handle 1 is moved upwards, the bottom of the arc-shaped protrusion 5 presses the wing 20 downwards, so that the positioning pin 4 drives the rotating shaft 2 to move upwards, when the handle 1 is pressed downwards, the side surface of the mounting block 11 is attached to the wing 20, so that the positioning pin 4 drives the rotating shaft 2 to move downwards, and the clamping rod 18 extends into the lower part of the clamping block 9 and is clamped with the clamping block 9.
As shown in fig. 1 and 3, the fastening assembly further includes a sleeve 17 and a special-shaped nut, a fastening ring 14 is fixed on the rotating shaft 2 at the upper portion of the fastening rod 18, a threaded portion 15 is arranged at the lower end of the fastening rod 18, the special-shaped nut 16 is in threaded connection with the threaded portion 15, the sleeve 17 is sleeved on the fastening rod 18 between the fastening ring 14 and the special-shaped nut 16, the fastening rod 18 is fixed at the outer side of the sleeve 17, and the fastening rod 18 is perpendicular to the rotating shaft 2.
As shown in fig. 1 and 3, two fastening rods 18 are respectively fixed on two sides of the sleeve 17, two fastening blocks 9 are provided, one side of each fastening block 9 is provided with an arc-shaped portion 91, the arc-shaped portions 91 of the two fastening blocks 9 are oppositely arranged, a gap corresponding to the fastening rod 18 is left between the two fastening blocks 9, the two fastening blocks are fixed on the mounting frame 10, and the mounting frame 10 is fixed on the machine body.
As shown in fig. 1 and 2, the aircraft further includes a mounting plate 7, the mounting plate 7 is disposed on the rotating shaft 2 between the wing 20 and the fastening rod 18, the mounting plate 7 is fixedly connected to the wing 20, the mounting plate 7 is slidably connected to the rotating shaft 2 through a reserved through hole, and an elastic member 8 is sleeved on the rotating shaft 2 between the mounting plate 7 and the snap ring 14.
As shown in fig. 1 and 4, a connecting rod 13 is further connected between the threaded portion 15 and the rotating shaft 2, the cross section of the connecting rod 13 is polygonal, a baffle plate 12 is further installed on the connecting rod 13 between the mounting plate 7 and the elastic member 8, the baffle plate 12 is in sliding connection with the connecting rod 13 through a reserved polygonal through hole corresponding to the connecting rod 13, the polygonal through hole is matched with the polygonal connecting rod 13 and is used for transmitting torque, the connecting rod 13 is fixed with the baffle plate 12 in the horizontal direction, the baffle plate is in sliding connection with the vertical direction, a special-shaped groove corresponding to the baffle plate 12 is further arranged at the bottom of the mounting plate 7, and the special-shaped groove is used for limiting the rotating angle of the baffle plate 12. The opposite sex recess can restrict baffle 12 clockwise, two anticlockwise directions all can only rotate 90 degrees to can make two calorie of accurate cards of solid pole 18 under the fixture block 9, play the fixed action to pivot 2 simultaneously, prevent that 2 activities of pivot from making the solid pole 18 of card rotate, influence the solid effect of card.
When the wing 20 is installed, the wing 20 is firstly placed on the fuselage, the bottom of the rotating shaft 2 is inserted into a reserved installation hole of the fuselage, the handle 1 is rotated, the two clamping rods 18 correspond to the reserved gaps between the two clamping blocks 9, the handle 1 is pressed downwards, the elastic part 8 applies downward pressure to the clamping ring 14, the rotating shaft 2 drives the clamping rods 18 to move downwards to the positions below the clamping blocks 9, the handle 1 is rotated for 90 degrees, the clamping rods 18 are clamped at the bottoms of the clamping blocks 9 and are attached to the bottoms of the clamping blocks 9, the handle 1 is lifted upwards, the rotating shaft 2 is tensioned upwards, the handle 1 is loosened, the installation can be completed, when the wing 20 is disassembled, the wing 20 can be separated from the fuselage only by pressing the handle 1 downwards and then rotating for 90 degrees in the reverse direction, and then pulling the wing 20 upwards, and the disassembly is completed.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides a fixed wing unmanned aerial vehicle wing and fuselage fast-assembling locking mechanism which characterized in that: including handle (1), pivot (2), the solid subassembly of card, fixture block (9), handle (1) sets up in unmanned aerial vehicle's wing (20) upper portion, and install at pivot (2) top handle (1), and the through-hole that wing (20) were reserved is run through in wing (20) in pivot (2) bottom, rotates with wing (20) to be connected, the solid subassembly of card is including the solid pole of card (18), and the solid pole of card (18) of card is installed at pivot (2) lower extreme, and fixture block (9) are installed on unmanned aerial vehicle's fuselage for block the solid pole of card (18).
2. The fast-assembling locking mechanism of wing and fuselage of fixed-wing unmanned aerial vehicle of claim 1, characterized in that: handle (1) are including dialling the board, installation piece (11), the bottom at dialling board one end is fixed in installation piece (11), and it has the opening that corresponds with pivot (2) to open on installation piece (11), and locating pin (4) are installed through the through-hole of reserving in installation piece (11), and installation piece (11) are connected with pivot (2) rotation through locating pin (4).
3. The fast-assembling locking mechanism of wing and fuselage of fixed-wing unmanned aerial vehicle of claim 2, characterized in that: installation piece (11) bottom is provided with arc arch (5), and the bottom of arc arch (5) sets up with the wing (20) laminating of unmanned aerial vehicle.
4. The fast-assembling locking mechanism of wing and fuselage of fixed-wing unmanned aerial vehicle of claim 1, characterized in that: the clamping and fixing assembly further comprises a sleeve (17) and a special-shaped nut, a clamping ring (14) is fixed on the rotating shaft (2) located on the upper portion of the clamping and fixing rod (18), a threaded portion (15) is arranged at the lower end of the clamping and fixing rod (18), the special-shaped nut (16) is in threaded connection with the threaded portion (15), the sleeve (17) is sleeved on the clamping and fixing rod (18) located between the clamping ring (14) and the special-shaped nut (16), the clamping and fixing rod (18) is fixed on the outer side of the sleeve (17), and the clamping and fixing rod (18) is perpendicular to the rotating shaft (2).
5. The fast-assembling locking mechanism of wing and fuselage of fixed-wing unmanned aerial vehicle of claim 4, characterized in that: the clamping and fixing rod (18) is provided with two clamping and fixing rods which are fixed on two sides of the sleeve (17) respectively, the clamping blocks (9) are provided with two clamping blocks, an arc-shaped portion (91) is arranged on one side of each clamping block (9), the arc-shaped portions (91) of the two clamping blocks (9) are arranged oppositely, a gap corresponding to the clamping and fixing rod (18) is reserved between the two clamping blocks (9), the two clamping and fixing rods are fixed on the mounting frame (10), and the mounting frame (10) is fixed on the machine body.
6. The fast-assembling locking mechanism of wing and fuselage of fixed-wing unmanned aerial vehicle of claim 4, characterized in that: the wing fixing device is characterized by further comprising a mounting plate (7), the mounting plate (7) is arranged on the rotating shaft (2) between the wing (20) and the clamping rod (18), the mounting plate (7) is fixedly connected with the wing (20), the mounting plate (7) is in sliding connection with the rotating shaft (2) through a reserved through hole, and an elastic part (8) is sleeved on the rotating shaft (2) between the mounting plate (7) and the clamping ring (14).
7. The fast-assembling locking mechanism of wing and fuselage of fixed-wing drone of claim 6, characterized in that: still be connected with connecting rod (13) between screw thread portion (15) and pivot (2), the cross section of connecting rod (13) is the polygon, still installs baffle (12) on connecting rod (13) between mounting panel (7) and elastic component (8), baffle (12) through the polygon through-hole that reserves correspond with connecting rod (13) and connecting rod (13) sliding connection, mounting panel (7) bottom still is equipped with the special-shaped groove that corresponds with baffle (12), the special-shaped groove is used for carrying on spacingly to the rotation angle of baffle (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022459198.3U CN214729606U (en) | 2020-10-29 | 2020-10-29 | Wing and fuselage fast-assembling locking mechanism of fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022459198.3U CN214729606U (en) | 2020-10-29 | 2020-10-29 | Wing and fuselage fast-assembling locking mechanism of fixed-wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN214729606U true CN214729606U (en) | 2021-11-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022459198.3U Active CN214729606U (en) | 2020-10-29 | 2020-10-29 | Wing and fuselage fast-assembling locking mechanism of fixed-wing unmanned aerial vehicle |
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| CN (1) | CN214729606U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
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2020
- 2020-10-29 CN CN202022459198.3U patent/CN214729606U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20230104 Address after: 510000 Room 202, building 13, Tian'an headquarters center, No. 555, North Panyu Avenue, Donghuan street, Panyu District, Guangzhou City, Guangdong Province Patentee after: GUANGZHOU HI-TARGET SURVEYING INSTRUMENT Co.,Ltd. Address before: Room A701, building 8, Airport Business Park East, Huanhe North Road, Tianjin Binhai New Area pilot free trade zone (Airport Economic Zone) Patentee before: TIANJIN TENGYUN ZHIHANG TECHNOLOGY CO.,LTD. |