CN213768959U - Collapsible unmanned aerial vehicle horn - Google Patents
Collapsible unmanned aerial vehicle horn Download PDFInfo
- Publication number
- CN213768959U CN213768959U CN202022876802.2U CN202022876802U CN213768959U CN 213768959 U CN213768959 U CN 213768959U CN 202022876802 U CN202022876802 U CN 202022876802U CN 213768959 U CN213768959 U CN 213768959U
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- Prior art keywords
- wing
- rotating shaft
- pivot
- wings
- fan blade
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- Expired - Fee Related
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Abstract
The utility model discloses a collapsible unmanned aerial vehicle horn, including fuselage shell, rear portion wing and draw-in groove, fuselage shell bilateral symmetry has been seted up and has been accomodate the groove, and accomodate the inslot and install anterior wing to be connected with anterior pivot between anterior wing one end and the fuselage shell, the rear portion wing is installed at anterior wing inboard, and is connected with the rear portion pivot between rear portion wing and the fuselage shell to be connected with the support frame on rear portion wing and the anterior wing, the support frame upside is provided with the flabellum pivot, and is connected with the biax flabellum in the flabellum pivot to install little pivot on the biax flabellum, the draw-in groove is seted up on anterior wing, and is connected with the bolt on the anterior wing other end to the bolt downside is provided with the tooth's socket, be connected with the gear on the tooth's socket, and install the control lever on the gear. This collapsible unmanned aerial vehicle horn, the space around the ability make full use of fuselage only occupies less space when folding to take in, so that hand-carry.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle horn technical field specifically is a collapsible unmanned aerial vehicle horn.
Background
Along with the continuous development of unmanned aerial vehicle technique, use unmanned aerial vehicle to replace the manual work to carry out aerial observation and being becoming the normality gradually, and unmanned aerial vehicle's convenience is one of its important characteristic, and the unmanned aerial vehicle of small and exquisite figure not only can be convenient for fly to the narrow and small region in space and observe, also can portable simultaneously, alleviates the burden that people used.
The important part that reduces unmanned aerial vehicle volume usually is to reduce the proportion space of unmanned aerial vehicle horn on the fuselage, and most unmanned aerial vehicle's horn can not fold totally, the horn after folding simultaneously has occupied unmanned aerial vehicle's most space, can not the maximize utilize unmanned aerial vehicle peripheral space to accomodate the horn, consequently can't effectively reduce unmanned aerial vehicle's the volume of accomodating, and then can not portable, to above-mentioned problem, the urgent need carries out the innovative design on the basis of original unmanned aerial vehicle horn.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a collapsible unmanned aerial vehicle horn to propose the space on traditional unmanned aerial vehicle horn can not the make full use of fuselage in solving above-mentioned background art, can not occupy less space when folding accomodating, and problem that can not portable.
In order to achieve the above object, the utility model provides a following technical scheme: a foldable unmanned aerial vehicle arm comprises a body shell, rear wings and clamping grooves, wherein the two sides of the body shell are symmetrically provided with accommodating grooves, the accommodating grooves are internally provided with the front wings, and a front rotating shaft is connected between one end of the front wing and the fuselage shell, the rear wing is arranged on the inner side of the front wing, a rear rotating shaft is connected between the rear wing and the fuselage shell, and the rear wing and the front wing are connected with a support frame, the upper side of the support frame is provided with a fan blade rotating shaft, and the fan blade rotating shaft is connected with a double-shaft fan blade, the double-shaft fan blades are provided with small rotating shafts, the clamping grooves are formed in the front wings, the other ends of the front wings are connected with bolts, and the lower side of the bolt is provided with a tooth socket, the tooth socket is connected with a gear, the gear is provided with a control rod, and one end of the control rod is provided with a central rotating shaft, and a connecting rod is arranged between the central rotating shaft and the fan blade rotating shaft.
Preferably, the front wing and the fuselage shell form a rotating structure through a front rotating shaft, the front wing is connected with the front rotating shaft in a sliding mode, and the length of the front wing is smaller than that of the rear wing.
Preferably, the rear wing and the fuselage shell form a rotating structure through a rear rotating shaft, the vertical height of the rear wing in the fuselage shell is greater than that of the front wing in the fuselage shell, and the sum of the lengths of the rear wing and the front wing is equal to the length of the accommodating groove.
Preferably, the fan blade rotating shaft forms a clamping structure with the front wing through the clamping groove, the fan blade rotating shaft forms a rotating structure with the double-shaft fan blade through the small rotating shaft, and the maximum rotating angle of the double-shaft fan blade on the fan blade rotating shaft is 90 degrees.
Preferably, the gear is meshed with the tooth grooves, the gear is rotatably connected with the control rod, and the control rod is connected with the front wing in a penetrating mode.
Preferably, the connecting rod forms a rotating structure with the control rod through a central rotating shaft, and the connecting rod is fixedly connected with the rotating shaft of the fan blade.
Compared with the prior art, the beneficial effects of the utility model are that: the foldable unmanned aerial vehicle arm adopts a novel structural design, when the device is used, the device can be conveniently folded and stored on the front wing through the structure of the front rotating shaft, the bolts, the tooth grooves, the gears and the control rod arranged on the front wing, so that the front wing can be folded by utilizing the space in the storage groove to the maximum extent, and the device can be conveniently folded and stored on the fan blade through the structure of the double-shaft fan blade, the small rotating shaft, the clamping groove, the central rotating shaft and the connecting rod arranged on the fan blade rotating shaft, so that the maximum space utilization rate is achieved;
1. the front wing is provided with a structure of a front rotating shaft, a bolt, a tooth groove, a gear and a control rod, the front wing is driven to rotate through the front rotating shaft and is stored in the storage groove, the gear is used for driving the front wing to vertically move on the tooth groove, and the control rod is used for driving the rotating shaft of the fan blade to keep unchanged in position, so that the device can conveniently fold and store the front wing, and the purpose that the front wing can be folded by utilizing the space in the storage groove to the maximum extent is achieved;
2. set up the structure of biax flabellum, little pivot, draw-in groove, central pivot and connecting rod in the flabellum pivot, utilize little pivot to rotate to one side in the flabellum pivot through biax flabellum and accomodate to the unchangeable principle of angle of biax flabellum when utilizing central pivot and connecting rod to keep the control lever to rotate, the realization device can be convenient for fold the flabellum of device and accomodate, so that reach the function of maximum space utilization.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic view of the front wing of the present invention;
FIG. 3 is a schematic view of a rear wing structure of the present invention;
FIG. 4 is a schematic view of a three-dimensional structure of a blade rotating shaft of the present invention;
fig. 5 is a schematic perspective view of a position a in fig. 4 according to the present invention.
In the figure: 1. a fuselage shell; 2. a receiving groove; 3. a front wing; 4. a front rotary shaft; 5. an aft wing; 6. a rear rotating shaft; 7. a support frame; 8. a fan blade rotating shaft; 9. biaxial fan blades; 10. a small rotating shaft; 11. A card slot; 12. a bolt; 13. a tooth socket; 14. a gear; 15. a control lever; 16. a central rotating shaft; 17. A connecting rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution: a foldable unmanned aerial vehicle arm comprises a machine body shell 1, accommodating grooves 2, front wings 3, front rotating shafts 4, rear wings 5, rear rotating shafts 6, supporting frames 7, fan blade rotating shafts 8, double-shaft fan blades 9, small rotating shafts 10, clamping grooves 11, bolts 12, tooth grooves 13, gears 14, control rods 15, central rotating shafts 16 and connecting rods 17, wherein the accommodating grooves 2 are symmetrically formed in two sides of the machine body shell 1, the front wings 3 are installed in the accommodating grooves 2, the front rotating shafts 4 are connected between one ends of the front wings 3 and the machine body shell 1, the rear wings 5 are installed on the inner sides of the front wings 3, the rear rotating shafts 6 are connected between the rear wings 5 and the machine body shell 1, the supporting frames 7 are connected to the rear wings 5 and the front wings 3, the upper sides of the supporting frames 7 are provided with the fan blade rotating shafts 8, the double-shaft fan blades 9 are connected to the fan blade rotating shafts 8, and the small rotating shafts 10 are installed on the double-shaft fan blades 9, the clamping groove 11 is formed in the front wing 3, the other end of the front wing 3 is connected with a bolt 12, a tooth groove 13 is formed in the lower side of the bolt 12, a gear 14 is connected to the tooth groove 13, a control rod 15 is installed on the gear 14, a central rotating shaft 16 is arranged at one end of the control rod 15, and a connecting rod 17 is installed between the central rotating shaft 16 and the fan blade rotating shaft 8.
The front wing 3 and the fuselage shell 1 form a rotating structure through a front rotating shaft 4, the front wing 3 is connected with the front rotating shaft 4 in a sliding mode, the length of the front wing 3 is smaller than that of the rear wing 5, the structure enables the distance between the front wing 3 and the fuselage shell 1 after the front wing 3 is unfolded to be the same as the distance between the rear wing 5 and the fuselage shell 1, and the space in the accommodating groove 2 can be fully utilized for accommodating.
The rear wings 5 and the fuselage shell 1 form a rotating structure through the rear rotating shaft 6, the vertical height of the rear wings 5 in the fuselage shell 1 is larger than that of the front wings 3 in the fuselage shell 1, the sum of the lengths of the rear wings 5 and the front wings 3 is equal to that of the accommodating grooves 2, the rear wings 5 and the front wings 3 can be mutually staggered and accommodated through the structure, and the accommodating space can be saved.
The fan blade rotating shaft 8 forms a clamping structure with the front wing 3 through the clamping groove 11, the fan blade rotating shaft 8 forms a rotating structure with the double-shaft fan blade 9 through the small rotating shaft 10, the maximum rotating angle of the double-shaft fan blade 9 on the fan blade rotating shaft 8 is 90 degrees, the double-shaft fan blade 9 can be conveniently stored and folded by the aid of the structure, and the double-shaft fan blade 9 can keep the same horizontal position with the front wing 3 and the rear wing 5.
The gear 14 is meshed with the tooth grooves 13, the gear 14 is rotatably connected with the control rod 15, the control rod 15 is connected with the front wing 3 in a penetrating mode, and the front wing 3 can stably slide on the front rotating shaft 4 in the vertical direction due to the structural arrangement.
The connecting rod 17 and the control rod 15 form a rotating structure through the central rotating shaft 16, and the connecting rod 17 is fixedly connected with the fan blade rotating shaft 8, and the arrangement of the structure enables the double-shaft fan blades 9 on the fan blade rotating shaft 8 to be consistent with the horizontal direction of the front wing 3 by utilizing the rotation of the central rotating shaft 16.
The working principle is as follows: when the device is used, according to the structure shown in fig. 2 and fig. 3, when the unmanned aerial vehicle needs to be stored, firstly, the double-shaft fan blades 9 on the front wing 3 and the rear wing 5 can be respectively rotated through the small rotating shafts 10, so that the double-shaft fan blades 9 are all folded towards the front rotating shaft 4 and the rear rotating shaft 6 on the front wing 3 and the rear wing 5, the fan blade rotating shaft 8 can slide into a clamping groove 11 arranged on the front wing 3, so that the lengths of the front wing 3 and the fan blade rotating shaft 8 can be kept consistent with the length of the accommodating groove 2, then the rear wing 5 rotates towards the inner side of the accommodating groove 2 along the rear rotating shaft 6, the long edge of the rear wing 5 is kept consistent with the inner side edge of the accommodating groove 2 in the horizontal direction, then the supporting frame 7 is rotated upwards to be folded at two sides of the front wing 3 and the rear wing 5;
according to the structure shown in fig. 1, 4 and 5, when the front wing 3 starts to be folded, the front wing 3 rotates along the front rotating shaft 4 to the inner side of the accommodating groove 2, at this time, the control rod 15 in the front wing 3 drives the fan blade rotating shaft 8 at the other end to rotate, the central rotating shaft 16 and the connecting rod 17 which are connected with the bottom of the fan blade rotating shaft 8 are used for keeping the rotating state, so that the rotating angle of the double-shaft fan blade 9 is kept unchanged, when the front wing 3 is received in the receiving groove 2, the bolt 12 on the front wing 3 can be loosened, then, the gear 14 slides downwards on the tooth grooves 13, so that the front wing 3 and the rear wing 5 are kept at staggered positions, so that make full use of accomodates the space of groove 2 and fold the horn and accomodate, finally keep unanimous with unmanned aerial vehicle's horn and fuselage shell 1's side reason, this is exactly the theory of operation of this collapsible unmanned aerial vehicle horn.
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. The utility model provides a collapsible unmanned aerial vehicle horn, includes fuselage shell (1), rear portion wing (5) and draw-in groove (11), its characterized in that: the aircraft body structure is characterized in that the two sides of the aircraft body shell (1) are symmetrically provided with accommodating grooves (2), front wings (3) are installed in the accommodating grooves (2), front rotating shafts (4) are connected between one ends of the front wings (3) and the aircraft body shell (1), the rear wings (5) are installed on the inner sides of the front wings (3), rear rotating shafts (6) are connected between the rear wings (5) and the aircraft body shell (1), supporting frames (7) are connected onto the rear wings (5) and the front wings (3), fan blade rotating shafts (8) are arranged on the upper sides of the supporting frames (7), double-shaft fan blades (9) are connected onto the fan blade rotating shafts (8), small rotating shafts (10) are installed onto the double-shaft fan blades (9), clamping grooves (11) are formed in the front wings (3), bolts (12) are connected onto the other ends of the front wings (3), and tooth grooves (13) are formed in the lower sides of the bolts (12), tooth's socket (13) are last to be connected with gear (14), and install control lever (15) on gear (14) to control lever (15) are served and are provided with central pivot (16), install connecting rod (17) simultaneously between central pivot (16) and flabellum pivot (8).
2. A foldable drone arm according to claim 1, characterised in that: the front wing (3) and the fuselage shell (1) form a rotating structure through a front rotating shaft (4), the front wing (3) is connected with the front rotating shaft (4) in a sliding mode, and the length of the front wing (3) is smaller than that of the rear wing (5).
3. A foldable drone arm according to claim 1, characterised in that: the rear wing (5) and the fuselage shell (1) form a rotating structure through a rear rotating shaft (6), the vertical height of the rear wing (5) in the fuselage shell (1) is larger than that of the front wing (3) in the fuselage shell (1), and the sum of the lengths of the rear wing (5) and the front wing (3) is equal to the length of the accommodating groove (2).
4. A foldable drone arm according to claim 1, characterised in that: fan blade pivot (8) pass through draw-in groove (11) and constitute the block structure with anterior wing (3), and fan blade pivot (8) constitute rotating-structure through little pivot (10) and biax flabellum (9) to biax flabellum (9) the biggest turned angle on fan blade pivot (8) is 90.
5. A foldable drone arm according to claim 1, characterised in that: the gear (14) is meshed with the tooth grooves (13), the gear (14) is rotatably connected with the control rod (15), and the control rod (15) is connected with the front wing (3) in a penetrating mode.
6. A foldable drone arm according to claim 1, characterised in that: the connecting rod (17) forms a rotating structure with the control rod (15) through the central rotating shaft (16), and the connecting rod (17) is fixedly connected with the fan blade rotating shaft (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022876802.2U CN213768959U (en) | 2020-12-04 | 2020-12-04 | Collapsible unmanned aerial vehicle horn |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022876802.2U CN213768959U (en) | 2020-12-04 | 2020-12-04 | Collapsible unmanned aerial vehicle horn |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213768959U true CN213768959U (en) | 2021-07-23 |
Family
ID=76895884
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022876802.2U Expired - Fee Related CN213768959U (en) | 2020-12-04 | 2020-12-04 | Collapsible unmanned aerial vehicle horn |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213768959U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114408157A (en) * | 2022-01-25 | 2022-04-29 | 深圳黑砂科技有限公司 | Unmanned aerial vehicle receipts oar mechanism system |
-
2020
- 2020-12-04 CN CN202022876802.2U patent/CN213768959U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114408157A (en) * | 2022-01-25 | 2022-04-29 | 深圳黑砂科技有限公司 | Unmanned aerial vehicle receipts oar mechanism system |
| CN114408157B (en) * | 2022-01-25 | 2023-12-22 | 深圳黑砂科技有限公司 | Unmanned aerial vehicle receives oar mechanism system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210723 Termination date: 20211204 |