CN205273850U - Rotor unmanned aerial vehicle - Google Patents
Rotor unmanned aerial vehicle Download PDFInfo
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- CN205273850U CN205273850U CN201520976377.0U CN201520976377U CN205273850U CN 205273850 U CN205273850 U CN 205273850U CN 201520976377 U CN201520976377 U CN 201520976377U CN 205273850 U CN205273850 U CN 205273850U
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- man
- outer shroud
- machine
- aerial vehicle
- unmanned aerial
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Abstract
The utility model discloses a rotor unmanned aerial vehicle, unmanned aerial vehicle includes fuselage, four at least rotors and connecting plate, through the both ends of first net bone with predetermine the pretightning force respectively in first outer loop with first inner ring is fixed, makes avoid the impact of external big foreign matter when two at least paddles are rotatory, and improved the security, on the other hand, first net bone has elasticity for taking elastic material, avoids the unmanned aerial vehicle rotor receives the rigid shock, the connecting plate is the magnetic sheet, makes the fuselage with rotor magnetism is connected, and convenient to detach has solved among the prior art that unmanned aerial vehicle rotor weight is big, the rotor receives and damages the rotor blade when great foreign matter strikes easily, and the lower and unmanned aerial vehicle of security dismantles inconvenient technical problem, reached provide an unmanned aerial vehicle rotor light in weight, impact resistance is big, the security is just high unmanned aerial vehicle dismantles convenient technological effect.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, in particular to rotor wing unmanned aerial vehicle.
Background technology
Unmanned spacecraft is called for short " without man-machine ", is the not manned aircraft utilizing wireless remote control equipment to handle with the programcontrol unit provided for oneself. Without cab on machine, but the equipment such as robot pilot, programcontrol unit, signal pickup assembly are installed. On ground, naval vessels or machine tool remote-controlled station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital transmission. Can take off as common aircraft under wireless remote control or launch with booster rocket, it is possible to take to by machine tool and throw in flight in the air.
Without man-machine aloft fly time, prior art is fixed on web member without man-machine rotary wing wheel hub, weight is relatively big, and rotor is subject to easily damaging when bigger foreign matter impacts the blade of rotor, and when rotor rotates, security is lower and inconvenient without man-machine dismounting.
Practical novel content
The utility model provides a kind of rotor wing unmanned aerial vehicle, solve big without man-machine rotor weight in prior art, rotor to be subject to easily damaging rotor blade when bigger foreign matter impacts, security is lower and without the technical problem of man-machine dismounting inconvenience, reach provide a kind of light without man-machine rotor weight, shock resistance big, security height and the described technique effect without man-machine convenient disassembly.
For solving the problems of the technologies described above, the utility model provides a kind of rotor wing unmanned aerial vehicle, comprises fuselage, at least four rotors, and described at least four rotors comprise: actuator; Turning axle, is connected with described actuator, and described turning axle can rotate relative to its axis; Propeller hub, is functionally connected on described turning axle in rotary manner; At least two blades, the axis of relatively described turning axle is functionally connected on described propeller hub in rotary manner; Guard portion, described guard portion comprises: front mesh enclosure, described front mesh enclosure comprises multiple first net bone, the first outer shroud and the first inner ring, and the two ends of the first net bone described in each are separately fixed in described first outer shroud and described first inner ring with certain preliminary tension, and described first net bone is the elastic material of band; Rear net cover, described rear net cover comprises the back up pad of multiple 2nd net bone, the 2nd outer shroud and circle, and described in each, one end of the 2nd net bone is fixed in described back up pad, and the other end is fixed on described 2nd outer shroud; Described actuator is removably fixed in described back up pad; Multiple connection beam, the one end connecting beam described in each is fixed on described first outer shroud, and the other end is fixed on described 2nd outer shroud; Described also comprise web plate without man-machine, described web plate be fixed on described between at least two adjacent connection beams, described at least four rotors are removably fixedly connected with at described web plate place with described fuselage.
Preferably, the material of described first outer shroud, described first inner ring, described 2nd outer shroud, described back up pad is carbon fiber; And/or, the material of described 2nd net bone is carbon fiber.
Preferably, the axis of described first inner ring and described back up pad is collinear.
Preferably, the size of described back up pad is more than or equal to the size of described actuator, to facilitate described actuator to be fixed in described back up pad.
Preferably, described first inner ring is arranged with described first outer shroud is concentric; And/or, described back up pad is arranged with described 2nd outer shroud is concentric.
Preferably, described first net bone is specially nylon wire.
Preferably, described actuator is specially motor.
Preferably, described web plate is magnetic web plate, and described in making, at least four rotors are connected with described fuselage magnetic.
Preferably, described web plate and described fuselage are bolted to connection.
The useful effect of the application is as follows:
The rotor wing unmanned aerial vehicle that the application provides, fixed respectively at described first outer shroud and described first inner ring with default preliminary tension by the two ends of described first net bone, the impact of extraneous big foreign matter is avoided when at least two blades rotate described in making, and improve security, on the other hand, described first net bone is the elastic material of band, has elasticity, avoids described being subject to rigid shock without man-machine rotor; Described web plate is magnetic plate, described fuselage is connected with described rotor magnetic, it is convenient to dismounting, solve big without man-machine rotor weight in prior art, rotor to be subject to easily damaging rotor blade when bigger foreign matter impacts, security is lower and without the technical problem of man-machine dismounting inconvenience, reach provide a kind of light without man-machine rotor weight, shock resistance big, security height and the described technique effect without man-machine convenient disassembly.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, below the accompanying drawing used required in embodiment being described is briefly described, it is appreciated that the accompanying drawing in the following describes is only embodiments more of the present utility model.
Fig. 1 is the structural representation of the application one better embodiment rotor wing unmanned aerial vehicle;
Fig. 2 is structural representation without man-machine rotor in Fig. 1
Accompanying drawing illustrates:
100-rotor wing unmanned aerial vehicle, 1-fuselage, 2-is without man-machine rotor, 21-turning axle, 22-propeller hub, 23-blade, 24-guard portion, 241-front mesh enclosure, 2411-first net bone, 2412-first outer shroud, 2413-first inner ring, 242-rear net cover, 2421-the 2nd net bone, 2422-the 2nd outer shroud, 2423-back up pad, 243-connects beam, 25-actuator, 3-web plate.
Embodiment
In order to better understand technique scheme, below in conjunction with Figure of description and concrete enforcement mode, technique scheme is described in detail.
Fig. 1 is the structural representation of the application one better embodiment rotor wing unmanned aerial vehicle, refers to Fig. 1, described comprises fuselage 1, at least four rotors 2 and web plate 3 without man-machine.
Described comprise actuator 25, turning axle 21, at least two blades 23 and guard portion 24 without man-machine rotor 2. For driving, described turning axle 21 rotates described actuator 25, and described actuator 25 is specially motor, and described turning axle 21 is connected with described actuator 25, and described turning axle 21 can rotate relative to its axis; Described propeller hub 22 is functionally connected on described turning axle 21 in rotary manner, and described propeller hub 22 is at least two blades 23 described in being fixedly connected with; The axis of the relatively described turning axle 21 of described at least two blades 23 is functionally connected on described propeller hub 22 in rotary manner.
Aspect, described guard portion 24 1, for supporting described actuator 25, on the other hand for the protection of described blade 23, avoids described blade 23 to be subject to the impact of foreign matter, and described guard portion 24 comprises front mesh enclosure 241, rear net cover 242 and multiple connection beam 243. Described front mesh enclosure 241 comprises multiple first net bone 2411, first outer shroud 2412 and the first inner ring 2413, the two ends of the first net bone 2411 described in each are separately fixed in described first outer shroud 2412 and described first inner ring 2413 with certain preliminary tension, described first net bone 2411 is the elastic material of band, in the present embodiment, described first net bone 2411 is specially nylon wire. The two ends of described first net bone 2411 are fixed respectively at described first outer shroud 2412 and described first inner ring 2413 with default preliminary tension, the impact of extraneous big foreign matter is avoided when at least two blades 23 rotate described in making, and improve security, on the other hand, described first net bone 2411 is the elastic material of band, there is elasticity, avoid described being subject to rigid shock without man-machine rotor 2.
Described rear net cover 242 comprises the back up pad 2423 of multiple 2nd net bone 2421, the 2nd outer shroud 2422 and circle, and one end of the 2nd net bone 2421 described in each is fixed in described back up pad 2423, and the other end is fixed on described 2nd outer shroud 2422; Described multiple 2nd net bones 2421 of described rear net cover 242, described 2nd outer shroud 2422 and described back up pad 2423 form bigger gap, while ensureing heat radiation, it is to increase security. The material of described first outer shroud 2412, described first inner ring 2413, described 2nd outer shroud 2422, described back up pad 2423 is carbon fiber; And/or, the material of described 2nd net bone 2421 is carbon fiber so that described without man-machine rotor 2 lighter weight. Described first inner ring 2413 is collinear with the axis of described back up pad 2423. The size of described back up pad 2423 is more than or equal to the size of described actuator 25, to facilitate described actuator 25 to be fixed in described back up pad 2423, instead of traditional employing web member and fix described propeller hub 22, reduce further the described weight without man-machine rotor 2, simplify the described structure without man-machine rotor 2. Described first inner ring 2413 is arranged with described first outer shroud 2412 is concentric; Described back up pad 2423 is arranged with described 2nd outer shroud 2422 is concentric, ensure that the stability in described guard portion 24.
Described multiple connection beam 243 is for connecting described front mesh enclosure 241 and described rear net cover 242, the one end connecting beam 243 described in each is fixed on described first outer shroud 2412, the other end is fixed on described 2nd outer shroud 2422, further enhancing the strength of joint of described front mesh enclosure 241 and described rear net cover 242.
Described also comprise web plate 3 without man-machine 100, described web plate 3 be fixed on described between at least two adjacent connection beams 243, described at least four rotors 2 are removably fixedly connected with at described web plate 3 place with described fuselage 1. In the present embodiment, described web plate 3 is magnetic web plate, and described in making, at least four rotors 2 are connected with described fuselage 1 magnetic; And/or described web plate 3 is bolted to connection with described fuselage 1 so that described be convenient to dismounting without man-machine.
The useful effect of the application is as follows:
The rotor wing unmanned aerial vehicle that the application provides, fixed respectively at described first outer shroud and described first inner ring with default preliminary tension by the two ends of described first net bone, the impact of extraneous big foreign matter is avoided when at least two blades rotate described in making, and improve security, on the other hand, described first net bone is the elastic material of band, has elasticity, avoids described being subject to rigid shock without man-machine rotor; Described web plate is magnetic plate, described fuselage is connected with described rotor magnetic, it is convenient to dismounting, solve big without man-machine rotor weight in prior art, rotor to be subject to easily damaging rotor blade when bigger foreign matter impacts, security is lower and without the technical problem of man-machine dismounting inconvenience, reach provide a kind of light without man-machine rotor weight, shock resistance big, security height and the described technique effect without man-machine convenient disassembly.
It should be noted last that, above embodiment is only in order to illustrate the technical solution of the utility model and unrestricted, although the utility model being described in detail with reference to example, it will be understood by those within the art that, the technical solution of the utility model can be modified or equivalent replacement, and not departing from the spirit and scope of technical solutions of the utility model, it all should be encompassed in the middle of right of the present utility model.
Claims (9)
1. a rotor wing unmanned aerial vehicle, comprises fuselage, at least four rotors, it is characterised in that, described at least four rotors comprise:
Actuator;
Turning axle, is connected with described actuator, and described turning axle can rotate relative to its axis;
Propeller hub, is functionally connected on described turning axle in rotary manner;
At least two blades, the axis of relatively described turning axle is functionally connected on described propeller hub in rotary manner;
Guard portion, described guard portion comprises:
Front mesh enclosure, described front mesh enclosure comprises multiple first net bone, the first outer shroud and the first inner ring, and the two ends of the first net bone described in each are separately fixed in described first outer shroud and described first inner ring with certain preliminary tension, and described first net bone is the elastic material of band;
Rear net cover, described rear net cover comprises the back up pad of multiple 2nd net bone, the 2nd outer shroud and circle, and described in each, one end of the 2nd net bone is fixed in described back up pad, and the other end is fixed on described 2nd outer shroud; Described actuator is removably fixed in described back up pad;
Multiple connection beam, the one end connecting beam described in each is fixed on described first outer shroud, and the other end is fixed on described 2nd outer shroud;
Described also comprise web plate without man-machine, described web plate be fixed on described between at least two adjacent connection beams, described at least four rotors are removably fixedly connected with at described web plate place with described fuselage.
2. as claimed in claim 1 without man-machine, it is characterised in that, the material of described first outer shroud, described first inner ring, described 2nd outer shroud, described back up pad is carbon fiber; And/or, the material of described 2nd net bone is carbon fiber.
3. as claimed in claim 1 without man-machine, it is characterised in that, the axis of described first inner ring and described back up pad is collinear.
4. as claimed in claim 1 without man-machine, it is characterised in that, the size of described back up pad is more than or equal to the size of described actuator, to facilitate described actuator to be fixed in described back up pad.
5. as claimed in claim 1 without man-machine, it is characterised in that, described first inner ring is arranged with described first outer shroud is concentric; And/or, described back up pad is arranged with described 2nd outer shroud is concentric.
6. as claimed in claim 1 without man-machine, it is characterised in that, described first net bone is specially nylon wire.
7. as claimed in claim 1 without man-machine, it is characterised in that, described actuator is specially motor.
8. as described in as arbitrary in claim 1-7 without man-machine, it is characterised in that, described web plate is magnetic web plate, and described in making, at least four rotors are connected with described fuselage magnetic.
9. as described in as arbitrary in claim 1-7 without man-machine, it is characterised in that, described web plate and described fuselage are bolted to connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520976377.0U CN205273850U (en) | 2015-11-30 | 2015-11-30 | Rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520976377.0U CN205273850U (en) | 2015-11-30 | 2015-11-30 | Rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205273850U true CN205273850U (en) | 2016-06-01 |
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ID=56058451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520976377.0U Expired - Fee Related CN205273850U (en) | 2015-11-30 | 2015-11-30 | Rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205273850U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585953A (en) * | 2016-12-27 | 2017-04-26 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN115158681A (en) * | 2022-08-30 | 2022-10-11 | 南京开天眼无人机科技有限公司 | Protective mesh enclosure for flight rotor wing, application and forming process thereof |
-
2015
- 2015-11-30 CN CN201520976377.0U patent/CN205273850U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585953A (en) * | 2016-12-27 | 2017-04-26 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN106585953B (en) * | 2016-12-27 | 2023-07-21 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN115158681A (en) * | 2022-08-30 | 2022-10-11 | 南京开天眼无人机科技有限公司 | Protective mesh enclosure for flight rotor wing, application and forming process thereof |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Patentee before: EWATT CO., LTD. |
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| 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: 20160601 Termination date: 20181130 |