CN106477024A - A kind of folding eight rotor wing unmanned aerial vehicles - Google Patents
A kind of folding eight rotor wing unmanned aerial vehicles Download PDFInfo
- Publication number
- CN106477024A CN106477024A CN201611123858.2A CN201611123858A CN106477024A CN 106477024 A CN106477024 A CN 106477024A CN 201611123858 A CN201611123858 A CN 201611123858A CN 106477024 A CN106477024 A CN 106477024A
- Authority
- CN
- China
- Prior art keywords
- horn
- undercarriage
- fuselage
- folding
- unmanned aerial
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention provides a kind of folding eight rotor wing unmanned aerial vehicles, adjust box including motor, propeller, horn, fuselage upper casing, fuselage lower casing, undercarriage cross bar, undercarriage montant, battery case and electricity；The closing of fuselage upper casing connects fuselage lower casing, and fuselage upper casing is smooth streamlined curved surface；Fuselage upper casing is connected with eight horns, and horn includes the first horn connector and the second horn connector, and the lower end of the first horn connector and the second horn connector is hinged by rotary shaft, also includes horn stay；The outer end of horn connects motor, propeller and electricity and adjusts box；The upper end of undercarriage montant is connected to the bottom sides of fuselage lower casing, and undercarriage cross bar is connected to the lower end of undercarriage montant by three-way piece.Beneficial effect is to reduce windage, increases the flight time, improves the unmanned plane of flight stability, particularly also can have stronger adaptability under conditions of environment is relatively more severe, and horn can fold, and conveniently transport and dismantle.
Description
Technical field
The invention belongs to aerospace flight vehicle field, especially relate to a kind of minimizing flight resistance, increase stable machine
Property and increase the flight time a kind of streamlined body eight rotor wing unmanned aerial vehicles.
Background technology
UAV referred to as " unmanned plane ", is to be manipulated with the presetting apparatus provided for oneself using radio robot
Not manned aircraft.No driving cabin on machine, but have automatic pilot, the equipment such as presetting apparatus.For currently on the market
Eight rotor wing unmanned aerial vehicle great majority assume one kind does not have shell or shell simple and crude, and in actual job, wind loading rating is poor, does not have streamline
The fuselage of type, in flight course, flight resistance increases, and decreases the flight time, does not have shell or the simple and crude unmanned plane of shell
Water-resistant performance is also poor, is unfavorable for operation in rugged environment, and existing horn can not fold it has not been convenient to transporting and tearing open
Unload.
Content of the invention
In view of this, it is contemplated that proposing a kind of folding eight rotor wing unmanned aerial vehicles, windage can be reduced, increase flight
Time, improve the unmanned plane of flight stability, particularly under conditions of environment is relatively more severe, also can have stronger adaptability, and
And horn can fold, conveniently transport and dismantle.
For reaching above-mentioned purpose, the technical scheme is that and be achieved in that：
A kind of folding eight rotor wing unmanned aerial vehicles, including motor, propeller, horn, fuselage upper casing, fuselage lower casing, rise and fall
Frame cross bar, undercarriage montant, battery case and electricity adjust box；Described fuselage upper casing closing connects described fuselage lower casing, on described fuselage
Shell is smooth streamlined curved surface；Described fuselage upper casing is connected with eight described horns, and described horn includes the first horn connector
With the second horn connector, it is hinged that rotary shaft is passed through in the lower end of described first horn connector and described second horn connector,
Also include the horn stay that the opening and closing place of described first horn connector and described second horn connector is flexibly connected；Institute
The outer end stating horn connects described motor, described propeller and described electricity tune box；The upper end of described undercarriage montant is connected to institute
State the bottom sides of fuselage lower casing, described undercarriage cross bar is connected to the lower end of described undercarriage montant by three-way piece.
Further, described battery case is connected to described fuselage lower casing bottom by XT90 plug.
Further, the bottom of described battery case is provided with gripper shoe.
Further, described fuselage upper casing, described fuselage lower casing, described undercarriage montant and described undercarriage cross bar are by multiple
Condensation material is made by formed in mould mode, and the section of described undercarriage montant and described undercarriage cross bar is in circle
Shape.
Further, the two ends of described undercarriage cross bar are socketed with damping footmuff.
Further, the dome interior of described fuselage upper casing is provided with GPS.
Further, described horn is made up of carbon pipe, and section is rounded.
With respect to prior art, folding eight rotor wing unmanned aerial vehicles of the present invention have the advantage that：
Fuselage upper casing and fuselage lower casing are formed by Mold Making using composite, and good forming effect is highly polished, weight
Amount is light, and fuselage upper casing is in smooth streamlined curved surface, reduces contact area windward according to aerodynamic principle, reduces wind
The advantage of resistance coefficient, meets aerodynamic requirement, can reduce resistance during practical flight, increases wind resistance,
Make flight more stable；Battery case is connected to fuselage lower casing bottom by XT90 plug, is individually put using battery case and flight control system
Put, it is to avoid the electromagnetic interference of internal wiring, and heat excessively concentrates the damage to electric elements；Effectively avoid outside evil
The interference to electronic equipment and control device for the bad environment.
Horn adopts foldable structure, gently pulls horn stay, and the second horn connector that horn connects can be around
Rotary shaft is rotated down 90 degree in the presence of the first horn connector, folds the overall chi that can reduce aircraft after completing
Very little, it is easy to store and transport.
Brief description
The accompanying drawing constituting the part of the present invention is used for providing a further understanding of the present invention, the schematic reality of the present invention
Apply example and its illustrate, for explaining the present invention, not constituting inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the positive structure diagram described in the embodiment of the present invention；
Fig. 2 is the overlooking the structure diagram described in the embodiment of the present invention；
Fig. 3 is the side structure schematic view described in the embodiment of the present invention；
Fig. 4 is the side structure schematic view such as just described in the embodiment of the present invention；
Fig. 5 is the foldable structure schematic diagram described in the embodiment of the present invention.
Description of reference numerals：
1- motor；2- propeller；3- electricity adjusts box；4- horn；5- the first horn connector；6- the second horn connector；7-
Undercarriage cross bar；8- undercarriage montant；9- fuselage upper casing；10- fuselage lower casing；11- horn stay；12- battery case；13-
XT90 plug；14- damping footmuff；15- three-way piece.
Specific embodiment
It should be noted that in the case of not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Mutually combine.
In describing the invention it is to be understood that term " " center ", " longitudinal ", " horizontal ", " on ", D score,
The orientation of instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description, rather than instruction or dark
Show the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that right
The restriction of the present invention.Additionally, term " first ", " second " etc. are only used for describing purpose, and it is not intended that indicating or hint phase
To importance or the implicit quantity indicating indicated technical characteristic.Thus, the feature defining " first ", " second " etc. can
To express or to implicitly include one or more this feature.In describing the invention, unless otherwise stated, " multiple "
It is meant that two or more.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or is integrally connected；Can
To be to be mechanically connected or electrical connection；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition
Concrete meaning in the present invention.
To describe the present invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
As shown in Fig. 1,2,3,4,5, the present invention provides a kind of folding eight rotor wing unmanned aerial vehicles, including motor 1, propeller
2nd, horn 4, fuselage upper casing 9, fuselage lower casing 10, undercarriage cross bar 7, undercarriage montant 8, battery case 12 and electricity adjust box 3；Described machine
Shell 9 closing with it connects described fuselage lower casing 10, and described fuselage upper casing 9 is smooth streamlined curved surface；Described fuselage upper casing 9 connects
There are eight described horns 4, described horn 4 includes the first horn connector 5 and the second horn connector 6, and described first horn is even
The lower end of fitting 5 and described second horn connector 6 is hinged by rotary shaft, also includes described first horn connector 5 He
The horn stay 11 that the opening and closing place of described second horn connector 6 is flexibly connected；The outer end of described horn 4 connects described motor
1st, described propeller 2 and described electricity adjust box 3；The upper end of described undercarriage montant 8 is connected to the bottom side of described fuselage lower casing 10
Face, described undercarriage cross bar 7 is connected to the lower end of described undercarriage montant 8 by three-way piece 15.
Described battery case 12 is connected to described fuselage lower casing 10 bottom by XT90 plug 13.
The bottom of described battery case 12 is provided with gripper shoe.
Described fuselage upper casing 9, described fuselage lower casing 10, described undercarriage montant 8 and described undercarriage cross bar 7 are by composite wood
Material is made by formed in mould mode, and the section of described undercarriage montant 8 and described undercarriage cross bar 7 is rounded.
The two ends of described undercarriage cross bar 7 are socketed with damping footmuff 14.
The dome interior of described fuselage upper casing 9 is provided with GPS.
Described horn 4 is made up of carbon pipe, and section is rounded.
The work process of this example：As shown in Figure 1,2,3, 4, whole fuselage appearance assumes a kind of smooth sweeping style,
Smooth fairshaped fuselage is not likely to produce sinuous flow in flight course, climbing power when increasing flight, and fuselage and battery case 12 are separately
Separated layout designs, and in flight, the resistance with respect to air will be smaller, and when in addition can dissipate work in time, battery produces
Raw heat, it is to avoid in thermal collecting, whole electronic equipment and flight control system are arranged in fuselage interior, by opening fuselage upper casing 9
The replacing to internal electronic equipment or debugging can be realized.Fuselage upper casing 9 and fuselage lower casing 10 are all to be passed through by composite
Mold Making forms, lightweight, and intensity is good, and air resistance coefficient is little.Horn 4 is made up of carbon pipe, and circular cross sectional shape ensure that light
Slippery and reduce windage.GPS is placed in the dome interior of fuselage upper casing 9, and GPS is higher than fuselage, away from the ministry of electronics industry of fuselage interior
Part, effectively avoids the interference of signal.There is a LED blinker, in aircraft away from oneself at battery case 12 rear portion
When can distinguish head and tail according to the difference of display lamp.As shown in figure 5, gently pulling horn stay 11, machine
The second horn connector 6 that arm 4 connects can be rotated down 90 degree around rotary shaft in the presence of the first horn connector 5,
Fold the overall dimensions that can reduce aircraft after completing, be easy to store and transport.The gripper shoe of battery case 12 bottom is permissible
Increase the carry ability of aircraft.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all essences in the present invention
Within god and principle, any modification, equivalent substitution and improvement made etc., should be included within the scope of the present invention.
Claims (7)
1. a kind of folding eight rotor wing unmanned aerial vehicles it is characterised in that：Including motor, propeller, horn, fuselage upper casing, fuselage
Lower casing, undercarriage cross bar, undercarriage montant, battery case and electricity adjust box；Described fuselage upper casing closing connects described fuselage lower casing, institute
Stating fuselage upper casing is smooth streamlined curved surface；Described fuselage upper casing is connected with eight described horns, and described horn includes the first machine
Arm connector and the second horn connector, rotation is passed through in the lower end of described first horn connector and described second horn connector
Axle is hinged, also includes the horn lock being flexibly connected the opening and closing place of described first horn connector and described second horn connector
Tight piece；The outer end of described horn connects described motor, described propeller and described electricity and adjusts box；The upper end of described undercarriage montant is even
It is connected on the bottom sides of described fuselage lower casing, described undercarriage cross bar is connected under described undercarriage montant by three-way piece
End.
2. folding eight rotor wing unmanned aerial vehicles according to claim 1 it is characterised in that：Described battery case passes through XT90 and inserts
Head is connected to described fuselage lower casing bottom.
3. folding eight rotor wing unmanned aerial vehicles according to claim 2 it is characterised in that：The bottom setting of described battery case
There is gripper shoe.
4. folding eight rotor wing unmanned aerial vehicles according to claim 1 it is characterised in that：Described fuselage upper casing, described machine
Body lower casing, described undercarriage montant and described undercarriage cross bar are made by formed in mould mode by composite, and
The section of described undercarriage montant and described undercarriage cross bar is rounded.
5. folding eight rotor wing unmanned aerial vehicles according to claim 1 or 4 any one it is characterised in that：Described undercarriage
The two ends of cross bar are socketed with damping footmuff.
6. folding eight rotor wing unmanned aerial vehicles according to claim 1 or 4 any one it is characterised in that：On described fuselage
The dome interior of shell is provided with GPS.
7. folding eight rotor wing unmanned aerial vehicles according to claim 1 it is characterised in that：Described horn is made up of carbon pipe,
And section is rounded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611123858.2A CN106477024A (en) | 2016-12-08 | 2016-12-08 | A kind of folding eight rotor wing unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611123858.2A CN106477024A (en) | 2016-12-08 | 2016-12-08 | A kind of folding eight rotor wing unmanned aerial vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106477024A true CN106477024A (en) | 2017-03-08 |
Family
ID=58275111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611123858.2A Pending CN106477024A (en) | 2016-12-08 | 2016-12-08 | A kind of folding eight rotor wing unmanned aerial vehicles |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106477024A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336826A (en) * | 2017-06-30 | 2017-11-10 | 浙江大学 | A kind of collapsible unmanned plane of more rotors |
| CN107352018A (en) * | 2017-06-30 | 2017-11-17 | 浙江大学 | A kind of folding unmanned plane undercarriage |
| CN107672799A (en) * | 2017-10-18 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane |
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| WO2019107009A1 (en) * | 2017-11-30 | 2019-06-06 | 株式会社プロドローン | Unmanned aerial vehicle |
| CN111315654A (en) * | 2017-06-01 | 2020-06-19 | 舒尔弗莱股份有限公司 | Auxiliary power system for rotorcraft having folding rotor arms and crush zone landing gear |
| WO2022095205A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Foldable arm and unmanned aerial vehicle |
| WO2024142199A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
-
2016
- 2016-12-08 CN CN201611123858.2A patent/CN106477024A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111315654A (en) * | 2017-06-01 | 2020-06-19 | 舒尔弗莱股份有限公司 | Auxiliary power system for rotorcraft having folding rotor arms and crush zone landing gear |
| CN107336826A (en) * | 2017-06-30 | 2017-11-10 | 浙江大学 | A kind of collapsible unmanned plane of more rotors |
| CN107352018A (en) * | 2017-06-30 | 2017-11-17 | 浙江大学 | A kind of folding unmanned plane undercarriage |
| CN107336826B (en) * | 2017-06-30 | 2023-08-15 | 浙江大学 | Many rotor folding unmanned aerial vehicle |
| CN107352018B (en) * | 2017-06-30 | 2023-09-08 | 浙江大学 | Folding unmanned aerial vehicle undercarriage |
| CN107672799A (en) * | 2017-10-18 | 2018-02-09 | 沈阳旋飞航空技术有限公司 | A kind of electronic unmanned plane |
| WO2019107009A1 (en) * | 2017-11-30 | 2019-06-06 | 株式会社プロドローン | Unmanned aerial vehicle |
| JP6543835B1 (en) * | 2017-11-30 | 2019-07-17 | 株式会社プロドローン | Unmanned air vehicle |
| US10882600B2 (en) | 2017-11-30 | 2021-01-05 | Prodrone Co., Ltd. | Foldable unmanned aerial vehicle |
| CN109050898A (en) * | 2018-08-16 | 2018-12-21 | 南京壹诺为航空科技有限公司 | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula |
| WO2022095205A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Foldable arm and unmanned aerial vehicle |
| WO2024142199A1 (en) * | 2022-12-27 | 2024-07-04 | 株式会社クボタ | Flying apparatus |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170308 |