CN106394858A - Folded six-rotor unmanned plane - Google Patents
Folded six-rotor unmanned plane Download PDFInfo
- Publication number
- CN106394858A CN106394858A CN201611123119.3A CN201611123119A CN106394858A CN 106394858 A CN106394858 A CN 106394858A CN 201611123119 A CN201611123119 A CN 201611123119A CN 106394858 A CN106394858 A CN 106394858A
- Authority
- CN
- China
- Prior art keywords
- horn
- upper casing
- unmanned aerial
- connector
- aerial vehicles
- Prior art date
- 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.)
- Pending
Links
- 230000005611 electricity Effects 0.000 claims description 8
- 239000002131 composite material Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 230000008901 benefit Effects 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 abstract description 2
- 230000009467 reduction Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 230000032258 transport Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 241000257468 Asterias amurensis Species 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000003592 biomimetic effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/04—Power-plant nacelles, fairings, or cowlings associated with fuselages
-
- 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
- B64C2001/0045—Fuselages characterised by special shapes
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides a folded six-rotor unmanned plane. The folded six-rotor unmanned plane comprises rotors, propellers, electronic speed controller boxes, arms, an upper fuselage shell, a lower fuselage and undercarriages; the upper fuselage shell is in sealed connection with the lower fuselage shell, and the upper fuselage shell is a smooth streamline curved surface; the upper fuselage shell is connected with six arms, every arm comprises a first arm connecting piece and a second arm connecting piece, the lower ends of the first arm connecting piece and the second arm connecting piece are hinged through a rotating shaft, and every arm also comprises an arm locking sheet used for movably connecting the opening and closing positions of the first arm connecting piece and the second arm connecting piece; the outer ends of the arms are connected with the rotors, the propellers and the electronic speed controller boxes; and the undercarriages are connected to the side portions of the bottom surface of the lower fuselage shell. The unmanned plane has the advantages of wind resistance reduction, flight time prolongation, and flight stability improvement, has high adaptability in hostile environment, and is convenient to transport and dismount due to the arms can be folded.
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, six rotor wing unmanned aerial vehicles of streamlined body.
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
Six 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.
Content of the invention
In view of this, it is contemplated that proposing a kind of six rotor wing unmanned aerial vehicles of folding, windage can be reduced, when increasing flight
Between, improve the unmanned plane of flight stability, particularly under conditions of environment is relatively more severe, also can have stronger adaptability, and
Horn can fold, and conveniently transport and dismantle.
For reaching above-mentioned purpose, the technical scheme is that and be achieved in that：
A kind of six rotor wing unmanned aerial vehicles of folding, adjust box, horn, fuselage upper casing, fuselage lower casing including motor, propeller, electricity
And undercarriage；Described fuselage upper casing closing connects described fuselage lower casing, and described fuselage upper casing is smooth streamlined curved surface；Described machine
Shell is connected with six described horns with it, and described horn includes the first horn connector and the second horn connector, and described first
The lower end of horn connector and described second horn connector is hinged by rotary shaft, also includes described first horn connector
The horn stay being flexibly connected with the opening and closing place of described second horn connector；The described motor of outer end connection of described horn,
Described propeller and described electricity adjust box；Described undercarriage is connected to described fuselage lower casing bottom surface sidepiece.
Further, described first horn connector, around described rotary shaft, is rotated down with respect to the second horn connector
Angle be 90 degree.
Further, described fuselage upper casing is in hexagram；Each described horn is connected to each of described fuselage upper casing
At coign.
Further, the side wall of described fuselage lower casing is set to battery door.
Further, described fuselage upper casing, described fuselage lower casing, described undercarriage by composite pass through formed in mould
Mode is made.
Further, the top of described fuselage upper casing is internally provided with GPS.
Further, described horn is made up of carbon pipe, and section is rounded.
With respect to prior art, six rotor wing unmanned aerial vehicles of folding 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 hexagram, and surface is streamlined curved surface, and the biomimetic features of similar Asterias amurensis Lutken have reduction windward
Contact area, reduces the advantage of air resistance coefficient, meets aerodynamic requirement, can reduce resistance during practical flight
Power, increases wind resistance, makes flight more stable；Electronic equipment all among the encirclement of fuselage upper casing and fuselage lower casing, effectively
Avoid the interference to electronic equipment and control device for the outside adverse circumstances.In addition, battery door is arranged on fuselage lower casing one
Side-walls, the design of battery compartment and fuselage combine together, have certain water-proof function, also allow for changing battery, and battery
Storehouse can separate flight control system and battery, it is to avoid the electromagnetic interference of internal wiring, and heat is excessively concentrated to electric elements
Damage.
Horn adopts foldable structure, gently pulls horn stay, and the first horn connector that horn connects can be around
Rotary shaft is rotated down 90 degree in the presence of the second 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-
Fuselage upper casing；8- undercarriage；9- horn stay；10- battery door；11- fuselage lower casing.
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 provide a kind of folding six rotor wing unmanned aerial vehicles, including motor 1, propeller 2,
Electricity adjusts box 3, horn 4, fuselage upper casing 7, fuselage lower casing 11 and undercarriage 8；Described fuselage upper casing 7 closing connects described fuselage lower casing
11, described fuselage upper casing 7 is smooth streamlined curved surface；Described fuselage upper casing 7 is connected with six described horns 4, and described horn 4 wraps
Include the first horn connector 5 and the second horn connector 6, described first horn connector 5 and described second horn connector 6
Lower end is hinged by rotary shaft, also includes living in the opening and closing place of described first horn connector 4 and described second horn connector 5
The horn stay 9 being dynamically connected；The outer end of described horn 4 connects described motor 1, described propeller 2 and described electricity and adjusts box 3；Institute
State undercarriage 8 and be connected to described fuselage lower casing 11 bottom surface sidepiece.
Described first horn connector 5 around described rotary shaft, the angle being rotated down with respect to the second horn connector 6 is
90 degree.
Described fuselage upper casing 7 is in hexagram；Each described horn 4 is connected at each coign of described fuselage upper casing 7.
The side wall of described fuselage lower casing 11 is set to battery door 10.
Described fuselage upper casing 7, described fuselage lower casing 11, described undercarriage 8 are by composite by formed in mould mode
It is made.
The top of described fuselage upper casing 7 is internally 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, and the design that fuselage and battery compartment combine together, in flight
Will be smaller with respect to the resistance of air, whole electronic equipment and flight control system are arranged in fuselage interior, by opening fuselage
Upper casing 7 can realize the replacing to internal electronic equipment or debugging.Fuselage upper casing 7 and fuselage lower casing 11 are all by composite
Formed by Mold Making, lightweight, intensity is good, and air resistance coefficient is little.Horn 4 is made up of carbon pipe, and circular cross sectional shape ensures
Smoothness and reduce windage.GPS is placed in the dome interior of fuselage upper casing 7, and GPS is higher than fuselage, away from the electricity of fuselage interior
Subassembly, effectively avoids the interference of signal.There is a LED blinker, in aircraft away from certainly at battery compartment afterbody
Oneself when can distinguish head and tail according to the difference of display lamp.As shown in figure 5, gently pulling horn stay 11,
The first horn connector 5 that horn 4 connects can be rotated down 90 around rotary shaft in the presence of the second horn connector 6
Degree, folds the overall dimensions that can reduce aircraft after completing, and is easy to store and transports.
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 six rotor wing unmanned aerial vehicles it is characterised in that：Including motor, propeller, electricity adjust box, horn, fuselage upper casing,
Fuselage lower casing and undercarriage；Described fuselage upper casing closing connects described fuselage lower casing, and described fuselage upper casing is smooth streamlined song
Face；Described fuselage upper casing is connected with six described horns, and described horn includes the first horn connector and the second horn connector,
The lower end of described first horn connector and described second horn connector is hinged by rotary shaft, also includes described first machine
The horn stay that the opening and closing place of arm connector and described second horn connector is flexibly connected；The outer end of described horn connects institute
State motor, described propeller and described electricity and adjust box；Described undercarriage is connected to described fuselage lower casing bottom surface sidepiece.
2. folding according to claim 1 six rotor wing unmanned aerial vehicles it is characterised in that：Described first horn connector is around institute
State rotary shaft, be 90 degree with respect to the angle that the second horn connector is rotated down.
3. folding according to claim 1 six rotor wing unmanned aerial vehicles it is characterised in that：Described fuselage upper casing is in Magen David
Shape；Each described horn is connected at each coign of described fuselage upper casing.
4. folding according to claim 1 six rotor wing unmanned aerial vehicles it is characterised in that：The side wall of described fuselage lower casing sets
It is set to battery door.
5. folding according to claim 1 six rotor wing unmanned aerial vehicles it is characterised in that：Described fuselage upper casing, described fuselage
Lower casing, described undercarriage are made by formed in mould mode by composite.
6. folding according to claim 1 six rotor wing unmanned aerial vehicles it is characterised in that：Inside the top of described fuselage upper casing
It is provided with GPS.
7. folding according to claim 1 six rotor wing unmanned aerial vehicles 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 |
|---|---|---|---|
| CN201611123119.3A CN106394858A (en) | 2016-12-08 | 2016-12-08 | Folded six-rotor unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611123119.3A CN106394858A (en) | 2016-12-08 | 2016-12-08 | Folded six-rotor unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106394858A true CN106394858A (en) | 2017-02-15 |
Family
ID=58084702
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611123119.3A Pending CN106394858A (en) | 2016-12-08 | 2016-12-08 | Folded six-rotor unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106394858A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107487432A (en) * | 2017-09-22 | 2017-12-19 | 贵州信鸽科技有限公司 | Unmanned vehicle and flight instruments |
| CN108284949A (en) * | 2018-03-05 | 2018-07-17 | 南京韬讯航空科技有限公司 | A kind of foldable staggeredly six rotorcraft |
| CN110865404A (en) * | 2018-08-28 | 2020-03-06 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| CN112607019A (en) * | 2020-12-14 | 2021-04-06 | 金肯职业技术学院 | Windproof type suspension shooting unmanned aerial vehicle and stable shooting method |
| CN117755542A (en) * | 2024-02-20 | 2024-03-26 | 泉州云卓科技有限公司 | High-adaptability multifunctional unmanned aerial vehicle support and unmanned aerial vehicle thereof |
-
2016
- 2016-12-08 CN CN201611123119.3A patent/CN106394858A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107487432A (en) * | 2017-09-22 | 2017-12-19 | 贵州信鸽科技有限公司 | Unmanned vehicle and flight instruments |
| CN108284949A (en) * | 2018-03-05 | 2018-07-17 | 南京韬讯航空科技有限公司 | A kind of foldable staggeredly six rotorcraft |
| CN108284949B (en) * | 2018-03-05 | 2023-09-08 | 南京韬讯航空科技有限公司 | Foldable staggered six-rotor aircraft |
| CN110865404A (en) * | 2018-08-28 | 2020-03-06 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| CN110865404B (en) * | 2018-08-28 | 2022-02-18 | 北京理工大学 | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles |
| CN112607019A (en) * | 2020-12-14 | 2021-04-06 | 金肯职业技术学院 | Windproof type suspension shooting unmanned aerial vehicle and stable shooting method |
| CN117755542A (en) * | 2024-02-20 | 2024-03-26 | 泉州云卓科技有限公司 | High-adaptability multifunctional unmanned aerial vehicle support and unmanned aerial vehicle thereof |
| CN117755542B (en) * | 2024-02-20 | 2024-05-31 | 泉州云卓科技有限公司 | High-adaptability multifunctional unmanned aerial vehicle support and unmanned aerial vehicle thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170215 |
|
| WD01 | Invention patent application deemed withdrawn after publication |