CN106394892A - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106394892A CN106394892A CN201611115715.7A CN201611115715A CN106394892A CN 106394892 A CN106394892 A CN 106394892A CN 201611115715 A CN201611115715 A CN 201611115715A CN 106394892 A CN106394892 A CN 106394892A
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- horn
- fuselage
- rotor
- unmanned plane
- fixedly connected
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- 238000009434 installation Methods 0.000 claims description 2
- 230000002159 abnormal effect Effects 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 4
- 230000007547 defect Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
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Classifications
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- 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)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention belongs to the technical field of aircrafts, and provides an unmanned aerial vehicle which comprises a vehicle body, a plurality of vehicle arms, a plurality of motors, a plurality of rotors, a foot stand and a control system. One ends of the vehicle arms are connected to the edge of the vehicle body, the motors correspond to the vehicle arms in a one-to-one mode and are fixedly connected to the ends, away from the vehicle body, of the vehicle arms, and the rotors correspond to the motors in a one-to-one mode and are fixedly connected to rotating shafts of the corresponding motors; every two adjacent rotors are opposite in rotating direction; and the control system comprises a controller which is arranged on the vehicle body and electrically connected with the motors. The stability of the vehicle body of the unmanned aerial vehicle in the flying process can be effectively guaranteed, the vehicle body is protected against abnormal inclination or rotation, and therefore normal work of the unmanned aerial vehicle is guaranteed, and the defects of the prior art are overcome.
Description
Technical field
The present invention relates to vehicle technology field, in particular to a kind of unmanned plane.
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 the equipment such as automatic pilot, presetting apparatus are installed.On ground, naval vessels or
Machine tool remote control station personnel pass through the equipment such as radar, it is tracked, positions, remote control, remote measurement and Digital Transmission.Unmanned plane can be
Take off as conventional airplane under wireless remotecontrol or launched with booster rocket, also aerial input can be taken to by machine tool and fly
OK.During recovery, can use the mode automatic Landing as conventional airplane landing mission, also can pass through remote control parachute or block
Reclaim.
Mostly there is the problem that flight course middle fuselage is unstable, easily tilts or rotates in existing unmanned plane.
Content of the invention
It is an object of the invention to provide a kind of unmanned plane, it can effectively ensure that the steady of flight course middle fuselage, prevents
Only abnormal inclination or rotates, thus ensureing the normal work of itself in fuselage.
Embodiments of the invention are realized in：
A kind of unmanned plane, it includes fuselage, horn, motor, rotor, foot rest and control system, and described horn has multiple
And one end is connected to the edge of described fuselage, described motor is had multiple and is corresponded with multiple described horns, Duo Gesuo
State motor and be respectively fixedly connected with one end away from described fuselage in multiple described horns, described rotor has multiple and described with multiple
Motor corresponds, and multiple described rotors are respectively fixedly connected with the rotating shaft of multiple described motors, two neighboring described rotor
Direction of rotation is contrary, and described control system includes controller, and described controller is arranged at described fuselage, and multiple described motors are respectively
Electrically connect with described controller.
Further, in preferred embodiments of the present invention, the quantity of described rotor is even number.
Further, in preferred embodiments of the present invention, described control system also includes angular-rate sensor, described angle
Velocity sensor is arranged at the edge of described fuselage, and described angular-rate sensor is connected with described controller.
Further, in preferred embodiments of the present invention, multiple described horns are away from one end of described motor accordingly
It is rotationally connected with described fuselage respectively, the horn that unmanned plane is also included for making described horn fixing with respect to described fuselage is spacing
Structure.
Further, in preferred embodiments of the present invention, described horn position limiting structure includes fixture block, card column and bullet
Spring, described fixture block is fixedly connected on described horn, and described fixture block includes planar portions and cambered surface portion, and described spring one end props up described
Fuselage, the other end props up described card column, and described card column is slidably connected to described fuselage and pushes down institute in the presence of described spring
State planar portions.
Further, in preferred embodiments of the present invention, described horn position limiting structure includes base plate and caging bolt, institute
State base plate and be fixedly connected on described fuselage, described caging bolt head props up the side away from described card column for the described base plate, stud
Portion passes through described base plate and is fixedly connected on described card column, and located at described stud portion and one end props up described bottom to described spring housing
Plate, the other end props up described card column.
Further, in preferred embodiments of the present invention, described horn position limiting structure also includes side plate and positive stop,
Described side plate has two and parallel interval is arranged at described fuselage, and two described side plates are respectively arranged with bar hole, described card column
Run through two described bar holes, described positive stop has two and is respectively arranged at the two ends of described card column, and two described spacing
Block is located at the outside of two described side plates respectively.
Further, in preferred embodiments of the present invention, unmanned plane also includes rotor mounting structure, rotor mounting structure
It is arranged at one end of the corresponding described rotor of described horn, described rotor mounting structure includes four fixed plates and an installing plate,
Each described fixed plate is provided with breach, one group two-by-two of four described fixed plates, and described in two groups, fixed plate is along described horn
Length direction interval setting, same group of two described fixed plates are connected with each other, the breach of same group of two described fixed plates
Mutually correspond to thus forming the fixing hole with described horn cooperation, described installing plate is fixedly connected on of fixed plate described in two groups
Side, described motor is fixedly connected on described installing plate.
Further, in preferred embodiments of the present invention, the outer wall of described horn is provided with two cannelures, two institutes
The diapire stating cannelure is provided with projection, the position of two described fixing holes, two described cannelures corresponding with described horn respectively
Cooperation, the inwall of two described fixing holes is respectively arranged with the groove with two described male cooperation.
A kind of unmanned plane, it includes fuselage, horn, motor, rotor, foot rest and control system, and described horn has multiple
And one end is connected to the edge of described fuselage, described motor is had multiple and is corresponded with multiple described horns, Duo Gesuo
State motor and be respectively fixedly connected with one end away from described fuselage in multiple described horns, described rotor has multiple and described with multiple
Motor corresponds, and multiple described rotors are respectively fixedly connected with the rotating shaft of multiple described motors, two neighboring described rotor
Direction of rotation is contrary, and described control system includes controller, and described controller is arranged at described fuselage, and multiple described motors are respectively
Electrically connect with described controller, described foot rest includes two supports being oppositely arranged, each described support all include the first pole,
Second pole and the 3rd pole, described first pole and described second pole be arranged in parallel and equal one end is connected to described machine
Body, the other end is connected to described 3rd pole, and described 3rd pole is parallel to described fuselage.
The beneficial effect of the embodiment of the present invention is：
This unmanned plane includes fuselage, horn, motor, rotor, and horn has multiple and one end to be connected to the edge of fuselage,
Motor is had multiple and is corresponded with multiple horns, and multiple motors are respectively fixedly connected with the one end in multiple horns away from fuselage,
Rotor is had multiple and is corresponded with multiple motors, and multiple rotors are respectively fixedly connected with the rotating shaft of multiple motors, two neighboring
The direction of rotation of rotor is contrary, the torsion that the torsion that so each rotor wing rotation produces just can be produced by adjacent rotor wing rotation
Offset, so that flight course middle fuselage steady is effectively ensured, prevent fuselage from abnormal inclination occurring or rotates, thus ensureing
The normal work of itself, compensate for the defect of prior art.
Brief description
In order to be illustrated more clearly that the technical scheme of the embodiment of the present invention, below will be attached to use required in embodiment
Figure is briefly described it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, and it is right to be therefore not construed as
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to this
A little accompanying drawings obtain other related accompanying drawings.
Fig. 1 is the structural representation of unmanned plane provided in an embodiment of the present invention；
Fig. 2 is the structural representation of horn position limiting structure provided in an embodiment of the present invention；
Fig. 3 is the structural representation at another visual angle of horn position limiting structure provided in an embodiment of the present invention；
Fig. 4 is the structural representation of rotor mounting structure provided in an embodiment of the present invention.
Icon：100- unmanned plane；110- fuselage；120- horn；130- motor；140- rotor；150- foot rest；
200- horn position limiting structure；210- fixture block；220- card column；230- caging bolt；240- spring；250- base plate；260-
Side plate；270- bar hole；300- rotor mounting structure；310- fixed plate；320- installing plate.
Specific embodiment
Purpose, technical scheme and advantage for making the embodiment of the present invention are clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described it is clear that described embodiment is
The a part of embodiment of the present invention, rather than whole embodiments.The present invention generally described and illustrated in accompanying drawing herein is implemented
The assembly of example can be arranged with various different configurations and design.
Therefore, below the detailed description of the embodiments of the invention providing in the accompanying drawings is not intended to limit claimed
The scope of the present invention, but be merely representative of the selected embodiment of the present invention.Based on the embodiment in the present invention, this area is common
The every other embodiment that technical staff is obtained under the premise of not making creative work, broadly falls into the model of present invention protection
Enclose.
It should be noted that：Similar label and letter represent similar terms in following accompanying drawing, therefore, once a certain Xiang Yi
It is defined in individual accompanying drawing, then do not need it to be defined further and explains in subsequent accompanying drawing.
In describing the invention, it should be noted that term " " center ", " on ", D score, "left", "right", " vertical ",
The orientation of instruction such as " level ", " interior ", " outward " or position relationship are based on orientation shown in the drawings or position relationship, or should
Orientation or position relationship that invention product is usually put when using, are for only for ease of the description present invention and simplify description, and not
It is instruction or the hint device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore not
It is understood that as limitation of the present invention.Additionally, term " first ", " second ", " the 3rd " etc. are only used for distinguishing description, and can not manage
Solve as indicating or implying relative importance.
Additionally, the term such as term " level ", " vertical " is not offered as requiring part abswolute level or pendency, but can be slightly
Low dip.As " level " only refers to for its direction relatively " vertical " more level, it is not that this structure of expression must be complete
Full level, but can be slightly tilted.
In describing the invention in addition it is also necessary to explanation, unless otherwise clearly defined and limited, term " setting ",
" installation ", " being connected ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or one
Body ground connects；Can be to be mechanically connected or electrically connect；Can be joined directly together it is also possible to by intermediary indirect
It is connected, can be the connection of two element internals.For the ordinary skill in the art, can be with concrete condition understanding
State term concrete meaning in the present invention.
With reference to Fig. 1, present embodiments provide a kind of unmanned plane 100, it includes fuselage 110, horn 120, motor 130, rotation
The wing 140, foot rest 150 and control system.
Wherein, horn 120 has multiple and one end to be rotationally connected with the edge of fuselage 110 respectively.Rotating the mode connecting has
A lot, in the present embodiment, horn 120 is connected with fuselage 110 by the way of hinged.In order to ensure horn 120 in unmanned plane 100
Stability in the course of work, the horn that unmanned plane 100 is additionally provided with for making horn 120 fixing with respect to fuselage 110 is spacing
Structure 200.
Reference picture 2-3, horn position limiting structure 200 can adopt various forms, as long as it can play fixation to horn 120
Act on.In the present embodiment, horn position limiting structure 200 includes fixture block 210, card column 220 and spring 240, and fixture block 210 is fixing
It is connected to horn 120, fixture block 210 includes planar portions and cambered surface portion, spring 240 one end props up fuselage 110, and the other end props up card column
220, card column 220 is slidably connected to fuselage 110 and pushes down planar portions in the presence of spring 240.
The operation principle of this horn position limiting structure 200 and process are such：When not needing rotating machine arm 120, due to card
The planar portions on fixture block 210 pushed down by post 220, and therefore fixture block 210 cannot rotate under the restriction of card column 220, correspondingly horn 120
Also cannot rotate；When needing to rotate horn 120, card column 220 is promoted to slide so that card column 220 leaves planar portions, now fixture block
210 restrictions losing card column 220, can rotate down, and correspondingly, horn 120 can also rotate, and user can be by horn 120
Rotate down (fixture block 210 is rotated up) to close to vertical position, to reduce the volume of whole unmanned plane 100, convenient nothing
Man-machine 100 movement and transport, now card column 220 can reset in the presence of spring 240；When needing horn 120 to reset, only need
Horn 120 to be rotated up, fixture block 210 then rotates down, its cambered surface portion meeting preferential contact card column 220, due to the characteristic of cambered surface,
During fixture block 210 rotates down, card column 220 can be close to cambered surface portion and constantly slide, and compression spring 240, when card
When block 210 turns to certain position, card column 220 opposite direction will be slided in the presence of spring 240, again pushes down planar portions,
Thus effectively fixing horn 120, prevent horn 120 from rotating.
In order to ensure the mounting stability of spring 240, prevent from coming off in spring 240 telescopic process it is ensured that whole horn limits
The normal work of bit architecture 200, in the present embodiment, horn position limiting structure 200 includes base plate 250 and caging bolt 230, base plate
250 are fixedly connected on fuselage 110, and caging bolt 230 head props up the side away from card column 220 for the base plate 250, and stud portion passes through bottom
Plate 250 and be fixedly connected on card column 220, spring 240 is sheathed on stud portion and one end and props up base plate 250, and the other end props up card column
220.
In order to ensure the sliding stability of card column 220, prevent card column 220 from coming off in sliding process, thus ensureing whole
The normal work of horn position limiting structure 200, in the present embodiment, horn position limiting structure 200 also includes side plate 260 and positive stop,
Side plate 260 has two and parallel interval is arranged at fuselage 110, and two side plates 260 are respectively arranged with bar hole 270, and card column 220 is passed through
Wear two bar holes 270, positive stop has two and is respectively arranged at the two ends of card column 220, and two positive stops are located at respectively
The outside of two side plates 260.
Motor 130 is had multiple and is corresponded with multiple horns 120, and multiple motors 130 are respectively fixedly connected with multiple machines
Arm 120 is away from one end of fuselage 110.
Rotor 140 is had multiple and is corresponded with multiple motors 130, and multiple rotors 140 are respectively fixedly connected with multiple horses
Reach 130 rotating shaft, the direction of rotation of two neighboring rotor 140 is contrary.In order to balance what multiple rotor 140 rotations produced as far as possible
Torsion, in the present embodiment, the quantity of rotor 140 is even number.
Further, in the present embodiment, unmanned plane 100 also includes the rotation for ensureing motor 130 and rotor 140 stability
Wing mounting structure 300.With reference to Fig. 4, in the present embodiment, rotor mounting structure 300 is arranged at the one of the corresponding rotor 140 of horn 120
End, rotor mounting structure 300 includes four fixed plates 310 and an installing plate 320, and each fixed plate 310 is provided with breach,
One group two-by-two of four fixed plates 310, along the length direction interval setting of horn 120, two of same group solid for two groups of fixed plates 310
Fixed board 310 is connected with each other, the breach of same group of two fixed plates 310 mutually corresponding thus being formed and consolidating that horn 120 coordinates
Determine hole, installing plate 320 is fixedly connected on the side of two groups of fixed plates 310, motor 130 is fixedly connected on installing plate 320.
In order to improve the mounting stability of motor 130 and rotor 140 further, the outer wall of horn 120 is provided with two rings
Shape groove, the diapire of two cannelures is provided with projection, and the position of two fixing holes, two cannelures corresponding with horn 120 respectively is joined
Close, the both sides inwall of cannelure is respectively held against the both sides of fixed plate 310, thus effectively preventing whole motor 130 and rotor 140 edge
Horn 120 length direction moves；The inwall of two fixing holes is respectively arranged with the groove with two male cooperation, thus effectively anti-
Stop whole motor 130 and rotor 140 around the axial line rotation of horn 120.
Control system includes controller and angular-rate sensor, and controller is arranged at the center of fuselage 110, angular speed
Sensor is arranged at the edge of fuselage 110, and angular-rate sensor and multiple motor 130 are electrically connected with the controller respectively.
The purpose of setting angular-rate sensor is to detect at any time state in flight course for the unmanned plane 100, one
Female role velocity sensor detects unmanned plane 100 abnormal inclination and rotates, and will send an electric signal to controller,
Controller will control the running status of corresponding motor 130 after receiving above-said current signal, such as rotating speed and direction etc., thus change
Become the stress of fuselage 110 so that fuselage 110 gradually recovery level and stop the rotation it is ensured that whole unmanned plane 100 flight
Stability.
To sum up, this unmanned plane 100 includes fuselage 110, horn 120, motor 130, rotor 140, and horn 120 has multiple and one
End is connected to the edge of fuselage 110, and motor 130 is had multiple and corresponded with multiple horns 120,130 points of multiple motor
Be not fixedly connected on multiple horns 120 one end away from fuselage 110, rotor 140 have multiple and with a pair of multiple motors 130 1
Should, multiple rotors 140 are respectively fixedly connected with the rotating shaft of multiple motors 130, and the direction of rotation of two neighboring rotor 140 is contrary,
The torsion that the torsion that so rotation of each rotor 140 produces just can be rotated generation by adjacent rotor 140 is offset, and is protected with effective
Demonstrate,prove the steady of flight course middle fuselage 110, prevent fuselage 110 from abnormal inclination occurring or rotates, thus ensureing itself
Normal work, compensate for the defect of prior art.
The present embodiment additionally provides a kind of unmanned plane 100, the technique effect of its unitary construction, operation principle and acquirement with
Above-mentioned unmanned plane 100 is essentially identical, and difference is the concrete structure of foot rest 150.Specifically, the foot rest of this unmanned plane 100
150 include two supports being oppositely arranged, and each support all includes the first pole, the second pole and the 3rd pole, first
Bar and the second pole be arranged in parallel and equal one end is connected to fuselage 110, and the other end is connected to the 3rd pole, the 3rd pole parallel to
Fuselage 110.
These are only the preferred embodiments of the present invention, be not limited to the present invention, for those skilled in the art
For member, the present invention can have various modifications and variations.All any modifications within the spirit and principles in the present invention, made,
Equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of unmanned plane is it is characterised in that include fuselage, horn, motor, rotor, foot rest and control system, described horn
Multiple and one end is had to be connected to the edge of described fuselage, described motor is had multiple and corresponded with multiple described horns,
Multiple described motors are respectively fixedly connected with the one end in multiple described horns away from described fuselage, described rotor have multiple and with many
Individual described motor corresponds, and multiple described rotors are respectively fixedly connected with the rotating shaft of multiple described motors, two neighboring described
The direction of rotation of rotor is contrary, and described control system includes controller, and described controller is arranged at described fuselage, multiple described horses
Reach and electrically connect with described controller respectively.
2. unmanned plane according to claim 1 is it is characterised in that the quantity of described rotor is even number.
3. unmanned plane according to claim 1 is it is characterised in that described control system also includes angular-rate sensor, institute
State the edge that angular-rate sensor is arranged at described fuselage, described angular-rate sensor is connected with described controller.
4. unmanned plane according to claim 1 is it is characterised in that multiple described horn is away from the one of described motor accordingly
End is rotationally connected with described fuselage respectively, and unmanned plane is also included for making the described horn horn limit fixing with respect to described fuselage
Bit architecture.
5. unmanned plane according to claim 4 it is characterised in that described horn position limiting structure include fixture block, card column and
Spring, described fixture block is fixedly connected on described horn, and described fixture block includes planar portions and cambered surface portion, and described spring one end props up institute
State fuselage, the other end props up described card column, described card column is slidably connected to described fuselage and pushes down in the presence of described spring
Described planar portions.
6. unmanned plane according to claim 5 is it is characterised in that described horn position limiting structure includes base plate and spacing spiral shell
Bolt, described base plate is fixedly connected on described fuselage, and described caging bolt head props up the side away from described card column for the described base plate,
Stud portion passes through described base plate and be fixedly connected on described card column, described spring housing located at described stud portion and one end prop up described
Base plate, the other end props up described card column.
7. unmanned plane according to claim 5 is it is characterised in that described horn position limiting structure also includes side plate and limiting block
Block, described side plate has two and parallel interval is arranged at described fuselage, and two described side plates are respectively arranged with bar hole, described card
Post runs through two described bar holes, and described positive stop has two and is respectively arranged at the two ends of described card column, two described limits
Position block is located at the outside of two described side plates respectively.
8. unmanned plane according to claim 1 it is characterised in that unmanned plane also includes rotor mounting structure, install by rotor
In one end of the corresponding described rotor of described horn, described rotor mounting structure includes four fixed plates and an installation to structure setting
Plate, each described fixed plate is provided with breach, one group two-by-two of four described fixed plates, and described in two groups, fixed plate is along described horn
Length direction interval setting, same group of two described fixed plates are connected with each other, the lacking of same group of two described fixed plates
Mouth mutually corresponds to thus forming the fixing hole with described horn cooperation, and described installing plate is fixedly connected on fixed plate described in two groups
Side, described motor is fixedly connected on described installing plate.
9. unmanned plane according to claim 8 is it is characterised in that the outer wall of described horn is provided with two cannelures, and two
The diapire of individual described cannelure is provided with projection, two described fixing holes, two described cannelures corresponding with described horn respectively
Position coordinates, and the inwall of two described fixing holes is respectively arranged with the groove with two described male cooperation.
10. a kind of unmanned plane is it is characterised in that include fuselage, horn, motor, rotor, foot rest and control system, described machine
Arm has multiple and one end to be connected to the edge of described fuselage, described motor have multiple and with a pair of multiple described horn 1
Should, multiple described motors are respectively fixedly connected with the one end in multiple described horns away from described fuselage, described rotor have multiple and
Correspond with multiple described motors, multiple described rotors are respectively fixedly connected with the rotating shaft of multiple described motors, two neighboring
The direction of rotation of described rotor is contrary, and described control system includes controller, and described controller is arranged at described fuselage, Duo Gesuo
State motor to electrically connect with described controller respectively, described foot rest includes two supports being oppositely arranged, each described support all wraps
Include the first pole, the second pole and the 3rd pole, described first pole and described second pole be arranged in parallel and equal one end company
It is connected to described fuselage, the other end is connected to described 3rd pole, and described 3rd pole is parallel to described fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611115715.7A CN106394892B (en) | 2016-12-07 | 2016-12-07 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611115715.7A CN106394892B (en) | 2016-12-07 | 2016-12-07 | Unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN106394892A true CN106394892A (en) | 2017-02-15 |
| CN106394892B CN106394892B (en) | 2019-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611115715.7A Expired - Fee Related CN106394892B (en) | 2016-12-07 | 2016-12-07 | Unmanned plane |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177767A (en) * | 2017-12-04 | 2018-06-19 | 陈威巍 | A kind of multi-rotor unmanned aerial vehicle |
| CN108945393A (en) * | 2017-05-20 | 2018-12-07 | 珠海磐磊智能科技有限公司 | Multi-axis aircraft |
| CN109292083A (en) * | 2018-11-20 | 2019-02-01 | 南京森林警察学院 | A kind of anti-collision push-style rotor wing unmanned aerial vehicle |
| CN110040242A (en) * | 2019-03-15 | 2019-07-23 | 湖北文理学院 | Four axis unmanned planes of one kind and flight instruments |
| CN110466297A (en) * | 2018-10-25 | 2019-11-19 | 长城汽车股份有限公司 | A kind of hovercar and hovercar control method |
| WO2019227439A1 (en) * | 2018-05-31 | 2019-12-05 | 深圳市大疆创新科技有限公司 | Fuselage, vehicle arm, rotor assembly, airframe, and multi-rotor unmanned aerial vehicle |
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| US20120077607A1 (en) * | 2010-09-27 | 2012-03-29 | Eurocopter | Flexible coupling means |
| CN205022919U (en) * | 2015-08-14 | 2016-02-10 | 湖北易瓦特科技股份有限公司 | Stabilize formula aircraft equipment |
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| CN205168881U (en) * | 2015-10-30 | 2016-04-20 | 韩鹏飞 | Multiaxial flying machine |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108945393A (en) * | 2017-05-20 | 2018-12-07 | 珠海磐磊智能科技有限公司 | Multi-axis aircraft |
| CN108945393B (en) * | 2017-05-20 | 2022-05-13 | 珠海磐磊智能科技有限公司 | Multi-axis aircraft |
| CN108177767A (en) * | 2017-12-04 | 2018-06-19 | 陈威巍 | A kind of multi-rotor unmanned aerial vehicle |
| CN108177767B (en) * | 2017-12-04 | 2021-04-16 | 陈威巍 | Multi-rotor unmanned aerial vehicle |
| WO2019227439A1 (en) * | 2018-05-31 | 2019-12-05 | 深圳市大疆创新科技有限公司 | Fuselage, vehicle arm, rotor assembly, airframe, and multi-rotor unmanned aerial vehicle |
| CN110466297A (en) * | 2018-10-25 | 2019-11-19 | 长城汽车股份有限公司 | A kind of hovercar and hovercar control method |
| CN109292083A (en) * | 2018-11-20 | 2019-02-01 | 南京森林警察学院 | A kind of anti-collision push-style rotor wing unmanned aerial vehicle |
| CN109292083B (en) * | 2018-11-20 | 2023-09-12 | 南京森林警察学院 | Anticollision formula rotor unmanned aerial vehicle |
| CN110040242A (en) * | 2019-03-15 | 2019-07-23 | 湖北文理学院 | Four axis unmanned planes of one kind and flight instruments |
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