CN107021206A - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN107021206A CN107021206A CN201710234950.4A CN201710234950A CN107021206A CN 107021206 A CN107021206 A CN 107021206A CN 201710234950 A CN201710234950 A CN 201710234950A CN 107021206 A CN107021206 A CN 107021206A
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- CN
- China
- Prior art keywords
- connecting rod
- fuselage
- unmanned plane
- rotor
- motor
- 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.)
- Granted
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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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
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- 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 present invention proposes a kind of unmanned plane, and the unmanned plane includes fuselage, wing, the first power set and the second power set, and wing is arranged at the opposite sides of waist；Rotor before first power set include two, rotor is correspondingly arranged in the opposite sides of front fuselage respectively before two；Preceding rotor includes first connecting rod and the first drive component, and one end of first connecting rod is provided with the first drive component, other end connection fuselage；Rotor after second power set include two, rotor is correspondingly arranged in the opposite sides of back body respectively after two；Rotor includes second connecting rod and the second drive component afterwards, and one end of second connecting rod is provided with the second drive component, other end connection fuselage；First connecting rod and second connecting rod one of which rotated with fuselage be connected and can be along its axial-rotation, another one is connected with fuselage rotation and has folded state and extended configuration.Technical solution of the present invention improves the horizontal flight speed of unmanned plane.
Description
Technical field
The present invention relates to unmanned aerial vehicle design technical field, more particularly to a kind of unmanned plane.
Background technology
A pair of preceding rotors and a pair of rear rotors are provided with a kind of fuselage of existing unmanned plane.Wherein, unmanned plane is hanging down
Straight takeoff phase, preceding rotor is worked simultaneously with rear rotor, and the lift risen is provided for unmanned plane；Unmanned plane rises to certain altitude
When enter the transition flight stage, preceding rotor rotational to horizontal level, then rotor then gradually reduction rotating speed until be stopped；Nothing
Man-machine entrance level flight stage, now preceding rotor work on, the thrust of horizontal flight is provided for unmanned plane, then rotor stops
Only work.
Because unmanned plane enters after level flight stage, although rear rotor stopped work, but be still within stretch-like
State, so increases the air drag being subject to during unmanned plane during flying, therefore so the speed of unmanned plane horizontal flight is relatively low.
The content of the invention
The main object of the present invention is to provide a kind of unmanned plane, it is intended to reduce the air that unmanned plane is subject in horizontal flight
Resistance.
To achieve the above object, a kind of unmanned plane proposed by the present invention, the unmanned plane is moved including fuselage, wing, first
Power apparatus and the second power set；The wing is arranged at the opposite sides of the waist；The first power set bag
Rotor before including two, preceding rotor is correspondingly arranged in the opposite sides of the front fuselage respectively described in two；The preceding rotor includes the
One connecting rod and the first drive component, one end of the first connecting rod are provided with first drive component, and other end connection is described
Fuselage；Rotor after second power set include two, rear rotor is correspondingly arranged in the phase of the back body respectively described in two
To both sides；The rear rotor includes second connecting rod and the second drive component, and one end of the second connecting rod is provided with described second
Drive component, the other end connects the fuselage；The first connecting rod and the second connecting rod one of which are rotated with the fuselage
Connection and can along the connecting rod axial-rotation, another one and the fuselage, which are rotated, to be connected and has folded state and extended configuration.
It is preferred that, the second connecting rod is rotated with the fuselage to be connected and has folded state and extended configuration.
It is preferred that, second power set also include foldable base, drive device and connecting rod rocking arm, and the foldable base is fixed
In in the fuselage, rear rotor is rotationally connected with the foldable base respectively described in two；Driven with described one end of the connecting rod rocking arm
Dynamic device is flexibly connected, and the other end is flexibly connected with the second connecting rod；The drive device is to drive the connecting rod rocking arm
Moved along the length direction of the fuselage.
It is preferred that, the drive device includes screw mandrel, motor and sliding block, and the motor connects the screw mandrel
One end and the screw mandrel is axially rotated, the sliding block is socketed the screw mandrel and simultaneously coordinated with the wire rod thread, described
Connecting rod rocking arm is flexibly connected with the sliding block.
It is preferred that, the one end of the screw mandrel away from the motor rotates with the foldable base and is connected.
It is preferred that, the drive device includes expansion link and motor, and the motor connects the expansion link
One end and the expansion link is stretched in the length direction of the fuselage, the activity of the connecting rod rocking arm and the expansion link is even
Connect.
It is preferred that, the connecting rod rocking arm includes connecting portion and is arranged at two holding sections of described connecting portion one end, and described the
Two connecting rods are located between holding section described in two and are hinged with holding section described in two, the one end of the connecting portion away from the holding section
It is hinged with the drive device.
It is preferred that, chute along its length is offered on the second connecting rod；One end of the connecting rod rocking arm with it is described
Drive device is hinged, and the other end is provided with the projection being fastened in the chute.
It is preferred that, second drive component also includes rotor blade, and the rotor blade is twayblade
It is preferred that, the unmanned plane includes controller, and second drive component also includes external rotor electric machine and motor cabinet,
It is provided with the external rotor electric machine on a magnet, the motor cabinet and is provided with magnetic inductor, the magnetic inductor is to work as
When stating external rotor electric machine and driving the magnet to go to predeterminated position, control signal, the controller control are sent to the controller
Make the external rotor electric machine to stop operating, so that the rotor blade is parallel with the second connecting rod.
Technical solution of the present invention sets first power set and second power set on the fuselage of unmanned plane,
When the unmanned plane takes off vertically, first power set can provide for unmanned plane simultaneously with the second power rotary device
Lift needed for it；When the unmanned plane enters level flight stage, first power set are filled with second power
One of which is put rotatably and for the thrust needed for the unmanned plane provides horizontal flight, another one is then foldable to reduce nothing with this
The man-machine resistance being subject in horizontal flight, so as to improve the horizontal flight speed of unmanned plane.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, put in do not pay creative work first, may be used also
Other accompanying drawings are obtained with the structure according to these accompanying drawings.
A kind of top view for unmanned plane that Fig. 1 provides for the present invention；
Fig. 2 is schematic diagram of the unmanned plane shown in Fig. 1 in extended configuration；
Fig. 3 is schematic diagram of the unmanned plane shown in Fig. 1 in folded state；
Fig. 4 is schematic diagram of second power set in extended configuration in Fig. 1；
Fig. 5 is schematic diagram of second power set in folded state in Fig. 1.
Drawing reference numeral explanation：
| Label | Title | Label | Title |
| 10 | Fuselage | 20 | Wing |
| 30 | Preceding rotor | 31 | First connecting rod |
| 32 | First drive component | 40 | Rotor afterwards |
| 41 | Second connecting rod | 42 | Second drive component |
| 421 | Rotor blade | 422 | External rotor electric machine |
| 423 | Motor cabinet | 43 | Foldable base |
| 431 | Mounting groove | 44 | Drive device |
| 441 | Screw mandrel | 442 | Motor |
| 443 | Sliding block | 45 | Connecting rod rocking arm |
| 451 | Connecting portion | 452 | Holding section |
| 50 | Rotating shaft | 60 | Latch |
| 70 | Base |
The realization, functional characteristics and advantage of the object of the invention will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.Base
Embodiment in the present invention, those of ordinary skill in the art put obtained all not making creative work first
Other embodiment, belongs to the scope of protection of the invention.
It is to be appreciated that institute is directional in the embodiment of the present invention indicates (such as upper and lower, left and right, first, second ...)
Relative position relation, motion conditions for being only used for explaining under a certain particular pose (as shown in drawings) between each part etc., such as
When really the particular pose changes, then directionality indicates also correspondingly therewith to change.
In addition, the description for being related to " first ", " second " etc. in the present invention is only used for describing purpose, and it is not intended that referring to
Show or imply its relative importance or the implicit quantity for indicating indicated technical characteristic.Thus, " first ", " are defined
At least one this feature can be expressed or be implicitly included to two " feature.In addition, the technical scheme between each embodiment can
To be combined with each other, but must can be implemented as basis with those of ordinary skill in the art, when the combination of technical scheme occurs
It is conflicting or when can not realize it will be understood that the combination of this technical scheme is not present, also not in the protection model of application claims
Within enclosing.
The present invention proposes a kind of unmanned plane, can be used for border cruise, can be used for geological mapping, can be also used for
Express transportation.Usual unmanned plane includes fuselage, and the about medium position of the fuselage is provided with wing, the two of the fuselage head
Rotor before side is symmetrically arranged with two, rotor after the both sides of the afterbody are symmetrically arranged with two.Wherein, the preceding rotor and institute
Stating rear rotor includes the motor of two rotor blades and driving rotor blade rotation.
When the rotor blade of the preceding rotor dress and the rear rotor is rotated in horizontal plane, the rotor blade with it is mutual
Effect, which can produce a upward thrust, makes the unmanned plane vertical ascent.When the preceding rotor with it is described after rotor rotor leaf
Piece is when perpendicular is rotated, and the rotor blade can produce a thrust forward with interaction makes the unmanned plane level
Flight, and the upward active force required for now the unmanned plane maintains certain altitude flight is provided by the wing
's.
A kind of unmanned plane provided referring to figs. 1 to Fig. 3, the present invention, the unmanned plane has fuselage 10.The unmanned plane bag
Wing 20 is included, the wing 20 is arranged at the opposite sides at the middle part of fuselage 10.
In the present embodiment, the unmanned plane includes the first power set and the second power set.The first power dress
The lift needed for taking off vertically can be provided for the unmanned plane simultaneously with the second power rotary device by putting.When the unmanned plane liter
When entering level flight stage to certain altitude, first power set and the second power set one of which are nobody
Machine provides the thrust needed for horizontal flight, and another one is then foldable to be packed up, and the resistance that unmanned plane is subject to is reduced with this.
Rotor 30 before first power set include two, preceding rotor 30 is correspondingly arranged in the fuselage 10 respectively described in two
The opposite sides of front end.The preceding rotor 30 includes the drive component 32 of first connecting rod 31 and first, the one of the first connecting rod 31
End is provided with first drive component 32, and the other end connects the fuselage 10.
Rotor 40 after second power set include two, rear rotor 40 is correspondingly arranged in the fuselage 10 respectively described in two
The opposite sides of rear end.The rear rotor 40 includes the drive component 42 of second connecting rod 41 and second, the one of the second connecting rod 41
End is provided with second drive component 42, and the other end connects the fuselage 10.
The first connecting rod 31 and the one of which of the second connecting rod 41 rotated with the fuselage 10 be connected and can be along the company
The axial-rotation of bar, another one is rotated with the fuselage 10 to be connected and has folded state and extended configuration.
For example, the first connecting rod 31 and the fuselage 10 rotate be connected and can along the first connecting rod 31 axial-rotation,
The second connecting rod 41 is rotated with the fuselage 10 to be connected and has folded state and extended configuration.When the unmanned plane vertically rises
When flying, the first connecting rod 31 and the second connecting rod 41 are respectively positioned on horizontal direction, first rotor blade 321 and described the
Two rotor blades 421 are rotated in the horizontal plane, to provide the lift required for rising for the unmanned plane.
When the unmanned plane fly to certain altitude carry out horizontal flight when, the first connecting rod 31 along its axial-rotation to hang down
Nogata is to first rotor blade 321 is rotated in the vertical plane, needed for providing horizontal flight for the unmanned plane
The thrust wanted.Now, the second connecting rod 41 is then folded to the direction close to the fuselage 10, so substantially reduces unmanned plane
The resistance being subject in horizontal flight, is conducive to improving the speed of its horizontal flight.
Technical solution of the present invention sets first power set to be filled with second power on the fuselage 10 of unmanned plane
Put, when the unmanned plane takes off vertically, first power set and the second power rotary device can be unmanned plane simultaneously
Lift needed for it is provided；When the unmanned plane enters level flight stage, first power set are moved with described second
Power apparatus one of which is rotatably and for the thrust needed for the unmanned plane provides horizontal flight, and another one is then foldable to be subtracted with this
The resistance that small unmanned plane is subject in horizontal flight, so as to improve the horizontal flight speed of unmanned plane.
In a preferred embodiment, the first connecting rod 31 and the fuselage 10 rotate be connected and can be along the first connecting rod 31
Axial-rotation.
The second connecting rod 41 is rotated with the fuselage 10 to be connected and has folded state and extended configuration.Unmanned plane is forward
During flight, because first rotor blade 321 is located at the front of the wing 20, the wing 20 will not hinder flow direction described
The air draught of first rotor blade 321, so do not interfere with first rotor blade 321 interacts what is produced with air-flow
Thrust forward, so as to be more beneficial for improving the horizontal flight speed of the unmanned plane.
Refering to Fig. 4 and Fig. 5, second power set also include foldable base 43, drive device 44 and connecting rod Rocker arm 45.Institute
State foldable base 43 to be fixed in the fuselage 10, rear rotor 40 is rotationally connected with the foldable base 43 respectively described in two.The company
One end of bar Rocker arm 45 is flexibly connected with the drive device 44, and the other end is flexibly connected with the second connecting rod 41.Here, institute
Drive device 44 is stated to drive length direction of the connecting rod Rocker arm 45 along the fuselage 10 to move.
In the present embodiment, the foldable base 43 can be cube shape structure, and rear rotor 40 passes through rotating shaft respectively described in two
50 are connected to the left and right sides of the foldable base 43.Specifically, the left and right sides of the foldable base 43 offers mounting groove
431, one end of the second connecting rod 41 is in the mounting groove 431, and the rotating shaft 50 sequentially passes through the foldable base 43
The second connecting rod 41 is connected to the foldable base 43 by the lower surface of upper surface, the second connecting rod 41 and the foldable base 43
On, and the second connecting rod 41 can along the rotating shaft 50 axial rotation.
In other embodiments, the left and right sides of the foldable base 43 can be opened up respectively sets ten thousand in blind hole, the blind hole
To wheel, one end of the second connecting rod 41 is connected with the universal wheel and can rotated around the axis of the universal wheel.
In the present embodiment, the drive device 44 includes screw mandrel 441, motor 442 and sliding block 443.The driving
Motor 442 connects one end of the screw mandrel 441 and the screw mandrel 441 is axially rotated, and the sliding block 443 is socketed described
Screw mandrel 441 simultaneously coordinates with the screw thread of screw mandrel 441.The connecting rod Rocker arm 45 is flexibly connected with the sliding block 443.
The screw mandrel 441 is in the motor 442 when being rotated by, and the sliding block 443 is due to by its both sides
Connecting rod Rocker arm 45 holdback force and moved along the length direction of the fuselage 10, one end of the connecting rod Rocker arm 45 is driven with this
Moved along the length direction of the fuselage 10.
Specifically, the motor 442 is to be provided with shaft coupling, the silk on Servo-controller, the Servo-controller
One end of bar 441 rotates with the shaft coupling and is connected.The sliding block 443 offers in through hole, the through hole and is provided with ball spiral shell
Mother, the sliding block 443 is sheathed on the screw mandrel 441 by the through hole, is matched somebody with somebody by ball nut with the screw thread of screw mandrel 441
Close.
It is understood that the one end of the screw mandrel 441 away from the motor 442 can be rotated with the foldable base 43
Connection.It can so prevent the screw mandrel 441 from being teetertottered during rotation, be conducive to the sliding block 443 in institute
State and slided on screw mandrel 441, so as to be conducive to the folding of the second connecting rod 41.
In another embodiment, the drive device 44 may also include expansion link and motor, be stretched described in the motor connection
One end of contracting bar and the expansion link is stretched in the length direction of the fuselage 10, the connecting rod Rocker arm 45 with it is described flexible
Bar is flexibly connected.Here, motor can be arranged on the rear of the foldable base 43, the upper of the foldable base 43 can also be arranged on
Side.For example, when motor is arranged on the rear of the foldable base 43, the expansion link is located between the foldable base 43 and motor,
And one end of the expansion link coordinates with motor gear, when motor is rotated clockwise, the expansion link is moved backward, the motor inverse time
When pin is rotated, the expansion link travels forward.
In the present embodiment, the connecting rod Rocker arm 45 includes connecting portion 451 and is arranged at the two of described one end of connecting portion 451
Holding section 452.The second connecting rod 41 is located between holding section 452 described in two and is hinged with holding section described in two 452, the company
The one end of socket part 451 away from the holding section 452 is hinged with the drive device 44.
Inserted it should be noted that the one end of the connecting portion 451 away from the holding section 452 and the sliding block 443 pass through
Pin 60 is flexibly connected, and holding section 452 described in two is flexibly connected with the second connecting rod 41 also by latch 60.The connecting rod rocking arm
Length direction of 45 one end along the fuselage 10 is moved, and the second connecting rod 41 is driven to the side close to the fuselage 10 with this
To folding.
In other embodiments, chute along its length can be offered on the second connecting rod 41.The connecting rod shakes
One end of arm 45 is hinged with the drive device 44, and the other end is provided with the projection being fastened in the chute.Specifically, institute
The one end for stating connecting rod Rocker arm 45 is flexibly connected with the sliding block 443 by latch, and the other end is fastened in described by the projection
In chute.
Reference picture 5, second drive component 42 also includes rotor blade 421, and the rotor blade 421 is twayblade.
If it is understood that the rotor blade 421 be three blades or quaterfoil, it is described when the second connecting rod 41 is folded
Rotor blade 421 can be collided and be damaged with the fuselage 10, while can also hinder the folding of the second connecting rod 41.
The unmanned plane include controller (not shown), second drive component 42 also include external rotor electric machine 422 and
It is provided with motor cabinet 423, the external rotor electric machine 422 on a magnet, the motor cabinet 423 and is provided with magnetic inductor, it is described
Magnetic inductor to the controller when the external rotor electric machine 422 drives the magnet to go to predeterminated position, to send and control
Signal processed, the controller controls the external rotor electric machine 422 to stop operating, so that the rotor blade 421 and described second
The direction of connecting rod 41 is consistent.The direction of the rotor blade 421 and the second connecting rod 41 is consistent, and can prevent institute
The rotor blade 421 when second connecting rod 41 is folded is stated to collide with the fuselage 10.
It should be noted that above-mentioned predeterminated position can be the magnet position farthest apart from the magnetic inductor,
Can be the magnet position nearest apart from the magnetic inductor.The motor cabinet 423 is fixed, thus the magnetic
The position of inductor is immobilized, but the magnet is rotated with the rotation of the external rotor electric machine 422.When the magnet turns
To with the magnetic inductor it is closest or farthest when, the magnetic inductor sends control signal to the controller, the control
Device processed controls the external rotor electric machine 422 to stop operating so that the rotor blade 421 stops operating.
Reference picture 4 and Fig. 5, second power set also include being used to fix the foldable base 43 and the motor
442 base 70.The setting of the base 70, improves the second powerplant configuration stability.It is understood that institute
The base 70 can also be not provided with by stating the second power set, and the foldable base 43 is directly anchored to the motor 442
In the fuselage 10.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the scope of the invention, it is every at this
Under the inventive concept of invention, the equivalent structure transformation made using description of the invention and accompanying drawing content, or directly/use indirectly
It is included in other related technical fields in the scope of patent protection of the present invention.
Claims (10)
1. a kind of unmanned plane, with fuselage, it is characterised in that including：
Wing, the wing is arranged at the opposite sides of the fuselage；
First power set, including rotor before two, preceding rotor is correspondingly arranged in relative the two of the front fuselage respectively described in two
Side；The preceding rotor includes first connecting rod and the first drive component, and one end of the first connecting rod is provided with first driving
Component, the other end connects the fuselage；
Second power set, including rotor after two, rear rotor is correspondingly arranged in relative the two of the back body respectively described in two
Side；The rear rotor includes second connecting rod and the second drive component, and one end of the second connecting rod is provided with second driving
Component, the other end connects the fuselage；
The first connecting rod and the second connecting rod one of which are rotated with the fuselage to be connected and can be revolved along the axial direction of the connecting rod
Turn, another one is rotated with the fuselage to be connected and have folded state and extended configuration.
2. unmanned plane as claimed in claim 1, it is characterised in that the second connecting rod is rotated with the fuselage to be connected and have
Folded state and extended configuration.
3. unmanned plane as claimed in claim 2, it is characterised in that second power set also include foldable base, driving dress
Put and be fixed on connecting rod rocking arm, the foldable base in the fuselage, rear rotor is rotationally connected with the foldable base respectively described in two；
One end of the connecting rod rocking arm is flexibly connected with the drive device, and the other end is flexibly connected with the second connecting rod；It is described to drive
Dynamic device is to drive length direction of the connecting rod rocking arm along the fuselage to move.
4. unmanned plane as claimed in claim 3, it is characterised in that the drive device includes screw mandrel, motor and sliding block,
One end of screw mandrel described in the motor connection and the screw mandrel is axially rotated, the sliding block be socketed the screw mandrel and with
The wire rod thread coordinates, and the connecting rod rocking arm is flexibly connected with the sliding block.
5. unmanned plane as claimed in claim 4, it is characterised in that the one end of the screw mandrel away from the motor with it is described
Foldable base rotates connection.
6. unmanned plane as claimed in claim 3, it is characterised in that the drive device includes expansion link and motor, institute
State motor to connect one end of the expansion link and make the expansion link to stretch in the length direction of the fuselage, the company
Bar rocking arm is flexibly connected with the expansion link.
7. the unmanned plane as described in any one of claim 3 to 6, it is characterised in that the connecting rod rocking arm includes connecting portion and set
Be placed in two holding sections of described connecting portion one end, the second connecting rod be located between holding section described in two and with holding section described in two
It is hinged, the one end of the connecting portion away from the holding section is hinged with the drive device.
8. the unmanned plane as described in any one of claim 3 to 6, it is characterised in that offered on the second connecting rod along length
The chute in direction；One end of the connecting rod rocking arm is hinged with the drive device, and the other end, which is provided with, to be fastened in the chute
Projection.
9. unmanned plane as claimed in claim 2, it is characterised in that second drive component also includes rotor blade, described
Rotor blade is twayblade.
10. unmanned plane as claimed in claim 9, it is characterised in that the unmanned plane includes controller, second driving group
Part also includes being provided with a magnet, the motor cabinet on external rotor electric machine and motor cabinet, the external rotor electric machine being provided with magnetic
Inductor, the magnetic inductor is to when the external rotor electric machine drives the magnet to go to predeterminated position, to the control
Device sends control signal, and the controller controls the external rotor electric machine to stop operating, so that the rotor blade and described the
Two connecting rods are parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710234950.4A CN107021206B (en) | 2017-04-11 | 2017-04-11 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710234950.4A CN107021206B (en) | 2017-04-11 | 2017-04-11 | Unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107021206A true CN107021206A (en) | 2017-08-08 |
| CN107021206B CN107021206B (en) | 2020-06-19 |
Family
ID=59526785
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710234950.4A Active CN107021206B (en) | 2017-04-11 | 2017-04-11 | Unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107021206B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107745811A (en) * | 2017-10-21 | 2018-03-02 | 雷安静 | A kind of VTOL becomes rotor wing unmanned aerial vehicle |
| CN108438204A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
| CN108495786A (en) * | 2017-08-31 | 2018-09-04 | 深圳市大疆创新科技有限公司 | The deformation rack and aircraft of aircraft |
| CN108883823A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Horn locking mechanism and aircraft |
| CN109018331A (en) * | 2018-09-10 | 2018-12-18 | 观典防务技术股份有限公司 | It is capable of the VTOL fixed-wing unmanned plane of folding and unfolding rotor when a kind of cruise |
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| RU2724006C1 (en) * | 2018-07-04 | 2020-06-18 | Др. Инг. Х.Ц.Ф. Порше Акциенгезелльшафт | Aircraft |
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| CN114013625A (en) * | 2021-11-17 | 2022-02-08 | 中山福昆航空科技有限公司 | Can dismantle fixed wing unmanned aerial vehicle |
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| WO2022099373A1 (en) * | 2020-11-13 | 2022-05-19 | Innovaero Technologies Pty Ltd | Aerial vehicles |
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| WO2022225421A1 (en) * | 2021-04-20 | 2022-10-27 | Общество С Ограниченной Ответственностью "Научно-Производственное Объединение Имени Петрова В.А." | Vertical take-off and landing aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1212238B1 (en) * | 1999-09-14 | 2003-11-26 | Eurocopter | Improvements to convertible aircraft with tilting rotors |
| US20100072325A1 (en) * | 2008-01-22 | 2010-03-25 | Kenneth William Sambell | Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft |
| WO2011066004A2 (en) * | 2009-08-19 | 2011-06-03 | Seiford Donald S | Convertible vehicle for road, air, and water usage |
| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN205098475U (en) * | 2015-11-11 | 2016-03-23 | 深圳智航无人机有限公司 | Vertical take -off and landing aircraft |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
-
2017
- 2017-04-11 CN CN201710234950.4A patent/CN107021206B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1212238B1 (en) * | 1999-09-14 | 2003-11-26 | Eurocopter | Improvements to convertible aircraft with tilting rotors |
| US20100072325A1 (en) * | 2008-01-22 | 2010-03-25 | Kenneth William Sambell | Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft |
| WO2011066004A2 (en) * | 2009-08-19 | 2011-06-03 | Seiford Donald S | Convertible vehicle for road, air, and water usage |
| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN205098475U (en) * | 2015-11-11 | 2016-03-23 | 深圳智航无人机有限公司 | Vertical take -off and landing aircraft |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
Cited By (23)
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| CN108495786A (en) * | 2017-08-31 | 2018-09-04 | 深圳市大疆创新科技有限公司 | The deformation rack and aircraft of aircraft |
| CN108883823A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Horn locking mechanism and aircraft |
| CN108883823B (en) * | 2017-08-31 | 2022-04-08 | 深圳市大疆创新科技有限公司 | Aircraft arm locking mechanical system and aircraft |
| CN108495786B (en) * | 2017-08-31 | 2022-01-28 | 深圳市大疆创新科技有限公司 | Deformation frame of aircraft and aircraft |
| CN107745811A (en) * | 2017-10-21 | 2018-03-02 | 雷安静 | A kind of VTOL becomes rotor wing unmanned aerial vehicle |
| CN108438204A (en) * | 2018-05-21 | 2018-08-24 | 中宇航通（北京）科技有限公司 | Vertical take-off and landing drone rotor foldable structure and its folding and method of deploying |
| US11358714B2 (en) | 2018-07-04 | 2022-06-14 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft |
| RU2724006C1 (en) * | 2018-07-04 | 2020-06-18 | Др. Инг. Х.Ц.Ф. Порше Акциенгезелльшафт | Aircraft |
| CN109018331A (en) * | 2018-09-10 | 2018-12-18 | 观典防务技术股份有限公司 | It is capable of the VTOL fixed-wing unmanned plane of folding and unfolding rotor when a kind of cruise |
| CN109260721B (en) * | 2018-11-08 | 2021-05-14 | 重庆大学 | Model rocket that fixed point was descended |
| CN109260721A (en) * | 2018-11-08 | 2019-01-25 | 重庆大学 | A kind of model rocket of pinpoint landing |
| WO2020122759A1 (en) * | 2018-12-14 | 2020-06-18 | Эллина Владимировна ЗИМЕНСКАЯ | Vertical take-off and landing aircraft |
| RU2700154C1 (en) * | 2018-12-14 | 2019-09-12 | Общество с ограниченной ответственностью "Техноветер" | Vertical take-off and landing aircraft |
| WO2021177862A1 (en) * | 2020-03-05 | 2021-09-10 | Общество С Ограниченной Ответственностью "Авиастроительная Компания "Техноветер" | Vertical take-off and landing aircraft |
| RU2738746C1 (en) * | 2020-03-05 | 2020-12-16 | Эллина Владимировна Зименская | Vertical take-off and landing aircraft |
| EP4244133A4 (en) * | 2020-11-13 | 2024-04-10 | Innovaero Technologies Pty Ltd | Aerial vehicles |
| WO2022099373A1 (en) * | 2020-11-13 | 2022-05-19 | Innovaero Technologies Pty Ltd | Aerial vehicles |
| WO2022225421A1 (en) * | 2021-04-20 | 2022-10-27 | Общество С Ограниченной Ответственностью "Научно-Производственное Объединение Имени Петрова В.А." | Vertical take-off and landing aircraft |
| CN114013625A (en) * | 2021-11-17 | 2022-02-08 | 中山福昆航空科技有限公司 | Can dismantle fixed wing unmanned aerial vehicle |
| CN114013625B (en) * | 2021-11-17 | 2024-05-31 | 中山福昆航空科技有限公司 | Can dismantle fixed wing unmanned aerial vehicle |
| CN114465065A (en) * | 2022-01-06 | 2022-05-10 | 广东汇天航空航天科技有限公司 | Aircraft main shaft slip ring device, aircraft rotor system and aircraft |
| CN114465065B (en) * | 2022-01-06 | 2023-11-03 | 广东汇天航空航天科技有限公司 | Aircraft main shaft slip ring device, aircraft rotor system and aircraft |
| CN114571931A (en) * | 2022-04-24 | 2022-06-03 | 浙江大学 | Amphibious unmanned aerial vehicle |
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