CN106672230A - Ducted unmanned aerial vehicle - Google Patents
Ducted unmanned aerial vehicle Download PDFInfo
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- CN106672230A CN106672230A CN201611114275.3A CN201611114275A CN106672230A CN 106672230 A CN106672230 A CN 106672230A CN 201611114275 A CN201611114275 A CN 201611114275A CN 106672230 A CN106672230 A CN 106672230A
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- 238000001514 detection method Methods 0.000 claims description 16
- 230000005611 electricity Effects 0.000 claims description 15
- 238000004891 communication Methods 0.000 claims description 11
- 239000000446 fuel Substances 0.000 claims description 9
- 230000006698 induction Effects 0.000 claims description 7
- 238000001914 filtration Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 2
- 230000008859 change Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 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 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000005856 abnormality Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 210000004247 hand Anatomy 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64U30/26—Ducted or shrouded rotors
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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
- B64U50/11—Propulsion using internal combustion piston engines
-
- 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
- B64U50/30—Supply or distribution of electrical power
- B64U50/37—Charging when not in flight
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Toys (AREA)
Abstract
The embodiment of the invention discloses a ducted unmanned aerial vehicle, which comprises a main body (9), a first duct (1), a second duct (2), a third duct (3), a fourth duct (4), a front landing gear and a rear landing gear, wherein the first duct (1) is connected with the first side of the main body (9); the second duct (2) is connected with the second side of the main body (9); the third duct (3) is connected with the third side of the main body (9); the fourth duct (4) is connected with the fourth side of the main body (9); the front landing gear is arranged below the head of the main body (9), and the rear landing gear is arranged below the tail of the main body (9); each of the first duct (1), the second duct (2), the third duct (3) and the fourth duct (4) is internally provided with a paddle and an engine for driving the paddle to rotate. The unmanned aerial vehicle is flexible in flight, high in safety, convenient to operate and long in flight duration.
Description
Technical field
The present invention relates to unmanned plane field, more particularly to a kind of culvert type unmanned plane.
Background technology
In recent years, unmanned plane is more and more extensive because the technical characterstic of its distinctness is all obtained in military and civilian field
Using and develop rapidly, especially agricultural plant protection, military surveillance, environmental abnormality detection, disaster relief and rescue, electric inspection process, mapping with
The field such as model, take photo by plane, entertaining and there is extensive demand, it represents an important development direction of following airborne vehicle, especially
It is over nearly 5 years, to have emerged the small-sized multi-axis rotor wing unmanned aerial vehicle of many bright characteristics.
In recent years multi-rotor unmanned aerial vehicle especially prevailing has larger potential safety hazard, and the normal someone of Jing is because misoperation
Or it is unskilled, injured or even disabled by the propeller of multi-rotor unmanned aerial vehicle；Simultaneously the motivation package system of propeller occupies many
The most space of rotor wing unmanned aerial vehicle so that multi-rotor unmanned aerial vehicle carrying platform area is little；At the same time multi-rotor unmanned aerial vehicle because
The speed that its architectural characteristic causes it to fly receives a definite limitation.In addition, rotary wind type unmanned plane is boisterous by strong wind etc.
Affect larger, the electricity of consumption is more.
The content of the invention
A kind of culvert type unmanned plane is embodiments provided, flexible, easy to operate, cruising time of flying is long.
A kind of culvert type unmanned plane is embodiments provided, the unmanned plane includes：
Fuselage main body (9), the first duct (1), the second duct (2), the 3rd duct (3), the 4th duct (4), nose-gear
And rear undercarriage；
First duct (1) is connected with the first side of the fuselage main body (9)；
Second duct (2) is connected with the second side of the fuselage main body (9)；
3rd duct (3) is connected with the 3rd side of the fuselage main body (9)；
4th duct (4) is connected with the 4th side of the fuselage main body (9)；Wherein, first duct (1) and institute
State the 3rd duct (3) to be symmetrical arranged relative to the fuselage main body (9), second duct (2) and the 4th duct (4) phase
For the fuselage main body (9) is symmetrical arranged；
The nose-gear is arranged on the lower head of the fuselage main body (9), and the rear undercarriage is arranged on the machine
The afterbody lower section of body main body (9)；
First duct (1), second duct (2), the 3rd duct (3) and the 4th duct (4) it is interior
The electromotor that portion is provided with blade and drives the blade to rotate.
In an optional implementation, first duct (1) is by the first duct direction controlling steering wheel (5) and institute
The first side for stating fuselage main body (9) rotates connection；
Second duct (2) is turned by the second duct direction controlling steering wheel (6) with the second side of the fuselage main body (9)
Dynamic connection；
3rd duct (3) is turned by the 3rd duct direction controlling steering wheel (7) with the 3rd side of the fuselage main body (9)
Dynamic connection；
4th duct (4) is turned by the 4th duct direction controlling steering wheel (8) with the 4th side of the fuselage main body (9)
Dynamic connection.
In an optional implementation, the first duct direction controlling steering wheel (5) by the first steering wheel with it is described
First side of fuselage main body (9) rotates connection；
The second duct direction controlling steering wheel (6) is rotated by the second steering wheel with the second side of the fuselage main body (9)
Connection；
3rd duct direction controlling steering wheel (7) is rotated by the 3rd steering wheel with the 3rd side of the fuselage main body (9)
Connection；
4th duct direction controlling steering wheel (8) is rotated by the 4th steering wheel with the 4th side of the fuselage main body (9)
Connection.
In an optional implementation, first duct (1), second duct (2), the 3rd duct
(3) and the 4th duct (4) is identical and duct internal diameter with the ratio of duct width in the range of 1.4-1.6, oar disk exists
At duct entrance 1/3rd, duct outlet diameter is with duct internal diameter ratio in the range of 1.1-1.2.
In an optional implementation, first duct (1), second duct (2), the 3rd duct
And the 4th duct (4) is identical and the duct internal diameter and the ratio of the duct width is 1.5, the duct (3)
Outlet diameter is 1.15 with the duct internal diameter ratio.
In an optional implementation, the unmanned plane also includes：The distribution of fuel engines, electromotor and power
Device；
The fuel engines, electromotor are connected respectively with the distributing means for power supply；
Power produced by the fuel engines is converted to the distributing means for power supply power for driving the blade
With the power for driving the electromotor.
In an optional implementation, the battery is rechargeable battery；
The battery is charged by wireless charging device；
Or, it is charged after the rectified filtering of alternating current of the battery by produced by electromotor.
In an optional implementation, the wireless charging device includes：Receiving coil and receiver module circuit；
The receiving coil and receiver module circuit are electrically connected with；
The receiving coil, for the electric current produced by induction field to be imported into the receiver module circuit；
The receiver module circuit, for after the electric current to be adjusted to the electric current for meeting the battery charge requirement,
The battery is charged.
In an optional implementation, the unmanned plane also includes：Controller；
It is the controller and the first duct direction controlling steering wheel and the first electromotor of first duct (1), described
Second duct direction controlling steering wheel of the second duct (2) and the second electromotor, the 3rd duct direction of the 3rd duct (3)
Control steering wheel and trimotor, the 4th duct direction controlling steering wheel of the 4th duct (4) and the 4th electromotor, institute
State undercarriage steering-engine to electrically connect；
The controller is by control first electromotor, second electromotor, the trimotor and described
The rotating speed of the 4th electromotor and first duct (1), second duct (2), the 3rd duct (3) and the described 4th
Flight of the direction of duct (4) to unmanned plane is controlled.
In an optional implementation, the unmanned plane also includes electric power detection module and wireless communication module；
The electric power detection module is electrically connected with respectively with the controller and the battery, the wireless communication module with
The controller is electrically connected with；
The electric power detection module, for the electric quantity data of the battery for detecting to be sent to into the controller；
The controller, for determining the electricity according to the electric quantity data for determining the electric power detection module transmission
The electricity in pond sends not enough power supply instruction, the electricity by the wireless communication module less than after preset value to control device
Deficiency instruction indicates that the electricity of unmanned plane is less than the preset value.
As can be seen from the above technical solutions, the embodiment of the present invention has advantages below：Duct in the embodiment of the present invention
Formula unmanned plane includes four ducts for being located at the unmanned plane not homonymy, is by described four ducts for being located at the unmanned plane not homonymy
The unmanned plane provides the adjustment of power and travel direction, it is to avoid the propeller of peripheral hardware may to it is artificial into injury, also cause
The flight of the unmanned plane is more flexible, and user's is more convenient to operate.The unmanned plane is using oil electric mixed dynamic or configuration nothing
Line charging device, enhances endurance.
Description of the drawings
Technical scheme in order to be illustrated more clearly that the embodiment of the present invention, below will be to making needed for embodiment description
Accompanying drawing is briefly introduced, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for this
For the those of ordinary skill in field, without having to pay creative labor, can be obtaining it according to these accompanying drawings
His accompanying drawing.
Fig. 1 is embodiment of the present invention culvert type unmanned plane structural representation；
Fig. 2 is the structural representation of embodiment of the present invention culvert type unmanned plane dynamical system；
Fig. 3 is the structural representation of embodiment of the present invention wireless charging receiver；
Fig. 4 is the structural representation of embodiment of the present invention receiver module circuit；
Fig. 5 is embodiment of the present invention culvert type unmanned plane structural representation.
Specific embodiment
In order that the object, technical solutions and advantages of the present invention are clearer, below in conjunction with accompanying drawing the present invention is made into
One step ground is described in detail, it is clear that described embodiment is only present invention some embodiments, rather than the enforcement of whole
Example.Based on the embodiment in the present invention, what those of ordinary skill in the art were obtained under the premise of creative work is not made
All other embodiment, belongs to the scope of protection of the invention.
Fig. 1 is referred to, Fig. 1 is a kind of structural representation of culvert type unmanned plane provided in an embodiment of the present invention.Such as Fig. 1 institutes
Show, the unmanned plane includes：Fuselage main body (9), the first duct (1), the second duct (2), the 3rd duct (3), the 4th duct (4),
Nose-gear and rear undercarriage；
Above-mentioned first duct (1) is connected with the first side of above-mentioned fuselage main body (9)；
Above-mentioned second duct (2) is connected with the second side of above-mentioned fuselage main body (9)；
Above-mentioned 3rd duct (3) is connected with the 3rd side of above-mentioned fuselage main body (9)；
Above-mentioned 4th duct (4) is connected with the 4th side of above-mentioned fuselage main body (9)；Wherein, above-mentioned first duct (1) and upper
State the 3rd duct (3) to be symmetrical arranged relative to above-mentioned fuselage main body (9), above-mentioned second duct (2) and above-mentioned 4th duct (4) phase
For above-mentioned fuselage main body (9) is symmetrical arranged；
Above-mentioned nose-gear is arranged on the lower head of above-mentioned fuselage main body (9), and above-mentioned rear undercarriage is arranged on above-mentioned machine
The afterbody lower section of body main body (9)；
Above-mentioned first duct (1), above-mentioned second duct (2), above-mentioned 3rd duct (3) and above-mentioned 4th duct (4) it is interior
The electromotor that portion is provided with blade and drives above-mentioned blade to rotate.
Above-mentioned fuselage main body can be different shapes, such as positive direction, rectangle, hexagon, circle etc..Above-mentioned first
Duct (1), above-mentioned second duct (2), above-mentioned 4th duct (4) specification of above-mentioned 3rd duct (3) are identical, it is believed that be identical
Duct.Above-mentioned first duct, above-mentioned second duct, above-mentioned 3rd duct, above-mentioned 4th duct provide power for the unmanned plane
With the flight for controlling the unmanned plane.Above-mentioned unmanned plane can provide power using fuel oil transmitter for above-mentioned blade.Rise before above-mentioned
Fall frame and rear undercarriage is connected respectively with corresponding steering-engine, it is ensured that the normal takeoff and landing of the unmanned plane.Above-mentioned first
Duct, above-mentioned second duct, above-mentioned 3rd duct, above-mentioned 4th duct are uniformly controlled by the controller of the unmanned plane, are passed through
Coordinate and control the rotating speed of the blade of above-mentioned each duct and control the unmanned plane by controlling the rotation of above-mentioned each steering wheel
Flight.
In the embodiment of the present invention, unmanned plane has main duct to provide the major impetus for rising, and four auxiliary ducts control this nobody
The direction of machine, flies more flexible.
The embodiment of the present invention is on the basis of front embodiment, there is provided the duct of unmanned plane and the connected mode of steering wheel, tool
Body is as follows：Above-mentioned first duct (1) is turned by the first duct direction controlling steering wheel (5) with the first side of above-mentioned fuselage main body (9)
Dynamic connection；
Above-mentioned second duct (2) is turned by the second duct direction controlling steering wheel (6) with the second side of above-mentioned fuselage main body (9)
Dynamic connection；
Above-mentioned 3rd duct (3) is turned by the 3rd duct direction controlling steering wheel (7) with the 3rd side of above-mentioned fuselage main body (9)
Dynamic connection；
Above-mentioned 4th duct (4) is turned by the 4th duct direction controlling steering wheel (8) with the 4th side of above-mentioned fuselage main body (9)
Dynamic connection.
Above-mentioned first duct direction controlling steering wheel, above-mentioned second duct direction controlling steering wheel, the control of above-mentioned 3rd duct direction
Steering wheel processed, above-mentioned 4th duct direction controlling steering wheel are connected respectively by rotating shaft with corresponding duct.Controller noted above is by control
That makes above-mentioned all directions control steering wheel rotates the direction that can just control corresponding duct.For example by the direction of four auxiliary ducts all
Dead ahead is gone to, the unmanned plane will be flown with maximum speed to dead ahead.
In the embodiment of the present invention, each duct can easily change direction and angle, and then easily change unmanned plane
State of flight.
The embodiment of the present invention is on the basis of front embodiment, there is provided all directions control steering wheel and the fuselage master of unmanned plane
The connected mode of body, it is specific as follows：
Above-mentioned first duct direction controlling steering wheel (5) is rotated by the first steering wheel with the first side of above-mentioned fuselage main body (9)
Connection；
Above-mentioned second duct direction controlling steering wheel (6) is rotated by the second steering wheel with the second side of above-mentioned fuselage main body (9)
Connection；
Above-mentioned 3rd duct direction controlling steering wheel (7) is rotated by the 3rd steering wheel with the 3rd side of above-mentioned fuselage main body (9)
Connection；
Above-mentioned 4th duct direction controlling steering wheel (8) is rotated by the 4th steering wheel with the 4th side of above-mentioned fuselage main body (9)
Connection.
In the embodiment of the present invention, each duct is rotated with the corresponding side of above-mentioned fuselage main body by corresponding steering wheel and is connected,
So that above-mentioned each duct can change bigger angle.
In the embodiment of the present invention, above-mentioned first duct (1), above-mentioned second duct (2), above-mentioned 3rd duct (3) are limited
With the specification of above-mentioned 4th duct (4), it is specific as follows：Above-mentioned first duct (1), above-mentioned second duct (2), above-mentioned 3rd duct
(3) and above-mentioned 4th duct (4) is identical and duct internal diameter with the ratio of duct width in the range of 1.4-1.6, oar disk exists
At duct entrance 1/3rd, duct outlet diameter is with duct internal diameter ratio in the range of 1.1-1.2.
Impact of the different duct of specification to unmanned plane performance is very big, and the duct in this enforcement at identical conditions can be with
More power are provided for unmanned plane.For example, when the duct internal diameter of above-mentioned duct and the ratio of duct width are in 1.4-1.6
In the range of can provide more climbing powers for the unmanned plane.When the duct outlet diameter of above-mentioned duct exists with duct internal diameter ratio
In the range of 1.1-1.2, the duct lift of above-mentioned duct is bigger.
Duct in the embodiment of the present invention, can provide more power with unmanned plane.
It is specific as follows in the embodiment of the present invention, it is proposed that a kind of specific duct：Above-mentioned first duct (1), above-mentioned second
Duct (2), above-mentioned 3rd duct (3) and above-mentioned 4th duct (4) are identical and above-mentioned duct internal diameter and above-mentioned duct width
Ratio be 1.5, above-mentioned duct outlet diameter is 1.15 with above-mentioned duct internal diameter ratio.
Through Theoretical Calculation and actual experiment, it is determined that the performance for possessing the duct of above-mentioned parameter is more preferable.
It is specific as follows in the embodiment of the present invention, it is proposed that a kind of method for providing power for blade：As shown in Fig. 2 above-mentioned
Unmanned plane also includes：Fuel engines 201, electromotor 203 and distributing means for power supply 202；
Above-mentioned fuel engines 201, above-mentioned electromotor 203 are connected respectively with above-mentioned distributing means for power supply 202；
Power produced by above-mentioned fuel engines is converted to above-mentioned distributing means for power supply the power for driving above-mentioned blade
With the power for driving above-mentioned electromotor.
Above-mentioned electromotor drives above-mentioned blade to be rotated.Flight shape of the above-mentioned distributing means for power supply according to above-mentioned unmanned plane
The electricity of condition and above-mentioned battery enters the distribution of action edge.The electricity that above-mentioned electromotor is provided can be charged to above-mentioned battery.
When the electricity of above-mentioned battery is sufficient, more power are distributed to into above-mentioned blade, when the not enough power supply of above-mentioned battery, be on
State blade and more power are provided.
In the embodiment of the present invention, the number of times changed battery and be charged to above-mentioned battery can be efficiently reduced.
In the embodiment of the present invention, above-mentioned battery is rechargeable battery；
Above-mentioned battery is charged by wireless charging device；
Or, it is charged after the rectified filtering of alternating current of the above-mentioned battery by produced by electromotor.
Can be reduced using rechargeable battery and change the inconvenience that battery brings.
In the embodiment of the present invention, wireless charging can be carried out for unmanned plane by wireless charging device, as shown in figure 3, above-mentioned
Wireless charging device includes：Receiving coil 301 and receiver module circuit 302；
Above-mentioned receiving coil 301 and receiver module circuit 302 are electrically connected with；
Above-mentioned receiving coil 301, for the electric current produced by induction field to be imported into above-mentioned receiver module circuit；
Above-mentioned receiver module circuit 302, for above-mentioned electric current to be adjusted to the electric current for meeting above-mentioned battery charge requirement
Afterwards, above-mentioned battery is charged.
Above-mentioned receiving coil can produce electric current with induction field, and the electric current for producing is imported into above-mentioned receiver module electricity
Road.After above-mentioned receiver module circuit is processed in the circuit for receiving, above-mentioned battery is charged.Above-mentioned wireless charging connects
At least one in being supported induction charging, magnetic resonance charging, radio waves type to charge by device.For example, on
Stating wireless charging receiving device can be with integrated induction charging and magnetic resonance two kinds of wireless charging mode of charging.Two kinds of nothings
Line charging device can respectively occupy a part for above-mentioned wireless charging receiving device, and above-mentioned wireless charging receiving device can also
Concentrate and support various wireless charging modes.Above-mentioned wireless charging receiving device can be selected according to the charging modes of wireless charging device
Select suitable wireless charging mode.As shown in figure 4, above-mentioned receiver module circuit can include reduction voltage circuit 401, rectification circuit
402 and charging control circuit 403.Above-mentioned receiving coil induction field is produced after electric current, is dropped by above-mentioned reduction voltage circuit 401
Pressure, and rectification is carried out by rectification circuit 402, finally above-mentioned battery is charged by charging control circuit 403.
It is specific as follows in the embodiment of the present invention, there is provided the flight control method of unmanned plane：Above-mentioned unmanned plane also includes：
Controller；
It is controller noted above and the first duct direction controlling steering wheel and the first electromotor of above-mentioned first duct (1), above-mentioned
Second duct direction controlling steering wheel of the second duct (2) and the second electromotor, the 3rd duct direction of above-mentioned 3rd duct (3)
Control steering wheel and trimotor, the 4th duct direction controlling steering wheel of above-mentioned 4th duct (4) and the 4th electromotor, on
State undercarriage steering-engine to electrically connect；
Controller noted above is by above-mentioned first electromotor of control, above-mentioned second electromotor, above-mentioned trimotor and above-mentioned
The rotating speed of the 4th electromotor and above-mentioned first duct (1), above-mentioned second duct (2), above-mentioned 3rd duct (3) and the above-mentioned 4th
Flight of the direction of duct (4) to unmanned plane is controlled.
Above-mentioned transmitter is arranged on inside corresponding duct, drives corresponding blade to rotate.Controller noted above is by control
Above-mentioned each steering wheel direction for rotating and then the direction for changing corresponding each duct, by the rotational speed regulation for controlling above-mentioned blade
Each torque, is realized that the flight to unmanned plane is controlled.
It is specific as follows in the embodiment of the present invention, there is provided the method for detection battery electric quantity：As shown in figure 5, above-mentioned unmanned plane
Also include：Electric power detection module 502 and wireless communication module 503；
Above-mentioned electric power detection module 502 is electrically connected with respectively with controller noted above 501 and above-mentioned battery 504, above-mentioned wireless
Communication module 503 is electrically connected with controller noted above 501；
Above-mentioned electric power detection module 502, for the electric quantity data of the above-mentioned battery 504 for detecting to be sent to into above-mentioned control
Device；
Controller noted above 501, it is above-mentioned for determining in the above-mentioned electric quantity data sent according to above-mentioned electric power detection module 502
The electricity of battery 504 sends not enough power supply instruction by above-mentioned wireless communication module 503 less than after preset value to control device,
Above-mentioned not enough power supply instruction indicates that the electricity of unmanned plane is less than above-mentioned preset value.
For example the processor can detect the surplus of above-mentioned battery with the above-mentioned electric power detection module of regular hour periodic notification
Remaining electricity, and whether preset value is less than according to above-mentioned dump energy.Above-mentioned control device can be the control for controlling above-mentioned unmanned plane
Device processed, or other terminals such as mobile phone, wearable device etc. of the unmanned plane binding.For example, when above-mentioned processor
When determining the not enough power supply of above-mentioned battery, warning message, above-mentioned handss are sent to the mobile phone of user by above-mentioned wireless communication module
Machine is bound by specific application with the mobile phone.
In the embodiment of the present invention, the electricity of battery is detected by electric power detection module, and sent by wireless communication module
To corresponding control device, user can be pointed out to be charged in time.
In the present embodiment, above-mentioned unmanned plane can have binding relationship with terminal unit.Above-mentioned terminal unit such as mobile phone,
Panel computer, desktop computer etc. can be bound by specific application with above-mentioned unmanned plane, above-mentioned terminal unit after binding
Various instructions, such as charging instruction, climb command, decline instruction can be sent to above-mentioned unmanned plane.Climb command can be indicated
The unmanned plane flies upwards.Decline instruction and indicate that the unmanned plane flies downwards.Controller noted above can control the wireless telecommunications mould
Block sends dump energy information, elevation information and the coordinate information of above-mentioned unmanned plane to above-mentioned terminal unit.Above-mentioned terminal unit
The information of the server active obtaining unmanned plane can be passed through, it is also possible to send to the unmanned plane by the server and refer to accordingly
Order.
The present invention preferably specific embodiment is these are only, but protection scope of the present invention is not limited thereto, it is any
Those familiar with the art the change that can readily occur in or replaces in the technical scope that the embodiment of the present invention is disclosed
Change, all should be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of claim
Enclose and be defined.
Claims (10)
1. a kind of culvert type unmanned plane, it is characterised in that include：
Fuselage main body (9), the first duct (1), the second duct (2), the 3rd duct (3), the 4th duct (4), nose-gear and
Undercarriage afterwards；
First duct (1) is connected with the first side of the fuselage main body (9)；
Second duct (2) is connected with the second side of the fuselage main body (9)；
3rd duct (3) is connected with the 3rd side of the fuselage main body (9)；
4th duct (4) is connected with the 4th side of the fuselage main body (9)；Wherein, first duct (1) and described
Three ducts (3) are symmetrical arranged relative to the fuselage main body (9), second duct (2) and the 4th duct (4) relative to
The fuselage main body (9) is symmetrical arranged；
The nose-gear is arranged on the lower head of the fuselage main body (9), and the rear undercarriage is arranged on the fuselage master
The afterbody lower section of body (9)；
The inside of first duct (1), second duct (2), the 3rd duct (3) and the 4th duct (4) is equal
The electromotor for being provided with blade and driving the blade to rotate.
2. unmanned plane according to claim 1, it is characterised in that
First duct (1) is rotated with the first side of the fuselage main body (9) by the first duct direction controlling steering wheel (5) and is connected
Connect；
Second duct (2) is rotated with the second side of the fuselage main body (9) by the second duct direction controlling steering wheel (6) and is connected
Connect；
3rd duct (3) is rotated with the 3rd side of the fuselage main body (9) by the 3rd duct direction controlling steering wheel (7) and is connected
Connect；
4th duct (4) is rotated with the 4th side of the fuselage main body (9) by the 4th duct direction controlling steering wheel (8) and is connected
Connect.
3. unmanned plane according to claim 1 and 2, it is characterised in that
The first duct direction controlling steering wheel (5) is rotated with the first side of the fuselage main body (9) by the first steering wheel and is connected；
The second duct direction controlling steering wheel (6) is rotated with the second side of the fuselage main body (9) by the second steering wheel and is connected；
3rd duct direction controlling steering wheel (7) is rotated with the 3rd side of the fuselage main body (9) by the 3rd steering wheel and is connected；
4th duct direction controlling steering wheel (8) is rotated with the 4th side of the fuselage main body (9) by the 4th steering wheel and is connected.
4. unmanned plane according to claim 3, it is characterised in that first duct (1), second duct (2), institute
State the 3rd duct (3) and the 4th duct (4) is identical and duct internal diameter with the ratio of duct width in 1.4-1.6 scopes
Interior, at duct entrance 1/3rd, duct outlet diameter is with duct internal diameter ratio in the range of 1.1-1.2 for oar disk.
5. unmanned plane according to claim 4, it is characterised in that first duct (1), second duct (2), institute
State the 3rd duct (3) and the 4th duct (4) is identical and the duct internal diameter is with the ratio of the duct width
1.5, the duct outlet diameter is 1.15 with the duct internal diameter ratio.
6. the unmanned plane according to claim 1 or 2 or 4, it is characterised in that the unmanned plane also includes：Fuel engines,
Electromotor and distributing means for power supply；
The fuel engines, electromotor are connected respectively with the distributing means for power supply；
Power produced by the fuel engines is converted to the distributing means for power supply power and the drive for driving the blade
Move the power of the electromotor.
7. the unmanned plane according to claim 4 or 5, it is characterised in that
The battery is rechargeable battery；
The battery is charged by wireless charging device；
Or, it is charged after the rectified filtering of alternating current of the battery by produced by electromotor.
8. unmanned plane according to claim 7, it is characterised in that the wireless charging device includes：Receiving coil and connect
Receive modular circuit；
The receiving coil and receiver module circuit are electrically connected with；
The receiving coil, for the electric current produced by induction field to be imported into the receiver module circuit；
The receiver module circuit, for after the electric current to be adjusted to the electric current for meeting the battery charge requirement, to institute
State battery to be charged.
9. unmanned plane according to claim 7, it is characterised in that the unmanned plane also includes：Controller；
The first duct direction controlling steering wheel and the first electromotor of the controller and first duct (1), described second
Second duct direction controlling steering wheel of duct (2) and the second electromotor, the 3rd duct direction controlling of the 3rd duct (3)
Steering wheel and trimotor, the 4th duct direction controlling steering wheel of the 4th duct (4) and the 4th electromotor, described
The frame steering-engine that falls is electrically connected；
The controller is by control first electromotor, second electromotor, the trimotor and the described 4th
The rotating speed of electromotor and first duct (1), second duct (2), the 3rd duct (3) and the 4th duct
(4) flight of the direction to unmanned plane is controlled.
10. unmanned plane according to claim 9, it is characterised in that the unmanned plane also includes：Electric power detection module and nothing
Line communication module；
The electric power detection module is electrically connected with respectively with the controller and the battery, the wireless communication module with it is described
Controller is electrically connected with；
The electric power detection module, for the electric quantity data of the battery for detecting to be sent to into the controller；
The controller, for determining the battery according to the electric quantity data for determining the electric power detection module transmission
Electricity sends not enough power supply instruction, the not enough power supply by the wireless communication module less than after preset value to control device
Instruction indicates that the electricity of unmanned plane is less than the preset value.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611114275.3A CN106672230A (en) | 2016-12-07 | 2016-12-07 | Ducted unmanned aerial vehicle |
| PCT/CN2017/074723 WO2018103203A1 (en) | 2016-12-07 | 2017-02-24 | Ducted unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611114275.3A CN106672230A (en) | 2016-12-07 | 2016-12-07 | Ducted unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672230A true CN106672230A (en) | 2017-05-17 |
Family
ID=58867720
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611114275.3A Pending CN106672230A (en) | 2016-12-07 | 2016-12-07 | Ducted unmanned aerial vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN106672230A (en) |
| WO (1) | WO2018103203A1 (en) |
Cited By (3)
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| CN109159633A (en) * | 2018-08-31 | 2019-01-08 | 长春工程学院 | A kind of amphibious unmanned plane |
| CN109747833A (en) * | 2017-11-03 | 2019-05-14 | 智飞智能装备科技东台有限公司 | A kind of removable duct spray appliance |
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| CN109435604B (en) * | 2018-12-18 | 2024-04-05 | 北京理工大学 | Flying car |
| WO2021014805A1 (en) * | 2019-07-23 | 2021-01-28 | パナソニックＩｐマネジメント株式会社 | Unmanned aerial vehicle and information processing method |
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Also Published As
| Publication number | Publication date |
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| WO2018103203A1 (en) | 2018-06-14 |
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