CN106347648A - Multi-rotor plant protection unmanned aerial vehicle - Google Patents
Multi-rotor plant protection unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106347648A CN106347648A CN201610994454.4A CN201610994454A CN106347648A CN 106347648 A CN106347648 A CN 106347648A CN 201610994454 A CN201610994454 A CN 201610994454A CN 106347648 A CN106347648 A CN 106347648A
- Authority
- CN
- China
- Prior art keywords
- control system
- horn
- plant protection
- unmanned plane
- protection unmanned
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007921 spray Substances 0.000 claims abstract description 35
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 15
- 238000009434 installation Methods 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 7
- 239000002828 fuel tank Substances 0.000 claims description 6
- 239000000725 suspension Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 5
- 238000013461 design Methods 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 230000009187 flying Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
-
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses a multi-rotor plant protection unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles. The multi-rotor plant protection unmanned aerial vehicle comprises an undercarriage, a body, a rack, arms, a main rotor, an auxiliary rotor, a spray system and a control system, wherein the body is arranged above the undercarriage and connected with the undercarriage; the rack is arranged above the body and connected with the body; the arms are mounted on the rack; even number of arms are provided and symmetrically distributed on the rack; an engine is arranged at the upper part of the rack; the main rotor is connected with an output shaft of the engine; an motor is arranged on each arm; an output shaft of each motor is connected with the corresponding auxiliary rotor; a spoiler is arranged on each arm; the spoilers are used for offsetting the anti-torque effect generated by the rotation of the main rotor; the control system, the engine and the motors are all connected with a power supply; and the control system controls the working states of the main rotor, the auxiliary rotors and the spray system. In the invention, gasoline-electric hybrid power is adopted, the whole structure is simplified, the structure is simple, and the time of endurance is long.
Description
Technical field
The present invention relates to a kind of unmanned plane, more particularly to a kind of many rotors plant protection unmanned plane.
Background technology
UAV abbreviation unmanned plane, because unmanned plane has the suitability to multiple environment and it is quickly anti-
Should be able to power, obtained rapid development in the last few years.Unmanned plane can be divided into polytype according to its construction features, including fixed-wing
Unmanned plane, pilotless helicopter, many rotor wing unmanned aerial vehicles etc., the wherein landing of fixed-wing unmanned plane need more spacious place simultaneously
Place with a varied topography can not be suitable for well；And the reaction torque producing during pilotless helicopter propeller rotational needs to use
Tail-rotor is balancing, and propeller drive to tail-rotor must assure that certain gear ratio, and engine output shaft need to be through slowing down in addition
Device reaches propeller, needs additional deceleration device, and propeller hub design structure is complicated simultaneously, its design, maintenance cost
Height, during propeller high-speed rotation, its drive disk assembly is relatively more, and any part, once going wrong, will result in immeasurable peace
Full hidden danger, the therefore pilotless helicopter fault rate when using is higher, simultaneously because body parts various cause to conduct oneself with dignity larger,
Lead to its payload to carry limited, be exactly also to keep helicopter to balance, setting up longer tail boom and cause overall structure
Size is larger, is unfavorable for packaging, carries and transport, also increases the weight of whole machine simultaneously.Although and its body of many rotor wing unmanned aerial vehicles
Appearance is flexibly light, taking photo by plane and scouting field has been applied, but because many rotor wing unmanned aerial vehicles are all using driven by power, and battery
Capacitance is little to cause whole machine payload to be very limited, and battery is short, and relative price is higher, and needs not
Disconnected charge, also lose time while increasing cost, also many rotor wing unmanned aerial vehicles in flight, if asking occurs in some rotor
Topic, will lead to the serious consequence of whole unmanned plane air crash, needs the rotor on each axle to run up in addition during many rotor flyings
Lift to be provided, therefore compares power consumption, the effective time greatly shortens, simultaneously if it is desired to increase power configuration then need bigger
The battery of capacity or be to increase number of batteries, the deadweight so resulting in many rotor wing unmanned aerial vehicles increases it is impossible to meet many rotors
The demand of unmanned plane heavy load.
In large-scale plant protection application, unmanned plane is needed to have the feature installed and easily rise and fall that is easy to carry,
Need to carry substantial amounts of medicine for plant protection simultaneously again, therefore cruising time length, rise and fall flexibly, structure is simple and load-carrying sufficient
It is directly for the feature required for plant protection unmanned plane.
Content of the invention
It is an object of the invention to provide many rotors plant protection unmanned plane that a kind of structure is simple, cruising time length, loading capacity are big,
To solve the problems, such as above-mentioned prior art.
For achieving the above object, the invention provides following scheme:
The present invention provides a kind of many rotors plant protection unmanned plane, including undercarriage, fuselage, frame, horn, main rotor, auxiliary
Rotor, sprinkling system and control system, described fuselage is arranged on above described undercarriage and is connected with described undercarriage, described machine
Frame is arranged on described body upper and is connected with described fuselage, and described horn is arranged in described frame, and described horn is even number
Individual and be symmetrically distributed in described frame, described upper rack is provided with electromotor, and described main rotor is defeated with described electromotor
Shaft connects, and each described horn is provided with motor, and the output shaft of each described motor is all revolved with corresponding described auxiliary
The wing connects, and each described horn is provided with spoiler, and described spoiler is used for offsetting produce during the rotation of described main rotor anti-
Moment of torsion acts on, and described control system, described electromotor and described motor are respectively connected with power supply, and described control system controls described
The working condition of main rotor, described auxiliary rotor and described sprinkling system.
Preferably, described control system includes the engine control system being arranged in described frame, described electromotor control
System processed and a steering wheel communication connection, described steering wheel is provided with a rocking bar, one end of the swinging end of described rocking bar and a connecting rod
Connect, the other end of described connecting rod is connected with the throttle of described electromotor, described steering wheel drives institute by the swing of described rocking bar
State connecting rod to move thus controlling the closure of throttle.
Preferably, the end of each described horn is provided with motor base (frame), and described motor is fixedly installed on described motor
On seat, described motor is connected with electron speed regulator, and described control system also includes flight control system, and described flight controls system
System is arranged in described frame, and described flight control system is communicated to connect with described electron speed regulator.
Preferably, described fuselage bottom is connected with described undercarriage, and described undercarriage is two horizon bars being oppositely arranged,
It is provided with rack in described fuselage, described rack is placed with fuel tank, described fuel tank is started with described by in-line
Machine connects.
Preferably, described sprinkling system includes medicine-chest, booster pump, spray boom and multiple nozzle, described medicine-chest and described supercharging
Connected by pencil between pump, described booster pump is connected by pencil with described spray boom, described nozzle is arranged on described spray boom
And connect with inside described spray boom, described medicine-chest is arranged on described rack, is provided with gondola in described fuselage, described supercharging
Pump is arranged in described gondola, and described spray boom suspension is arranged on the medium position of two described horizon bars of described undercarriage, institute
State control system and also include spray control system, described spray control system is arranged in described frame, described sprinkling controls system
System and described booster pump communication connection.
Preferably, described power supply includes the first power supply, second source and the 3rd power supply, described steering wheel, described electromotor control
System processed, described flight control system and each described motor are all connected with described first power supply, described electromotor and described the
Two power supplys connect, and described spray control system is connected with described 3rd power supply, is provided with battery compartment in described fuselage, and described first
Power supply, described second source and described 3rd power supply are arranged in described battery compartment；Described control system also includes remote control,
Described remote control and described engine control system, described flight control system and the communication connection of described spray control system.
Preferably, described horn is connected with described frame by folding keeper, and described horn passes through described folding and positions
Part is in launch, be folded down or be folded up state and position during its above-mentioned three kinds of state is positioned, described horn exhibition
Formed with horizontal direction when opening to tilt up or down and angle is 5 ° of angle.
Preferably, described folding keeper includes two symmetrically arranged fixed installation plates and mounting cylinder, and two described solid
Determine installing plate to connect by support, one end of described horn is connected with one end of described mounting cylinder, the other end of described mounting cylinder
It is connected with a pull bar, described pull bar is connected with one end of a Flexible Connector, the other end of described Flexible Connector is fixed on institute
State on fixed installation plate, two described mounting plates are provided with draw-in groove, described draw-in groove two ends have location hole, described pull bar
Two ends are connected in the described draw-in groove on two described mounting plates, and described pull bar can move in described draw-in groove, and two
Individual described mounting plate is arranged in described frame.
Preferably, the top of the medium position of described main rotor is provided with trouserss, and described spoiler tilts to be installed on institute
State on horn.
Preferably, described horn is 4, diagonally relative to two described auxiliary rotors turn to two identical, adjacent institutes
State auxiliary rotor to turn on the contrary.
The present invention achieves following technique effect with respect to prior art:
Many rotors plant protection unmanned plane of the present invention adopts oil electric mixed dynamic, directly provides liter by driven by engine main rotor
Power, the flight time is more permanent, and load is bigger；Auxiliary rotor rotation is driven by motor, auxiliary rotor is responsible for keeping during flight
Balance and the adjustment of flight attitude, very low to the prescription of auxiliary rotor, even if any one auxiliary rotor breaks down
Also it is not result in air crash, eliminate tail boom, empennage and propeller to the actuating device of empennage, complete machine structure pole simultaneously
It simplifies, and deadweight substantially reduces, and effectively improves the service life of motor.Engine output shaft is directly connected to main rotor, saves
Requisite drive mechanism, deceleration device and chiller in depopulated helicopter, enormously simplify the structure of unmanned plane
And then alleviate own wt so that payload is significantly lifted；Additionally, being provided with spoiler on horn, master can be offset
The reaction torque effect producing during rotor wing rotation is it is ensured that aircraft smooth flight.
Brief description
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
Need use accompanying drawing be briefly described it should be apparent that, drawings in the following description be only the present invention some enforcement
Example, for those of ordinary skill in the art, without having to pay creative labor, can also be according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is the front view of the present invention many rotors plant protection unmanned plane；
Fig. 2 is the top view of the present invention many rotors plant protection unmanned plane；
In figure: 1- undercarriage, 11- medicine-chest, 12- booster pump, 13- spray boom, 2- fuselage, 21- gondola, 3- frame, 31- rudder
Machine, 32- flight control system, 33- folding keeper, 4- horn, 5- main rotor, 51- trouserss, 6- auxiliary rotor, 7- start
Machine, 8- motor, 81- motor base (frame), 82- electron speed regulator, 9- spoiler, 10- power supply.
Specific 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 description is it is clear that described embodiment is only a part of embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of not making creative work
Embodiment, broadly falls into the scope of protection of the invention.
It is an object of the invention to provide many rotors plant protection unmanned plane that a kind of structure is simple, cruising time length, loading capacity are big,
To solve the problems, such as above-mentioned prior art.
Understandable for enabling the above objects, features and advantages of the present invention to become apparent from, below in conjunction with the accompanying drawings and specifically real
The present invention is further detailed explanation to apply mode.
Embodiment one
The present embodiment provides a kind of many rotors plant protection unmanned plane, as shown in figure 1, including undercarriage 1, fuselage 2, frame 3, machine
Arm 4, main rotor 5, auxiliary rotor 6, sprinkling system and control system, fuselage 2 is arranged on undercarriage 1 top and is connected with undercarriage 1
Connect, frame 3 is arranged on fuselage 2 top and is connected with fuselage 2, and horn 4 is arranged in frame 3, horn 4 is even number and symmetrical point
In frame 3, frame 3 top is provided with electromotor 7 to cloth, and main rotor 5 is connected with the output shaft of electromotor 7, and each horn 4 is all provided with
It is equipped with motor 8, the output shaft of each motor 8 is all connected with corresponding auxiliary rotor 6, and each horn 4 is provided with spoiler
9, spoiler 9 is used for offsetting the reaction torque effect producing during main rotor 6 rotation, and control system, electromotor 7 and motor 8 all connect
It is connected to power supply 10, control system controls the working condition of main rotor 5, auxiliary rotor 6 and sprinkling system.
Many rotors plant protection unmanned plane in the present embodiment adopts oil electric mixed dynamic, and electromotor 7 adopts petrol engine, by
Electromotor 7 drives main rotor 5 directly to provide lift, and the flight time is more permanent, and load is bigger；Auxiliary rotor 6 is driven by motor 8
Rotation, the adjustment of the responsible balance keeping during flight of auxiliary rotor 6 and flight attitude, eliminate tail boom, tail simultaneously
To the actuating device of empennage, complete machine structure extremely simplifies, and deadweight substantially reduces, and effectively improves motor 8 for the wing and propeller
Service life.Electromotor 7 output shaft is directly connected to main rotor 5, eliminates requisite transmission knot in depopulated helicopter
Structure, deceleration device and chiller, enormously simplify the structure of unmanned plane and then alleviate own wt so that payload is big
Amplitude is lifted；Additionally, spoiler 9 is provided with horn 4, can offset main rotor 5 rotation when produce reaction torque effect it is ensured that
Aircraft smooth flight.
Embodiment two
The present embodiment provides a kind of many rotors plant protection unmanned plane, as shown in Figure 1, 2, on the basis of embodiment one, this reality
The control system applying example includes the engine control system that is arranged in frame 3, and engine control system is communicated with a steering wheel 31
Connect, steering wheel 31 is provided with a rocking bar, the swinging end of rocking bar is connected with one end of a connecting rod, the other end of connecting rod and electromotor
Throttle connect.Engine control system can be controlled to the working condition of rocking bar on steering wheel 31 according to control signal, steering wheel
31 make the coupled one end of rocking bar rotate, and drive the other end of rocking bar to swing, then are moved by the swing drivening rod of rocking bar
Thus controlling the closure of throttle, control the air inflow of electromotor, thus adjusting the rotating speed of main rotor 5.
The end of each horn 4 is provided with motor base (frame) 81, and motor 8 is fixedly installed on motor base (frame) 81, and motor 8 is even
It is connected to electron speed regulator 82, control system also includes flight control system 32, flight control system 32 is arranged in frame 3, fly
Row control system 32 is communicated to connect with electron speed regulator 82, and flight control system 32 is entered to electron speed regulator 82 according to control signal
Row controls, thus adjusting the rotating speed of motor 8, realizes the regulation of the rotating speed of auxiliary rotor 6.
Fuselage 2 bottom is connected with undercarriage 1, and undercarriage 1 is two horizon bars being oppositely arranged, and is provided with and puts in fuselage 2
Put frame, rack is placed with fuel tank, fuel tank is connected with electromotor 7 by in-line.
Sprinkling system includes medicine-chest 11, booster pump 12, spray boom 13 and multiple nozzle, passes through between medicine-chest 11 and booster pump 12
Pencil connects, and booster pump 12 is connected by pencil with spray boom 13, and nozzle is arranged on spray boom 13 and is connected with spray boom 13 inside, medicine
Case 11 is arranged on rack, is provided with gondola 21 in fuselage 2, and booster pump 12 is arranged in gondola 21, and spray boom 13 suspension is installed
In the medium position of two horizon bars of undercarriage 1, spray boom 13 is provided with nozzle, control system also includes spraying controlling system
System, spray control system is arranged in frame 3, and spray control system is communicated to connect with booster pump 12, and spray control system can root
According to control signal, the working condition of booster pump 12 is controlled, booster pump 12 is delivered to spray after extracting medicinal liquid in medicine-chest 11 out
Bar 13, sprays through nozzle.
Power supply 10 includes the first power supply, second source and the 3rd power supply, and steering wheel 31, engine control system, flight control
System 32 and each motor 8 are all connected with the first power supply, and electromotor 7 is connected with second source, spray control system and the 3rd electricity
Source connects, and is provided with battery compartment, the first power supply, second source and the 3rd power supply are arranged in battery compartment in fuselage 2；Control system
System also includes remote control, remote control and engine control system, flight control system 32 and spray control system communication connection, distant
Control device transmits corresponding control signal to engine control system, flight control system 32 and spray control system, thus controlling
The rotating speed of electromotor 7, motor 8 and booster pump 12.
Horn 4 is passed through folding keeper 33 and is connected with frame 3 so that horn 4 is folding structure, above high degree
Transport and carry；Horn 4 pass through fold keeper 33 be in launch, be folded down or be folded up state and to its above-mentioned three
Position during kind of state positioned so that state when horn 4 launches or folds more consolidate it is ensured that the plant protection of many rotors no
Man-machine stability in flight and transportation, forms with horizontal direction to tilt up or down and angle when horn 4 launches
For 5 ° of angle, compare horn parastate, the stability in flight course is more preferable.
Fold keeper and include two symmetrically arranged fixed installation plates and mounting cylinder, two fixed installation plates pass through support
Connect, one end of horn 4 is connected with one end of mounting cylinder, the other end of mounting cylinder is connected with a pull bar, and pull bar and an elasticity are even
One end of fitting connects, and the other end of Flexible Connector is fixed on fixed installation plate, and two mounting plates are provided with card
Groove, draw-in groove two ends have location hole, and pull bar two ends are connected in the draw-in groove on two mounting plates, and pull bar can be in draw-in groove
Interior movement, two mounting plates are arranged in frame, and when the positioning in the hole of pull bar movement to two ends, location hole can be by pull bar
Card column, and the elastic reaction due to Flexible Connector, pull bar can not move out location hole easily, just can achieve determining of horn 4
Position is it is ensured that many rotors plant protection unmanned plane is flying and the stability in transportation.
The top of the medium position of main rotor 5 is provided with trouserss 51, can reduce resistance during main rotor rotation, during startup
Also convenient.
Spoiler 9 tilts to be installed on horn 4, and spoiler 9 is lightweight, the rectangular slab of good toughness, and the direction of inclination corresponds to
The direction of air-flow that main rotor produces when rotating, the present embodiment, the setting number of horn 4 is preferably 4, diagonally relative to two
Auxiliary rotor 6 turns to identical, adjacent two auxiliary rotor 6 and turns on the contrary, using diagonally relative to the auxiliary rotor identical, phase of steering
Adjacent auxiliary rotor turns to contrary feature and balances anti-twisted power with spoiler 9 cooperation it is ensured that aircraft smooth flight；So
Eliminate tail boom and empennage, eliminate rotor to the actuating device of empennage, complete machine structure extremely simplifies simultaneously, deadweight is dropped significantly
Low.
Apply specific case in the present invention principle of the present invention and embodiment are set forth, above example
Illustrate that being only intended to help understands the method for the present invention and its core concept；Simultaneously for one of ordinary skill in the art, according to
According to the thought of the present invention, all will change in specific embodiments and applications.In sum, this specification content
Should not be construed as limitation of the present invention.
Claims (10)
1. a kind of many rotors plant protection unmanned plane it is characterised in that: include undercarriage, fuselage, frame, horn, main rotor, auxiliary rotation
The wing, sprinkling system and control system, described fuselage is arranged on above described undercarriage and is connected with described undercarriage, described frame
It is arranged on described body upper and is connected with described fuselage, described horn is arranged in described frame, described horn is even number
And be symmetrically distributed in described frame, described upper rack is provided with electromotor, the output of described main rotor and described electromotor
Axle connects, and each described horn is provided with motor, the output shaft of each described motor all with corresponding described auxiliary rotor
Connect, each described horn is provided with spoiler, described spoiler is used for offsetting produce during the rotation of described main rotor anti-twisted
Square acts on, and described control system, described electromotor and described motor are respectively connected with power supply, and described control system controls described master
The working condition of rotor, described auxiliary rotor and described sprinkling system.
2. many rotors plant protection unmanned plane according to claim 1 it is characterised in that: described control system includes being arranged on institute
State the engine control system in frame, described engine control system and steering wheel communication connection, described steering wheel is provided with
One rocking bar, the swinging end of described rocking bar is connected with one end of a connecting rod, the throttle of the other end of described connecting rod and described electromotor
Connect, described steering wheel drives described connecting rod mobile thus controlling the closure of throttle by the swing of described rocking bar.
3. many rotors plant protection unmanned plane according to claim 2 it is characterised in that: the end of each described horn is provided with electricity
Engine-bed, described motor is fixedly installed on described motor base (frame), and described motor is connected with electron speed regulator, described control
System also includes flight control system, and described flight control system is arranged in described frame, described flight control system and institute
State electron speed regulator communication connection.
4. many rotors plant protection unmanned plane according to claim 3 it is characterised in that: described fuselage bottom and described undercarriage
Connect, described undercarriage is two horizon bars being oppositely arranged, and is provided with rack in described fuselage, described rack is placed
There is fuel tank, described fuel tank is connected with described electromotor by in-line.
5. many rotors plant protection unmanned plane according to claim 4 it is characterised in that: described sprinkling system includes medicine-chest, increasing
Press pump, spray boom and multiple nozzle, are connected by pencil between described medicine-chest and described booster pump, described booster pump and described spray boom
Connected by pencil, described nozzle is arranged on described spray boom and connects with inside described spray boom, and described medicine-chest is arranged on described
On rack, in described fuselage, it is provided with gondola, described booster pump is arranged in described gondola, described spray boom suspension is arranged on institute
State the medium position of two described horizon bars of undercarriage, described control system also includes spray control system, described sprinkling control
System processed is arranged in described frame, and described spray control system is communicated to connect with described booster pump.
6. many rotors plant protection unmanned plane according to claim 5 it is characterised in that: described power supply include the first power supply,
Two power supplys and the 3rd power supply, described steering wheel, described engine control system, described flight control system and each described motor are equal
It is connected with described first power supply, described electromotor is connected with described second source, described spray control system is electric with the described 3rd
Source connects, and is provided with battery compartment, described first power supply, described second source and described 3rd power supply are arranged in described fuselage
In described battery compartment；Described control system also includes remote control, described remote control and described engine control system, described flight
Control system and the communication connection of described spray control system.
7. many rotors plant protection unmanned plane according to claim 6 it is characterised in that: described horn pass through fold keeper with
Described frame connects, and described horn is in launch, be folded down or be folded up state and to thereon by described folding keeper
State position during three kinds of states to be positioned, form inclination up or down when described horn launches with horizontal direction and angle is
5 ° of angle.
8. many rotors plant protection unmanned plane according to claim 7 it is characterised in that: described folding keeper include two right
Claim fixed installation plate and the mounting cylinder of setting, two described fixed installation plates are connected by support, one end of described horn and institute
The one end stating mounting cylinder connects, and the other end of described mounting cylinder is connected with a pull bar, and the one of described pull bar and a Flexible Connector
End connects, and the other end of described Flexible Connector is fixed on described fixed installation plate, and two described mounting plates are arranged
There is draw-in groove, described draw-in groove two ends have location hole, described pull bar two ends are connected to the described card on two described mounting plates
In groove, and described pull bar can move in described draw-in groove, and two described mounting plates are arranged in described frame.
9. many rotors plant protection unmanned plane according to claim 1 it is characterised in that: the medium position of described main rotor upper
Side is provided with trouserss, and described spoiler tilts to be installed on described horn.
10. many rotors plant protection unmanned plane according to claim 1 it is characterised in that: described horn is 4, diagonally relatively
Two described auxiliary rotors turn to the described auxiliary rotors of identical, adjacent two turn to contrary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610994454.4A CN106347648A (en) | 2016-11-11 | 2016-11-11 | Multi-rotor plant protection unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610994454.4A CN106347648A (en) | 2016-11-11 | 2016-11-11 | Multi-rotor plant protection unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106347648A true CN106347648A (en) | 2017-01-25 |
Family
ID=57862220
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610994454.4A Pending CN106347648A (en) | 2016-11-11 | 2016-11-11 | Multi-rotor plant protection unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106347648A (en) |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986019A (en) * | 2017-04-17 | 2017-07-28 | 四川建筑职业技术学院 | A kind of motor cabinet for changing multi-rotor unmanned aerial vehicle rotor face angle of inclination |
| CN107161332A (en) * | 2017-05-31 | 2017-09-15 | 南京航空航天大学 | A kind of double-deck eight rotor wing unmanned aerial vehicle |
| CN107193285A (en) * | 2017-04-20 | 2017-09-22 | 湖北工业大学 | Many rotor fuel cell plant protection unmanned aerial vehicle control systems and its method of work |
| CN107651193A (en) * | 2017-10-23 | 2018-02-02 | 郑州方达电子技术有限公司 | Review for Helicopter auto-folder spray boom |
| CN107891985A (en) * | 2017-12-15 | 2018-04-10 | 青岛港湾职业技术学院 | A kind of switchable type tilting rotor unmanned plane |
| CN108313279A (en) * | 2018-04-09 | 2018-07-24 | 重庆国飞通用航空设备制造有限公司 | A kind of special fire extinguishing multi-rotor unmanned aerial vehicle system of fire-fighting |
| CN108423165A (en) * | 2018-05-09 | 2018-08-21 | 重庆零创屹立科技有限公司 | A kind of plant protection drone |
| CN108513639A (en) * | 2017-07-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Motor drives and flight control method, electricity tune, dynamical system and UAV system |
| CN108609173A (en) * | 2018-03-30 | 2018-10-02 | 陈玮 | A kind of energy conservation and environmental protection unmanned helicopter |
| CN108995815A (en) * | 2018-09-08 | 2018-12-14 | 灵翼飞航（天津）科技有限公司 | A kind of cross-arranging type multi-rotor unmanned aerial vehicle |
| CN109221060A (en) * | 2018-09-14 | 2019-01-18 | 广州市华科尔科技股份有限公司 | A kind of plant protection drone spray assemblies and spraying method |
| CN109383797A (en) * | 2017-08-04 | 2019-02-26 | 上海裕芮信息技术有限公司 | A kind of agriculture and forestry special intelligent unmanned plane |
| CN109733622A (en) * | 2019-01-28 | 2019-05-10 | 河南正大航空工业股份有限公司 | A kind of mixed dynamic unmanned plane of oil electricity |
| 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 |
| CN110395386A (en) * | 2019-09-06 | 2019-11-01 | 山东蜂巢航空科技有限公司 | Six rotor wing unmanned aerial vehicles of oily electricity mixing |
| CN110481780A (en) * | 2019-09-11 | 2019-11-22 | 北方民族大学 | Hybrid power unmanned plane and its control method with two kinds of rotors |
| WO2020029600A1 (en) * | 2018-08-09 | 2020-02-13 | 深圳市翔农创新科技有限公司 | Nozzle assembly, plant protection drone and spray method |
| CN113665812A (en) * | 2021-08-09 | 2021-11-19 | 广东新创华科环保股份有限公司 | Multi-channel unmanned aerial vehicle control system and method |
| CN114248926A (en) * | 2022-01-19 | 2022-03-29 | 安徽文达信息工程学院 | Plant protection unmanned aerial vehicle |
| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014131914A1 (en) * | 2013-02-28 | 2014-09-04 | Axter Aerospace Sl | Hybrid power system for piston engine aircrafts |
| CN104843179A (en) * | 2015-05-25 | 2015-08-19 | 张凯 | Multi-rotor hybrid power plant protection unmanned aerial vehicle |
| CN205059995U (en) * | 2015-10-15 | 2016-03-02 | 湖南云顶智能科技有限公司 | A collapsible horn for unmanned aerial vehicle |
| CN205396531U (en) * | 2016-03-17 | 2016-07-27 | 山西施普乐航空植保科技有限公司 | Electric control oil moves many rotor unmanned aerial vehicle |
| CN205602109U (en) * | 2016-04-12 | 2016-09-28 | 郑州郑航通用航空工业科技有限公司 | Unmanned plant protection machine |
| CN106081064A (en) * | 2016-07-28 | 2016-11-09 | 上海威碳新材料有限公司 | A kind of folding horn for unmanned plane |
| CN206141823U (en) * | 2016-11-11 | 2017-05-03 | 北京航空航天大学 | Many rotors plant protection unmanned aerial vehicle |
-
2016
- 2016-11-11 CN CN201610994454.4A patent/CN106347648A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014131914A1 (en) * | 2013-02-28 | 2014-09-04 | Axter Aerospace Sl | Hybrid power system for piston engine aircrafts |
| CN104843179A (en) * | 2015-05-25 | 2015-08-19 | 张凯 | Multi-rotor hybrid power plant protection unmanned aerial vehicle |
| CN205059995U (en) * | 2015-10-15 | 2016-03-02 | 湖南云顶智能科技有限公司 | A collapsible horn for unmanned aerial vehicle |
| CN205396531U (en) * | 2016-03-17 | 2016-07-27 | 山西施普乐航空植保科技有限公司 | Electric control oil moves many rotor unmanned aerial vehicle |
| CN205602109U (en) * | 2016-04-12 | 2016-09-28 | 郑州郑航通用航空工业科技有限公司 | Unmanned plant protection machine |
| CN106081064A (en) * | 2016-07-28 | 2016-11-09 | 上海威碳新材料有限公司 | A kind of folding horn for unmanned plane |
| CN206141823U (en) * | 2016-11-11 | 2017-05-03 | 北京航空航天大学 | Many rotors plant protection unmanned aerial vehicle |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986019B (en) * | 2017-04-17 | 2023-05-30 | 四川建筑职业技术学院 | Motor cabinet capable of changing inclination angle of rotary wing surface of multi-rotor unmanned aerial vehicle |
| CN106986019A (en) * | 2017-04-17 | 2017-07-28 | 四川建筑职业技术学院 | A kind of motor cabinet for changing multi-rotor unmanned aerial vehicle rotor face angle of inclination |
| CN107193285A (en) * | 2017-04-20 | 2017-09-22 | 湖北工业大学 | Many rotor fuel cell plant protection unmanned aerial vehicle control systems and its method of work |
| CN107161332A (en) * | 2017-05-31 | 2017-09-15 | 南京航空航天大学 | A kind of double-deck eight rotor wing unmanned aerial vehicle |
| CN108513639A (en) * | 2017-07-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Motor drives and flight control method, electricity tune, dynamical system and UAV system |
| CN109383797A (en) * | 2017-08-04 | 2019-02-26 | 上海裕芮信息技术有限公司 | A kind of agriculture and forestry special intelligent unmanned plane |
| CN107651193A (en) * | 2017-10-23 | 2018-02-02 | 郑州方达电子技术有限公司 | Review for Helicopter auto-folder spray boom |
| 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 |
| CN107891985A (en) * | 2017-12-15 | 2018-04-10 | 青岛港湾职业技术学院 | A kind of switchable type tilting rotor unmanned plane |
| CN108609173A (en) * | 2018-03-30 | 2018-10-02 | 陈玮 | A kind of energy conservation and environmental protection unmanned helicopter |
| CN108313279A (en) * | 2018-04-09 | 2018-07-24 | 重庆国飞通用航空设备制造有限公司 | A kind of special fire extinguishing multi-rotor unmanned aerial vehicle system of fire-fighting |
| CN108313279B (en) * | 2018-04-09 | 2024-04-05 | 重庆国飞通用航空设备制造有限公司 | Fire-extinguishing multi-rotor unmanned aerial vehicle system special for fire control |
| CN108423165A (en) * | 2018-05-09 | 2018-08-21 | 重庆零创屹立科技有限公司 | A kind of plant protection drone |
| CN108423165B (en) * | 2018-05-09 | 2023-06-06 | 重庆零创屹立科技有限公司 | Plant protection unmanned aerial vehicle |
| WO2020029600A1 (en) * | 2018-08-09 | 2020-02-13 | 深圳市翔农创新科技有限公司 | Nozzle assembly, plant protection drone and spray method |
| CN108995815A (en) * | 2018-09-08 | 2018-12-14 | 灵翼飞航（天津）科技有限公司 | A kind of cross-arranging type multi-rotor unmanned aerial vehicle |
| CN109221060A (en) * | 2018-09-14 | 2019-01-18 | 广州市华科尔科技股份有限公司 | A kind of plant protection drone spray assemblies and spraying method |
| CN109733622A (en) * | 2019-01-28 | 2019-05-10 | 河南正大航空工业股份有限公司 | A kind of mixed dynamic unmanned plane of oil electricity |
| CN109733622B (en) * | 2019-01-28 | 2023-09-08 | 河南正大航空工业股份有限公司 | Oil-electricity hybrid unmanned aerial vehicle |
| CN110395386A (en) * | 2019-09-06 | 2019-11-01 | 山东蜂巢航空科技有限公司 | Six rotor wing unmanned aerial vehicles of oily electricity mixing |
| CN110481780A (en) * | 2019-09-11 | 2019-11-22 | 北方民族大学 | Hybrid power unmanned plane and its control method with two kinds of rotors |
| CN113665812A (en) * | 2021-08-09 | 2021-11-19 | 广东新创华科环保股份有限公司 | Multi-channel unmanned aerial vehicle control system and method |
| CN114248926A (en) * | 2022-01-19 | 2022-03-29 | 安徽文达信息工程学院 | Plant protection unmanned aerial vehicle |
| CN114248926B (en) * | 2022-01-19 | 2023-09-22 | 安徽文达信息工程学院 | Plant protection unmanned aerial vehicle |
| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106347648A (en) | Multi-rotor plant protection unmanned aerial vehicle | |
| CN106927030B (en) | Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof | |
| CN101837195B (en) | Model airplane with vertical takeoff and landing | |
| CN107416200B (en) | Electric composite wing aircraft | |
| CN204642152U (en) | New oil moves many rotors plant protection unmanned plane | |
| CN102390530B (en) | Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof | |
| CN105539833A (en) | Fixed-wing multi-shaft aircraft | |
| CN206141823U (en) | Many rotors plant protection unmanned aerial vehicle | |
| CN104760696A (en) | Multi-rotor aircraft | |
| CN200951831Y (en) | Multi-rotor wing craft | |
| CN107140192A (en) | A kind of hybrid power unmanned plane | |
| CN113370730B (en) | Flying car | |
| CN102358420A (en) | Attitude transforming aircraft | |
| CN106428527A (en) | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings | |
| CN105667780A (en) | Multi-rotor aircraft | |
| CN1843847A (en) | Multi-rotor aerocraft | |
| CN206857002U (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft | |
| CN103979104A (en) | Vertical take-off and landing miniature air vehicle with variable X-type wing | |
| CN113753229A (en) | Foldable fixed-wing four-rotor composite unmanned aerial vehicle and control method thereof | |
| CN105775122A (en) | Tilt rotor type aircraft | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| CN110466754A (en) | A kind of tailstock formula tilting rotor vertical take-off and landing drone | |
| CN201744174U (en) | Model airplane vertically taking off and landing | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170125 |