CN207759016U - A kind of vertical take-off and landing drone electrical system - Google Patents
A kind of vertical take-off and landing drone electrical system Download PDFInfo
- Publication number
- CN207759016U CN207759016U CN201721836672.1U CN201721836672U CN207759016U CN 207759016 U CN207759016 U CN 207759016U CN 201721836672 U CN201721836672 U CN 201721836672U CN 207759016 U CN207759016 U CN 207759016U
- Authority
- CN
- China
- Prior art keywords
- power supply
- driving motor
- supply module
- vertical take
- wing
- 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.)
- Active
Links
Landscapes
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The utility model discloses a kind of vertical take-off and landing drone electrical systems, it include controller, fuel engines, driving motor and the power supply module being connect respectively with controller, fuel engines connect driving fixed-wing rotation with fixed-wing and realizes unmanned plane cruise, driving motor connect the more rotor wing rotations of driving with more rotors and realizes unmanned plane landing, engine includes startup electricity generation system, and driving motor, startup electricity generation system, controller connect realization power supply with power supply module.The utility model sends throttle control signal to fuel engines, driving motor by controller, fuel engines, driving motor are carried out automatically controlling, the VTOL and cruise for realizing unmanned plane monitor, and two kinds of working mode changes are quick and precisely, without carrying out rotor steering, the stability of flight ensure that.
Description
Technical field
The utility model is related to vertical take-off and landing drone field, specifically a kind of vertical take-off and landing drone electrical system.
Background technology
Relative to traditional Fixed Wing AirVehicle and rotor craft, can VTOL Fixed Wing AirVehicle due to using
The composite construction forms of fixed-wing+more rotors, it may be unnecessary to runway and landing spatial domain, it can be in complexity such as mountain area, hills, jungles
Landform and the intensive smooth operation in region of building, and avoid slow multi-rotor aerocraft flying speed, air mileage and endurance
Short problem.
The patent that number of patent application is 201510073872 disclose a kind of band vert fixed-wing multi-rotor aerocraft and
Its control method.It, which is specifically disclosed on the fuselage of aircraft, is arranged multiple symmetrical rotors and fixed-wing, and rotor is symmetrically set
It sets in the front and back end of fuselage, and rotating speed and pitch by adjusting rotor increase the lift of aircraft, so that aircraft is realized straight
Rise machine offline mode.The patent that number of patent application is 2015104500114 discloses a kind of fixed-wing of more rotor VTOL
Aircraft, operation principle are：After aircraft takeoff, rear rotor verts backward under, and tilt angle maximum can be 90 °,
When tilt angle reaches 90 °, while preceding rotor can be closed and save power, aircraft enters fixed-wing offline mode, rear to revolve
The wing can vert to the left or to the right maximum angle be 45 °, realize aircraft turning.It can be seen by above-mentioned two publications
Go out, is all by controlling the corner of rotor come the adjustment to heading, in this way when existing Fixed Wing AirVehicle takes off vertically
In aircraft when turning to, need to realize by controlling rotor steering, to cause the structural soundness of aircraft itself
It reduces.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of vertical take-off and landing drone electrical systems, by fuel oil
The dynamic Control of engine and driving motor realizes the work and switching of hang down drop pattern and cruise mode.
The technical solution of the utility model is：
A kind of vertical take-off and landing drone electrical system, the vertical take-off and landing drone include fuselage, are set to fuselage
On fixed-wing and more rotors, the vertical take-off and landing drone electrical system includes controller, is connect respectively with controller
Fuel engines, driving motor and power supply module, it is real that the fuel engines connect driving fixed-wing rotation with fixed-wing
Existing unmanned plane cruise, the driving motor connect the more rotor wing rotations of driving with more rotors and realize unmanned plane landing, the hair
Motivation includes startup electricity generation system, and the driving motor, startup electricity generation system, controller connect realization with power supply module
Power supply.
Link communication system and load system are connected on the controller, the load system connects with power supply module
Realization power supply is connect, the link communication system is connected with ground communication system communication, ground load monitoring system, ground flying
Control system is connect with ground communication system.
The power supply module selects lithium battery power supply module.
The vertical take-off and landing drone electrical system further includes having generator, the electric energy output of power supply module and generator
End connection, the power intake of the generator and the output end of fuel engines connect.
The advantages of the utility model：
The utility model sends throttle control signal to fuel engines, driving motor by controller, starts to fuel oil
Machine, driving motor carry out automatically controlling, and realize that the VTOL of unmanned plane and cruise monitor, and two kinds of working mode changes are quick
Accurately, without carrying out rotor steering, it ensure that the stability of flight.
Description of the drawings
Fig. 1 is the structural schematic diagram of vertical take-off and landing drone of the present invention.
Fig. 2 is the principle of the present invention block diagram, wherein " --- " indicates signal connection, "-- " indicate power supply connection, "-
" indicate be connected by power.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
The fixed-wing 2 and more rotors 3 that vertical take-off and landing drone includes fuselage 1, is set on fuselage 1；A kind of vertical
It includes controller 4 to drop unmanned electrical-mechanical system, fuel engines 5, driving motor 6, the power supply mould being connect respectively with controller 4
Block 7, generator 8, link communication system 9 and load system 10, fuel engines 5 connect driving fixed-wing 2 with fixed-wing 2 and rotate
Realize that unmanned plane cruise, driving motor 6 connect the more rotations of rotor 3 of driving with more rotors 3 and realize that unmanned plane landing, engine 5 are wrapped
It has included and has started electricity generation system 51, driving motor 6, startup electricity generation system 51, controller 4, load system 10 connect with power supply module 7
Realization power supply is connect, power supply module 7 selects lithium battery power supply module, power supply module 7 to be connect with the electric energy output end of generator 8, sends out
The power intake of motor 8 is connect with the output end of fuel engines 5, and link communication system 9 is communicated with ground communication system 11
Connection, ground load monitoring system 12, ground flying control system 13 are connect with ground communication system 11.
The operation principle of the present invention：
Vertical take-off and landing drone is transferred to appointed place expansion, then carries out steering engine for unmanned plane（Wing flap）Test and load work(
It can test.
Completion to be tested starts unmanned plane, starts fuel engines 5 first, makes it into idling mode, then controller
The rotating speed of 4 control driving motors 6 makes more rotors 3 rotate unmanned plane and enters propradation, waits for that unmanned plane rises to certain altitude,
Controller 4 reduces the rotating speed of driving motor 6 and increases the throttle amount of fuel engines 5, until unmanned plane horizontal velocity reaches certain
One thresholding, unmanned plane enter cruise mode, and the drive volume of driving motor 6 is zero at this time, and unmanned mechanomotive force is started by fuel oil completely
Machine 5 drives fixed-wing to generate.
Descent path is set in advance in monitoring unmanned task to be done, unmanned plane, into vertical drop pattern, fuel engines 5
Throttle amount slowly reduce, the rotating speed of driving motor 6 slowly rises, and has waited until predetermined landing place, at this time driving motor 6 drive
The lift that more rotors 3 generate has been more than the lift that fuel engines 5 drives fixed-wing 2 to generate, and fuel engines 5 decays to rapidly
After idling mode, after completing powershift, unmanned plane slowly reduces height, while can also carry out horizontal displacement by a small margin, passes through
More rotor rotationals complete aircraft landing.
The whole flight of unmanned plane is all communicated by link communication system 9 and ground communication system 11, ground communication system
11 send out flight directive, and aircraft control action is converted to by flying control.Simultaneously in flight course, load system 10 is also by chain
Road communication system 9, ground communication system 11 and ground load monitoring system 12 carry out real-time communication, complete various task tests.
When aircraft enters cruise mode, fuel engines 5 drives generator 8 to generate electricity, and generator 8 connects with power supply module 7
It connects, you can power to various equipment, can also carry out low current charge to lithium battery.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is appreciated that can these embodiments be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (4)
1. a kind of vertical take-off and landing drone electrical system, the vertical take-off and landing drone include fuselage, are set on fuselage
Fixed-wing and more rotors, it is characterised in that：The vertical take-off and landing drone electrical system includes controller, respectively with control
Fuel engines, driving motor and the power supply module of device connection processed, the fuel engines connect driving with fixed-wing and fix
Wing rotation realizes that unmanned plane cruise, the driving motor connect the more rotor wing rotations of driving with more rotors and realize unmanned plane landing,
The engine includes startup electricity generation system, and the driving motor starts electricity generation system, controller and power supply module
Power supply is realized in connection.
2. a kind of vertical take-off and landing drone electrical system according to claim 1, it is characterised in that：On the controller
It is connected with link communication system and load system, the load system connect realization power supply, the link with power supply module
The communication of communication system and ground communication system connects, and ground load monitoring system, ground flying control system are and ground communications
System connects.
3. a kind of vertical take-off and landing drone electrical system according to claim 1, it is characterised in that：The power supply module
Select lithium battery power supply module.
4. a kind of vertical take-off and landing drone electrical system according to claim 1, it is characterised in that：The VTOL
Unmanned electrical-mechanical system further includes having generator, the electric energy output end connection of power supply module and generator, the generator
The output end of power intake and fuel engines connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721836672.1U CN207759016U (en) | 2017-12-25 | 2017-12-25 | A kind of vertical take-off and landing drone electrical system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721836672.1U CN207759016U (en) | 2017-12-25 | 2017-12-25 | A kind of vertical take-off and landing drone electrical system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207759016U true CN207759016U (en) | 2018-08-24 |
Family
ID=63184466
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721836672.1U Active CN207759016U (en) | 2017-12-25 | 2017-12-25 | A kind of vertical take-off and landing drone electrical system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207759016U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927923A (en) * | 2019-03-15 | 2019-06-25 | 安徽云翼航空技术有限公司 | A kind of reconnaissance system based on VTOL fixed-wing unmanned plane |
| CN112660368A (en) * | 2019-10-15 | 2021-04-16 | 上海峰飞航空科技有限公司 | Control method and system for flight resistance of vertical take-off and landing unmanned aerial vehicle |
-
2017
- 2017-12-25 CN CN201721836672.1U patent/CN207759016U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927923A (en) * | 2019-03-15 | 2019-06-25 | 安徽云翼航空技术有限公司 | A kind of reconnaissance system based on VTOL fixed-wing unmanned plane |
| CN112660368A (en) * | 2019-10-15 | 2021-04-16 | 上海峰飞航空科技有限公司 | Control method and system for flight resistance of vertical take-off and landing unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105173075B (en) | A kind of hybrid power can tilt wing aircraft | |
| CN103359284A (en) | Petrol-electric hybrid four-rotor unmanned aerial vehicle | |
| CN106155083B (en) | A kind of composite wing unmanned plane emergency operating device | |
| CN206520748U (en) | A kind of oil electric mixed dynamic multi-rotor unmanned aerial vehicle | |
| WO2020107373A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| CN109733621A (en) | A kind of hybrid power unmanned plane promoting mode more | |
| CN205602114U (en) | Unmanned aerial vehicle with multiple rotor wings | |
| CN106564604A (en) | Fuel-electric hybrid four-rotor power unit and control method thereof | |
| CN105398570A (en) | Oil-operated multi- rotor aerocraft | |
| CN105711826A (en) | Tandem type oil-electric hybrid unmanned aerial vehicle | |
| CN206704537U (en) | A kind of fixed-wing unmanned plane | |
| CN105912015A (en) | Composite wing unmanned plane automatic pilot and control method employed by composite wing unmanned plane automatic pilot | |
| CN105752331A (en) | Single-internal combustion engine power multi-rotor wing unmanned aerial vehicle based on variable pitch control | |
| CN104494820A (en) | Oil-driven four-rotor-wing unmanned aerial vehicle | |
| CN108163193A (en) | A kind of active main rotor vertically taking off and landing flyer | |
| CN207759016U (en) | A kind of vertical take-off and landing drone electrical system | |
| CN204433050U (en) | The hardware platform of dynamic four rotor unmanned aircrafts of oil | |
| CN105197237A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN207791151U (en) | A kind of novel hybrid complex controll aircraft | |
| CN104925248B (en) | Multi-rotor-wing unmanned aerial vehicle with novel pneumatic layout and motor control method thereof | |
| CN109250096A (en) | A kind of aircraft of more rotors in conjunction with fixed-wing | |
| CN206819162U (en) | A kind of unmanned plane based on CAN flies control hardware system | |
| CN105035328B (en) | Hybrid-power flight vehicle | |
| CN106275416A (en) | The composite aircraft that fixed-wing forms with many rotors | |
| CN205450786U (en) | Composite wing unmanned aerial vehicle automatic pilot |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |