CN105905293B - A kind of oil electricity mixing multi-rotor aerocraft - Google Patents
A kind of oil electricity mixing multi-rotor aerocraft Download PDFInfo
- Publication number
- CN105905293B CN105905293B CN201610332130.4A CN201610332130A CN105905293B CN 105905293 B CN105905293 B CN 105905293B CN 201610332130 A CN201610332130 A CN 201610332130A CN 105905293 B CN105905293 B CN 105905293B
- Authority
- CN
- China
- Prior art keywords
- oil machine
- oil
- steering wheel
- controller
- gravity sensor
- 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
- 230000005611 electricity Effects 0.000 title claims abstract description 14
- 230000005484 gravity Effects 0.000 claims abstract description 27
- 239000003921 oil Substances 0.000 description 40
- 238000010276 construction Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000010727 cylinder oil Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002917 insecticide Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000013589 supplement Substances 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- 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
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of oil electricity mixing multi-rotor aerocraft, controller is provided with flying body, gravity sensor is installed with flying body above controller, central plate is installed above gravity sensor, steering wheel is installed above central plate, oil machine is provided with above steering wheel, transfer case is provided with above oil machine, it is connected above transfer case with the first flying wing and the second flying wing, export positive and negative pair of oar power using transfer case realizes the balance of power output by accurately adjusting, solve single-blade moment of torsion imbalance problem, the stable output of oil machine power is realized by the accurate control of controller and gravity sensor, generator can be installed additional in oil machine simultaneously, the electric power continuation of the journey problem of many rotors is solved by oil machine supplementary power.
Description
Technical field
The present invention relates to mechanical field, and in particular to a kind of oil electricity mixing multi-rotor aerocraft.
Background technology
Electronic multi-rotor aerocraft it is easy it is handling increasingly favored by user, but cruising time and heavy－duty system
The about development of many rotors.The problem of oil machine Dan Xuan and many rotations solve cruising time and heavy－duty, but the dynamic gyroplane of oil is needed
Professional training is wanted to manipulate, and flight stability is not so good, thus can not be by big well-established.Current oil electricity mixing is more
The reason for rotor craft is handling bad is mainly：Oily electric power match control is bad；The torsion that the power output of oil machine is produced
Square is offset by the rotating speed or angle of electronic many rotors, it is impossible to active balance；The throttle of oil machine can only be by controlling, no manually
It can adjust in real time；The balance of automatic vehicle can not be realized, higher is required to manipulator.
The present invention is to fix a single cylinder or multi-cylinder oil machine, the output shaft above oil machine at existing multi-rotor aerocraft center
A coaxial reverse transfer case is fixed at end, by the power of output by transfer case, and coaxial positive and negative both direction is exported above transfer case
The power of rotation, two power of transfer case output act on positive and negative two propellers in top, are provided by this positive and negative two propeller
The pulling force risen, the size of its pulling force is by the weight size of I/O circuit acquisition aircraft is Lai accurately control controls turn of oil machine automatically
Speed, so as to obtain required pulling force, itself propeller of many rotors controls flight attitude by battery offer power, and battery electric power can
To carry electricity generation system to supplement by oil machine so as to reaching the flight demand of long-time heavy－duty.
The content of the invention
In view of the shortcomings of the prior art, the present invention provides a kind of simple in construction, easy to operate, and work and operational efficiency are high,
The high oil electricity mixing multi-rotor aerocraft of automaticity, many defects for solving prior art presence.
The technical proposal of the invention is realized in this way：A kind of oil electricity mixing multi-rotor aerocraft, including carry battery
Flying body, be provided with the flying body above controller, controller on described flying body and be installed with gravity
It is provided with above sensor, gravity sensor above central plate, central plate and steering wheel is installed, oil machine is provided with above steering wheel, oil
It is provided with above transfer case, transfer case and is connected with the first flying wing and the second flying wing above machine.
Supercharging transmitter is installed inside described controller and voltage turns PWM module, gravity sensor by wire with
Supercharging transmitter is connected, and supercharging transmitter turns PWM module by wire and voltage and is connected, and voltage turns PWM module by leading
Line is connected with steering wheel, and steering wheel is connected with the input throttle end of oil machine.
Described battery is arranged on controller bottom, and battery passes through wire and controller and gravity sensor and rudder
Machine is connected.
The voltage of described gravity sensor output signal be 0 to 20mv, supercharging transmitter output signal voltage for 0 to
10v。
The quantity of described gravity sensor is at least 1.
The present invention has following good effect：This product is simple in construction first, easy to operate, using transfer case output just
Anti- double oar power realize the balance of power output by accurately adjusting, and solve single-blade moment of torsion imbalance problem, pass through
The accurate control of controller and gravity sensor realizes the stable output of oil machine power, while generating can be installed additional in oil machine
Machine, the electric power continuation of the journey problem of many rotors is solved by oil machine supplementary power.
Brief description of the drawings
Fig. 1 is structural representation of the invention.
Fig. 2 is controller architecture schematic diagram of the present invention.
Embodiment
As shown in Figure 1, 2, a kind of oil electricity mixing multi-rotor aerocraft, including carry the flying body 1 of battery, it is described
It is provided with flying body 1 on controller 2, the flying body 1 of the top of controller 2 and is installed with gravity sensor 3, gravity is passed
The top of sensor 3 is provided with central plate 4, and the top of central plate 4 is provided with steering wheel 5, and the top of steering wheel 5 is provided with oil machine 6, the top of oil machine 6
Transfer case 7 is provided with, the top of transfer case 7 is connected with the first flying wing 9 and the second flying wing 8.
Supercharging transmitter 10 is installed inside described controller 2 and voltage turns PWM module 11, gravity sensor 3 passes through
Wire is connected with supercharging transmitter 10, and supercharging transmitter turns PWM module 11 by wire and voltage and is connected, and voltage turns PWM
Module 11 is connected by wire with steering wheel 5, and steering wheel 5 is connected with the input throttle end of oil machine 6.Described battery is arranged on
The bottom of controller 2, battery is connected by wire with controller 2 and gravity sensor 3 and steering wheel 5.Described gravity is passed
The voltage of the output signal of sensor 3 is 0 to 20mv, and the voltage of the supercharging output signal of transmitter 10 is 0 to 10v.Described gravity is passed
The quantity of sensor 3 is at least 1.
The present invention installs gravity sensing device additional in the weight bearing area of aircraft, and gravity is converted into voltage by the device（0-5mv
Or 0-10mv）Signal output（Voltage increases with the increase of gravity）, voltage signal is by being pressurized transmitter by 0-10mv voltages
Signal is converted into 0-5v or 0-10v voltage signal（The voltage signal of device output can adjust output electricity according to the actual requirements
It is pressed between 0-10v）, voltage signal is being turned PWM module by voltage and walked around to turn to PWM pulse-width signals, PWM pulsewidths are adjusted
Signal control steering wheel processed, which is rotated, fills the swing arm arm by the conversion meeting of above-mentioned signal according to institute's loading capacity on respective angles, steering wheel
Size swing corresponding amplitude, the throttle of swing arm connection oil machine is so as to automatically controlling the size of throttle.The device is sensed
Gravitation information the throttle control signal of oil machine is converted to control the rotation of throttle servomotor so that oil machine output is corresponding
Power meet flight needs.The power of oil machine can be increased with the increase of take-off weight in real time by installing gravity sensing device additional
Output, on the contrary the power output of oil machine can be reduced with the reduction of take-off weight, and equally working as also can be accurate in flight course
Control the power output of oil machine.Pass through such accurate control, it is ensured that the power output stabilization of the electric propeller of many rotors exists
Suitable state, thus come ensure flight stability and heading it is easy to be handling
The present invention can be used in plant protection（Spray insecticide）It is very heavy that aircraft has just started take-off weight, the weight during sprinkling
Amount is more and more lighter, and general oil is electrically coupled machine will suitably reduce oil machine pulling force manually after sprinkling a period of time, and not so pulling force is excessive
Aircraft will rise automatically, can so make manipulator in a rush, be prone to accidents.Using the invention, manipulator just may not be used
With the power output for considering oil machine, need to only be operated as common multi-rotor aerocraft just can be with, so reduces manipulation difficult
Degree also add security.In addition, when implementing rescue using aircraft, empty machine, which gets on, wants carry weight by weight after hovering
Transport is sling, is usually first to increase after oil machine pulling force is sling to control flight again, oil machine pulling force is slowly reduced when reaching purpose and is come
Weight is put, so loses time very much to be also less prone to control.Normal hoisting aircraft is only needed using the invention, oil machine can increase with gravity
Plus and increase rotating speed increase pulling force automatically, transport, arrive at when putting down weight, oil machine reduces rotating speed automatically after directly slinging
Pulling force is reduced, security is also add with all manipulation difficulty that reduces.
Machine sensor compression force signal signal at ground is not converted for negative value, is turned after oil start with idling
It is dynamic, produce smaller pulling force, produce upward pulling force when taking off again by powered part, when electronic pulling force and oil machine idling produce pulling force it
With more than during moiety by weight, sensor is changed into pulling force signal from pressure signal on central plate, powered part pulling force is continued to lift up, when
When the pulling force signal that sensor is produced is certain numerical value, pulling force signal starts to be converted to controllable steering wheel signal, and throttle steering wheel is opened
Beginning work, the lifting of oil machine rotating speed, while pulling force increases, this is that powered part pulling force is constant, because oil machine pulling force increases sensor
Pulling force increases therewith, and throttle steering wheel continues to increase throttle, and rotating speed further increases, and pulling force is continued to lift up, until leaving ground, passes
Sensor starts to produce constant force, and machine can just fly up work, and equally when foot stool weight is reduced, oil machine pulling force accordingly drops
It is low,
The present invention can change pulling force size automatically in zone of reasonableness, allow powered part to be operated in optimum state to control to fly
Row posture, and electronic pulling force substantially constant, are more prone to gesture stability, double oars are reverse a little with reference to the work of double oars inversely
The torsion that each propeller is produced can be effectively offset, is that machine flight is more stablized, is more prone to realization and automatically controls.
Claims (4)
1. a kind of oil electricity mixing multi-rotor aerocraft, including carry the flying body of battery（1）, it is characterised in that：Described
Flying body（1）On be provided with controller（2）, controller（2）The flying body of top（1）On be installed with gravity sensor
（3）, gravity sensor（3）Top is provided with central plate（4）, central plate（4）Top is provided with steering wheel（5）, steering wheel（5）Top is set
It is equipped with oil machine（6）, oil machine（6）Top is provided with transfer case（7）, transfer case（7）Top and the first flying wing（9）With the second flight
The wing（8）It is connected；Described controller（2）Inside is provided with supercharging transmitter（10）Turn PWM module with voltage（11）, gravity biography
Sensor（3）Pass through wire and supercharging transmitter（10）It is connected, supercharging transmitter turns PWM module by wire and voltage（11）Phase
Connection, voltage turns PWM module（11）Pass through wire and steering wheel（5）It is connected, steering wheel（5）With oil machine（6）Input throttle end phase
Connection.
2. oil electricity mixing multi-rotor aerocraft according to claim 1, it is characterised in that：Described battery is arranged on control
Device processed（2）Bottom, battery passes through wire and controller（2）And gravity sensor（3）And steering wheel（5）It is connected.
3. oil electricity mixing multi-rotor aerocraft according to claim 1, it is characterised in that：Described gravity sensor（3）
The voltage of output signal is 0 to 20mv, is pressurized transmitter（10）The voltage of output signal is 0 to 10v.
4. oil electricity mixing multi-rotor aerocraft according to claim 1, it is characterised in that：Described gravity sensor（3）
Quantity be at least 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610332130.4A CN105905293B (en) | 2016-05-19 | 2016-05-19 | A kind of oil electricity mixing multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610332130.4A CN105905293B (en) | 2016-05-19 | 2016-05-19 | A kind of oil electricity mixing multi-rotor aerocraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105905293A CN105905293A (en) | 2016-08-31 |
| CN105905293B true CN105905293B (en) | 2017-09-22 |
Family
ID=56749280
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610332130.4A Active CN105905293B (en) | 2016-05-19 | 2016-05-19 | A kind of oil electricity mixing multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105905293B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107219794B (en) * | 2017-06-13 | 2022-03-04 | 长沙灵动航空科技有限公司 | Manual and automatic voltage switching control method and device for long-endurance unmanned aerial vehicle electromechanical system |
| CN111099024B (en) * | 2018-10-29 | 2021-07-16 | 中科灵动航空科技成都有限公司 | Ignition restarting method, system and memory for oil-electricity hybrid power rotor unmanned aerial vehicle |
| CN109398704A (en) * | 2018-12-19 | 2019-03-01 | 向杰 | A kind of urgent transport flight equipment |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6378470B1 (en) * | 1999-08-10 | 2002-04-30 | James R. Keever | Rotary engine and helicopter application |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN204895855U (en) * | 2015-09-11 | 2015-12-23 | 辽宁力德航空科技有限公司 | Many rotors of oil -electricity hybrid vehicle unmanned vehicles |
| CN105197232A (en) * | 2015-10-10 | 2015-12-30 | 南昌华梦达航空科技发展有限公司 | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle |
| CN105460212A (en) * | 2015-11-29 | 2016-04-06 | 陈蜀乔 | Oil-electric hybrid power multi-rotor aircraft |
| CN205738082U (en) * | 2016-05-19 | 2016-11-30 | 新野宇丰实业有限公司 | A kind of oil electricity mixing multi-rotor aerocraft |
-
2016
- 2016-05-19 CN CN201610332130.4A patent/CN105905293B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6378470B1 (en) * | 1999-08-10 | 2002-04-30 | James R. Keever | Rotary engine and helicopter application |
| CN104986328A (en) * | 2015-06-24 | 2015-10-21 | 辽宁锐翔通用航空有限公司 | Variable-propeller-pitch multi-rotor aircraft driven by multiple oil engines |
| CN204895855U (en) * | 2015-09-11 | 2015-12-23 | 辽宁力德航空科技有限公司 | Many rotors of oil -electricity hybrid vehicle unmanned vehicles |
| CN105197232A (en) * | 2015-10-10 | 2015-12-30 | 南昌华梦达航空科技发展有限公司 | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle |
| CN105460212A (en) * | 2015-11-29 | 2016-04-06 | 陈蜀乔 | Oil-electric hybrid power multi-rotor aircraft |
| CN205738082U (en) * | 2016-05-19 | 2016-11-30 | 新野宇丰实业有限公司 | A kind of oil electricity mixing multi-rotor aerocraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105905293A (en) | 2016-08-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106414238B (en) | Drone configuration and battery augmentation for drone internal combustion engine, and related systems and methods | |
| CN106864747B (en) | A kind of variant efficient small vertical take-off and landing drone using distributed hybrid power | |
| CN107499506B (en) | Distributed propulsion tailstock type vertical take-off and landing fixed-wing aircraft | |
| CN106927030A (en) | A kind of oil electric mixed dynamic multi-rotor aerocraft and its flight control method | |
| CN105905293B (en) | A kind of oil electricity mixing multi-rotor aerocraft | |
| CN104859853A (en) | Six-rotor hybrid aircraft | |
| WO2020107373A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| CN106379525A (en) | Wing connected unmanned plane | |
| CN204674826U (en) | A kind of multi-rotor aerocraft | |
| CN105667780A (en) | Multi-rotor aircraft | |
| CN105882954A (en) | Hybrid-power unmanned aerial vehicle with four auxiliary wings and control method thereof | |
| CN207791151U (en) | A kind of novel hybrid complex controll aircraft | |
| CN104229137A (en) | Tailstock aircraft | |
| CN106542093A (en) | Efficient multi-rotor aerocraft | |
| CN204124364U (en) | A kind of tail sitting posture aircraft | |
| CN106741904A (en) | A kind of compound unmanned vehicle | |
| CN106427433A (en) | Amphibious mobile house generating power through wind energy and solar energy | |
| CN205738082U (en) | A kind of oil electricity mixing multi-rotor aerocraft | |
| CN104015915A (en) | Unmanned gas saucer and manufacturing method thereof | |
| CN108045569A (en) | A kind of semi-ring rotor aircraft | |
| CN211281465U (en) | Coaxial dual-rotor tilting unmanned aerial vehicle | |
| CN206871352U (en) | Hybrid power unmanned plane with small rotor | |
| CN107539468A (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN205524965U (en) | Multi -rotor aircraft | |
| CN205440864U (en) | Unmanned helicopter of many rotors |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190222 Address after: 450046 No. 82, 9th floor, No. 2 Building, No. 8 Xiangsheng Street, Zhengdong New District, Zhengzhou City, Henan Province Patentee after: Henan Tongxing Environmental Protection Technology Co.,Ltd. Address before: 473500 Xinye Yufeng Industrial Co., Ltd. in the north of the east section of Xinye County Textile Road, Nanyang City, Henan Province Patentee before: XINYE YUFENG INDUSTRIAL CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230423 Address after: F1-201, Yanhuang Science and Technology Park, No. 333 Kaiyuan Avenue, Luolong District, Luoyang City, Henan Province, 471000 Patentee after: Luoyang Liyao Aerospace Technology Co.,Ltd. Address before: 450046 No. 82, 9th floor, No. 2 Building, No. 8 Xiangsheng Street, Zhengdong New District, Zhengzhou City, Henan Province Patentee before: Henan Tongxing Environmental Protection Technology Co.,Ltd. |