CN105905293A - Oil and electricity hybrid multi-rotor aircraft - Google Patents
Oil and electricity hybrid multi-rotor aircraft Download PDFInfo
- Publication number
- CN105905293A CN105905293A CN201610332130.4A CN201610332130A CN105905293A CN 105905293 A CN105905293 A CN 105905293A CN 201610332130 A CN201610332130 A CN 201610332130A CN 105905293 A CN105905293 A CN 105905293A
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- China
- Prior art keywords
- oil
- gravity sensor
- controller
- voltage
- steering wheel
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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 41
- 238000005507 spraying Methods 0.000 description 3
- 230000032258 transport Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000010727 cylinder oil Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency 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
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to an oil and electricity hybrid multi-rotor aircraft. A controller is arranged on a flight body. A gravity sensor is fixedly installed at the portion, above the controller, of the flight body. A center board is installed above the gravity sensor. A steering engine is installed above the center board. An oil engine is arranged above the steering engine. A transfer case is arranged above the oil engine. The position above the transfer case is connected with a first flight wing and a second flight wing. The transfer case is used for outputting forward and reverse double-propeller power, the torque balance of power output is achieved through accurate adjustment, and the problem that the single-propeller torque is not balanced is solved. Through the accurate control of the controller and the gravity sensor, the power of the oil engine is stably output, meanwhile, an engine can be additionally arranged on the oil engine, and the problem about the multi-rotor power running mileage is solved through supplementary power supply of the oil engine.
Description
Technical field
The present invention relates to mechanical field, be specifically related to a kind of oil electricity mixing multi-rotor aerocraft.
Background technology
The the most handling of electronic multi-rotor aerocraft is increasingly favored by user, but cruising time and heavy－duty constrain the development of many rotors.Oil machine Dan Xuan and many rotations solve the problem of cruising time and heavy－duty, but the dynamic gyroplane of oil needs professional training to manipulate, and flight stability is not so good, thus can not be by the most well-established.The current oil electricity mixing handling bad reason of multi-rotor aerocraft is mainly: oil electric power match control is bad；The moment of torsion that the power output of oil machine produces is offset by rotating speed or the angle of electronic many rotors, it is impossible to active balance；The throttle of oil machine can only manually control, it is impossible to adjusts in real time；The balance of automatic vehicle cannot be realized, manipulator is required higher.
The present invention is to fix a single cylinder or multi-cylinder oil machine at existing multi-rotor aerocraft center, output shaft end above oil machine fixes a coaxial reverse transfer case, the power of output is passed through transfer case, the power that coaxial positive and negative both direction rotates is exported above transfer case, two power of transfer case output act on positive and negative two screws in top, the pulling force risen is provided by these positive and negative two screws, the weight size that the size of its pulling force is obtained aircraft by I/O circuit carrys out the most accurate rotating speed controlling oil machine, thus the pulling force needed for obtaining, self screw of many rotors is provided power to control flight attitude by battery, battery electric power can be carried electricity generation system by oil machine and supplement thus the flight demand that reaches long-time heavy－duty.
Summary of the invention
For the deficiencies in the prior art, the present invention provides a kind of simple in construction, easy to operate, and work and operational efficiency are high, and the oil electricity mixing multi-rotor aerocraft that automaticity is high, for solving many defects that prior art exists.
The technical scheme is that and be achieved in that: a kind of oil electricity mixing multi-rotor aerocraft, including the flying body carrying battery, it is provided with controller on described flying body, it is installed with gravity sensor on flying body above controller, gravity sensor is arranged above central plate, and central plate is arranged above steering wheel, and steering wheel is provided above oil machine, oil machine is provided above transfer case, is connected with the first flying wing and the second flying wing above transfer case.
Described controller is internally installed has supercharging transmitter and voltage to turn PWM module, gravity sensor is connected with supercharging transmitter by wire, supercharging transmitter turns PWM module by wire with voltage and is connected, voltage is turned PWM module and is connected with steering wheel by wire, and steering wheel is connected with the input throttle end of oil machine.
Described battery is arranged on controller bottom, and battery is connected by wire and controller and gravity sensor and steering wheel.
The voltage of described gravity sensor output signal is 0 to 20mv, and the voltage of supercharging transmitter output signal is 0 to 10v.
The quantity of described gravity sensor is at least 1.
The present invention has following good effect: first this product structure is simple, easy to operate, transfer case is utilized to export positive and negative pair of oar power by accurately adjusting the balance achieving power output, solve single-blade moment of torsion imbalance problem, the stable output of oil machine power by the accurate control realization of controller and gravity sensor, generator can be installed in oil machine additional simultaneously, be solved the electric power continuation of the journey problem of many rotors by oil machine supplementary power.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
Fig. 2 is controller architecture schematic diagram of the present invention.
Detailed description of the invention
As shown in Figure 1, 2, a kind of oil electricity mixing multi-rotor aerocraft, including the flying body 1 carrying battery, being provided with controller 2 on described flying body 1, the flying body 1 above controller 2 is installed with gravity sensor 3, gravity sensor 3 is arranged above central plate 4, central plate 4 is arranged above steering wheel 5, steering wheel 5 is provided above oil machine 6, and oil machine 6 is provided above transfer case 7, is connected with the first flying wing 9 and the second flying wing 8 above transfer case 7.
Described controller 2 is internally installed has supercharging transmitter 10 and voltage to turn PWM module 11, gravity sensor 3 is connected with supercharging transmitter 10 by wire, supercharging transmitter turns PWM module 11 by wire with voltage and is connected, voltage is turned PWM module 11 and is connected with steering wheel 5 by wire, and steering wheel 5 is connected with the input throttle end of oil machine 6.Described battery is arranged on controller 2 bottom, and battery is connected by wire and controller 2 and gravity sensor 3 and steering wheel 5.The voltage of described gravity sensor 3 output signal is 0 to 20mv, and the voltage of supercharging transmitter 10 output signal is 0 to 10v.The quantity of described gravity sensor 3 is at least 1.
The present invention installs gravity sensing device additional at the weight bearing area of aircraft, gravity is converted into voltage (0-5mv or 0-10mv) signal output (voltage increases) with the increase of gravity by this device, 0-10mv voltage signal is converted into the voltage signal (voltage signal of this device output can adjust output voltage between 0-10v according to the actual requirements) of 0-5v or 0-10v by voltage signal by supercharging transmitter, voltage signal is walked around and turned to PWM pulse-width signal turning PWM module by voltage, PWM pulse-width signal controls steering wheel and rotates respective angles, fill this arm of a swing arm on steering wheel and can swing corresponding amplitude according to the size of institute's loading capacity by the conversion of above-mentioned signal, swing arm connects the throttle of oil machine thus automatically controls the size of throttle.The gravitation information that this device senses is converted to the throttle control signal of oil machine to control the rotation of throttle servomotor, so that oil machine exports corresponding power and meets flight needs.Install gravity sensing device additional and can increase in real time the power output of oil machine along with the increase of take-off weight, otherwise the power output of oil machine can be reduced along with the minimizing of take-off weight, equally when also can the power output of Precise Control of Oil machine in flight course.By such accurate control, it is ensured that the power output of the electric propeller of many rotors is stable in suitable state, thus ensures the stability of flight and the most handling of heading
The present invention can use that just to have started take-off weight at plant protection (spraying insecticide) aircraft the heaviest, during spraying, weight is more and more lighter, general oil is electrically coupled machine the most suitably to reduce oil machine pulling force after spraying a period of time, not so the excessive aircraft of pulling force to rise automatically, manipulator so can be allowed in a rush, be prone to accidents.Utilize this invention manipulator just can consider the power output of oil machine, only need to operate the most permissible as common multi-rotor aerocraft, which decrease manipulation difficulty and also add security.Additionally, when rescuing utilizing aircraft to implement, want carry weight in transport of being sling by weight after the hovering up of empty machine, be usually first increase oil machine pulling force and control flight again after slinging, slowly to reduce oil machine pulling force to put weight when arriving purpose, lose time the most very much to be also less prone to control.This invention is utilized only to need normal hoisting aircraft, oil machine can increase with gravity and automatically increase rotating speed and increase pulling force, transports after directly slinging, and arrives at when putting down weight, oil machine automatically reduces rotating speed and reduces pulling force, also add security with all manipulation difficulty that reduces.
nullMachine sensor when ground this signal of signal that is stressed is that negative value is not converted，With idle after oil start，Produce less pulling force，Produced upwards pulling force again by powered part when taking off，When electronic pulling force and oil machine idling produce pulling force sum more than central plate upper part weight，Sensor is become pulling force signal from pressure signal，Continue to lift up powered part pulling force，When the pulling force signal that sensor produces is certain numerical value，Pulling force signal starts to be converted to controlled steering wheel signal，Throttle steering wheel is started working，Oil machine rotating speed promotes，Pulling force increases simultaneously，This is that powered part pulling force is constant，Increase therewith owing to oil machine pulling force increases sensor pulling force，Throttle steering wheel continues to increase throttle，Rotating speed increases further，Pulling force continues to lift up，Until leaving ground，Sensor starts to produce constant force，Machine just can fly up work，It is same when foot rest weight reduces，Oil machine pulling force reduces accordingly，
The present invention can change pulling force size automatically at zone of reasonableness, powered part is allowed to be operated in optimum state to control flight attitude, and electronic pulling force substantially constant, the work reverse in conjunction with double oars makes a little gesture stability be more prone to, the torsion that each screw produces inversely can effectively be offset by double oars, it is that machine flight is more stable, is more prone to realization and automatically controls.
Claims (5)
1. an oil electricity mixing multi-rotor aerocraft, including the flying body (1) carrying battery, it is characterized in that: on described flying body (1), be provided with controller (2), it is installed with gravity sensor (3) on the flying body (1) of controller (2) top, gravity sensor (3) is arranged above central plate (4), central plate (4) is arranged above steering wheel (5), steering wheel (5) is provided above oil machine (6), oil machine (6) is provided above transfer case (7), transfer case (7) top is connected with the first flying wing (9) and the second flying wing (8).
Oil electricity mixing multi-rotor aerocraft the most according to claim 1, it is characterized in that: described controller (2) is internally installed has supercharging transmitter (10) and voltage to turn PWM module (11), gravity sensor (3) is connected with supercharging transmitter (10) by wire, supercharging transmitter turns PWM module (11) by wire with voltage and is connected, voltage is turned PWM module (11) and is connected with steering wheel (5) by wire, and steering wheel (5) is connected with the input throttle end of oil machine (6).
Oil electricity mixing multi-rotor aerocraft the most according to claim 1, it is characterised in that: described battery is arranged on controller (2) bottom, and battery is connected by wire and controller (2) and gravity sensor (3) and steering wheel (5).
Oil electricity mixing multi-rotor aerocraft the most according to claim 2, it is characterised in that: the voltage of described gravity sensor (3) output signal is 0 to 20mv, and the voltage of supercharging transmitter (10) output signal is 0 to 10v.
Oil electricity mixing multi-rotor aerocraft the most according to claim 2, it is characterised in that: the quantity of described gravity sensor (3) is 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 |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610332130.4A CN105905293B (en) | 2016-05-19 | 2016-05-19 | A kind of oil electricity mixing multi-rotor aerocraft |
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| Publication Number | Publication Date |
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| CN105905293A true CN105905293A (en) | 2016-08-31 |
| CN105905293B CN105905293B (en) | 2017-09-22 |
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| CN201610332130.4A Active CN105905293B (en) | 2016-05-19 | 2016-05-19 | A kind of oil electricity mixing multi-rotor aerocraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107219794A (en) * | 2017-06-13 | 2017-09-29 | 长沙灵动航空科技有限公司 | A kind of long endurance unmanned aircraft oil-electricity system voltage hand control method for automatically switching and control device |
| CN109398704A (en) * | 2018-12-19 | 2019-03-01 | 向杰 | A kind of urgent transport flight equipment |
| CN111099024A (en) * | 2018-10-29 | 2020-05-05 | 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 |
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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107219794A (en) * | 2017-06-13 | 2017-09-29 | 长沙灵动航空科技有限公司 | A kind of long endurance unmanned aircraft oil-electricity system voltage hand control method for automatically switching and control device |
| CN111099024A (en) * | 2018-10-29 | 2020-05-05 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105905293B (en) | 2017-09-22 |
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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. |
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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. |
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