CN105197232A - Petrol-electricity hybrid multi-rotor unmanned aerial vehicle - Google Patents
Petrol-electricity hybrid multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105197232A CN105197232A CN201510653050.4A CN201510653050A CN105197232A CN 105197232 A CN105197232 A CN 105197232A CN 201510653050 A CN201510653050 A CN 201510653050A CN 105197232 A CN105197232 A CN 105197232A
- Authority
- CN
- China
- Prior art keywords
- bevel gear
- rotor
- gear
- output
- output shaft
- 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
- 230000005611 electricity Effects 0.000 claims abstract description 15
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 9
- 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 7
- 230000005540 biological transmission Effects 0.000 abstract 3
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 210000003746 feather Anatomy 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
Landscapes
- Gear Transmission (AREA)
Abstract
The invention discloses a petrol-electricity hybrid multi-rotor unmanned aerial vehicle which comprises a power system, a conical gear transmission system, a stander, a rotor rotation output shaft and rotors, and is characterized in that the power system comprises an engine, a motor, an output shaft and a straight gear; the straight gear and a bevel gear of the conical gear transmission system are mounted on the output shaft; the bevel gear outputs power to the conical gear transmission system; a unidirectional bearing is mounted at the output end of the engine, and an engine output gear is mounted on the unidirectional bearing; a unidirectional bearing is mounted at the output end of the motor, and a motor output gear is mounted on the unidirectional bearing; and the engine output gear is meshed with the straight gear, and the motor output gear is also meshed with the straight gear. The petrol-electricity hybrid multi-rotor unmanned aerial vehicle can be switched between a petrol power mode and an electricity power mode, so that the continuation time of the aerial vehicle is prolonged.
Description
Technical field
The present invention relates to a kind of many rotor unmanned aircrafts, belong to unmanned air vehicle technique field.
Background technology
Traditional many rotor wing unmanned aerial vehicles have two kinds: one, rotor and motor coaxial, the rotating speed of rotor is changed by the size of electricity regulation and control electric current processed, thus carry out posture changing, this posture changing is very dumb, and electric key saves the rotating speed of each motor, deviation due to electronic signal often causes the fugitiveness of flying, and each rotor will expend the state of kinematic motion that much electricity goes to control flight, so want continuation of the journey for a long time will increase the capacity of battery, and the quality of the larger battery of capacity of cell is larger, this increases the weight of cost and aircraft self, also be difficult to meet long-time duration flight simultaneously, two, realize posture changing by feather, generally all have employed belt transport kinetic energy, make kinetic energy loss larger, this is for not enough many rotor unmanned aircrafts of inherently continuing a journey, and is a more fatal weakness, these shortcomings constrain its application in aviation unmanned plane field.
Summary of the invention
In order to overcome existing technological deficiency, the present invention provides a kind of oil electricity mixed dynamic many rotor unmanned aircrafts, by oil electric mixed dynamic mode, extends the cruise duration of aircraft greatly.
The technical solution used in the present invention is: the mixed dynamic many rotor unmanned aircrafts of a kind of oil electricity, comprise power system, bevel gear tooth system, frame, rotor rotational output shaft, rotor, it is characterized in that: bevel gear tooth system comprises helical wheel, 4 axles, being equipped with of each axle inputs finishing bevel gear cuter and output bevel gear wheel, power system and 4 axles are arranged in frame, the output bevel gear wheel drive rotor rotational output shaft of axle, rotor rotational output shaft drives rotor, helical wheel engages with the input finishing bevel gear cuter of each axle, described power system comprises driving engine, motor, output shaft, straight gear, output shaft is installed the helical wheel of straight gear and bevel gear tooth system, the mouth of driving engine is installed unilateral bearing and on unilateral bearing, installs driving engine output gear, the mouth of motor unilateral bearing is installed and on unilateral bearing mounted motor output gear, driving engine output gear engages with straight gear, motor output gear also engages with straight gear.
Further preferably, the output bevel gear wheel wherein on 2 axles is forward output, and the output bevel gear wheel on another 2 axles, for oppositely exporting, realizes rotating and reverse of rotor like this.
Further preferably, between the input finishing bevel gear cuter of helical wheel and axle 90 ° rotate and export.
Particularly, the input end finishing bevel gear cuter of rotor rotational output shaft is taken turns with the output bevel gear of axle and is engaged.
In order to regulate rotor distance, regulate state of flight, the basis of such scheme arranges pitch control system, described rotor rotational output shaft is set with sculler arm, pushing disk and folder pedestal, rotor mounting clamp symmetry is arranged on folder pedestal, and rotor is fixed on rotor mounting clamp, described pushing disk connects with sculler arm, pushing disk also connects with L-type connecting rod, is controlled the motion of L-type connecting rod by Servo-controller, thus the total journey of change pitch controls flight attitude.Pitch control system is constituted by 4 Servo-controllers, L-type connecting rod, folder pedestal and pushing disk.
For controlling the state of flight of aircraft, need install flight control system in frame, flight control system controls Servo-controller, driving engine, motor.
The mixed dynamic many rotor unmanned aircrafts of oil electricity of the present invention, by oil electric mixed dynamic mode, extend the cruise duration of aircraft greatly; By the electric combination drive mode of oil, reduce the danger of engine off; By gear spindle drive system, the used efficiency that the oily electricity of maximum performance mixes; By the mode of feather, make many rotors more flexible.
Accompanying drawing explanation
Fig. 1 is agent structure schematic diagram of the present invention.
Fig. 2 is power system schematic diagram of the present invention.
Fig. 3 is bevel gear tooth system schematic diagram of the present invention.
Fig. 4 is that pitch of the present invention regulates schematic diagram.
Detailed description of the invention
As Fig. 1, shown in 2 and 3, the mixed dynamic many rotor unmanned aircrafts of a kind of oil electricity, comprise frame, power system (1), bevel gear tooth system (2), pitch control system (3), rotor rotational output shaft (3-3), rotor (3-4), bevel gear tooth system (2) comprises helical wheel (2-1), 4 axles (2-3), the input finishing bevel gear cuter (2-2) at each axle (2-3) two ends and output bevel gear wheel (2-4, 2-5), also comprise the input end finishing bevel gear cuter (2-6) of rotor rotational output shaft (3-3), power system (1) and 4 axles (2-3) are arranged in frame, output bevel gear wheel (the 2-4 of axle (2-3), 2-5) engage with the input end finishing bevel gear cuter (2-6) of rotor rotational output shaft (3-3), helical wheel (2-1) engages with the input finishing bevel gear cuter (2-2) of each axle (2-3), described power system (1) comprises driving engine (1-1), motor (1-2), output shaft (1-7), straight gear (1-5), output shaft (1-7) is coaxially installed the helical wheel (2-1) of straight gear (1-5) and bevel gear tooth system (2), the mouth of driving engine (1-1) is installed unilateral bearing (1-4) and is above installed driving engine output gear (1-3) at unilateral bearing (1-4), the mouth of motor (1-2) unilateral bearing is installed and on unilateral bearing mounted motor output gear (1-6), driving engine output gear (1-3) engages with straight gear (1-5), motor output gear (1-6) also engages with straight gear (1-5).
As shown in Figure 4, described rotor rotational output shaft (3-3) upper suit sculler arm (3-6), pushing disk (3-2) and folder pedestal (3-1), rotor mounting clamp (3-1) symmetry is arranged on folder pedestal (3-7), rotor (3-4) is fixed on rotor mounting clamp (3-1), described pushing disk (3-2) connects with sculler arm (3-6), pushing disk (3-2) also connects with L-type connecting rod (3-5), controlled the motion of L-type connecting rod (3-5) by Servo-controller, thus the total journey of change pitch controls flight attitude.Pitch control system (3) is constituted by 4 Servo-controllers, L-type connecting rod (3-5), folder pedestal (3-7) and pushing disk (3-2).
More specifically, install flight control system in frame, flight control system controls Servo-controller, driving engine (1-1), motor (1-2).
As better embodiment, as shown in Figure 3, output bevel gear wheel (2-5) wherein on 2 axles (2-3) is forward output, and output bevel gear wheel (2-4) on another 2 axles (2-3) is oppositely export, and realizes rotating and reverse of rotor (3-4) like this.Between the input finishing bevel gear cuter (2-2) of helical wheel (2-1) and axle (2-3), 90 ° rotate and export.
Because driving engine output gear (1-3) and motor output gear (1-6) are all equipped with unilateral bearing, can switching power mode between driving engine (1-1) and motor (1-2), when driving engine (1-1) arrive determine revolution time, constant speed drive, when engine oil low, send signal, by flight control system Received signal strength, switch to motor (1-2) running, when motor (1-2) running is to same number of revolutions, driving engine (1-1) stops working, coaxial helical wheel (2-1) is driven to rotate by the straight gear (1-5) on output shaft (1-7), driven the input finishing bevel gear cuter (2-2) of the axle (2-3) be interspersed around helical wheel (2-1) circumference to rotate again by helical wheel (2-1), with four little input finishing bevel gear cuters (2-2) coaxial be that two forward output bevel gears take turns (2-5) and two reverse output bevel gears are taken turns (2-4) respectively, forward output bevel gear wheel (2-5) or two reverse output bevel gears wheel (2-4) can drive rotor rotational output shaft (3-3) to rotate, thus rotor (3-4) is rotated, the motion of L-type connecting rod (3-5) is controlled by Servo-controller, thus the total journey of change pitch controls flight attitude.
Claims (6)
1. the mixed dynamic many rotor unmanned aircrafts of oil electricity, comprise power system, bevel gear tooth system, frame, rotor rotational output shaft, rotor, it is characterized in that: bevel gear tooth system comprises helical wheel, 4 axles, being equipped with of each axle inputs finishing bevel gear cuter and output bevel gear wheel, power system and 4 axles are arranged in frame, the output bevel gear wheel drive rotor rotational output shaft of axle, rotor rotational output shaft drives rotor, helical wheel engages with the input finishing bevel gear cuter of each axle, described power system comprises driving engine, motor, output shaft, straight gear, output shaft is installed the helical wheel of straight gear and bevel gear tooth system, the mouth of driving engine is installed unilateral bearing and on unilateral bearing, installs driving engine output gear, the mouth of motor unilateral bearing is installed and on unilateral bearing mounted motor output gear, driving engine output gear engages with straight gear, motor output gear also engages with straight gear.
2. the mixed dynamic many rotor unmanned aircrafts of oil electricity according to claim 1, it is characterized in that: described rotor rotational output shaft is set with sculler arm, pushing disk and folder pedestal, rotor mounting clamp symmetry is arranged on folder pedestal, rotor is fixed on rotor mounting clamp, described pushing disk connects with sculler arm, pushing disk also connects with L-type connecting rod, is controlled the motion of L-type connecting rod by Servo-controller.
3. the mixed dynamic many rotor unmanned aircrafts of oil electricity according to claim 1, it is characterized in that: the output bevel gear wherein on 2 axles is taken turns as forward exports, the output bevel gear wheel on another 2 axles is oppositely output, realizes rotating and reverse of rotor like this.
4. the mixed dynamic many rotor unmanned aircrafts of oil electricity according to claim 1, is characterized in that: between the input finishing bevel gear cuter of helical wheel and axle, 90 ° rotate and export.
5. the mixed dynamic many rotor unmanned aircrafts of oil electricity according to claim 1, is characterized in that: the input end finishing bevel gear cuter of rotor rotational output shaft is taken turns with the output bevel gear of axle and engaged.
6. the mixed dynamic many rotor unmanned aircrafts of oil electricity according to claim 2, it is characterized in that: install flight control system in frame, flight control system controls Servo-controller, driving engine, motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510653050.4A CN105197232A (en) | 2015-10-10 | 2015-10-10 | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510653050.4A CN105197232A (en) | 2015-10-10 | 2015-10-10 | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105197232A true CN105197232A (en) | 2015-12-30 |
Family
ID=54945300
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510653050.4A Pending CN105197232A (en) | 2015-10-10 | 2015-10-10 | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105197232A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691611A (en) * | 2016-03-09 | 2016-06-22 | 杨小韬 | Hybrid power multi-rotor type aircraft and control method thereof |
| CN105857623A (en) * | 2016-03-28 | 2016-08-17 | 苏州妙旋无人机应用有限公司 | Engine special for unmanned aerial vehicle |
| CN105905293A (en) * | 2016-05-19 | 2016-08-31 | 新野宇丰实业有限公司 | Oil and electricity hybrid multi-rotor aircraft |
| CN106005443A (en) * | 2016-07-29 | 2016-10-12 | 安翔泰岳（镇江）航空科技有限公司 | Unmanned aerial vehicle |
| CN106477053A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | A kind of oil electricity mixes many rotor unmanned aircrafts |
| WO2017206003A1 (en) * | 2016-05-29 | 2017-12-07 | 深圳市欸阿技术有限公司 | Unmanned aerial vehicle |
| CN108945412A (en) * | 2018-06-21 | 2018-12-07 | 北京理工大学 | Dynamical system, starting control method and the system of heavy rotor craft |
| CN110869281A (en) * | 2017-06-26 | 2020-03-06 | Acc创新公司 | Rotor craft |
| CN112407303A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Many rotor unmanned aerial vehicle drive mechanism |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050011307A1 (en) * | 2003-07-16 | 2005-01-20 | Yuriy Gmirya | Split-torque gear box |
| CN101367436A (en) * | 2008-09-28 | 2009-02-18 | 沈阳锐翼科技有限公司 | Miniature hybrid power flying platform and implementing method thereof |
| US20100013223A1 (en) * | 2008-07-18 | 2010-01-21 | Eurocopter | Hybrid engine installation and a method of controlling such an engine installation |
| CN102514711A (en) * | 2011-12-02 | 2012-06-27 | 叶洪新 | Multi-rotor oil-electric hybrid aircraft |
| CN103803069A (en) * | 2012-11-15 | 2014-05-21 | 西安韦德沃德航空科技有限公司 | Bevel-gear-transmission four-rotor-wing aircraft |
| CN104139860A (en) * | 2014-04-23 | 2014-11-12 | 李晓宇 | Multi-shaft rotor aircraft and transmission mechanism thereof |
| CN203996885U (en) * | 2014-06-03 | 2014-12-10 | 王雪阳 | Combustion engine powered multirotor helicopter |
| CN104627375A (en) * | 2013-11-10 | 2015-05-20 | 华中农业大学 | Single-power multi-shaft aircraft |
-
2015
- 2015-10-10 CN CN201510653050.4A patent/CN105197232A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050011307A1 (en) * | 2003-07-16 | 2005-01-20 | Yuriy Gmirya | Split-torque gear box |
| US20100013223A1 (en) * | 2008-07-18 | 2010-01-21 | Eurocopter | Hybrid engine installation and a method of controlling such an engine installation |
| CN101367436A (en) * | 2008-09-28 | 2009-02-18 | 沈阳锐翼科技有限公司 | Miniature hybrid power flying platform and implementing method thereof |
| CN102514711A (en) * | 2011-12-02 | 2012-06-27 | 叶洪新 | Multi-rotor oil-electric hybrid aircraft |
| CN103803069A (en) * | 2012-11-15 | 2014-05-21 | 西安韦德沃德航空科技有限公司 | Bevel-gear-transmission four-rotor-wing aircraft |
| CN104627375A (en) * | 2013-11-10 | 2015-05-20 | 华中农业大学 | Single-power multi-shaft aircraft |
| CN104139860A (en) * | 2014-04-23 | 2014-11-12 | 李晓宇 | Multi-shaft rotor aircraft and transmission mechanism thereof |
| CN203996885U (en) * | 2014-06-03 | 2014-12-10 | 王雪阳 | Combustion engine powered multirotor helicopter |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691611A (en) * | 2016-03-09 | 2016-06-22 | 杨小韬 | Hybrid power multi-rotor type aircraft and control method thereof |
| CN105857623A (en) * | 2016-03-28 | 2016-08-17 | 苏州妙旋无人机应用有限公司 | Engine special for unmanned aerial vehicle |
| CN106477053A (en) * | 2016-04-13 | 2017-03-08 | 北京天宇新超航空科技有限公司 | A kind of oil electricity mixes many rotor unmanned aircrafts |
| CN105905293B (en) * | 2016-05-19 | 2017-09-22 | 新野宇丰实业有限公司 | A kind of oil electricity mixing multi-rotor aerocraft |
| CN105905293A (en) * | 2016-05-19 | 2016-08-31 | 新野宇丰实业有限公司 | Oil and electricity hybrid multi-rotor aircraft |
| CN107635871B (en) * | 2016-05-29 | 2020-02-07 | 深圳市欸阿技术有限公司 | Unmanned aerial vehicle |
| WO2017206003A1 (en) * | 2016-05-29 | 2017-12-07 | 深圳市欸阿技术有限公司 | Unmanned aerial vehicle |
| CN107635871A (en) * | 2016-05-29 | 2018-01-26 | 深圳市欸阿技术有限公司 | A kind of unmanned vehicle |
| CN106005443A (en) * | 2016-07-29 | 2016-10-12 | 安翔泰岳（镇江）航空科技有限公司 | Unmanned aerial vehicle |
| CN110869281A (en) * | 2017-06-26 | 2020-03-06 | Acc创新公司 | Rotor craft |
| US12091165B2 (en) | 2017-06-26 | 2024-09-17 | Acc Innovation Ab | Rotor flight vehicle |
| CN108945412A (en) * | 2018-06-21 | 2018-12-07 | 北京理工大学 | Dynamical system, starting control method and the system of heavy rotor craft |
| CN108945412B (en) * | 2018-06-21 | 2024-06-11 | 北京理工大学 | Power system, starting control method and system of heavy-duty rotor craft |
| CN112407303A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Many rotor unmanned aerial vehicle drive mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105197232A (en) | Petrol-electricity hybrid multi-rotor unmanned aerial vehicle | |
| RU2589212C2 (en) | Convertiplane | |
| US10814991B2 (en) | Propulsion system and methods of use thereof | |
| US20190382121A1 (en) | Aircraft system with distributed propulsion | |
| CN103803064A (en) | Belt-transmission four-rotor-wing aircraft | |
| CN105644776A (en) | Multi-rotor unmanned helicopter | |
| CN104760696A (en) | Multi-rotor aircraft | |
| CN104859853A (en) | Six-rotor hybrid aircraft | |
| CN104691753A (en) | Oil-relay multi-rotor helicopter driving system | |
| CN204056307U (en) | Unmanned aerial vehicle composite power device | |
| CN105015768A (en) | Multi-rotor aircraft | |
| CN112340032A (en) | Hybrid four-duct manned aircraft | |
| CN207791151U (en) | A kind of novel hybrid complex controll aircraft | |
| CN105480418A (en) | Ducted fixed-wing oil-electric hybrid unmanned aircraft | |
| CN205076044U (en) | Oil moves four rotor unmanned aerial vehicle power - transmission system of displacement | |
| CN105620765A (en) | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system | |
| CN103803069A (en) | Bevel-gear-transmission four-rotor-wing aircraft | |
| CN208715474U (en) | A multi-rotor drone | |
| CN103803076A (en) | Gear-transmission four-rotor-wing aircraft | |
| CN207466966U (en) | A kind of dynamic displacement quadrotor unmanned plane of oil | |
| CN103803075A (en) | Solar gear-transmission disc type multi-rotor-wing aircraft | |
| CN205440864U (en) | Unmanned helicopter of many rotors | |
| CN111874226A (en) | Tilt rotor aircraft | |
| CN205087140U (en) | Oil moves six coaxial rotor unmanned aerial vehicle frame systems of displacement | |
| CN103803073A (en) | Fuel-driven bevel-gear-transmission disc type multi-rotor-wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20151230 |