CN105644776A - Multi-rotor unmanned helicopter - Google Patents
Multi-rotor unmanned helicopter Download PDFInfo
- Publication number
- CN105644776A CN105644776A CN201610152884.1A CN201610152884A CN105644776A CN 105644776 A CN105644776 A CN 105644776A CN 201610152884 A CN201610152884 A CN 201610152884A CN 105644776 A CN105644776 A CN 105644776A
- Authority
- CN
- China
- Prior art keywords
- rotor
- fuselage
- main rotor
- helicopter
- electromotor
- 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
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- 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 abstract description 6
- 239000000446 fuel Substances 0.000 claims description 7
- 230000005611 electricity Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 230000005540 biological transmission Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241001155433 Centrarchus macropterus Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
Classifications
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- 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
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- 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
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention relates to a multi-rotor unmanned helicopter. The multi-rotor unmanned helicopter comprises a fuselage, main rotors, and assistant rotor systems, wherein the fuselage is provided with a flight control system for controlling the operation of the helicopter; an electricity supply system is also mounted in the fuselage and comprises engines, a generator and a battery unit, wherein the engines drive the generator; the generator provides electric energy for the battery unit; the main rotors are used for providing lifting force for the helicopter, and are vertically arranged at the top of the fuselage, the engines provide power for driving the main rotors; the assistant rotor systems are used for changing the flight attitude of the helicopter, are fixed on the periphery side of the fuselage and are electrically connected with the battery unit; the battery unit provides electric energy for the assistant rotor systems. The multi-rotor unmanned helicopter disclosed by the invention has the beneficial effects that the loads are large, the endurance is long, the unmanned helicopter can also land perpendicularly when assistant rotors are failed without depending on an electronic control system too much, and the unmanned helicopter has the characteristic of being high in reliability and the like.
Description
Technical field
The invention belongs to depopulated helicopter field, be specifically related to a kind of many rotor unmanned helicopters.
Background technology
Existing depopulated helicopter, it mostly is battery-driven rotor and lift and gesture stability are provided, it is subject to the restriction of battery capacity, lifting capacity and flying power are extremely limited, maximum load about 20 kilograms when general increase battery, cruising time is about 10 minutes, and due to the reason of battery, frequent flier needs to carry a large amount of set of cells, and the set of cells charging interval is oversize. Therefore, battery-driven unmanned air vehicle technique index seriously limits its applied generalization. Another kind of helicopter is the helicopter of the dynamic normal arrangement of single oil, is changed control flight attitude by the pitch of main rotor, but, its bad response, control accuracy is not high, poor reliability, and structure is complicated, fault rate is high, and too relies on Electronic Control, and electronic device breaks down very easily air crash.
Summary of the invention
In order to solve the problems referred to above that prior art exists, the invention provides a kind of many rotor unmanned helicopters, it has, and loading capacity is big, cruising time length, feature that reliability is higher.
The technical solution adopted in the present invention is:
A kind of many rotor unmanned helicopters, including fuselage, main rotor and secondary rotor system,
Described fuselage, is provided with to control the flight control system that described helicopter runs; Being also equipped with electric power system in described fuselage, described electric power system includes electromotor, electromotor and set of cells, and described electromotor drives described electromotor, and described electromotor provides electric energy for described set of cells;
Described main rotor, for providing lift for described helicopter, is vertically arranged in the top of described fuselage, and described main rotor is provided power drive by electromotor;
Described secondary rotor system, for changing the flight attitude of described helicopter, is fixed on all sides of described fuselage, and described secondary rotor system electrically connects with set of cells, and described set of cells provides electric energy to described secondary rotor system.
Further, described main rotor includes the first main rotor and the second main rotor, described first main rotor and the described second coaxial setting of main rotor, and the direction of rotation of described first main rotor and the second main rotor is contrary.
Further, being additionally provided with at least one fuel engines in described fuselage, described fuel engines drives described electromotor, and described fuel engines is connected with described first main rotor, the second main-rotor drive.
Further, described secondary rotor system includes multiple secondary rotor, and the quantity of described secondary rotor is 4,6 or 8, and all of described secondary rotor is evenly distributed on all sides of described fuselage centered by described main rotor.
Further, when described helicopter flight, described electromotor is the charging of described set of cells.
The invention have the benefit that electromotor drives the main rotor of contrarotation, main rotor provides prevailing lift, and the secondary rotor of 4 to 8, periphery is responsible for secondary lift and gesture stability. Owing to main rotor is spacing not tilting rotor, its first main rotor and the second main rotor positive and negative counter-rotation time, do not produce any deflection torque, though the electric propeller of gesture stability all lost efficacy also can vertical grease it in, simply lose the ability of moving in parallel. While starting to be contrarotation main rotor offer power, electromotor is also driven to be continuously set of cells charging, therefore, it may be achieved need not charge the battery and change battery and use immediately, it is not necessary to worry that dead battery falls machine. Lifting capacity and the cruising time of the present invention are greatly improved, and easily realize 50 to 200 Kg load and several hours even flying power of longer time.
Accompanying drawing explanation
Fig. 1 is the structural representation of one embodiment of the present of invention.
In figure: 1, fuselage; 2, main rotor; 3, secondary rotor system; 4, electromotor; 5, set of cells; 6, flight control system; 7; Electromotor.
Detailed description of the invention
The invention provides a kind of many rotor unmanned helicopters, including fuselage 1, main rotor 2 and secondary rotor system 3, being provided with electric power system in described fuselage 1, described electric power system includes electromotor 7, electromotor 4 and set of cells 5, and described electromotor 4 electrically connects with described set of cells 5; Described main rotor 2, for providing lift for described helicopter, is vertically arranged in the top of described fuselage 1, and described main rotor 2 is driven by described electromotor; Described secondary rotor system 3, for changing the flight attitude of described helicopter, is fixed on all sides of described fuselage 1, and described set of cells 5 electrically connects with described secondary rotor system 3, and described secondary rotor system 3 provides power; It is also equipped with controlling the flight control system 6 that (be specially the taking off of aircraft, hover, advance, land and the action such as charging of electromotor and set of cells) described helicopter runs in described fuselage 1.
As an embodiment of the invention, as shown in Figure 1, multiple stage fuel engines 7 can be provided with in described fuselage 1, these electromotors 7 all can drive described electromotor 4 to generate electricity, when helicopter flight, electromotor 4 utilizes produced electric energy to charge for set of cells 5, therefore, without being individually for set of cells charging, also avoid the air crash accident caused because set of cells there is not electricity to run out of steam.
Described main rotor 2 includes the first main rotor and the second main rotor, described first main rotor and the described second coaxial setting of main rotor. Such as, the rotating shaft of the first main rotor and the second main rotor can vertically connect together, and keeps axis on the same line, and the first main rotor and the second main rotor are directly installed in respective rotating shaft, quick-disassembly structure can be passed through, it is achieved the installation and removal of the first main rotor and the second main rotor. Needs according to Different Altitude, are replaced main rotor, and main rotor is realized at each altitude by different rotating speeds. Therefore, not incline structure, this makes structure significantly simplify, and greatly increases reliability, almost without maintaining.
The output shaft of electromotor 7 connects helical gear and carries out power transmission, simultaneously described first main rotor, the second main rotor the tip of the axis that turns be equipped with helical gear, pass through meshed transmission gear, the rotating speed of the first main rotor and the second main rotor is identical, but direction of rotation is contrary, thus realizing the contrarotation of main rotor. Therefore, main rotor positive and negative counter-rotation time torsion cancel out each other, do not produce any deflection torque, it is not necessary to set up balance paddle, in hgher efficiency, and the most lift in helicopter flight process are provided.
Described secondary rotor system 3 includes multiple secondary rotor, and the quantity of described secondary rotor is 4,6 or 8, and in order to keep the steady of flight, all of described secondary rotor is evenly distributed on all sides of described fuselage centered by described main rotor. Flight control system 6 can drive the secondary rotor of four direction adjust fuselage balance by speed discrepancy and tilt, thus realizing the motion of each parallel direction. Main rotor is installed below pose adjustment rudder face, and gesture stability pair rotor can be coordinated under the control of flight controller to use, it is also possible to Emergency use after secondary rotor lost efficacy.
The present invention is not limited to above-mentioned preferred forms; those skilled in the art can draw other various forms of products under the enlightenment of the present invention; no matter but in its shape or structure, do any change; every have same or like with the application like technical scheme, all fall within protection scope of the present invention.
Claims (5)
1. rotor unmanned helicopter more than a kind, it is characterised in that: include fuselage, main rotor and secondary rotor system,
Described fuselage, is provided with to control the flight control system that described helicopter runs; Being also equipped with electric power system in described fuselage, described electric power system includes electromotor, electromotor and set of cells, and described electromotor drives described electromotor, and described electromotor provides electric energy for described set of cells;
Described main rotor, for providing lift for described helicopter, is vertically arranged in the top of described fuselage, and described main rotor is provided power drive by electromotor;
Described secondary rotor system, for changing the flight attitude of described helicopter, is fixed on all sides of described fuselage, and described secondary rotor system electrically connects with set of cells, and described set of cells provides electric energy to described secondary rotor system.
2. many rotor unmanned helicopters according to claim 1, it is characterized in that: described main rotor includes the first main rotor and the second main rotor, described first main rotor and the described second coaxial setting of main rotor, and the direction of rotation of described first main rotor and the second main rotor is contrary.
3. many rotor unmanned helicopters according to claim 2, it is characterized in that: in described fuselage, be provided with at least one fuel engines, described fuel engines drives described electromotor, and described fuel engines is connected with described first main rotor, the second main-rotor drive.
4. many rotor unmanned helicopters according to claim 1, it is characterized in that: described secondary rotor system includes multiple secondary rotor, the quantity of described secondary rotor is 4,6 or 8, and all of described secondary rotor is evenly distributed on all sides of described fuselage centered by described main rotor.
5. many rotor unmanned helicopters according to claim 1, it is characterised in that: when described helicopter flight, described electromotor is the charging of described set of cells.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610152884.1A CN105644776A (en) | 2016-03-17 | 2016-03-17 | Multi-rotor unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610152884.1A CN105644776A (en) | 2016-03-17 | 2016-03-17 | Multi-rotor unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105644776A true CN105644776A (en) | 2016-06-08 |
Family
ID=56493987
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610152884.1A Pending CN105644776A (en) | 2016-03-17 | 2016-03-17 | Multi-rotor unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105644776A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
| CN106114842A (en) * | 2016-07-27 | 2016-11-16 | 西安交通大学 | A kind of oil electricity mixing coaxial dual-rotor helicopter and using method thereof |
| CN106542093A (en) * | 2017-01-11 | 2017-03-29 | 刘海涛 | Efficient multi-rotor aerocraft |
| CN106628154A (en) * | 2017-02-21 | 2017-05-10 | 云南高科新农科技有限公司 | Multiple-rotor-wing unmanned aerial vehicle with double rotor wing systems |
| CN106697277A (en) * | 2016-12-09 | 2017-05-24 | 周欣 | Cascading style reverse rotor power device |
| CN106741903A (en) * | 2017-01-24 | 2017-05-31 | 天津曙光天成科技有限公司 | A kind of hybrid power unmanned plane |
| CN107054633A (en) * | 2017-01-13 | 2017-08-18 | 北京航空航天大学 | A kind of bady micro helicopter system |
| CN107187593A (en) * | 2017-06-22 | 2017-09-22 | 云南高科新农科技有限公司 | A kind of multiple degrees of freedom unmanned plane with twin rotor system |
| CN107187592A (en) * | 2017-06-15 | 2017-09-22 | 山川创智(北京)科技有限公司 | A kind of many rotors of combined type are tethered at UAS |
| CN107458595A (en) * | 2017-09-05 | 2017-12-12 | 南京荣骏科技发展有限公司 | A kind of oil electricity mixes heavily loaded multirotor helicopter |
| CN107539468A (en) * | 2017-09-01 | 2018-01-05 | 牟正芳 | A kind of multi-rotor unmanned aerial vehicle |
| CN108032994A (en) * | 2017-12-06 | 2018-05-15 | 余姚市荣事特电子有限公司 | A kind of unmanned helicopter |
| EP3375707A1 (en) * | 2017-03-17 | 2018-09-19 | Ricoh Company Ltd. | Aircraft and flight system |
| CN109398686A (en) * | 2018-09-14 | 2019-03-01 | 上海歌尔泰克机器人有限公司 | Rotor wing unmanned aerial vehicle and its attitude control method |
| CN109677622A (en) * | 2019-01-11 | 2019-04-26 | 南京航空航天大学 | The hybrid power four-rotor helicopter system of multi-operation mode |
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| CN204037896U (en) * | 2014-08-12 | 2014-12-24 | 中国航空工业经济技术研究院 | A kind of logistics depopulated helicopter |
| CN204383745U (en) * | 2015-01-17 | 2015-06-10 | 山东菁华环境科技有限公司 | A kind of engine installation of unmanned plane |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
| US9248908B1 (en) * | 2013-06-12 | 2016-02-02 | The Boeing Company | Hybrid electric power helicopter |
| CN205044954U (en) * | 2015-10-22 | 2016-02-24 | 周明 | Coaxial two thick liquid hybrid gyroplane |
| CN205440864U (en) * | 2016-03-17 | 2016-08-10 | 秦建法 | Unmanned helicopter of many rotors |
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2016
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| US9248908B1 (en) * | 2013-06-12 | 2016-02-02 | The Boeing Company | Hybrid electric power helicopter |
| CN204037896U (en) * | 2014-08-12 | 2014-12-24 | 中国航空工业经济技术研究院 | A kind of logistics depopulated helicopter |
| CN204383745U (en) * | 2015-01-17 | 2015-06-10 | 山东菁华环境科技有限公司 | A kind of engine installation of unmanned plane |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
| CN205044954U (en) * | 2015-10-22 | 2016-02-24 | 周明 | Coaxial two thick liquid hybrid gyroplane |
| CN205440864U (en) * | 2016-03-17 | 2016-08-10 | 秦建法 | Unmanned helicopter of many rotors |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005385A (en) * | 2016-06-22 | 2016-10-12 | 北京航空航天大学 | Gasoline-electric hybrid coaxial helicopter based on multi-rotor manipulation |
| CN106114842A (en) * | 2016-07-27 | 2016-11-16 | 西安交通大学 | A kind of oil electricity mixing coaxial dual-rotor helicopter and using method thereof |
| CN106114842B (en) * | 2016-07-27 | 2018-05-15 | 西安交通大学 | A kind of oil electricity mixing coaxial dual-rotor helicopter and its application method |
| CN106697277A (en) * | 2016-12-09 | 2017-05-24 | 周欣 | Cascading style reverse rotor power device |
| CN106542093A (en) * | 2017-01-11 | 2017-03-29 | 刘海涛 | Efficient multi-rotor aerocraft |
| CN107054633A (en) * | 2017-01-13 | 2017-08-18 | 北京航空航天大学 | A kind of bady micro helicopter system |
| CN107054633B (en) * | 2017-01-13 | 2020-02-14 | 北京航空航天大学 | Practical miniature helicopter system |
| CN106741903A (en) * | 2017-01-24 | 2017-05-31 | 天津曙光天成科技有限公司 | A kind of hybrid power unmanned plane |
| CN106741903B (en) * | 2017-01-24 | 2023-12-15 | 天津凤凰智能科技有限公司 | Hybrid unmanned aerial vehicle |
| CN106628154A (en) * | 2017-02-21 | 2017-05-10 | 云南高科新农科技有限公司 | Multiple-rotor-wing unmanned aerial vehicle with double rotor wing systems |
| EP3375707A1 (en) * | 2017-03-17 | 2018-09-19 | Ricoh Company Ltd. | Aircraft and flight system |
| US10717523B2 (en) | 2017-03-17 | 2020-07-21 | Ricoh Company, Ltd. | Aircraft and flight system |
| CN107187592A (en) * | 2017-06-15 | 2017-09-22 | 山川创智(北京)科技有限公司 | A kind of many rotors of combined type are tethered at UAS |
| CN107187593A (en) * | 2017-06-22 | 2017-09-22 | 云南高科新农科技有限公司 | A kind of multiple degrees of freedom unmanned plane with twin rotor system |
| CN107539468A (en) * | 2017-09-01 | 2018-01-05 | 牟正芳 | A kind of multi-rotor unmanned aerial vehicle |
| CN107458595A (en) * | 2017-09-05 | 2017-12-12 | 南京荣骏科技发展有限公司 | A kind of oil electricity mixes heavily loaded multirotor helicopter |
| CN108032994A (en) * | 2017-12-06 | 2018-05-15 | 余姚市荣事特电子有限公司 | A kind of unmanned helicopter |
| CN109398686A (en) * | 2018-09-14 | 2019-03-01 | 上海歌尔泰克机器人有限公司 | Rotor wing unmanned aerial vehicle and its attitude control method |
| CN109677622A (en) * | 2019-01-11 | 2019-04-26 | 南京航空航天大学 | The hybrid power four-rotor helicopter system of multi-operation mode |
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Application publication date: 20160608 |
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