CN205440864U - Unmanned helicopter of many rotors - Google Patents
Unmanned helicopter of many rotors Download PDFInfo
- Publication number
- CN205440864U CN205440864U CN201620208324.9U CN201620208324U CN205440864U CN 205440864 U CN205440864 U CN 205440864U CN 201620208324 U CN201620208324 U CN 201620208324U CN 205440864 U CN205440864 U CN 205440864U
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- China
- Prior art keywords
- rotor
- fuselage
- main rotor
- helicopter
- electromotor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model relates to an unmanned helicopter of many rotors, including fuselage, main rotor and vice rotor system, the fuselage, install be used for control the flight control of helicopter operation, still install power supply system in the fuselage, power supply system includes engine, generator and group battery, engine driven the generator, the generator does the group battery provides the electric energy, the main rotor is used for doing the helicopter provides lift, and vertical setting is in the top of fuselage, just the main rotor provides power drive by the engine, vice rotor system is used for changing the flight gesture of helicopter is fixed the week side of fuselage, vice rotor system is connected with the group battery electricity, the group battery is given vice rotor system provides the electric energy. The beneficial effects of the utility model are that: but still vertical landing after it has, and the loading capacity is big, time of endurance long, vice rotor lost efficacy does not rely on too much electronic control system, the more high characteristics of reliability.
Description
Technical field
This utility model belongs to depopulated helicopter field, is 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, limited by battery capacity, lifting capacity and flying power are extremely limited, maximum load about 20 kilograms in the case of 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 that single oil moves normal arrangement, is changed control flight attitude by the pitch of main rotor, but, its bad response, control accuracy is the highest, poor reliability, and structure is complicated, fault rate is high, and too relies on Electronic Control, and electronic device breaks down easily air crash.
Utility model content
In order to solve the problems referred to above that prior art exists, this utility model provides a kind of many rotor unmanned helicopters, and it has, and loading capacity is big, the higher feature of length in cruising time, reliability.
The technical scheme that this utility model is used 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 beneficial effects of the utility model are: electromotor drives the main rotor of contrarotation, and 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, also drive electromotor to be continuously set of cells charging, therefore, can realize need not charging the battery and change battery and use immediately, it is not necessary to worry that dead battery falls machine.Lifting capacity of the present utility model and cruising time are greatly improved, and easily realize 50 to 200 Kg load, and several hours even more long flying powers.
Accompanying drawing explanation
Fig. 1 is the structural representation of an embodiment of the present utility model.
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
This utility model 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 that electromotor 7, electromotor 4 and set of cells 5, described electromotor 4 electrically connect 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 (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 present utility model, 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 first main rotor and the installation and removal of the second main rotor.According to the needs of Different Altitude, being replaced main rotor, main rotor is realized at each altitude by different rotating speeds.Therefore, not incline structure, this makes structure significantly simplify, greatly increases reliability, almost without maintaining.
Connect helical gear on the output shaft of electromotor 7 and carry out power transmission, the most described first main rotor, the tip of the axis that turns of the second main rotor are 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 realizes 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 during helicopter flight 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 to adjust fuselage by speed discrepancy and balances and tilt, thus realizes the motion of each parallel direction.Pose adjustment rudder face is installed below main rotor, 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.
This utility model is not limited to above-mentioned preferred forms; those skilled in the art can draw other various forms of products under enlightenment of the present utility model; no matter but in its shape or structure, make any change; every have same as the present application or akin technical scheme, within all falling within protection domain of the present utility model.
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.
Many rotor unmanned helicopters the most 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.
Many rotor unmanned helicopters the most 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.
Many rotor unmanned helicopters the most 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.
Many rotor unmanned helicopters the most 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 |
|---|---|---|---|
| CN201620208324.9U CN205440864U (en) | 2016-03-17 | 2016-03-17 | Unmanned helicopter of many rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620208324.9U CN205440864U (en) | 2016-03-17 | 2016-03-17 | Unmanned helicopter of many rotors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205440864U true CN205440864U (en) | 2016-08-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620208324.9U Expired - Fee Related CN205440864U (en) | 2016-03-17 | 2016-03-17 | Unmanned helicopter of many rotors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205440864U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644776A (en) * | 2016-03-17 | 2016-06-08 | 秦建法 | Multi-rotor unmanned helicopter |
| CN112623224A (en) * | 2020-12-30 | 2021-04-09 | 江苏大学 | Linear multi-rotor-wing plant protection aircraft structure |
-
2016
- 2016-03-17 CN CN201620208324.9U patent/CN205440864U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644776A (en) * | 2016-03-17 | 2016-06-08 | 秦建法 | Multi-rotor unmanned helicopter |
| CN112623224A (en) * | 2020-12-30 | 2021-04-09 | 江苏大学 | Linear multi-rotor-wing plant protection aircraft structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170721 Address after: 1, No. 2, electronic information industry park, Fukang Road, No. 065000, Fukang hi tech Industrial Zone, Anci District, Hebei, Langfang Patentee after: Langfang Maher Aviation Technology Co., Ltd. Address before: 062552, 6, 3 units, 501 Sunshine Road, Hai Hui Road, Cangzhou, Hebei, Renqiu Patentee before: Qin Jianfa |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160810 Termination date: 20180317 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |