CN104773297A - Electric-driven unmanned helicopter - Google Patents
Electric-driven unmanned helicopter Download PDFInfo
- Publication number
- CN104773297A CN104773297A CN201510205421.2A CN201510205421A CN104773297A CN 104773297 A CN104773297 A CN 104773297A CN 201510205421 A CN201510205421 A CN 201510205421A CN 104773297 A CN104773297 A CN 104773297A
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- motor
- machine controller
- electric machine
- electric
- helicopter
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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
Abstract
The invention relates to an electric-driven unmanned helicopter which comprises a helicopter body, a tail beam, a speed reducer, a power battery pack (1), a motor and a motor controller. The power battery pack (1) can supply power for the motor controller (2) through two wires b (6); the motor controller (2) is connected with the motor (3) through three wires a (5) and can supply power for the motor (3), so that the motor (3) can be driven to rotate; the motor controller (2) can change the current size through a multiphase staggered parallel-connection Buck circuit, so that the rotating speed of the motor can be changed, the variable speed output of the helicopter in a full-power state can be obtained, and the cruise efficiency at low blade tip speed is improved. Meanwhile, the fuel consumption of the electric-driven helicopter is eliminated, and the noise of the helicopter is reduced.
Description
Technical field
The present invention relates to electric drive Helicopter Technology field.
Background technology
Along with the development of Helicopter Technology, require more and more higher to the environmental-protecting performance of helicopter, electric drive helicopter becomes new trend.Conventional helicopter mechanism type is using aero-engine as propulsion source, and during flight, fuel oil consumption is huge, the tail gas pollution environment of discharge, and the noise of aero-engine arrives 95dB greatly.The rotation speed change scope of aero-engine is little, and helicopter variable speed under full power state can not be made to export.
Summary of the invention
In order to solve the problem, the invention provides a kind of electric drive depopulated helicopter, eliminating the aero-engine in helicopter, eliminate fuel oil consumption, reduce helicopter noise.The variable speed of helicopter under full power state can be realized export, improve the cruise efficiency at low tip speed.
Electric drive depopulated helicopter of the present invention, comprise the fuselage of helicopter, tail boom and retarder etc., also comprise power battery pack, motor and electric machine controller, wherein, power battery pack is powered to electric machine controller by two wire b, and electric machine controller by three wire a connection motors and to feeding electric motors, thus realizes motor rotation.Described electric machine controller changes the size of electric current by the Buck circuit of multiphase interleaving, thus changes the rotating speed of motor; Power battery pack is fixed on fuselage by installing frame, and motor and electric machine controller are fixed on fuselage by mounting bracket.
Preferably, described retarder comprises main reduction gear and tail reducer, and main reduction gear is connected with motor by spline.
In above-mentioned either a program preferably, described tail reducer is fixed in tail boom by mounting bracket, and described tail reducer is connected with described main reduction gear by plunging joint, and motor can drive rotor and tail-rotor to rotate by main reduction gear and tail reducer.
In above-mentioned either a program preferably, electric machine controller is made up of the Buck changer of three-phase crisscross parallel, three phase inverter bridge and DSP control system, the power main loop of electric machine controller carries out pressure regulation by described three-phase interleaving buck converte, export to described three phase inverter bridge, control and then drive motor body high-speed cruising through corresponding.
In above-mentioned either a program preferably, the variable voltage control of described DSP control system controls by carrying out the control of Current Voltage inner ring, the sharing control of heterogeneous Buck and rotating speed outer shroud control realization on the Buck changer of described three-phase crisscross parallel.
Key point of the present invention is:
Electric current superposes mutually, reduces input, output current ripple, reduces electromagnetic interference, improves the power density of system; The conduction loss of switching valve, square being directly proportional of Copper Foil loss and received current effective value.Reduce conduction loss, improve efficiency; Because each phase current reduces, small-sized outputting inductance can be adopted, easily integrated, transient response speed during load changing is improved.
Accompanying drawing explanation
Fig. 1 is the structural representation of the preferred embodiment according to electric drive depopulated helicopter of the present invention.
Fig. 2 is the connection diagram of power battery pack, motor and electric machine controller embodiment illustrated in fig. 1.
Wherein, 1 is power battery pack, and 2 is electric machine controller, and 3 is motor, and 4 is main reduction gear, and 5 is wire a, and 6 is wire b.
Detailed description of the invention
Below in conjunction with accompanying drawing, electric drive depopulated helicopter involved in the present invention is described in further details.
Driven by power helicopter of the present invention, eliminates traditional aero-engine, and adopt lithium ion battery as propulsion source, drive helicopter flight, Li-ion batteries piles is arranged in cabin, is connected with electric machine controller, for electric machine controller and motor provide power.Motor is connected with main reduction gear, during motor rotation, by main reduction gear, drives Helicopter Main rotor wing rotation.Helicopter Main rotor provides lift required for helicopter flight and pulling force, and helicopter is upwards climbed and flight forward.Tail reducer is connected with tail-rotor, drives tail-rotor to rotate, the reactive torque that tail-rotor balancing helicopter main rotor produces during motor rotation by tail reducer, keeps helicopter flight steady.
This electric drive depopulated helicopter, cancels except fuel oil consumption, reduces helicopter noise.The variable speed of helicopter under full power state can be realized export, improve the cruise efficiency at low tip speed.
Electric drive depopulated helicopter of the present invention, comprise the fuselage of helicopter, tail boom and retarder etc., also comprise power battery pack 1, motor 3 and electric machine controller 2, wherein, power battery pack 1 is powered to electric machine controller 2 by two wire b, and electric machine controller 2 by three wire a connection motors 3 and to feeding electric motors, thus realizes motor rotation.The electric machine controller 2 weight 25Kg adopted, oad is less than 550mm × 350mm × 200mm, and the described electric machine controller of operating ambient temperature-20-+60 DEG C changes the size of electric current by the Buck circuit of multiphase interleaving, thus changes the rotating speed of motor; Described driven by motor main reduction gear rotates, and main reduction gear 4 drives propeller hub and tail reducer to rotate simultaneously, and propeller hub drives rotor wing rotation, and tail reducer drives tail-rotor to rotate.Gyroplane rotate speed 100-2500 rpm; Tail-rotor rotating speed 800-6000 rpm.Rotor rotational provides lift and ahead power, realizes described driven by power helicopter and rises and flight forward.Tail-rotor rotates provides thrust, realizes the driftage of described driven by power helicopter.Power battery pack 1 is fixed on fuselage by installing frame, and motor 3 and electric machine controller 2 are fixed on fuselage by mounting bracket.
Above-mentioned 5 is wire b, refers to electric machine controller and motor connecting wire cable, and have 2 groups of lines to be connected between electric machine controller with electrical motor, one group is power lead, and another group connects the line of Hall; 6 is wire a, refers to electrokinetic cell and electric machine controller connecting cable, because of the easy problem such as overheated, adopts three-phase generation unit.
In the present embodiment, described retarder comprises main reduction gear 4 and tail reducer, and main reduction gear 4 is connected with motor by spline.Described tail reducer is fixed in tail boom by mounting bracket, and described tail reducer is connected with described main reduction gear by plunging joint, and motor can drive rotor and tail-rotor to rotate by main reduction gear and tail reducer.Electric machine controller is made up of the Buck changer of three-phase crisscross parallel, three phase inverter bridge and DSP control system, the power main loop of electric machine controller carries out pressure regulation by described three-phase interleaving buck converte, export to described three phase inverter bridge, control and then drive motor body high-speed cruising through corresponding.The variable voltage control of described DSP control system controls by carrying out the control of Current Voltage inner ring, the sharing control of heterogeneous Buck and rotating speed outer shroud control realization on the Buck changer of described three-phase crisscross parallel.
It should be noted that; electric drive depopulated helicopter of the present invention comprises any one and combination in any thereof in above-described embodiment; but embodiment recited above is only be described the preferred embodiment of the present invention; not the scope of the invention is limited; do not departing under the present invention designs spiritual prerequisite; the various distortion that the common engineering staff in this area make technical scheme of the present invention and improvement, all should fall in protection domain that claims of the present invention determine.
Claims (5)
1. an electric drive depopulated helicopter, comprise the fuselage of helicopter, tail boom and retarder, it is characterized in that: also comprise power battery pack (1), motor and electric machine controller, wherein, power battery pack (1) is powered to electric machine controller (2) by two wire b (6), electric machine controller (2) connects motor (3) by three wire a (5) and powers to motor (3), thus realize motor (3) rotation, described electric machine controller (2) changes the size of electric current by the Buck circuit of multiphase interleaving, thus change the rotating speed of motor, power battery pack (1) is fixed on fuselage by installing frame, and motor (3) and electric machine controller (2) are fixed on fuselage by mounting bracket.
2. electric drive depopulated helicopter according to claim 1, is characterized in that: described retarder comprises main reduction gear (4) and tail reducer, and main reduction gear (4) is connected with motor (3) by spline.
3. electric drive depopulated helicopter according to claim 2, it is characterized in that: described tail reducer is fixed in tail boom by mounting bracket, described tail reducer is connected with described main reduction gear by plunging joint, and motor can drive rotor and tail-rotor to rotate by main reduction gear and tail reducer.
4. electric drive depopulated helicopter according to claim 1, it is characterized in that: electric machine controller (2) is made up of the Buck changer of three-phase crisscross parallel, three phase inverter bridge and DSP control system, the power main loop of electric machine controller (2) carries out pressure regulation by described three-phase interleaving buck converte, export to described three phase inverter bridge, control and then drive motor body high-speed cruising through corresponding.
5. electric drive depopulated helicopter according to claim 4, is characterized in that: the variable voltage control of described DSP control system controls by carrying out the control of Current Voltage inner ring, the sharing control of heterogeneous Buck and rotating speed outer shroud control realization on the Buck changer of described three-phase crisscross parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510205421.2A CN104773297A (en) | 2015-04-27 | 2015-04-27 | Electric-driven unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510205421.2A CN104773297A (en) | 2015-04-27 | 2015-04-27 | Electric-driven unmanned helicopter |
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| CN104773297A true CN104773297A (en) | 2015-07-15 |
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| CN201510205421.2A Pending CN104773297A (en) | 2015-04-27 | 2015-04-27 | Electric-driven unmanned helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661329A (en) * | 2020-06-12 | 2020-09-15 | 杭州海康机器人技术有限公司 | Method and device for eliminating magnetic field interference, unmanned aerial vehicle and storage medium |
Citations (6)
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| CN103503764A (en) * | 2012-06-28 | 2014-01-15 | 珠海羽人飞行器有限公司 | Unmanned helicopter with pneumatic pollination device |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN103683989A (en) * | 2014-01-02 | 2014-03-26 | 东南大学 | Wide-input AC-DC (alternating current-direct current) converter for high-speed low-voltage power generator and control method for wide-input AC-DC converter |
| CN103888033A (en) * | 2012-12-21 | 2014-06-25 | 北京奇峰聚能科技有限公司 | Integrated dual-motor control system for magnetic-suspension energy-storing flywheel |
| EP2750969A2 (en) * | 2011-09-04 | 2014-07-09 | Eric Chantriaux | Aircraft comprising a distributed electric power unit with free wheels |
| CN104386238A (en) * | 2014-10-20 | 2015-03-04 | 深圳华越力合科技有限公司 | Agricultural unmanned helicopter |
-
2015
- 2015-04-27 CN CN201510205421.2A patent/CN104773297A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2750969A2 (en) * | 2011-09-04 | 2014-07-09 | Eric Chantriaux | Aircraft comprising a distributed electric power unit with free wheels |
| CN103503764A (en) * | 2012-06-28 | 2014-01-15 | 珠海羽人飞行器有限公司 | Unmanned helicopter with pneumatic pollination device |
| CN103888033A (en) * | 2012-12-21 | 2014-06-25 | 北京奇峰聚能科技有限公司 | Integrated dual-motor control system for magnetic-suspension energy-storing flywheel |
| CN103523199A (en) * | 2013-09-29 | 2014-01-22 | 郭献民 | Novel tubular-structure electric unmanned helicopter |
| CN103683989A (en) * | 2014-01-02 | 2014-03-26 | 东南大学 | Wide-input AC-DC (alternating current-direct current) converter for high-speed low-voltage power generator and control method for wide-input AC-DC converter |
| CN104386238A (en) * | 2014-10-20 | 2015-03-04 | 深圳华越力合科技有限公司 | Agricultural unmanned helicopter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661329A (en) * | 2020-06-12 | 2020-09-15 | 杭州海康机器人技术有限公司 | Method and device for eliminating magnetic field interference, unmanned aerial vehicle and storage medium |
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Application publication date: 20150715 |
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