CN104354870B - For electric direct-drive formula tail-rotor component, the helicopter of hybrid power helicopter - Google Patents
For electric direct-drive formula tail-rotor component, the helicopter of hybrid power helicopter Download PDFInfo
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- CN104354870B CN104354870B CN201410594441.9A CN201410594441A CN104354870B CN 104354870 B CN104354870 B CN 104354870B CN 201410594441 A CN201410594441 A CN 201410594441A CN 104354870 B CN104354870 B CN 104354870B
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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
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a kind of electric direct-drive formula tail-rotor component for hybrid power helicopter and the helicopter with it, electric direct-drive formula tail-rotor component includes：Tail-rotor；Motor, the motor is connected with the tail-rotor and drives the tail-rotor to rotate；And integral type mixed power plant, the integral type mixed power plant includes generator and engine, and the generator includes rotor, and the rotor is formed as the flywheel of engine, and the generator is connected with the motor, to drive the motor rotation.Electric direct-drive formula tail-rotor component according to embodiments of the present invention, tail-rotor passes through motor-driven, it is not necessary to additionally set deceleration device, effectively simplifies the drive mechanism of tail-rotor, and reliability is improved；Meanwhile, generator and the integrated setting of engine, the rotor of generator solves the bottleneck of conventional engines Electricity Generation as the flywheel of engine, while the weight of the integral type mixed power plant can be reduced effectively.
Description
Technical field
The present invention relates to technical field of aerospace, more particularly, to a kind of electric direct-drive for hybrid power helicopter
Formula tail-rotor component and the helicopter with the electric direct-drive formula tail-rotor component.
Background technology
Main oar is with the conventional configuration that tail-rotor is helicopter.Wherein, on the one hand tail-rotor is used for producing lateral dynamic balance main rotor
Reaction torque, on the other hand provide course on manipulation.In the related art, the frequent origins of tail-rotor power are that engine will be dynamic
Power output is delivered to tail-rotor to reducing gear by way of machine driving (such as belt pulley, power transmission shaft), drives tail-rotor to rotate.
Because the rotating speed for going out rotating speed and rotor of engine differs larger with tail-rotor rotating speed, it is necessary to be the rotation list of tail-rotor
Solely design decelerator, increases the weight of helicopter, while also reducing the reliability of helicopter.Simultaneously because tail-rotor rotating speed is relative
It is higher, it is necessary in view of overall lubrication problem, which increases the complexity of system.
Tail-rotor is changed into motor-driven design, it is necessary to increase Electricity Generation component to drive electricity for single
Dynamic tail-rotor.Produce heat larger when being worked due to high-power generator, it is necessary to be individually for its design heat abstractor, it is same to increase straight
The empty weight of the machine of liter.
The content of the invention
It is contemplated that at least solving one of technical problem in correlation technique to a certain extent.Therefore, the present invention is carried
Go out a kind of electric direct-drive formula tail-rotor component for hybrid power helicopter, it is described for the electronic straight of hybrid power helicopter
Drive formula tail-rotor lightweight packages mitigate and reliability is high.
The invention allows for a kind of with the straight of the above-mentioned electric direct-drive formula tail-rotor component for hybrid power helicopter
The machine of liter.
Electric direct-drive formula tail-rotor component for hybrid power helicopter according to embodiments of the present invention, including：Tail-rotor；Electricity
Motivation, the motor is connected with the tail-rotor and drives the tail-rotor to rotate；And integral type mixed power plant, described one
Body formula mixed power plant includes generator and engine, and the generator includes rotor, and the rotor is formed as engine
Flywheel, the generator is connected with the motor, to drive the motor rotation.
Electric direct-drive formula tail-rotor component according to embodiments of the present invention, tail-rotor passes through motor-driven, it is not necessary to additionally set
Deceleration device is put, the drive mechanism of tail-rotor is effectively simplified, reliability is improved；Meanwhile, generator is integrated with engine
Design, the rotor of generator is used as the flywheel of engine, the bottleneck of conventional engines Electricity Generation is solved, while having
Effect reduces the weight of the integral type mixed power plant, so as to reduce the empty weight of helicopter and improve the reliability of power transmission
Property.
In addition, the electric direct-drive formula tail-rotor component for hybrid power helicopter according to the above embodiment of the present invention may be used also
With with following additional technical characteristic：
According to one embodiment of present invention, the generator be embedded into the engine interior and with the engine
Piston is shared machine oil the generator is cooled down with using machine oil.
According to one embodiment of present invention, the motor has output shaft, and the tail-rotor has rotary shaft, described defeated
Shaft is joined directly together to control the rotating speed of the tail-rotor with the rotary shaft.
According to one embodiment of present invention, the electric direct-drive formula tail-rotor component for hybrid power helicopter also includes electricity
Cell system, the battery system is connected with the motor.
According to one embodiment of present invention, the battery system is connected with the generator and stores the generator and produces
Raw electric energy.
According to one embodiment of present invention, the electric direct-drive formula tail-rotor component for hybrid power helicopter also includes becoming
Away from operating mechanism, the pitch control mechanism is connected to control the pitch of the tail-rotor with the tail-rotor.
Helicopter according to embodiments of the present invention, including the electricity for hybrid power helicopter according to embodiments of the present invention
Dynamic direct-drive type tail-rotor component.
Additional aspect of the invention and advantage will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by practice of the invention.
Brief description of the drawings
Fig. 1 is the internal structure schematic diagram of electric direct-drive formula tail-rotor component according to embodiments of the present invention；
Fig. 2 is that the structure of the integral type mixed power plant of electric direct-drive formula tail-rotor component according to embodiments of the present invention is shown
It is intended to.
Reference：
Electric direct-drive formula tail-rotor component 100；
Tail-rotor 10；
Motor 20；
Integral type mixed power plant 30；Engine 31；Housing 311；Output shaft 312；Generator 32；
Battery system 40.
Specific embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from start to finish
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
It is exemplary to scheme the embodiment of description, it is intended to for explaining the present invention, and be not considered as limiting the invention.
Describe the electric direct-drive formula for hybrid power helicopter according to embodiments of the present invention in detail below in conjunction with the accompanying drawings
Tail-rotor component 100.
Shown referring to Figures 1 and 2, the according to embodiments of the present invention electric direct-drive formula tail-rotor for hybrid power helicopter
Component 100 includes tail-rotor 10, motor 20 and integral type mixed power plant 30.Integral type mixed power plant 30 can be mixed
Close power helicopter and power resources are provided.
Specifically, integral type mixed power plant 30 includes generator 32 and engine 31, the electricity that generator 32 sends
Motor 20 can be transferred to, be rotated with drive motor 20.Motor 20 is connected with tail-rotor 10, and motor 20 drives 10 turns of tail-rotor
It is dynamic.Thus, tail-rotor 10 is driven by motor 20, and need not be driven through machine driving by engine 31, so that without installing
The deceleration device of tail-rotor 10, effectively simplifies the structure of tail-rotor transmission system, while reducing the weight of helicopter, improves
The reliability of helicopter.
Wherein, motor 20 has output shaft, and tail-rotor 10 has rotary shaft, and the output shaft of motor 20 can be with tail-rotor 10
Rotary shaft be joined directly together, without decelerator and power transmission shaft, tail-rotor 10 directly passes through motor-driven, tail-rotor transmission system for centre
Simpler direct, unlubricated requirement reduces system complexity, increases lifetime of system.
Generator 32 includes rotor, and rotor is formed as the flywheel of engine 31.That is, the rotor and hair of generator 32
The flywheel of motivation 31 is structural member, the structural member operationally, while as the rotor and engine 31 of generator 32
Flywheel is used.In the design process, the rotor of generator 32 and the rotary inertia of flywheel are suitable, and engine 31 is being effectively ensured just
Often operating.
It should be noted that for usual engine, the piston of engine drives crank rotation, bent axle by connecting rod
It is connected with flywheel.Flywheel mainly ensures that engine piston remains to remain in operation at equilbrium position with its inertia, therefore flywheel
Quality cannot mitigate.
And electric direct-drive formula tail-rotor component 100 according to embodiments of the present invention, substitute hair by with the rotor of generator 32
The flywheel of motivation 31, while operation, engine 31 can also normally run generator 32, and generating link no longer individually sets
Put, effectively improve the integrated level of the integral type mixed power plant 30 and reduce the weight of the integral type mixed power plant 30
Amount, so as to reduce the empty weight of helicopter and improve the reliability of power transmission.
As shown in Fig. 2 generator 32 is located in the housing 311 of engine 31, i.e., generator 32 is embedded into engine 31
It is internal.Thus, the rotor of generator 32 shares machine oil with the piston of engine 31, by using the machine oil of engine 31 to generating electricity
The power coil of machine 32 is cooled down, so as to the radiating of built-in high power generator is effectively ensured.
As shown in figure 1, electric direct-drive formula tail-rotor component 100 according to embodiments of the present invention can also include battery system
40, battery system 40 is connected with motor 20.Battery system 40 can provide electric energy to motor 20, drive motor 20
Dynamic tail-rotor 10 is rotated.In the case where integral type mixed power plant 30 cannot provide the driving electric energy of enough tail-rotors 10, Ke Yitong
Crossing battery system 40 carries out energy supplement, and after the integral type mixed power plant 30 failure, the energy of tail-rotor 10 can
To be provided by battery system 40 completely, so as to greatly improve the reliability of helicopter.
Further, battery system 40 can be connected with generator 32, generator 32 can by the electric energy of generation transmit to
Battery system 40.Battery system 40 includes energy content of battery memory cell and battery management unit, and battery system 40 can store hair
The electric energy that motor 32 is produced, it is possible to further transmit to motor 20 electric energy.
In some embodiments of the invention, electric direct-drive formula tail-rotor component 100 can also include pitch control mechanism (figure
It is not shown), pitch control mechanism is connected with tail-rotor 10.Pitch control mechanism can control the pitch of tail-rotor 10, make tail-rotor 10
Rotating speed and pitch are realized coordinating control simultaneously, improve the operating efficiency of tail-rotor 10.Wherein, pitch control mechanism and helicopter
Flight control system is connected, and pitch control mechanism controls the torque of tail-rotor 10 according to control command.
In a word, electric direct-drive formula tail-rotor component 100 according to embodiments of the present invention has advantages below：
1st, tail reducer and tail transmission mechanism are not needed, weight is reduced, is improve the reliability of system.
2nd, rotary shaft of the output shaft of motor 20 directly with tail-rotor 10 is connected, and unlubricated requirement reduces system complex
Degree, extends lifetime of system.
3rd, the displacement and rotating speed of tail-rotor 10 are simultaneously controllable, improve the efficiency of tail-rotor 10.
4th, engine 31 collectively forms mixed power plant, the single high-power hair of removal with the integrated design of generator 32
Electric link, alleviates weight, improves generating efficiency.
Helicopter according to embodiments of the present invention includes the electricity for hybrid power helicopter according to embodiments of the present invention
Dynamic direct-drive type tail-rotor component 100.The engine 31 of electric direct-drive formula tail-rotor component 100 is connected with the main rotor of helicopter.Specifically
Ground, engine 31 has been internally integrated decelerator, and output shaft 312 is connected with main oar.Electric direct-drive formula tail-rotor component 100 and main oar
Cooperate, it is ensured that the operation of helicopter.Because electric direct-drive formula tail-rotor component 100 according to embodiments of the present invention is with upper
State beneficial technique effect, therefore helicopter weight saving and reliability raising according to embodiments of the present invention.
Other of helicopter according to embodiments of the present invention constitute and operate to come for one of ordinary skill in the art
Say it is knowable, be not described in detail herein.
In the description of the invention, it is to be understood that the orientation or position of the instruction such as term "front", "rear", " interior ", " outward "
The relation of putting is, based on orientation shown in the drawings or position relationship, to be for only for ease of the description present invention and simplify description, rather than
Indicate or imply signified device or element and must have specific orientation, with specific azimuth configuration and operation, therefore can not
It is interpreted as limitation of the present invention.
In the present invention, unless otherwise clearly defined and limited, the term such as term " connected ", " connection ", " fixation " should
It is interpreted broadly, for example, it may be fixedly connected, or be detachably connected, or integrally；Can mechanically connect,
It can be electrical connection；Can be joined directly together, it is also possible to be indirectly connected to by intermediary.For the ordinary skill people of this area
For member, above-mentioned term concrete meaning in the present invention can be as the case may be understood.
In the description of this specification, the description meaning of reference term " one embodiment ", " some embodiments ", " example " etc.
Refer to that the specific features, structure, material or the feature that are described with reference to the embodiment or example are contained in of the invention at least one real
In applying example or example.In this manual, the schematic representation of above-mentioned term is necessarily directed to identical embodiment or
Example.And, the specific features of description, structure, material or feature can in any one or more embodiments or example with
Suitable mode is combined.Additionally, in the case of not conflicting, those skilled in the art can be by described in this specification
Different embodiments or the feature of example and different embodiment or example be combined and combine.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, changes, replacing and modification.
Claims (6)
1. a kind of electric direct-drive formula tail-rotor component for hybrid power helicopter, it is characterised in that including：
Tail-rotor；
Motor, the motor is connected with the tail-rotor and drives the tail-rotor to rotate；And
Integral type mixed power plant, the integral type mixed power plant includes generator and engine, the generator bag
Rotor is included, the rotor is formed as the flywheel of engine, and the generator is connected with the motor, to drive the motor
Rotate, the generator is embedded into the engine interior and shares machine oil with the piston of the engine to utilize machine oil to institute
Generator is stated to be cooled down.
2. the electric direct-drive formula tail-rotor component for hybrid power helicopter according to claim 1, it is characterised in that institute
Stating motor has output shaft, and the tail-rotor has rotary shaft, and the output shaft is joined directly together to control with the rotary shaft
State the rotating speed of tail-rotor.
3. the electric direct-drive formula tail-rotor component for hybrid power helicopter according to claim 1, it is characterised in that also
Including battery system, the battery system is connected with the motor.
4. the electric direct-drive formula tail-rotor component for hybrid power helicopter according to claim 3, it is characterised in that institute
State the electric energy that battery system is connected with the generator and stores the generator generation.
5. the electric direct-drive formula tail-rotor component for hybrid power helicopter according to any one of claim 1-4, its
It is characterised by, also including pitch control mechanism, the pitch control mechanism is connected to control the oar of the tail-rotor with the tail-rotor
Away from.
6. a kind of helicopter, it is characterised in that including any one of claim 1-5 for hybrid power helicopter
Electric direct-drive formula tail-rotor component.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410594441.9A CN104354870B (en) | 2014-10-29 | 2014-10-29 | For electric direct-drive formula tail-rotor component, the helicopter of hybrid power helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410594441.9A CN104354870B (en) | 2014-10-29 | 2014-10-29 | For electric direct-drive formula tail-rotor component, the helicopter of hybrid power helicopter |
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| Publication Number | Publication Date |
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| CN104354870A CN104354870A (en) | 2015-02-18 |
| CN104354870B true CN104354870B (en) | 2017-06-06 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667786B (en) * | 2016-01-12 | 2017-11-10 | 深圳清华大学研究院 | The tail-rotor drive system and its control method of helicopter, helicopter |
| CN105966609B (en) * | 2016-05-26 | 2019-11-26 | 北京理工大学 | A kind of heavy autogyro hybrid power richochet system with variable-distance teetering rotor head |
| CN110155344B (en) * | 2019-05-17 | 2021-01-12 | 清华大学 | Hybrid power unmanned helicopter energy control system and helicopter with same |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101249888A (en) * | 2003-01-17 | 2008-08-27 | 杨福顺 | Hybrid power-drive mechanism |
| CN102933461A (en) * | 2010-05-19 | 2013-02-13 | 伊德斯德国股份有限公司 | Hybrid drive for helicopters |
| CN102971216A (en) * | 2010-05-19 | 2013-03-13 | 伊德斯德国股份有限公司 | Hybrid drive and energy system for aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4936247A (en) * | 1988-09-06 | 1990-06-26 | Sundstrand Corporation | Visual and tactile indication of coupling status of an integrated drive generator |
| CN203806139U (en) * | 2014-02-12 | 2014-09-03 | 无锡汉和航空技术有限公司 | Hybrid-type minitype unmanned helicopter |
| CN203819019U (en) * | 2014-03-25 | 2014-09-10 | 天津市松正电动汽车技术股份有限公司 | Hybrid power system structure |
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2014
- 2014-10-29 CN CN201410594441.9A patent/CN104354870B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101249888A (en) * | 2003-01-17 | 2008-08-27 | 杨福顺 | Hybrid power-drive mechanism |
| CN102933461A (en) * | 2010-05-19 | 2013-02-13 | 伊德斯德国股份有限公司 | Hybrid drive for helicopters |
| CN102971216A (en) * | 2010-05-19 | 2013-03-13 | 伊德斯德国股份有限公司 | Hybrid drive and energy system for aircraft |
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| CN104354870A (en) | 2015-02-18 |
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Effective date of registration: 20161128 Address after: 518057 Guangdong city of Shenzhen province high tech Industrial Park, high-tech South Road seven Shenzhen Research Institute of Tsinghua University Applicant after: Shenzhen Institute of Stinghua University Address before: 100084 Haidian District 100084-82 mailbox Beijing Applicant before: Tsinghua University Applicant before: Shenzhen Institute of Stinghua University |
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Effective date of registration: 20180320 Address after: 100084 Beijing City, Haidian District Tsinghua Yuan Patentee after: Tsinghua University Address before: 518057 Guangdong city of Shenzhen province high tech Industrial Park, high-tech South Road seven Shenzhen Research Institute of Tsinghua University Patentee before: Shenzhen Institute of Stinghua University |
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Effective date of registration: 20211009 Address after: 519040 plant a, No. 10, sanjiawan ninth Road, Jinwan District, Zhuhai City, Guangdong Province Patentee after: ZHUHAI LONGHUA HELICOPTER TECHNOLOGY Co.,Ltd. Address before: 100084 Tsinghua Yuan, Beijing, Haidian District Patentee before: TSINGHUA University |
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