CN106184779A - A kind of hybrid power aeroplane coupled system - Google Patents
A kind of hybrid power aeroplane coupled system Download PDFInfo
- Publication number
- CN106184779A CN106184779A CN201610831435.XA CN201610831435A CN106184779A CN 106184779 A CN106184779 A CN 106184779A CN 201610831435 A CN201610831435 A CN 201610831435A CN 106184779 A CN106184779 A CN 106184779A
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- Prior art keywords
- electromotor
- transmission shaft
- power transmission
- aeroplane
- coupled system
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- 230000005540 biological transmission Effects 0.000 claims abstract description 58
- 230000008878 coupling Effects 0.000 abstract description 10
- 238000010168 coupling process Methods 0.000 abstract description 10
- 238000005859 coupling reaction Methods 0.000 abstract description 10
- 238000010276 construction Methods 0.000 abstract description 5
- 230000005611 electricity Effects 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- FGRBYDKOBBBPOI-UHFFFAOYSA-N 10,10-dioxo-2-[4-(N-phenylanilino)phenyl]thioxanthen-9-one Chemical compound O=C1c2ccccc2S(=O)(=O)c2ccc(cc12)-c1ccc(cc1)N(c1ccccc1)c1ccccc1 FGRBYDKOBBBPOI-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000002372 labelling Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
nullThe present invention provides a kind of hybrid power aeroplane coupled system being applied to hybrid power aeroplane technical field，The hybrid power aeroplane coupled system of described hybrid power aeroplane is arranged between driving motor (2) and propeller (3)，Coupled system includes epicyclic train (4)，The sun gear (5) of epicyclic train (4) is connected with driving motor (2)，Planetary gear (6) engages with sun gear (5) and gear ring (7)，Planet carrier (8) engages with the drive (10) on power transmission shaft (9)，Propeller (3) is connected with power transmission shaft (9) one end，Electromotor (1) is connected with power transmission shaft (9) other end，The hybrid power aeroplane coupled system of the present invention，Simple in construction，Convenient and reliable can realize the connection in aircraft power source and propeller，Realize the electromotor of aircraft and the power coupling driving motor，Thus effectively control electromotor work，General Promotion aeroplane performance.
Description
Technical field
The invention belongs to hybrid power aeroplane technical field, more specifically, relate to a kind of hybrid power aeroplane coupling
System.
Background technology
Along with energy crisis and environmental pollution are day by day serious, development new forms of energy aircraft is an inexorable trend, and wherein electricity is made
It is preferred option for clean energy resource, owing to being restricted by battery technology, it is desirable to have individual transition scheme, this generates oil electricity mixing
Dynamical system scheme.Oil electric mixed dynamic system framework mainly has tandem at present, parallel, series parallel type etc.；Tandem energy
Utilization rate is relatively low, simple in construction；Parallel type energy utilization rate is higher than tandem, and structure is more complicated；Series parallel type capacity usage ratio is relatively
Height, structure is complicated.The parallel one of which important technology difficult point with series parallel type, it is simply that how to go the synthesis solving power to ask
Topic, i.e. engine power how with the power coupling driving motor.Scheme of the prior art cannot solve above-mentioned asking well
Topic.
Summary of the invention
The technical problem to be solved is: for the deficiencies in the prior art, it is provided that one can convenient and reliable reality
Existing aircraft power source and the connection of propeller, it is achieved the electromotor of aircraft and the power coupling driving motor, thus effectively control
Electromotor works, the hybrid power aeroplane coupled system of General Promotion aeroplane performance.
Techniques discussed above problem to be solved, the technical scheme that the present invention takes is:
The present invention is a kind of hybrid power aeroplane coupled system, and described hybrid power aeroplane includes electromotor, drives electricity
Machine, propeller, described hybrid power aeroplane coupled system is arranged between driving motor and propeller, and coupled system includes row
Star gear train, the sun gear of epicyclic train is connected with driving motor, and planetary gear engages with sun gear and gear ring, planet carrier and biography
Drive engagement on moving axis, propeller is connected with power transmission shaft one end, and electromotor is connected with the power transmission shaft other end.
Arranging rotor in described driving motor, the sun gear of epicyclic train is fixing with rotor to be connected, and passes
Moving axis is through the through hole in the middle of rotor.
Described electromotor with can control electromotor start and stop and rotating speed height control parts is connected, driving motor with can
Control to drive the control parts of motor start and stop and rotating speed height to connect.
Arrange between described electromotor and power transmission shaft and can disconnect electromotor and clutch that power transmission shaft is connected, electromotor
Being connected with the ISG motor that can start electromotor and generating, described ISG motor is connected with the battery that can store electric energy.
Described driving motor is connected with battery, and clutch is connected with power transmission shaft.
When described clutch disconnects electromotor and power transmission shaft and controls component controls driving electric machine rotation, motor is driven to set
It is set to be operated alone the structure of drive axis.
Described clutch connects electromotor and power transmission shaft and controls component controls when driving electric machine rotation, electromotor and driving
Galvanic electricity machine is configured to simultaneously drive the structure of drive axis.
When described clutch connects electromotor and power transmission shaft and controls component controls driving motor stalls, electromotor
It is configured to be operated alone the structure of drive axis.
Described gear ring is fixing with the electric machine casing driving motor to be connected.
Use technical scheme, can obtain following beneficial effect:
Hybrid power aeroplane coupled system of the present invention, according to hybrid power aeroplane flying power needs, Ke Yiyou
Electromotor works independently, and electromotor is operated alone drive axis, and transmission driving force is to propeller, it is also possible to by driving motor list
Solely work, drives motor by sun gear, planetary gear, planet carrier, drive, power transmission shaft, and transmission driving force is to propeller, it is achieved
Drive driven by motor propeller works, it is also possible to according to hybrid power aeroplane flying power needs, control electromotor and drive electricity
Machine works simultaneously, and so, the driving force of electromotor output superposes with the driving force driving motor output, it is achieved the conjunction of two kinds of power
Become, thus effectively driving force is on power transmission shaft, drives propeller works by power transmission shaft.The hybrid power aeroplane coupling of the present invention
System, simple in construction, it is possible to the convenient and reliable connection realizing aircraft power source and propeller, it is achieved the electromotor of aircraft and driving
The power coupling of motor, thus effectively control electromotor work, General Promotion aeroplane performance.
Accompanying drawing explanation
Content expressed by accompanying drawing each to this specification and the labelling in figure make brief description below:
Fig. 1 is the structural representation of hybrid power aeroplane coupled system of the present invention；
Reference is: 1, electromotor；2, motor is driven；3, propeller；4, epicyclic train；5, sun gear；6, planet
Wheel；7, gear ring；8, planet carrier；9, power transmission shaft；10, drive；11, rotor；12, through hole；13, parts are controlled；14, clutch
Device；15, ISG motor；16, battery.
Detailed description of the invention
Below against accompanying drawing, by the description to embodiment, each structure the most involved to the detailed description of the invention of the present invention
Mutual alignment and annexation, the effect of each several part and operation principle etc. between the shape of part, structure, each several part are made further
Detailed description:
As shown in Figure 1, the present invention is a kind of hybrid power aeroplane coupled system, and described hybrid power aeroplane includes sending out
Motivation 1, drive motor 2, propeller 3, described hybrid power aeroplane coupled system be arranged on driving motor 2 and propeller 3 it
Between, coupled system includes epicyclic train 4, and the sun gear 5 of epicyclic train 4 is connected with driving motor 2, planetary gear 6 and the sun
Wheel 5 and gear ring 7 engage, and planet carrier 8 engages with the drive 10 on power transmission shaft 9, and propeller 3 is connected with power transmission shaft 9 one end, starts
Machine 1 is connected with power transmission shaft 9 other end.Said structure is arranged, according to hybrid power aeroplane flying power needs, and can be by electromotor
Working independently, electromotor is operated alone drive axis, and transmission driving force is to propeller, it is also possible to by driving the independent work of motor
Making, drive motor by sun gear, planetary gear, planet carrier, drive, power transmission shaft, transmission driving force is to propeller, it is achieved drive
Driven by motor propeller works, it is also possible to according to hybrid power aeroplane flying power needs, controls electromotor and drives motor same
Time work, so, electromotor output driving force with drive motor export driving force superpose, it is achieved the synthesis of two kinds of power,
Thus effectively driving force is on power transmission shaft, drives propeller works by power transmission shaft.Hybrid power aeroplane coupling of the present invention
Assembly system, simple in construction, it is possible to the convenient and reliable connection realizing aircraft power source and propeller, it is achieved the electromotor of aircraft with drive
The power coupling of galvanic electricity machine, thus effectively control electromotor work, General Promotion aeroplane performance.
Arranging rotor 11 in described driving motor 2, the sun gear 5 of epicyclic train 4 is fixed with rotor 11
Connecting, power transmission shaft 9 is through the through hole 12 in the middle of rotor 11.Such structure, when driving motor work, drives motor to lead to
Cross rotor transmission driving force to sun gear, then arrive planetary gear, planet carrier, drive, power transmission shaft successively, transmit driving force and arrive
Propeller, it is achieved drive driven by motor propeller works, such structure, it is achieved that drive motor that propeller work is operated alone
Make, manipulate simple and reliable.
Described electromotor 1 is connected with the control parts 13 that can control electromotor 1 start and stop and rotating speed height, drives motor 2
It is connected with the control parts 13 that can control driving motor 2 start and stop and rotating speed height.Such structure, the work start and stop of electromotor
By controlling component controls, it is achieved the reliable control to electromotor.
Arrange between described electromotor 1 and power transmission shaft 9 and can disconnect electromotor 2 and clutch 14 that power transmission shaft 9 is connected,
Electromotor 2 with can start electromotor 2 and generating ISG motor 15 be connected, described ISG motor 15 with can store electric energy
Battery 16 connects.So, the setting of clutch, it is possible to realize the clutch between electromotor and power transmission shaft, when the independent work of electromotor
When work or electromotor work with driving motor simultaneously, clutch realizes the connection between electromotor and power transmission shaft, and when driving electricity
When machine works independently, the connection between electromotor and power transmission shaft is disconnected by clutch, and electromotor can be shut down, by driving motor list
Solely drive.
Described driving motor 2 is connected with battery 16, and clutch 14 is connected with power transmission shaft 9.Drive motor electric energy from
In battery, and when the electric energy of battery comes from electromotor work, drive ISG motor 15 work generating, and output be stored into battery,
And ISG motor 15 is also used for during electromotor work starting electromotor.
Described clutch 14 disconnects electromotor 1 and power transmission shaft 9 and controls parts 13 and control to drive motor 2 when rotating, and drives
Galvanic electricity machine 2 is configured to structure that power transmission shaft 9 rotate is operated alone.Such structure is arranged, when driving motor to work independently,
Need to disconnect electromotor and the connection of power transmission shaft, control component controls simultaneously and drive electric machine rotation, so, be achieved that driving electricity
Machine individually controls the purpose of propeller.
Described clutch 14 connects electromotor 1 and power transmission shaft 9 and controls parts 13 and control to drive motor 2 when rotating, and sends out
Motivation 1 and driving motor 2 are configured to simultaneously drive the structure that power transmission shaft 9 rotates.
Described clutch 14 connects electromotor 1 and power transmission shaft 9 and control parts 13 control to drive motor 2 to stop operating
Time, electromotor 1 is configured to structure that power transmission shaft 9 rotate is operated alone.Such structure arrange, engine start and with biography
Moving axis realizes connecting, it becomes possible to individually output drive force propeller.
Described gear ring 7 is fixing with the electric machine casing driving motor to be connected.So, gear ring is in stationary state.
Hybrid power aeroplane coupled system of the present invention, according to hybrid power aeroplane flying power needs, Ke Yiyou
Electromotor works independently, and electromotor is operated alone drive axis, and transmission driving force is to propeller, it is also possible to by driving motor list
Solely work, drives motor by sun gear, planetary gear, planet carrier, drive, power transmission shaft, and transmission driving force is to propeller, it is achieved
Drive driven by motor propeller works, it is also possible to according to hybrid power aeroplane flying power needs, control electromotor and drive electricity
Machine works simultaneously, and so, the driving force of electromotor output superposes with the driving force driving motor output, it is achieved the conjunction of two kinds of power
Become, thus effectively driving force is on power transmission shaft, drives propeller works by power transmission shaft.The hybrid power aeroplane coupling of the present invention
System, simple in construction, it is possible to the convenient and reliable connection realizing aircraft power source and propeller, it is achieved the electromotor of aircraft and driving
The power coupling of motor, thus effectively control electromotor work, General Promotion aeroplane performance.
Above in conjunction with accompanying drawing, the present invention is carried out exemplary description, it is clear that concrete implementation of the present invention is not by above-mentioned
The restriction of mode, if the various improvement that the method design that have employed the present invention is carried out with technical scheme, or the most improved by this
Design and the technical scheme of invention directly apply to other occasions, the most within the scope of the present invention.
Claims (9)
1. a hybrid power aeroplane coupled system, described hybrid power aeroplane includes electromotor (1), drives motor (2), spiral shell
Rotation oar (3), it is characterised in that: described hybrid power aeroplane coupled system be arranged on driving motor (2) and propeller (3) it
Between, coupled system includes epicyclic train (4), and the sun gear (5) of epicyclic train (4) is connected with driving motor (2), planetary gear
(6) engaging with sun gear (5) and gear ring (7), planet carrier (8) engages with the drive (10) on power transmission shaft (9), propeller (3)
Being connected with power transmission shaft (9) one end, electromotor (1) is connected with power transmission shaft (9) other end.
Hybrid power aeroplane coupled system the most according to claim 1, it is characterised in that: in described driving motor (2)
Arranging rotor (11), the sun gear (5) of epicyclic train (4) is fixing with rotor (11) to be connected, and power transmission shaft (9) passes
Through hole (12) in the middle of rotor (11).
Hybrid power aeroplane coupled system the most according to claim 1, it is characterised in that: described electromotor (1) with can
The control parts (13) controlling electromotor (1) start and stop and rotating speed height connect, and drive motor (2) and can control to drive motor
(2) the control parts (13) of start and stop and rotating speed height connect.
Hybrid power aeroplane coupled system the most according to claim 2, it is characterised in that: described electromotor (1) and biography
Arrange between moving axis (9) and electromotor (2) can be disconnected and clutch (14) that power transmission shaft (9) connects, electromotor (2) with can rise
The ISG motor (15) of dynamic electromotor (2) and generating connects, described ISG motor (15) and the battery (16) that can store electric energy
Connect.
Hybrid power aeroplane coupled system the most according to claim 2, it is characterised in that: described driving motor (2) with
Battery (16) connects, and clutch (14) is connected with power transmission shaft (9).
Hybrid power aeroplane coupled system the most according to claim 4, it is characterised in that: described clutch (14) disconnects
When electromotor (1) and power transmission shaft (9) and control parts (13) control to drive motor (2) to rotate, motor (2) is driven to be configured to
Structure that power transmission shaft (9) rotate is operated alone.
Hybrid power aeroplane coupled system the most according to claim 4, it is characterised in that: described clutch (14) connects
When electromotor (1) and power transmission shaft (9) and control parts (13) control to drive motor (2) to rotate, electromotor (1) and driving motor
(2) it is configured to simultaneously drive the structure that power transmission shaft (9) rotates.
Hybrid power aeroplane coupled system the most according to claim 4, it is characterised in that: described clutch (14) connects
When electromotor (1) and power transmission shaft (9) and control parts (13) control to drive motor (2) to stop operating, electromotor (1) is arranged to
Structure that power transmission shaft (9) rotate enough is operated alone.
Hybrid power aeroplane coupled system the most according to claim 1, it is characterised in that: described gear ring (7) and driving
The electric machine casing of motor (2) is fixing to be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610831435.XA CN106184779A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane coupled system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610831435.XA CN106184779A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane coupled system |
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| CN106184779A true CN106184779A (en) | 2016-12-07 |
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| CN201610831435.XA Pending CN106184779A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane coupled system |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542100A (en) * | 2017-01-13 | 2017-03-29 | 必扬星环（北京）航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
| CN107856488A (en) * | 2017-11-16 | 2018-03-30 | 四川省特种设备检验研究院 | It is a kind of can VTOL plug-in hybrid hovercar power drive system |
| CN108082500A (en) * | 2018-01-29 | 2018-05-29 | 吉林大学 | A kind of fixed-wing formula hybrid power aircraft driving device and driving method |
| CN108545199A (en) * | 2018-04-16 | 2018-09-18 | 中电科芜湖通用航空产业技术研究院有限公司 | Parallel type hybrid dynamic aircraft power system |
| CN108791905A (en) * | 2017-05-03 | 2018-11-13 | 朗星无人机系统有限公司 | A kind of aircraft hybrid power integrated unit |
| 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 |
| CN110316387A (en) * | 2018-03-30 | 2019-10-11 | 空中客车运营公司 | Propeller propulsion unit including Thermal Motor and electric motor and the aircraft including such propeller propulsion unit |
| CN116215861A (en) * | 2022-11-03 | 2023-06-06 | 清华大学 | Aviation parallel hybrid power system |
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| CN110316387A (en) * | 2018-03-30 | 2019-10-11 | 空中客车运营公司 | Propeller propulsion unit including Thermal Motor and electric motor and the aircraft including such propeller propulsion unit |
| CN108545199A (en) * | 2018-04-16 | 2018-09-18 | 中电科芜湖通用航空产业技术研究院有限公司 | Parallel type hybrid dynamic aircraft power system |
| 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 |
| CN116215861A (en) * | 2022-11-03 | 2023-06-06 | 清华大学 | Aviation parallel hybrid power system |
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| CB02 | Change of applicant information |
Address after: 241100 Anhui city of Wuhu province Wuhu Aviation Industrial Park Wuhu County Economic and Technological Development Zone office building two floor Applicant after: Wuhu Dianke in General Industrial Technology Research Institute of Aviation Company Limited Address before: 241100 Anhui city of Wuhu province Wuhu Aviation Industrial Park Wuhu County Economic and Technological Development Zone office building two floor Applicant before: CETC Wuhu diamond Aircraft Design Institute Co. Ltd. |
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| CB03 | Change of inventor or designer information |
Inventor after: Li Huiying Inventor after: Guo Mao Inventor after: Sun Xinyu Inventor after: Tan Teng Inventor after: Sheng Wenxing Inventor after: Xu Hui Inventor after: Lin Lin Inventor after: Zhang Benhui Inventor before: Li Huiying Inventor before: Lin Lin Inventor before: Zhang Benhui Inventor before: Tan Teng |
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| CB03 | Change of inventor or designer information | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161207 |
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| RJ01 | Rejection of invention patent application after publication |