CN108791905A - A kind of aircraft hybrid power integrated unit - Google Patents
A kind of aircraft hybrid power integrated unit Download PDFInfo
- Publication number
- CN108791905A CN108791905A CN201710303856.XA CN201710303856A CN108791905A CN 108791905 A CN108791905 A CN 108791905A CN 201710303856 A CN201710303856 A CN 201710303856A CN 108791905 A CN108791905 A CN 108791905A
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- CN
- China
- Prior art keywords
- engine
- motor
- aircraft
- gear
- integrated unit
- 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
Links
- 238000005183 dynamical system Methods 0.000 claims abstract description 12
- 230000008878 coupling Effects 0.000 claims abstract description 7
- 238000010168 coupling process Methods 0.000 claims abstract description 7
- 238000005859 coupling reaction Methods 0.000 claims abstract description 7
- 239000000446 fuel Substances 0.000 claims abstract description 7
- 238000012423 maintenance Methods 0.000 claims abstract description 6
- 230000005540 biological transmission Effects 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 3
- 238000004064 recycling Methods 0.000 claims description 2
- 230000010006 flight Effects 0.000 claims 1
- 239000007858 starting material Substances 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 5
- 230000005611 electricity Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000008450 motivation Effects 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 239000002699 waste material Substances 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
- 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
-
- 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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Hybrid Electric Vehicles (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
- Arrangement Of Transmissions (AREA)
Abstract
The present invention provides a kind of aircraft hybrid power integrated units, which includes engine, motor, propeller, power supply, electronic control system and planetary gear mechanism.Planetary gear mechanism includes：Input terminal I；Input terminal II；Output end；External toothing axis；Brake；Planet carrier；Planetary gear；Duplicate gear；Output shaft；Speed increasing gear；Speedup axis.In the present invention, engine and motor can work independently, power coupling output can be carried out again, output power is remained to when engine or motor break down, increase dynamical system safety margin, compact-sized, engine can always work in high efficiency range, improve fuel efficiency, increase the engine components service life, engine maintenance cost is reduced, improves dynamical system safety, while motor can be as the starter of engine, it can also be used as generator use, it may insure power supply not power shortage, improve cruising ability, to General Promotion aircraft performance.
Description
Technical field
The present invention relates to aviation oil electric mixed dynamic technical field, especially a kind of aircraft is integrated single with hybrid power
Member.
Background technology
Fuel efficiency and cruising ability are the very important technical indicator of aircraft, aircraft required power when taking off
Greatly, power only accounts for half when taking off or so needed for cruising, and the type selecting of engine must meet aircraft takeoff demand first, and
Traditional engine oil consumption rate under high-power state is high, and component life reduces, this is resulted in entirely in flight profile, mission profile dynamical system
It unites inefficient, cruising power bulk redundancy causes fuel oil to waste, and reduces aircraft cruise duration；And Electric aircraft is limited
It is helpless for Large Scale Space Vehicle in the power and battery weight of motor, thus oil electric mixed dynamic system become solve this
The scheme of one problem.By long-term exploration and practice, Technology of Hybrid Electric Vehicle has been widely used on automobile, but is led in aviation
Domain is also in the experiment starting stage.Technology application how mixed will be moved to aviation field, fuel utilization ratio is improved, reduce oil consumption, increase
Add cruising ability, promote dynamical system safety, reduce engine maintenance cost etc. be presently, there are problem.
Hybrid power system can be divided into according to coupled modes：Tandem, parallel and series parallel type.Series connection may be implemented to send out
The optimum control of motivation, but energy loss is larger；Parallel connection can realize preferable transmission efficiency, but engine and export shaft mechanical
Connection, it cannot be guaranteed that engine is in preferably working region always；Series-parallel connection can then combine series connection and advantage in parallel, but skill
Art difficulty is big, and structure and control system are complicated.In aviation field, prior art can not solve the above problems very well.
Invention content
For the above problem in the prior art, the present invention provides one kind can realizing that oil moves or electronic single power is defeated
Go out, and can realize the aircraft hybrid power integrated unit of oily electric power coupling output, for solving existing aircraft fuel oil
Efficiency is low, and cruising ability is poor, and engine maintenance is of high cost etc. cannot be satisfied existing the problem of requiring.
The present invention provides a kind of aircraft hybrid power integrated unit, the aircraft is integrated single with hybrid power
Member includes engine, motor, propeller, power supply, electronic control system and planetary gear mechanism；
The planetary gear mechanism includes：Input terminal I, the input terminal I connection engines；Input terminal II, described is defeated
Enter to hold II connection motor；Output end, the output end connect propeller；External toothing axis, the external toothing axis connection are defeated
Enter to hold II；Brake, the brake can control the start and stop of external toothing axis；Planet carrier；Planetary gear, the planetary gear are mounted on
Gear ring engagement on planet carrier and on external toothing axis；Duplicate gear；Output shaft, described output shaft one end and planet carrier are fixed
Cooperation, the other end are connected with output end；Speed increasing gear；Speedup axis, the speedup axis and speed increasing gear cooperation and input terminal II
Connection；
When aircraft of the present invention couples output power with hybrid power integrated unit, engine power is incoming from input terminal I, passes through
External toothing axis transmits；Motor power (output) is incoming from input terminal II, is transmitted by speed increasing gear, duplicate gear；Pass through planetary gear
Mechanism realizes that power coupling, coupled power are exported through planet carrier, output shaft.
Preferably, the external toothing axis is that external toothing and axis are integrally formed part, and external toothing axis is set in by sliding part
Output shaft.
Preferably, the duplicate gear can slide on output shaft, and the small end gear and planetary gear of duplicate gear are nibbled
It closes, is the sun gear of planetary gear train；The big end gear and speed increasing gear of duplicate gear engage, and are the transmission gears of speedup component；
Two member parallels are arranged side by side.
Preferably, the power supply is connected with motor, provides electric energy for motor, while can store produced by motor
Electric energy.
Preferably, when the engine and motor work at the same time, using electronic control system, to engine and electronic
The input speed of machine is adjusted, and variable speed output may be implemented.
Preferably, when the engine breaks down or is stopped, when brake brakes external toothing axis, Ke Yishi
Existing motor individual output power, increases dynamical system safety margin, improves dynamical system security reliability.
Preferably, when the aircraft is started with hybrid power integrated unit, motor can opening as engine
Dynamic motor, while under different flying conditions, motor can also be used as generator, be power source charges, it is ensured that power supply will not lose
Electricity, lifting system cruising ability.
The advantageous effect of aircraft of the present invention hybrid power integrated unit：In aircraft in Integrated power unit, send out
Motivation and motor can work independently and carry out power coupling output and drive loaded work piece, while engine can also drive
Motor generates electricity extra power, improves efficiency of energy utilization, avoids power supply power shortage.Whole system is with the shape of power unit
Formula exists, compact-sized, has very strong external interference resistance, while improving fuel efficiency, reduces oil consumption, increases
Cruising ability, engine can maintain high efficiency range work, improve engine fuel efficiency always, extend the engine components longevity
Life reduces maintenance cost, improves Power System of Flight Vehicle safety, General Promotion aircraft power performance.
Description of the drawings
Fig. 1 is a kind of schematic diagram of aircraft hybrid power integrated unit according to a first embodiment of the present invention.
Figure acceptance of the bid, which is remembered, is respectively：1, engine；2, motor；3, propeller；4, power supply；5, electronic control system I；6, row
Star gear mechanism；7, input terminal I；8, input terminal II；9, output end；10, external toothing axis；11, brake；12, planet carrier；13,
Planetary gear；14, duplicate gear；15, output shaft；16, speed increasing gear；17, speedup axis.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.Described embodiment is the present invention one
Section Example, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to be used for
It explains the present invention, and is not considered as limiting the invention.Based on the embodiments of the present invention, those of ordinary skill in the art
The every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Below
The embodiment of the present invention is described in detail in conjunction with attached drawing.
Present invention will be further explained below with reference to the attached drawings and specific embodiments.
As shown in Fig. 1, the present invention is a kind of first embodiment of aircraft hybrid power integrated unit, and described flies
Row device hybrid power integrated unit includes engine 1, motor 2, propeller 3, power supply 4, electronic control system 5 and planet tooth
Take turns mechanism 6；
The planetary gear mechanism 6 includes：Input terminal I7, the input terminal I7 connections engine 1；Input terminal II8, it is described
Input terminal II8 connections motor 2；Output end 9, the output end 9 connect propeller 3；External toothing axis 10, the external tooth
It encloses axis 10 and connects input terminal I7；Brake I11, the brake I11 can control the start and stop of external toothing axis 10；Planet carrier 12；
Planetary gear 13, the planetary gear 13 are mounted on the gear ring engagement on planet carrier 12 and on external toothing axis 10；Duplicate gear 14；It is defeated
Shaft 15,12 secure fit of 15 one end of output shaft and planet carrier, the other end and output end 9 connect；Speed increasing gear 16；Increase
Fast axis 17, the speedup axis 17 and the cooperation of speed increasing gear 16 are connected with input terminal II8；
When aircraft of the present invention moves output power with hybrid power integrated unit is mixed, 1 power of engine is incoming from input terminal I7, warp
Cross the transmission of external toothing axis 10；2 power of motor is incoming from input terminal II8, is transmitted by speed increasing gear 16, duplicate gear 14；It is logical
It crosses planetary gear mechanism 6 and realizes that power coupling, coupled power are exported through planet carrier 12, output shaft 15.
In the present embodiment, the duplicate gear 14 can slide on output shaft 15, the small end tooth of duplicate gear 14
Wheel and planetary gear 13 engage, and are the sun gears of planetary gear train；The big end gear and speed increasing gear 17 of duplicate gear 14 engage, and are to increase
The transmission gear of fast component；Two member parallels are arranged side by side.
In the present embodiment, the power supply 4 and motor 2 connect, and provide electric energy for motor 2, while can store
The electric energy that motor 2 generates.
In the present embodiment, when the engine 1 and motor 2 work at the same time, using electronic control system 5, to hair
The input speed of motivation 1 and motor 2 is adjusted, and variable speed may be implemented.
In the present embodiment, when the engine breaks down or is stopped, when brake brakes external toothing axis,
Motor individual output power may be implemented, increase dynamical system safety margin, improve dynamical system security reliability.
In the present embodiment, 1 individual output power of engine, motor 2 work in either a generation, will be produced
In power storage to power supply 4, while the recycling of the energy in aircraft landing may be implemented to realize that short distance lands.
In the present embodiment, when the aircraft is started with hybrid power integrated unit, motor 2, which can be used as, to be started
The startup motor of machine 1, while under different flying conditions, motor 2 can also be used as generator, charge for power supply 4, it is ensured that electricity
Source 4 will not power shortage, lifting system cruising ability.
Using the advantageous effect of above scheme：In aircraft in Integrated power unit, engine and motor can be independent
Work, and power coupling output can be carried out and drive loaded work piece, increase dynamical system safety margin；Whole system is with power unit
Form exist, it is compact-sized, have very strong external interference resistance, engine can always work in high efficiency range, carry
High fuel efficiency, increases the engine components service life, reduces engine maintenance cost, improve dynamical system safety, simultaneously
Motor can also be used as generator use as the starter of engine, it can be ensured that power supply not power shortage improves continuous
Boat ability, General Promotion aircraft power performance.
Above example is only to the technical solution that present invention be described in more detail, and it cannot be said that the specific reality of the present invention
The mode of applying is confined to these explanations.For those of ordinary skill in the art to which the present invention belongs, this hair is not being departed from
The other embodiment obtained under bright technical solution, should be included within the scope of the present invention.
Claims (9)
1. a kind of aircraft hybrid power integrated unit, the aircraft hybrid power integrated unit includes engine
（1）, motor（2）, propeller（3）, power supply（4）, electronic control system（5）And planetary gear mechanism（6）；
The planetary gear mechanism（6）Including：Input terminal I（7）, the input terminal I（7）Connect engine（1）；Input terminal
II（8）, the input terminal II（8）Connect motor（2）；Output end（9）, the output end（9）Connect propeller（3）；
External toothing axis（10）, the external toothing axis（10）Connect input terminal I（7）；Brake（11）, the brake（11）It can control
External toothing axis processed（10）Start and stop；Planet carrier（12）；Planetary gear（13）, the planetary gear（13）Mounted on planet carrier（12）On,
With external toothing axis（10）On gear ring engagement；Duplicate gear（14）；Output shaft（15）, the output shaft（15）One end and planet
Frame（12）Secure fit, the other end and output end（9）Connection；Speed increasing gear（16）；Speedup axis（17）, the speedup axis（17）
And speed increasing gear（16）Cooperation and input terminal II（8）Connection；
When aircraft of the present invention couples output power with hybrid power integrated unit, engine（1）Power is from input terminal I（7）It passes
Enter, by external toothing axis（10）Transmission；Motor（2）Power is from input terminal II（8）It is incoming, by speed increasing gear（16）, duplex
Gear（14）Transmission；Power coupling is realized by planetary gear mechanism, and coupled power is through planet carrier（12）, output shaft（15）It is defeated
Go out.
2. a kind of aircraft hybrid power integrated unit according to claim 1, which is characterized in that the external toothing axis
（10）It is that external toothing and axis are integrally formed part, external toothing axis（10）It is set in output shaft by sliding part（15）.
3. a kind of aircraft hybrid power integrated unit according to claim 2, which is characterized in that the duplicate gear
（14）It can be in output shaft（15）Upper sliding, duplicate gear（14）Small end gear and planetary gear（13）Engagement, is planetary gear train
Sun gear；Duplicate gear（14）Big end gear and speed increasing gear（16）Engagement, is the transmission gear of speedup component；Two components
It is parallel to be arranged side by side.
4. a kind of aircraft hybrid power integrated unit according to claim 3, which is characterized in that the power supply
（4）And motor（2）Connection is motor（2）Electric energy is provided, while motor can be stored（2）The electric energy of generation.
5. a kind of aircraft hybrid power integrated unit according to claim 4, which is characterized in that the engine
（1）And motor（2）When working at the same time, electronic control system is utilized（5）, to engine（1）And motor（2）Input speed
It is adjusted, variable speed may be implemented.
6. a kind of aircraft hybrid power integrated unit according to claim 5, which is characterized in that engine（1）Go out
When showing failure or being stopped, the brake（11）To external toothing axis（10）Braking, may be implemented motor（2）It is individually defeated
Go out power, increases dynamical system safety margin.
7. a kind of aircraft hybrid power integrated unit according to claim 6, which is characterized in that engine（1）It is single
Only output power, motor（2）It works in either a generation, by produced power storage to power supply（4）In, while may be implemented
The recycling of energy is to realize that short distance lands when aircraft landing.
8. a kind of aircraft hybrid power integrated unit according to claim 7, which is characterized in that the aircraft
When being started with hybrid power integrated unit, motor（2）Engine can be used as（1）Startup motor, while in different flights
Under the conditions of, motor（2）Generator is can also be used as, is power supply（4）Charging, it is ensured that power supply（4）Will not power shortage, lifting system is continuous
Boat ability.
9. a kind of aircraft hybrid power integrated unit according to claim 8, which is characterized in that the aircraft
When being worked with hybrid power integrated unit, engine（1）High efficiency range work can be maintained always, improve engine fuel effect
Rate increases the engine components service life, reduces engine maintenance cost, promotes dynamical system safety.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710303856.XA CN108791905A (en) | 2017-05-03 | 2017-05-03 | A kind of aircraft hybrid power integrated unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710303856.XA CN108791905A (en) | 2017-05-03 | 2017-05-03 | A kind of aircraft hybrid power integrated unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108791905A true CN108791905A (en) | 2018-11-13 |
Family
ID=64053578
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710303856.XA Pending CN108791905A (en) | 2017-05-03 | 2017-05-03 | A kind of aircraft hybrid power integrated unit |
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| Country | Link |
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| CN (1) | CN108791905A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of the oil electric mixed dynamic matching process and system of rotary-wing aircraft |
| CN111409837A (en) * | 2020-04-28 | 2020-07-14 | 深圳市三庆新能源科技有限公司 | Hybrid power driving device and unmanned aerial vehicle |
| CN111674544A (en) * | 2020-06-19 | 2020-09-18 | 四川省天域航通科技有限公司 | Large-scale freight transportation unmanned aerial vehicle's screw device and actuating system thereof |
| CN111846253A (en) * | 2019-04-25 | 2020-10-30 | 黑龙江翼飞科技有限公司 | Multi-rotor unmanned aerial vehicle timely speed regulation internal tooth planetary gear train mechanism |
| CN111976997A (en) * | 2020-07-29 | 2020-11-24 | 清华大学 | Helicopter variable-rotating-speed hybrid power system and helicopter using same |
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
| CN116215861A (en) * | 2022-11-03 | 2023-06-06 | 清华大学 | Aviation parallel hybrid power system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140010652A1 (en) * | 2012-07-09 | 2014-01-09 | Mcmaster University | Hybrid powertrain system |
| CN204037914U (en) * | 2014-07-18 | 2014-12-24 | 吉林大学 | Double dynamical output aircraft |
| CN106184779A (en) * | 2016-09-19 | 2016-12-07 | 中电科芜湖钻石飞机设计研究院有限公司 | A kind of hybrid power aeroplane coupled system |
| CN207433818U (en) * | 2017-05-03 | 2018-06-01 | 朗星无人机系统有限公司 | A kind of aircraft hybrid power integrated unit |
-
2017
- 2017-05-03 CN CN201710303856.XA patent/CN108791905A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140010652A1 (en) * | 2012-07-09 | 2014-01-09 | Mcmaster University | Hybrid powertrain system |
| CN204037914U (en) * | 2014-07-18 | 2014-12-24 | 吉林大学 | Double dynamical output aircraft |
| CN106184779A (en) * | 2016-09-19 | 2016-12-07 | 中电科芜湖钻石飞机设计研究院有限公司 | A kind of hybrid power aeroplane coupled system |
| CN207433818U (en) * | 2017-05-03 | 2018-06-01 | 朗星无人机系统有限公司 | A kind of aircraft hybrid power integrated unit |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606701A (en) * | 2018-11-27 | 2019-04-12 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of the oil electric mixed dynamic matching process and system of rotary-wing aircraft |
| CN111846253A (en) * | 2019-04-25 | 2020-10-30 | 黑龙江翼飞科技有限公司 | Multi-rotor unmanned aerial vehicle timely speed regulation internal tooth planetary gear train mechanism |
| CN111409837A (en) * | 2020-04-28 | 2020-07-14 | 深圳市三庆新能源科技有限公司 | Hybrid power driving device and unmanned aerial vehicle |
| CN111674544A (en) * | 2020-06-19 | 2020-09-18 | 四川省天域航通科技有限公司 | Large-scale freight transportation unmanned aerial vehicle's screw device and actuating system thereof |
| CN111976997A (en) * | 2020-07-29 | 2020-11-24 | 清华大学 | Helicopter variable-rotating-speed hybrid power system and helicopter using same |
| CN111976997B (en) * | 2020-07-29 | 2022-04-19 | 清华大学 | Helicopter variable-rotating-speed hybrid power system and helicopter using same |
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
| CN116215861A (en) * | 2022-11-03 | 2023-06-06 | 清华大学 | Aviation parallel hybrid power system |
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Application publication date: 20181113 |