CN106275457A - A kind of hybrid power aeroplane distance increasing unit - Google Patents
A kind of hybrid power aeroplane distance increasing unit Download PDFInfo
- Publication number
- CN106275457A CN106275457A CN201610831347.XA CN201610831347A CN106275457A CN 106275457 A CN106275457 A CN 106275457A CN 201610831347 A CN201610831347 A CN 201610831347A CN 106275457 A CN106275457 A CN 106275457A
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- China
- Prior art keywords
- electromotor
- increasing unit
- hybrid power
- distance increasing
- parts
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- 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.)
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- 239000000446 fuel Substances 0.000 claims description 8
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000000605 extraction Methods 0.000 claims description 3
- 238000010276 construction Methods 0.000 abstract description 4
- 230000005611 electricity Effects 0.000 description 8
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 2
- 240000002853 Nelumbo nucifera Species 0.000 description 2
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 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
- 238000003306 harvesting Methods 0.000 description 1
- 238000002372 labelling Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B64D27/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- 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
nullThe present invention provides a kind of hybrid power aeroplane distance increasing unit being applied to aircraft product technical field，The rotary engine (1) of described hybrid power aeroplane distance increasing unit is connected with electromotor (2)，Described electromotor (2) is connected with generator control parts (3)，Generator control parts (3) are connected with high voltage power distribution parts (4)，Generator set control parts (8) are connected with the engine control device (5) of rotary engine (1)，Hybrid power aeroplane distance increasing unit of the present invention，Simple in construction，Easily and reliably the interior of aircraft engine can be converted into electric energy，Information according to load controls rotating speed and the load of electromotor，And according to the flight condition of aircraft, electric energy can be carried out reasonable distribution，Thus meet airplane load requirement，Guarantee that aircraft various aspects of performance meets requirement，Save energy resource consumption simultaneously，Avoid environment.
Description
Technical field
The invention belongs to aircraft product technical field, more specifically, relate to a kind of hybrid power aeroplane distance increasing unit.
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, parallel, series parallel type etc.；Tandem Energy harvesting
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 higher, knot
Structure is complicated.Consider, preferably tandem scheme.One crucial technological difficulties of tandem scheme, it is simply that the interior energy of fuel
Change into electric energy, and meet loading demand, increase course continuation mileage；The interior device that can change into electric energy of fuel is called increasing journey
Device.And distance increasing unit of the prior art, it is impossible to meet the demand of aircraft product.
Summary of the invention
The technical problem to be solved is: the technical deficiency existed for prior art, it is provided that a kind of structure letter
Single, it is possible to easily and reliably by the interior electric energy that can be converted into of aircraft engine, and can be according to the flight condition of aircraft to electricity
Reasonable distribution can be carried out, thus meet airplane load requirement, it is ensured that aircraft various aspects of performance meets requirement, save the energy simultaneously,
Avoid the hybrid power aeroplane distance increasing unit to environment.
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 distance increasing unit, and described hybrid power aeroplane distance increasing unit includes that rotor starts
Machine, rotary engine is connected with electromotor, and described electromotor is connected with generator control parts, and generator control parts are with high
Pressure power distribution unit connects, and generator set control parts are connected with the engine control device of rotary engine.
Described high voltage power distribution parts are connected with electrokinetic cell and driving motor respectively.
It is galvanic structure that described generator control parts are configured to the AC conversion of electromotor.
Described generator set control parts are configured to receive electrokinetic cell by network and drive the load of motor
Information, and the structure of the output according to load information demand regulation rotary engine.
Described engine control device is configured to adjust rotary engine rotating speed height and the structure of payload, sends out
When group of motors controls parts according to load information demand regulation rotary engine output, generator set control parts are set to
The structure of signal can be sent to engine control device.
Described generator set control parts are when engine control device sends signal, and engine control device is set to
Rotating speed height and the structure of payload of rotary engine is adjusted according to aforementioned signal.
Described rotary engine includes that gas handling system, gas extraction system, fuel system and cooling system, described rotor are sent out
Motivation is connected with electromotor by shaft coupling.
Use technical scheme, can obtain following beneficial effect:
Hybrid power aeroplane distance increasing unit of the present invention, rotary engine work drives generator operation, by fuel
The interior electric energy that can be converted into, and the electric energy that electromotor sends is transferred to generator control parts, generator control by power cable
Parts are transferred to high voltage power distribution parts by power cable, and high tension distribution system carries out electric energy and distributes to related load.And generate electricity
The setting of unit allocation parts, then obtain electrokinetic cell by network and drive the information of motor even load, to electromotor control
One input quantity (signal) of parts, engine control device, according to this signal, controls rotating speed and the load of electromotor, and exports full
The power of foot loading demand, so that it is guaranteed that aircraft reliably working.The hybrid power aeroplane distance increasing unit of the present invention, simple in construction, energy
Enough easily and reliably the interior of aircraft engine can be converted into electric energy, control the rotating speed of electromotor according to the information of load and bear
Lotus, and according to the flight condition of aircraft, electric energy can be carried out reasonable distribution, meet airplane load requirement, it is ensured that aircraft each side
Face performance meets requirement, saves energy resource consumption, it is to avoid to environment simultaneously.
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 distance increasing unit of the present invention；
Fig. 2 is the parts annexation schematic diagram of hybrid power aeroplane distance increasing unit of the present invention；
Accompanying drawing acceptance of the bid note is respectively as follows: 1, rotary engine；2, electromotor；3, generator control parts；4, high voltage power distribution portion
Part；5, engine control device；6, electrokinetic cell；7, motor is driven；8, generator set control parts；9, gas handling system；10, row
Gas system；11, shaft coupling.
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 accompanying drawing 1, accompanying drawing 2, the present invention is a kind of hybrid power aeroplane distance increasing unit, and described hybrid power aeroplane increases
Journey device includes that rotary engine 1, rotary engine 1 are connected with electromotor 2, and described electromotor 2 is with generator control parts 3 even
Connecing, generator control parts 3 are connected with high voltage power distribution parts 4, and generator set control parts 8 (APU controls parts) are sent out with rotor
The engine control device 5 of motivation 1 connects.Said structure is arranged, and rotary engine works, and drives generator operation, by fuel
The interior electric energy that can be converted into, and the electric energy that electromotor sends is transferred to generator control parts, electromotor control by power cable
Parts processed are transferred to high voltage power distribution parts by power cable, and high tension distribution system carries out electric energy and distributes to related load.And send out
Group of motors controls the setting of parts 8, then obtain electrokinetic cell by network and drive the information of motor even load, to electromotor control
One input quantity (signal) of parts processed, engine control device, according to this signal, controls rotating speed and the load of electromotor, and exports
Meet the power of loading demand, so that it is guaranteed that aircraft reliably working.Hybrid power aeroplane distance increasing unit of the present invention, structure letter
Single, it is possible to easily and reliably the interior of aircraft engine to be converted into electric energy, the rotating speed of electromotor is controlled according to the information of load
And load, and according to the flight condition of aircraft, electric energy can be carried out reasonable distribution, thus meet airplane load requirement, it is ensured that
Aircraft various aspects of performance meets requirement, saves energy resource consumption, it is to avoid to environment simultaneously.
Described high voltage power distribution parts 4 are connected with electrokinetic cell 6 and driving motor 7 respectively.Such structure is arranged, for
The electric energy that the electromotor of driven by engine produces, it is possible to be allocated by high-tension fitting parts is as bigger in aircraft loading demand
During electric energy, high voltage power distribution parts then distribute electric energy that electromotor sends all for driving motor, and inadequate electric energy height is press-fitted
Electricity parts can also supplement from electrokinetic cell, and during such as loading demand small electric energy, high voltage power distribution parts are then by electromotor
Producing electric energy and be mostly used in driving motor load, another part is to power battery charging, as electrical power storage, has both ensured aircraft
Normal use, electric energy can be carried out rational Distribution utilization again, it is to avoid the waste of electric energy, save the flight energy and cost.
It is galvanic structure that described generator control parts 3 are configured to the AC conversion of electromotor 2.Send out
Alternating current is not only changed into unidirectional current by motor control component 3, and controls the electricity size of output.
It is negative with drive motor 7 that described generator set control parts 8 are configured to receive electrokinetic cell 6 by network
Information carrying ceases, and the structure of the output according to load information demand regulation rotary engine 1.
Described engine control device 5 is configured to adjust rotary engine 1 rotating speed height and the structure of payload,
When generator set control parts 8 are according to load information demand regulation rotary engine 1 output, generator set control parts 8
It is configured to send the structure of signal to engine control device 5.
Described generator set control parts 8 are when engine control device 5 sends signal, and engine control device 5 sets
It is set to adjust rotating speed height and the structure of payload of rotary engine 1 according to aforementioned signal.
Described rotary engine 1 includes gas handling system 9, gas extraction system 10, fuel system and cooling system, and described turns
Sub-electromotor 1 is connected with electromotor 2 by shaft coupling 11.Shaft coupling 11 is used to carry out even between rotary engine 1 and electromotor 2
Connect, electromotor 2 when rotary engine 1 rotates, can be driven to generate electricity, and the electric energy that electromotor produces is flowed to generating
Machine controls parts, then is transported to high voltage power distribution parts 4 and carries out reasonable distribution, it is ensured that drive motor reliably working, it is ensured that power current
Pond electric energy meets the requirements.
Hybrid power aeroplane distance increasing unit of the present invention, rotary engine work drives generator operation, by fuel
The interior electric energy that can be converted into, and the electric energy that electromotor sends is transferred to generator control parts, generator control by power cable
Parts are transferred to high voltage power distribution parts by power cable, and high tension distribution system carries out electric energy and distributes to related load.And generate electricity
The setting of unit allocation parts, then obtain electrokinetic cell by network and drive the information of motor even load, to electromotor control
One input quantity (signal) of parts, engine control device, according to this signal, controls rotating speed and the load of electromotor, and exports full
The power of foot loading demand, so that it is guaranteed that aircraft reliably working.The hybrid power aeroplane distance increasing unit of the present invention, simple in construction, energy
Enough easily and reliably the interior of aircraft engine can be converted into electric energy, control the rotating speed of electromotor according to the information of load and bear
Lotus, and according to the flight condition of aircraft, electric energy can be carried out reasonable distribution, meet airplane load requirement, it is ensured that aircraft each side
Face performance meets requirement, saves energy resource consumption, it is to avoid to environment simultaneously.
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 (7)
1. a hybrid power aeroplane distance increasing unit, it is characterised in that: described hybrid power aeroplane distance increasing unit includes that rotor starts
Machine (1), rotary engine (1) is connected with electromotor (2), and described electromotor (2) is connected with generator control parts (3), sends out
Motor control component (3) is connected with high voltage power distribution parts (4), and generator set control parts (8) start with rotary engine (1)
Machine controls parts (5) and connects.
Hybrid power aeroplane distance increasing unit the most according to claim 1, it is characterised in that: described high voltage power distribution parts (4)
It is connected with electrokinetic cell (6) and driving motor (7) respectively.
Hybrid power aeroplane distance increasing unit the most according to claim 1, it is characterised in that: described generator control parts
(3) being configured to the AC conversion of electromotor (2) is galvanic structure.
Hybrid power aeroplane distance increasing unit the most according to claim 1, it is characterised in that: described generator set control parts
(8) it is configured to receive electrokinetic cell (6) by network and drive the load information of motor (7), and according to load information need
Seek the structure of the output of regulation rotary engine (1).
Hybrid power aeroplane distance increasing unit the most according to claim 4, it is characterised in that: described engine control device (5)
Being configured to adjust rotary engine (1) rotating speed height and the structure of payload, generator set control parts (8) are according to negative
When carrying information requirement regulation rotary engine (1) output, generator set control parts (8) are configured to electromotor control
Parts processed (5) send the structure of signal.
Hybrid power aeroplane distance increasing unit the most according to claim 5, it is characterised in that: described generator set control parts
(8) when engine control device (5) sends signal, engine control device (5) is set to adjust rotor according to aforementioned signal
The rotating speed height of electromotor (1) and the structure of payload.
Hybrid power aeroplane distance increasing unit the most according to claim 1, it is characterised in that: described rotary engine (1) bag
Include gas handling system (9), gas extraction system (10), (and cooling system, described rotary engine (1) passes through shaft coupling to fuel system
(11) it is connected with electromotor (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610831347.XA CN106275457A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane distance increasing unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610831347.XA CN106275457A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane distance increasing unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275457A true CN106275457A (en) | 2017-01-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610831347.XA Pending CN106275457A (en) | 2016-09-19 | 2016-09-19 | A kind of hybrid power aeroplane distance increasing unit |
Country Status (1)
| Country | Link |
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| CN (1) | CN106275457A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108412655A (en) * | 2018-03-20 | 2018-08-17 | 中电科芜湖钻石飞机制造有限公司 | Rotary engine inspires integrated apparatus and its control method |
| CN108438250A (en) * | 2018-04-16 | 2018-08-24 | 中电科芜湖通用航空产业技术研究院有限公司 | Serial mixed power aircraft power system testboard bay |
| CN108528735A (en) * | 2018-04-16 | 2018-09-14 | 中电科芜湖通用航空产业技术研究院有限公司 | Serial mixed power aircraft and its control method |
| CN108715229A (en) * | 2018-08-01 | 2018-10-30 | 中电科芜湖通用航空产业技术研究院有限公司 | Hybrid power aeroplane power plant integrated mounting system |
| CN108995826A (en) * | 2018-08-01 | 2018-12-14 | 中电科芜湖通用航空产业技术研究院有限公司 | The assembly method of mixed power plant |
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| CN105680554A (en) * | 2015-12-28 | 2016-06-15 | 海鹰航空通用装备有限责任公司 | Power supply and distribution control device for unmanned aerial vehicle |
| CN105711826A (en) * | 2016-03-31 | 2016-06-29 | 陈萌 | Tandem type oil-electric hybrid unmanned aerial vehicle |
| CN206050083U (en) * | 2016-09-19 | 2017-03-29 | 中电科芜湖钻石飞机设计研究院有限公司 | Hybrid power aeroplane distance increasing unit |
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| US20160107748A1 (en) * | 2013-06-12 | 2016-04-21 | The Boeing Company | Hybrid power rotary wing aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108412655A (en) * | 2018-03-20 | 2018-08-17 | 中电科芜湖钻石飞机制造有限公司 | Rotary engine inspires integrated apparatus and its control method |
| CN108438250A (en) * | 2018-04-16 | 2018-08-24 | 中电科芜湖通用航空产业技术研究院有限公司 | Serial mixed power aircraft power system testboard bay |
| CN108528735A (en) * | 2018-04-16 | 2018-09-14 | 中电科芜湖通用航空产业技术研究院有限公司 | Serial mixed power aircraft and its control method |
| CN108528735B (en) * | 2018-04-16 | 2021-06-29 | 中电科芜湖通用航空产业技术研究院有限公司 | Tandem type hybrid power aircraft and control method thereof |
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| CN108995826A (en) * | 2018-08-01 | 2018-12-14 | 中电科芜湖通用航空产业技术研究院有限公司 | The assembly method of mixed power plant |
| CN108715229B (en) * | 2018-08-01 | 2024-01-26 | 中电科芜湖通用航空产业技术研究院有限公司 | Integrated mounting system for power device of hybrid power aircraft |
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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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Inventor after: Zeng Rui Inventor after: Li Huiying Inventor after: Wei Feng Inventor after: Guo Mao Inventor after: Ji Pengpeng Inventor after: Lei Hu Inventor after: Wang Xuecai Inventor before: Zeng Rui Inventor before: Li Huiying Inventor before: Zhou Yi Inventor before: Zhang Huiqin |
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20170104 |