CN106564603A - Tandem type gas-electric hybrid power system of general-purpose airplane - Google Patents
Tandem type gas-electric hybrid power system of general-purpose airplane Download PDFInfo
- Publication number
- CN106564603A CN106564603A CN201610951944.6A CN201610951944A CN106564603A CN 106564603 A CN106564603 A CN 106564603A CN 201610951944 A CN201610951944 A CN 201610951944A CN 106564603 A CN106564603 A CN 106564603A
- Authority
- CN
- China
- Prior art keywords
- port
- valve
- general
- storage tank
- internal combustion
- 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
- 238000002485 combustion reaction Methods 0.000 claims abstract description 35
- 239000000446 fuel Substances 0.000 claims abstract description 31
- 230000005540 biological transmission Effects 0.000 claims abstract description 22
- 238000009834 vaporization Methods 0.000 claims description 30
- 230000008016 vaporization Effects 0.000 claims description 30
- 230000005611 electricity Effects 0.000 claims description 19
- 238000009413 insulation Methods 0.000 claims description 18
- 238000007599 discharging Methods 0.000 claims description 17
- 239000002826 coolant Substances 0.000 claims description 6
- 230000001105 regulatory effect Effects 0.000 claims description 6
- 239000000110 cooling liquid Substances 0.000 claims description 3
- 230000006837 decompression Effects 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 239000003949 liquefied natural gas Substances 0.000 abstract description 57
- 238000003912 environmental pollution Methods 0.000 abstract description 7
- 239000006200 vaporizer Substances 0.000 abstract 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 239000003208 petroleum Substances 0.000 description 4
- 238000005183 dynamical system Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 238000009510 drug design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 230000008450 motivation 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
- 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
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a tandem type gas-electric hybrid power system of a general-purpose airplane. The tandem type gas-electric hybrid power system comprises a motor, a power generator, an internal combustion engine, a storage battery, an LNG storage tank and an LNG vaporizer, wherein one path of a power supply port of the motor is connected with a power transmission port of the storage battery, and the other path of the power supply port is connected with a power transmission port of the power generator; a main shaft of the power generator is connected with a power output shaft of the internal combustion engine; a fuel input hole of the internal combustion engine is connected with a fuel output hole of the LNG storage tank through the LNG vaporizer; the power transmission port of the power generator is connected with a charging port of the storage battery; a fuel supply assembly is arranged between the internal combustion engine and the LNG vaporizer; and the LNG storage tank is equipped with a storage tank self-pressurization assembly. The tandem type gas-electric hybrid power system disclosed by the invention adopts the internal combustion engine which takes liquefied natural gas as fuel, carries out reasonable design on fuel supply and a transmission pipeline, and carries out matching and coordination on liquid natural gas and electric power, so that the general-purpose airplane has the capacity of using gas-electric hybrid power, and therefore, environmental pollution is further reduced, and cruising ability of the general-purpose airplane is guaranteed.
Description
Technical field
The invention belongs to general-purpose aircraft dynamical system technical field, more particularly to a kind of tandem general-purpose aircraft pneumoelectric is mixed
Close dynamical system.
Background technology
General-purpose aircraft to be referred to and be engaged in other civilian boats in addition to the public air transport aircraft such as regular passenger traffic, shipping is engaged in
The aircraft general name of empty activity, and general-purpose aircraft dynamical system refers to aircraft engine and ensures that engine work institute is necessary
Adnexa general name.At present, the electromotor for being used on general-purpose aircraft includes piston aviation engine, rotator type aeroplane engine
Mechanical, electrical dynamic electromotor and oil electric mixed dynamic electromotor.
General-purpose aircraft quantity using piston aviation engine and rotator type aero-engine is most, and above two
Electromotor is mainly with the petroleum based fuels such as gasoline or aerial kerosene as the energy, but the problem of environmental pollution of petroleum based fuels is all the time
Its short slab.
In order to avoid pollution of the petroleum based fuels to environment, researched and developed in succession using the general-purpose aircraft of genemotor merely
Out, but by battery technology instantly limited, cause the endurance of general-purpose aircraft low.Therefore, merely using electronic
The general-purpose aircraft inferior position of motivation is fairly obvious.
In order to reduce that endurance is can also ensure that while environmental pollution, using the general of oil electric mixed dynamic electromotor
Aircraft gradually increases, and by fuel oil type internal combustion engine and genemotor the energy for needed for aircraft is provided is cooperated to, this
To a certain extent really can with pollution remission, and with merely using genemotor compared with, also make the endurance of general-purpose aircraft
Increase, but, because fuel oil type internal combustion engine still needs the base fuel that consumes petroleum, its problem of environmental pollution does not obtain root
This solution.
If liquefied natural gas (Liquefied Natural Gas, abbreviation LNG) is introduced into general-purpose aircraft and as fuel
To use, compared with the general-purpose aircraft of oil electric mixed dynamic, environmental pollution not only can be further reduced, it can also be ensured that general
The endurance of aircraft.Therefore, it is very necessary to design the gas-electricity power combined system of a set of brand-new general-purpose aircraft.
The content of the invention
For the problem that prior art is present, the present invention provides a kind of tandem general-purpose aircraft gas-electricity power combined system,
The internal combustion engine with liquefied natural gas as fuel is employed, and rational Design on Plane has been carried out with transport pipeline to fuel supply, to liquid
Changing natural gas and electric power both energy has carried out coordinating matching, general-purpose aircraft is possessed using gas-electricity power combined energy
Power, reduce further environmental pollution, and ensure that the endurance of general-purpose aircraft.
To achieve these goals, the present invention is adopted the following technical scheme that：A kind of tandem general-purpose aircraft pneumoelectric mixing is dynamic
Force system, including motor, electromotor, internal combustion engine, accumulator, LNG storage tank and LNG vaporization device；The power end of the motor
Mouth is connected all the way with the transmission of electricity port of accumulator, and another road is connected with the transmission of electricity port of electromotor；The main shaft of the electromotor with
The power output shaft of internal combustion engine is connected, and the fueling ports of internal combustion engine pass through the fuel delivery outlet phase of LNG vaporization device and LNG storage tank
Even；The transmission of electricity port of the electromotor is connected with the charging port of accumulator.
The thermal source of the LNG vaporization device is the coolant of internal combustion engine, the cooling liquid outlet of internal combustion engine and the heat of LNG vaporization device
Source inlet is connected, and the coolant inlet of internal combustion engine is connected with the thermal source outlet of LNG vaporization device.
Hand switch is connected between the transmission of electricity port of the accumulator and the power port of motor, in accumulator
Automatic switch is connected between charging port and the transmission of electricity port of electromotor, in power port and the electromotor of the motor
Transmission of electricity adds rectifier transformer between port.
Fuel supply component is provided between the internal combustion engine and LNG vaporization device, the fuel supply component includes slow
Tank, electromagnetic valve, cleaner and manostat are rushed, the arrival end of the surge tank is connected with the fuel delivery outlet of LNG vaporization device, delayed
The port of export for rushing tank passes sequentially through electromagnetic valve, cleaner and manostat and is connected with the fuel delivery outlet of LNG storage tank.
The LNG storage tank is fitted with storage tank from pressurizing pack, the storage tank from pressurizing pack include stop valve, pressure regulator valve,
Supercharging carburator and return-air valve；The arrival end of the stop valve and the intracavity inter-connection of LNG storage tank, the port of export of stop valve according to
Secondary to be connected with the arrival end of return-air valve by pressure regulator valve and supercharging carburator, the port of export of return-air valve is interior with LNG storage tank
Chamber is connected.
Three-way valve is connected with pipeline between the supercharging carburator and return-air valve, supercharging passes through three with carburator
Port valve is connected with air relief valve, and air relief valve is connected with atmospheric valve by the first regulating valve.
The LNG storage tank includes double-deck thermal insulation tank body, topping up joint, topping up pipe, shower, discharging tube, the first check valve
And filter；The intracavity inter-connection that the topping up joint passes through the adiabatic tank body of topping up pipe and bilayer, the port of export of topping up pipe is located at
In the inner chamber of double-deck thermal insulation tank body, the shower is connected to the port of export of topping up pipe；The arrival end of the discharging tube is located at double
In the inner chamber of the adiabatic tank body of layer, the filter is connected to the arrival end of discharging tube, the port of export of discharging tube and the first check valve
Arrival end be connected, the port of export of the first check valve is connected all the way with atmospheric valve, and another road is defeated with the fuel of LNG vaporization device
Entrance is connected.
The second regulation is connected with turn between the port of export of first check valve and the fueling ports of LNG vaporization device
Valve, go out hydraulic control valve, overvoltage protection valve and the second check valve.
Pressure gauge is installed on the double-deck thermal insulation tank body, liquidometer is installed in the inner chamber of double-deck thermal insulation tank body,
Double-deck thermally insulated tank external body is provided with signal adapter and display, the signal output part of liquidometer by signal adapter with
Display is connected.
The first relief valve is provided with the topping up pipe, the second relief valve is provided with the discharging tube.
Beneficial effects of the present invention：
The present invention compared with prior art, employs the internal combustion engine with liquefied natural gas as fuel, and to fuel supply with
Transport pipeline has carried out rational Design on Plane, and liquefied natural gas and electric power both energy have been carried out to coordinate matching, makes general flying
Equipment reduce further environmental pollution for using gas-electricity power combined ability, and ensure that the continuation of the journey of general-purpose aircraft
Ability.
Description of the drawings
Fig. 1 is a kind of structure principle chart of the gas-electricity power combined system of tandem general-purpose aircraft of the present invention；
In figure, 1-motor, 2-electromotor, 3-internal combustion engine, 4-accumulator, 5-LNG storage tank, 6-LNG vaporization device,
7-hand switch, 8-automatic switch, 9-surge tank, 10-electromagnetic valve, 11-cleaner, 12-manostat, 13-cut-off
Valve, 14-pressure regulator valve, 15-supercharging carburator, 16-return-air valve, 17-three-way valve, 18-air relief valve, 19-the first is adjusted
Valve, 20-atmospheric valve, 21-double-deck thermal insulation tank body, 22-topping up joint, 23-topping up pipe, 24-shower, 25-discharging tube,
26-the first check valve, 27-filter, the 28-the second regulating valve, 29-go out hydraulic control valve, 30-overvoltage protection valve, 31-the
Two check valves, 32-pressure gauge, 33-liquidometer, 34-signal adapter, 35-display, the 36-the first relief valve, 37-
Second relief valve, 38-rectifier transformer.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention is described in further detail with specific embodiment.
As shown in figure 1, a kind of gas-electricity power combined system of tandem general-purpose aircraft, including motor 1, electromotor 2, internal combustion
Machine 3, accumulator 4, LNG storage tank 5 and LNG vaporization device 6；The power port of the motor 1 all the way with the transmission of electricity port of accumulator 4
It is connected, another road is connected with the transmission of electricity port of electromotor 2；The power output shaft phase of the main shaft of the electromotor 2 and internal combustion engine 3
Even, the fueling ports of internal combustion engine 3 are connected by LNG vaporization device 6 with the fuel delivery outlet of LNG storage tank 5；The electromotor 2
Transmission of electricity port is connected with the charging port of accumulator 4.
The thermal source of the LNG vaporization device 6 for internal combustion engine 3 coolant, the cooling liquid outlet of internal combustion engine 3 and LNG vaporization device 6
Thermal source inlet be connected, the coolant inlet of internal combustion engine 3 is connected with the thermal source outlet of LNG vaporization device 6.
Hand switch 7 is connected between the transmission of electricity port of the accumulator 4 and the power port of motor 1, in electric power storage
Be connected with automatic switch 8 between the charging port in pond 4 and the transmission of electricity port of electromotor 2, the motor 1 power port with
Rectifier transformer 38 is added between the transmission of electricity port of electromotor 2, it is ensured that the power of motor 1 can be exported steadily.
Fuel supply component is provided between the internal combustion engine 3 and LNG vaporization device 6, the fuel supply component includes
Surge tank 9, electromagnetic valve 10, cleaner 11 and manostat 12, the arrival end of the surge tank 9 is exported with the fuel of LNG vaporization device 6
Mouthful it is connected, it is defeated with the fuel of LNG storage tank 5 that the port of export of surge tank 9 passes sequentially through electromagnetic valve 10, cleaner 11 and manostat 12
Outlet is connected.
The LNG storage tank 5 is fitted with storage tank from pressurizing pack, and the storage tank includes stop valve 13, pressure regulation from pressurizing pack
Valve 14, supercharging carburator 15 and return-air valve 16；The arrival end of the stop valve 13 and the intracavity inter-connection of LNG storage tank 5, cut-off
The port of export of valve 13 passes sequentially through pressure regulator valve 14 and supercharging carburator 15 is connected with the arrival end of return-air valve 16, return-air valve 16
The port of export and LNG storage tank 5 intracavity inter-connection.
Three-way valve 17, supercharging carburator are connected with pipeline between the supercharging carburator 15 and return-air valve 16
15 are connected with air relief valve 18 by three-way valve 17, and air relief valve 18 is connected with atmospheric valve 20 by the first regulating valve 19.
The LNG storage tank 5 includes double-deck thermal insulation tank body 21, topping up joint 22, topping up pipe 23, shower 24, discharging tube 25,
First check valve 26 and filter 27；The topping up joint 22 is connected by topping up pipe 23 with the inner chamber of double-deck thermal insulation tank body 21
Logical, the port of export of topping up pipe 23 is located in the inner chamber of double-deck thermal insulation tank body 21, and the shower 24 is connected to going out for topping up pipe 23
Mouth end；The arrival end of the discharging tube 25 is located in the inner chamber of double-deck thermal insulation tank body 21, and the filter 27 is connected to discharging tube
25 arrival end, the port of export of discharging tube 25 is connected with the arrival end of the first check valve 26, the port of export of the first check valve 26
It is connected with atmospheric valve 20 all the way, another road is connected with the fueling ports of LNG vaporization device 6.
Second is connected with turn between the port of export of first check valve 26 and the fueling ports of LNG vaporization device 6
Regulating valve 28, go out hydraulic control valve 29, the check valve 31 of overvoltage protection valve 30 and second.
Pressure gauge 32 is installed on the double-deck thermal insulation tank body 21, liquid is installed in the inner chamber of double-deck thermal insulation tank body 21
Position meter 33, outside double-deck thermal insulation tank body 21 signal adapter 34 and display 35, the signal output part of liquidometer 33 are provided with
It is connected with display 35 by signal adapter 34.
The first relief valve 36 is provided with the topping up pipe 23, the second relief valve is provided with the discharging tube 25
37, the pressure in LNG storage tank 5 is remained in safety range by the first relief valve 36 and the second relief valve 37.
By taking a kind of light propeller airplane as an example, the gas-electricity power combined system of tandem general-purpose aircraft of the present invention is which employs
System.
In the present embodiment, accumulator 4 uses that aviation is storage battery dedicated, and it is a kind of universal high energy-storage battery；
Electromotor 2 uses the electromotor that General Aviation is commonly used, and efficiently can be converted to the mechanical energy that internal combustion engine 3 is produced
Electric energy.
Before aircraft starts, first proper amount of liquefied natural gas is filled with into LNG storage tank 5 by topping up joint 22, in storage
Tank is under pressurizing pack effect, it is ensured that the pressure in LNG storage tank 5, so that liquefied natural gas is acted in pressure in LNG storage tank 5
Flowed out by discharging tube 25 down, until flowing in LNG vaporization device 6, liquefied natural gas will be changed into gaseous state in LNG vaporization device 6.
When aircraft starts, gaseous natural gas is used in internal combustion engine 3 as fuel, and internal combustion engine 3 produces mechanical energy again
Electric energy is converted to by electromotor 2, the electric energy exported finally by electromotor 2 is that motor 1 provides driving force, and then drives spiral shell
Rotation oar rotation.
When aircraft in start, accelerate and climb etc. big operating mode when, need aircraft increase horsepower flight, now pilot can
To close hand switch 7, electromotor 2 and accumulator 4 is set to provide electric energy for motor 1 jointly；When aircraft is in cruising condition,
Surrounding flow is steady, and without the need for high-power flight, now pilot can disconnect hand switch 7, be only individually for by electromotor 2 electronic
Machine 1 provides electric energy, makes the steady running of motor 1, reduces vibration and aloft noise level.
When 4 not enough power supply of accumulator, automatic switch 8 is closed automatically, and now electromotor 2 starts to be charged for accumulator 4, when
After the electricity of accumulator 4 is full of, automatic switch 8 disconnects automatically.
Scheme in embodiment and being not used to limits the scope of patent protection of the present invention, it is all without departing from carried out by the present invention etc.
Effect is implemented or is changed, in being both contained in the scope of the claims of this case.
Claims (10)
1. the gas-electricity power combined system of a kind of tandem general-purpose aircraft, it is characterised in that：Including motor, electromotor, internal combustion engine,
Accumulator, LNG storage tank and LNG vaporization device；The power port of the motor is connected all the way with the transmission of electricity port of accumulator, another
Road is connected with the transmission of electricity port of electromotor；The main shaft of the electromotor is connected with the power output shaft of internal combustion engine, the combustion of internal combustion engine
Material input port is connected by LNG vaporization device with the fuel delivery outlet of LNG storage tank；The transmission of electricity port of the electromotor and accumulator
Charging port is connected.
2. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 1, it is characterised in that：It is described
The thermal source of LNG vaporization device is the coolant of internal combustion engine, and the cooling liquid outlet of internal combustion engine is connected with the thermal source inlet of LNG vaporization device
Logical, the coolant inlet of internal combustion engine is connected with the thermal source outlet of LNG vaporization device.
3. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 1, it is characterised in that：Described
Hand switch is connected between the transmission of electricity port of accumulator and the power port of motor, in charging port and the generating of accumulator
Automatic switch is connected between the transmission of electricity port of machine, is added between the power port of the motor and the transmission of electricity port of electromotor
Equipped with rectifier transformer.
4. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 1, it is characterised in that：Described
Fuel supply component is provided between internal combustion engine and LNG vaporization device, the fuel supply component includes surge tank, electromagnetic valve, filter
Clear device and manostat, the arrival end of the surge tank is connected with the fuel delivery outlet of LNG vaporization device, the port of export of surge tank according to
It is secondary to be connected with the fuel delivery outlet of LNG storage tank by electromagnetic valve, cleaner and manostat.
5. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 1, it is characterised in that：It is described
LNG storage tank is fitted with storage tank from pressurizing pack, and the storage tank includes stop valve, pressure regulator valve, supercharging carburator from pressurizing pack
And return-air valve；The arrival end of the stop valve and the intracavity inter-connection of LNG storage tank, the port of export of stop valve passes sequentially through pressure regulator valve
And supercharging carburator is connected with the arrival end of return-air valve, the port of export of return-air valve and the intracavity inter-connection of LNG storage tank.
6. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 5, it is characterised in that：Described
Three-way valve is connected with pipeline between supercharging carburator and return-air valve, supercharging carburator is connected with decompression by three-way valve
Valve, air relief valve is connected with atmospheric valve by the first regulating valve.
7. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 6, it is characterised in that：It is described
LNG storage tank includes double-deck thermal insulation tank body, topping up joint, topping up pipe, shower, discharging tube, the first check valve and filter；It is described
The intracavity inter-connection that topping up joint passes through the adiabatic tank body of topping up pipe and bilayer, the port of export of topping up pipe is located at double-deck thermal insulation tank body
In inner chamber, the shower is connected to the port of export of topping up pipe；The arrival end of the discharging tube is located at the interior of double-deck thermal insulation tank body
In chamber, the filter is connected to the arrival end of discharging tube, and the port of export of discharging tube is connected with the arrival end of the first check valve,
The port of export of the first check valve is connected all the way with atmospheric valve, and another road is connected with the fueling ports of LNG vaporization device.
8. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 7, it is characterised in that：Described
Be connected with turn between the port of export of the first check valve and the fueling ports of LNG vaporization device the second regulating valve, go out hydraulic control valve,
Overvoltage protection valve and the second check valve.
9. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 7, it is characterised in that：Described
Pressure gauge is installed on double-deck thermal insulation tank body, liquidometer is installed in the inner chamber of double-deck thermal insulation tank body, in double-deck thermal insulation tank body
Outside is provided with signal adapter and display, and the signal output part of liquidometer is connected by signal adapter with display.
10. the gas-electricity power combined system of a kind of tandem general-purpose aircraft according to claim 7, it is characterised in that：Institute
State and the first relief valve is provided with topping up pipe, the second relief valve is provided with the discharging tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610951944.6A CN106564603A (en) | 2016-11-02 | 2016-11-02 | Tandem type gas-electric hybrid power system of general-purpose airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610951944.6A CN106564603A (en) | 2016-11-02 | 2016-11-02 | Tandem type gas-electric hybrid power system of general-purpose airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106564603A true CN106564603A (en) | 2017-04-19 |
Family
ID=58535309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610951944.6A Pending CN106564603A (en) | 2016-11-02 | 2016-11-02 | Tandem type gas-electric hybrid power system of general-purpose airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106564603A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454864A (en) * | 2018-04-16 | 2018-08-28 | 中电科芜湖通用航空产业技术研究院有限公司 | General-purpose aircraft series connection type hybrid power system |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202115704U (en) * | 2011-05-14 | 2012-01-18 | 珠海银通航空器材有限公司 | Electric aircraft |
| US20120301814A1 (en) * | 2010-01-29 | 2012-11-29 | Paul Beasley | Electrically driven aircraft |
| US20130147204A1 (en) * | 2010-05-19 | 2013-06-13 | Eurocopter Deutschland Gmbh | Hybrid Drive And Energy System For Aircraft |
| US20140283519A1 (en) * | 2013-03-25 | 2014-09-25 | Airbus Helicopters | Rotary wing aircraft with a hybrid power plant |
| CN105179933A (en) * | 2015-08-17 | 2015-12-23 | 沈阳航空航天大学 | Universal aircraft power system with liquefied natural gas (LNG) as fuel and fuel supply method of universal aircraft power system |
-
2016
- 2016-11-02 CN CN201610951944.6A patent/CN106564603A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120301814A1 (en) * | 2010-01-29 | 2012-11-29 | Paul Beasley | Electrically driven aircraft |
| US20130147204A1 (en) * | 2010-05-19 | 2013-06-13 | Eurocopter Deutschland Gmbh | Hybrid Drive And Energy System For Aircraft |
| CN202115704U (en) * | 2011-05-14 | 2012-01-18 | 珠海银通航空器材有限公司 | Electric aircraft |
| US20140283519A1 (en) * | 2013-03-25 | 2014-09-25 | Airbus Helicopters | Rotary wing aircraft with a hybrid power plant |
| CN105179933A (en) * | 2015-08-17 | 2015-12-23 | 沈阳航空航天大学 | Universal aircraft power system with liquefied natural gas (LNG) as fuel and fuel supply method of universal aircraft power system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454864A (en) * | 2018-04-16 | 2018-08-28 | 中电科芜湖通用航空产业技术研究院有限公司 | General-purpose aircraft series connection type hybrid power system |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Lapeña-Rey et al. | First fuel-cell manned aircraft | |
| CN106494625A (en) | A kind of gas-electricity power combined system of parallel general-purpose aircraft | |
| RU2462397C2 (en) | Aircraft power plant | |
| US20150014479A1 (en) | Independent power generation in aircraft | |
| US10569892B2 (en) | Supplemental power for reduction of prime mover | |
| EP3551493B1 (en) | Systems and methods for vehicular power generation | |
| CN108045587B (en) | Waste heat recovery system of oxygen consumption type inerting fuel tank based on thermoelectric generation technology | |
| CN107140229A (en) | One kind is tethered at unmanned plane energy supplyystem | |
| US20210300576A1 (en) | Dual engine hybrid-electric aircraft | |
| CN110985215A (en) | Starting and launching integrated system for micro turbojet engine | |
| CN106564603A (en) | Tandem type gas-electric hybrid power system of general-purpose airplane | |
| CN108298095A (en) | A kind of Small General Aircraft boat coal piston engine power plants | |
| US20200277078A1 (en) | Electrical power system for aircraft having hybrid-electric propulsion system | |
| KR101685853B1 (en) | Dual fuel internal combustion engine impelling apparatus | |
| CN106150762A (en) | The liquid hydrogen vaporization control method of hydrogen energy source unmanned plane | |
| CN102434281A (en) | Dual-mode gas generating device and generating method | |
| CN210149505U (en) | Natural gas supply system and aerodynamic ship | |
| Berton et al. | An analytical performance assessment of a fuel cell-powered, small electric airplane | |
| WO2023040191A1 (en) | Zero-carbon ship power system, and method for driving ship | |
| CN109878680A (en) | A kind of parallel ship hybrid power system of pneumoelectric that band LNG is cooling | |
| CN117940341A (en) | Environment-friendly aircraft | |
| CN202213716U (en) | Aerial energy charging station | |
| CN114248899A (en) | Zero-carbon ship power system and method for driving ship | |
| Snyder et al. | Using liquid natural gas fuel to cryogenically cool and enhance a hybrid electric aircraft power system | |
| Gang et al. | Performance evaluation of a compact designed electric power system composed of a two‐stroke gasoline engine, generator, and battery for high‐endurance unmanned aerial vehicles |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170419 |
|
| RJ01 | Rejection of invention patent application after publication |