CN108172874A - A kind of proton exchange film fuel battery system of aviation simplification - Google Patents
A kind of proton exchange film fuel battery system of aviation simplification Download PDFInfo
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- CN108172874A CN108172874A CN201611115546.7A CN201611115546A CN108172874A CN 108172874 A CN108172874 A CN 108172874A CN 201611115546 A CN201611115546 A CN 201611115546A CN 108172874 A CN108172874 A CN 108172874A
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- fuel cell
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- battery system
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04007—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
- H01M8/04029—Heat exchange using liquids
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
- H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
- H01M8/04119—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying
- H01M8/04126—Humidifying
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/06—Combination of fuel cells with means for production of reactants or for treatment of residues
- H01M8/0662—Treatment of gaseous reactants or gaseous residues, e.g. cleaning
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Fuel Cell (AREA)
Abstract
The present invention relates to a kind of proton exchange film fuel battery system of aviation simplification, hydrogen cylinder connects fuel cell with pressure maintaining valve by pressure reducing valve, and hydrogen enters fuel cell as fuel after pressure reducing valve and pressure maintaining valve；Wind turbine, for air to be input to fuel cell, oxidant of the oxygen as fuel cell in air；Fuel cell forms closed loop with water tank and water pump, is radiated by recirculated water for fuel cell；Exhaust gas drive module connects fuel cell, and the tail gas that control solenoid valve generates fuel cell is discharged；Motor electricity tune connects fuel cell, and power source output is provided for aircraft.The present invention simplifies control strategy, simplied system structure, optimization control scheme mitigates weight, improves performance and stability for this application environment of aerospace applications.
Description
Technical field
The present invention relates to fuel cell module integrated technology, specifically a kind of proton exchange membrane of aviation simplification
Fuel cell system.
Background technology
Proton Exchange Membrane Fuel Cells (PEMFC) has that energy conversion efficiency is high, environmental-friendly, simple in structure, operation side
Just the advantages that, thus it is widely used in the numerous areas such as aerospace, new-energy automobile, distributed power station.
PEMFC carries out electrification at low temperature typically using hydrogen as anode fuel, using air or oxygen as cathode oxidant
Reaction is learned, reaction product is water.Although cell reaction principle is simple, as modular battery also need to will gas supply,
Many execution units such as exhaust emissions, power electric control, waste heat discharge are integrated.For different application fields, to battery
And applying working condition, use environment, weight, volume of battery system etc. has different requirements, so system integration technology is also
It is different.Conventional fuel cell system includes electronic control unit (ECU), gas cylinder, humidifier components, sensor, valve member, hydro-thermal management
Component etc..The problem of having to aerospace applications in face of loss of weight and simplifying control strategy.
A kind of humidification air supply system of fuel cell is proposed in patent CN201110254614, including water pump, wind turbine, temperature
Degree probe and controller.System complex, weight is big, is not suitable in the aviation fuel cell system to weight sensitive.This
Invention without using humidification system, but battery using metal bipolar plate technique come loss of weight, it is such while using from humidification membrane technology
Membrane electrode does not need to be humidified within certain temperature, and complicated humidifier components are thus omitted.
The fuel cell system that unmanned plane uses is referred in patent 201610581987.X, using lithium battery as startup
It powers with joint, connecing battery using DC-DC exports, and adjustment voltage is followed by motor electricity tune.The present invention starts combustion without using lithium battery
Expect battery, and use external trigger power initiation battery system.Also voltage is adjusted without using DC-DC, but utilizes regulating cell
Output voltage and wide scope motor electricity transfer directly to power for motor and wind turbine.
Invention content
In view of the deficiencies of the prior art, the present invention provides a kind of proton exchange film fuel battery system of aviation simplification,
For this application environment of aerospace applications, control strategy, simplied system structure are simplified, optimization control scheme mitigates weight, improves
Performance and stability.
Present invention technical solution used for the above purpose is：
A kind of proton exchange film fuel battery system of aviation simplification, including：
Hydrogen cylinder connects fuel cell with pressure maintaining valve by pressure reducing valve, and hydrogen is as fuel, by pressure reducing valve and pressure maintaining valve
Enter fuel cell afterwards；
Wind turbine, for air to be input to fuel cell, oxidant of the oxygen as fuel cell in air；
Fuel cell forms closed loop with water tank and water pump, is radiated by recirculated water for fuel cell；
Exhaust gas drive module connects fuel cell, and the tail gas that control solenoid valve generates fuel cell is discharged；
Motor electricity tune connects fuel cell, and power source output is provided for aircraft.
The fuel cell uses metal double polar plates, and replaces humidifier with from moistened membrane.
Described from moistened membrane is Nafion/SiO2 composite membranes, and SiO2 is nano particle, grain size 5nm-20nm, SiO2
Shared ratio is 1-10wt.% in Nafion membrane, and the thickness of film is 25-150 μm.
Aircraft on the water tank is aweather located to set radiating fin, for radiating.
The pressure of hydrogen gas side and air side keeps balance.
The exhaust gas drive module uses 555 timing circuits that end occurs as pulse signal, is amplified using power tube and driven
Electromagnetism valve timing is vented.
Single-pole double-throw switch (SPDT) is set between battery output and external power supply, for switching external trigger power supply and fuel cell
Power supply.
The switching external power supply and fuel cell power source are：
During startup, single-pole double-throw switch (SPDT) is switched on external trigger power supply, and is passed through hydrogen and sky to fuel cell simultaneously
Gas until fuel cell enters open-circuit condition, is completed to start；Then adjustment single-pole double-throw switch (SPDT) is switched on fuel cell, is made
System only passes through fuel cell powers.
The operating voltage of the output voltage range of the fuel cell and wind turbine, water pump, last row solenoid valve and radiator fan
Matching.
The invention has the advantages that and advantage：
1. the present invention abandons membrane humidifier, and control electricity using metal double polar plates and the fuel cell from the membrane technology that is humidified
Pond temperature, with this come reduce weight and reduce volume；
2. the operating point of designing fuel cell of the present invention make fuel cell output voltage range and battery system wind turbine and
The operating voltage matching of motor electricity tune can so save the DC-DC module of voltage transformation；
3. battery last row valve of the present invention realizes adjustable automatic last row using independent program control module control circuit, using outer
Portion triggers power initiation battery, eliminates startup battery.
Description of the drawings
Fig. 1 is the system structure connection figure of the present invention.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and embodiments.
System structure connection figure for the present invention as shown in Figure 1.
Wind turbine provides air for battery, and oxygen therein is as oxidant by wind turbine with certain wind pressure input fuel electricity
Pond.Hydrogen cylinder memory hydrogen enters fuel cell as fuel by pressure reducing valve pressure maintaining valve.The tail gas that cell reaction generates passes through
The solenoid valve discharge of program control driving module drive.There is heat recirculated water in water tank, it will be electric by inside battery for recycling
Pond heat is taken out of, and water pump provides power for recirculated water.Aviation electromechanics tune since the motor is using electricity tune, can accomplish width
Control source can also be directly connected to battery as power source.
Hydrogen-air fuel cell module generally requires humidification to ensure membrane electrode performance.But consider that humidifier components are answered from system
Miscellaneous and weight is big.The present invention is not used humidification but is protected using the scheme for changing battery composition and control battery operating temperature
Demonstrate,prove membrane electrode performance.Specifically using metal double polar plates and from humidification membrane technology, such battery exists Proton Exchange Membrane Fuel Cells
It does not need to be humidified in certain temperature range, humidifier components is omitted with this.
It is as follows from the preparation detailed process of moistened membrane：First, by Nafion (115, NRE212) film in vacuum drying chamber
Dry 12h removals moisture content, spare under the conditions of 80 DEG C.Then film is immersed to a certain proportion of 30 DEG C of methanol/water solution (CH3OH/
H2O in), 1h is impregnated wherein.After its swelling fully balance, sample is taken out, surface residual liquid is carefully wiped with filter paper.So
Nafion membrane after swelling is put into 30 DEG C of a certain proportion of methanol/ethyl orthosilicate (CH3OH/TEOS) solution afterwards, at this point,
Sol gel reaction will carry out in film.Reaction time is 5min to NRE212, is 3min to Nafion115 films.It takes out anti-
Should after film, by its in vacuum drying chamber 80 DEG C of dry 48h to get to Nafion/SiO2 composite membranes.
In order to control battery temperature, need from the aspect of heat production and heat dissipation two.Battery as the heat producing components in system,
Its heating power is limited by load requirement.The efficiency of Proton Exchange Membrane Fuel Cells can reach 50% or so, that is,
It says if exporting the electric energy of 1kWh, the heat of 1kWh, work of the aviation power motor when cruising, climbing, glide can be supervened
Condition requirement cell output is also different, and the maximum power and general duration that climb when requires calculate the heat generated
Amount.So coordinate the calculating of the heat radiation power of cooling system again and passing through experimental verification can keep battery temperature to be maintained at just
There is not big fluctuation in normal operating temperature (such as 60 DEG C or so).The waste heat that battery generates will discharge battery in time, otherwise electric
It pond can overtemperature damage.Here radiating fin is installed additional by heat derives, on water tank using small water pump driving recirculated water and is placed in aircraft
Aweather (windward) at radiate, can also be placed near propeller, utilize propeller wind-force heat dissipation.
In the case that water pump, wind turbine, program control driving module in systems etc. all use 24VDC power supplys, such as the present invention
Patent is 30 section left and right batteries, and for output voltage in 30-18V or so, it is the confession of above-mentioned component not needed in this way using autocratic DC-DC
Electricity.For load motor, voltage request is different under different situations, and wide scope can directly use cell output voltage；And for
Point voltage requirement such as 24VDC voltages, then needs to use with the unified 24V's using a total power of system 24VDC equipment
DC-DC.Such as the load motor using other voltages, then also need to one independent DC-DC of installation and be supplied to load.So load
Motor is preferably selected brushless motor for such as charging tune of wide scope etc..High power D C-DC can be saved in this way, and not only loss of weight subtracts
Few volume, can also improve efficiency.
Proton Exchange Membrane Fuel Cells gas supply part is also system important component, inside battery hydrogen side and air side pressure
Power must balance, if pressure difference crosses the damage that conference causes film.The especially startup of high-pressure system or docking process.The present invention
By pressure reduction, hydrogen side pressure is directly entered inside battery by pressure-reduced and-regulated to 0.2-0.7bar.Air side gas supply is using wind
Machine, wind pressure are matched with hydrogen side.Pressure at both sides can accomplish in a basic balance in this way, to battery membranes when being started with guarantee, run, stopped
The protection of electrode.
The hydrogen utilization ratio of Proton Exchange Membrane Fuel Cells is 95% or even more than 99%, during the work time by air source
Impurity and the compositions such as the complete hydrogen of unreacted and a small amount of vapor tail gas need in time from battery discharge.Due to cancelling
ECU, so the present invention has made a program control driving module, directly drives last row solenoid valve emission.
External trigger power supply is needed during fuel cell start-up, in advance to water pump, wind turbine, program control driving module in system etc.
It is powered.The present invention is directly switched using a single-pole double-throw switch (SPDT) between external trigger power supply and battery, and when startup cuts
It changes on external trigger power supply, opens bottle valve air inlet, fuel cell enters open-circuit condition, and fuel battery voltage is open circuit at this time
30V or so completes startup at this time.Then, by switching to battery-powered state, external trigger power supply, Account Dept are removed
Part provides power supply in itself by fuel cell and eliminates the reliance on external trigger power supply, and battery is at standby mode at this time, works as load
When motor works under different operating modes, fuel cell corresponds to output electric energy.After docking process is unloading, manually or automatically close
Switching switch is stated, various parts power-off is out of service.Air source is finally closed, completes parking.
Claims (9)
1. a kind of proton exchange film fuel battery system of aviation simplification, which is characterized in that including：
Hydrogen cylinder connects fuel cell with pressure maintaining valve by pressure reducing valve, and hydrogen is laggard by pressure reducing valve and pressure maintaining valve as fuel
Enter fuel cell；
Wind turbine, for air to be input to fuel cell, oxidant of the oxygen as fuel cell in air；
Fuel cell forms closed loop with water tank and water pump, is radiated by recirculated water for fuel cell；
Exhaust gas drive module connects fuel cell, and the tail gas that control solenoid valve generates fuel cell is discharged；
Motor electricity tune connects fuel cell, and power source output is provided for aircraft.
2. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：The combustion
Battery is expected using metal double polar plates, and replaces humidifier with from moistened membrane.
3. the proton exchange film fuel battery system of aviation simplification according to claim 2, it is characterised in that：It is described from
Moistened membrane is Nafion/SiO2 composite membranes, and SiO2 is nano particle, grain size 5nm-20nm, the SiO2 institute in Nafion membrane
The ratio accounted for is 1-10wt.%, and the thickness of film is 25-150 μm.
4. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：Described
Aircraft on water tank is aweather located to set radiating fin, for radiating.
5. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：Hydrogen gas side
Balance is kept with the pressure of air side.
6. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：The row
Gas drive module uses 555 timing circuits that end occurs as pulse signal, is vented using power tube amplification drive magnetic valve timing.
7. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：In battery
Single-pole double-throw switch (SPDT) is set between output and external power supply, for switching external trigger power supply and fuel cell power source.
8. the proton exchange film fuel battery system of aviation simplification according to claim 7, it is characterised in that：It is described to cut
It changes external power supply and fuel cell power source is：
During startup, single-pole double-throw switch (SPDT) is switched on external trigger power supply, and is passed through hydrogen and air to fuel cell simultaneously, directly
Enter open-circuit condition to fuel cell, complete to start；Then adjustment single-pole double-throw switch (SPDT) is switched on fuel cell, makes system only
Pass through fuel cell powers.
9. the proton exchange film fuel battery system of aviation simplification according to claim 1, it is characterised in that：The combustion
The output voltage range of material battery is matched with the operating voltage of wind turbine, water pump, last row solenoid valve and radiator fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611115546.7A CN108172874B (en) | 2016-12-07 | 2016-12-07 | Simplified proton exchange membrane fuel cell system for aviation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611115546.7A CN108172874B (en) | 2016-12-07 | 2016-12-07 | Simplified proton exchange membrane fuel cell system for aviation |
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| Publication Number | Publication Date |
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| CN108172874A true CN108172874A (en) | 2018-06-15 |
| CN108172874B CN108172874B (en) | 2020-09-01 |
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| CN201611115546.7A Active CN108172874B (en) | 2016-12-07 | 2016-12-07 | Simplified proton exchange membrane fuel cell system for aviation |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2588216A (en) * | 2019-10-16 | 2021-04-21 | Gkn Aerospace Services Ltd | Apparatus |
Citations (4)
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|---|---|---|---|---|
| EP1401041A2 (en) * | 2002-09-17 | 2004-03-24 | Nissan Motor Co., Ltd. | Fuel cell system and related operating method |
| CN101043082A (en) * | 2007-04-27 | 2007-09-26 | 新源动力股份有限公司 | Fuel batter system with proton exchange film used for high-performance vehicle and ship |
| CN202662713U (en) * | 2012-06-14 | 2013-01-09 | 李凌华 | Electricity generating and supplying device for hydrogen energy fuel cell stack |
| CN204011562U (en) * | 2014-07-14 | 2014-12-10 | 江苏冰城电材股份有限公司 | Hydrogen power supply based on metal double polar plates |
-
2016
- 2016-12-07 CN CN201611115546.7A patent/CN108172874B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1401041A2 (en) * | 2002-09-17 | 2004-03-24 | Nissan Motor Co., Ltd. | Fuel cell system and related operating method |
| CN101043082A (en) * | 2007-04-27 | 2007-09-26 | 新源动力股份有限公司 | Fuel batter system with proton exchange film used for high-performance vehicle and ship |
| CN202662713U (en) * | 2012-06-14 | 2013-01-09 | 李凌华 | Electricity generating and supplying device for hydrogen energy fuel cell stack |
| CN204011562U (en) * | 2014-07-14 | 2014-12-10 | 江苏冰城电材股份有限公司 | Hydrogen power supply based on metal double polar plates |
Non-Patent Citations (2)
| Title |
|---|
| 缪智力，俞红梅等: "掺杂SiO2对PEMFC低湿度性能的影响", 《电源技术》 * |
| 韩力群，张力，何晨光等: "《空中机器人》", 30 June 2016, 中国民主法治出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2588216A (en) * | 2019-10-16 | 2021-04-21 | Gkn Aerospace Services Ltd | Apparatus |
| GB2588216B (en) * | 2019-10-16 | 2022-07-27 | Gkn Aerospace Services Ltd | Aircraft fluid release systems |
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| Publication number | Publication date |
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| CN108172874B (en) | 2020-09-01 |
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