CN104049212A - Low-pressure work performance test system for hydrogen-air fuel cell - Google Patents
Low-pressure work performance test system for hydrogen-air fuel cell Download PDFInfo
- Publication number
- CN104049212A CN104049212A CN201310083679.0A CN201310083679A CN104049212A CN 104049212 A CN104049212 A CN 104049212A CN 201310083679 A CN201310083679 A CN 201310083679A CN 104049212 A CN104049212 A CN 104049212A
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- air
- fuel cell
- air fuel
- pressure
- 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
Abstract
The invention relates to a low-pressure work performance test system for a hydrogen-air fuel cell. The system comprises the hydrogen-air fuel cell disposed in a low-pressure environment cabin, and further comprises a hydrogen bottle and a hydrogen vacuum pressure-reducing valve which are connected. The hydrogen vacuum pressure-reducing valve is connected with the hydrogen-air fuel cell. The system further comprises an air inlet, an air flowmeter and an air vacuum pressure-reducing valve which are successively connected. The air vacuum pressure-reducing valve is connected with the hydrogen-air fuel cell. The system also comprises a hydrogen flow control valve, a hydrogen vacuum buffer tank, a hydrogen path vacuum pump and a hydrogen evacuation port which are successively connected. The hydrogen flow control valve is connected with the hydrogen-air fuel cell. The system further comprises an air flow control valve, an air path vacuum pump and an air evacuation port which are successively connected. The air flow control valve is connected with the inside of the low-pressure environment cabin. The system also comprises a load, a cooling fan and an electronic monitoring system which are respectively connected with the hydrogen-air fuel cell. According to the invention, work performance testing of the cell under the condition of low pressure can be finished, and data support is provided for application of a fuel cell power system to an unmanned plane.
Description
Technical field
The present invention relates to a kind of hydrogen-air fuel cell infrabar serviceability test macro, particularly relate to a kind of gaseous tension that enters fuel cell by control lower than atmospheric pressure state, draw the volt-ampere characteristic of battery, for the hydrogen-air fuel cell infrabar serviceability test macro of experimental basis is established in the application of fuel cell power system on High Altitude UAV.
Background technology
In the application of High Altitude UAV, along with the increase of flying height, environmental pressure also decreases, and the reduction of pressure will directly affect the output efficiency of battery, thereby the use power of battery is decreased, and even affects the normal flight of unmanned plane.
Hydrogen-air fuel cell is minimum at the test pressure of the state of ground is 1 atmospheric pressure, and conventional test method as shown in Figure 1.
Hydrogen road reduces to normal pressure by hydrogen reduction valve 21 by the gases at high pressure in hydrogen cylinder 1 and enters battery, enters the Hydrogen Vapor Pressure of battery by pressure-measuring-point P1 monitoring, and the water of the foreign gas on hydrogen road and generation is discharged battery by bleed valve 20.The supply of air is thrown the air in environment into battery by air inlet pump 19, utilizes flow control valve 15 to control the air mass flow that enters battery, and battery side distribution air outlet 4, is directly discharged to remaining reaction air in ambient atmosphere.The used heat that battery produces falls apart in environment by cooling fan 6, will connect corresponding load 3 and be used for electric energy and the battery TT&C system 9 that consuming cells produces, the monitoring of the index such as pressure, temperature of completion system when simultaneously battery operated.
Under subatmospheric environment, the Performance Ratio atmospheric pressure state of fuel cell reduces how many, also not relevant test introduction.Therefore, design a kind of hydrogen-air fuel cell Performance Test System of (lower than an atmospheric pressure) under hypobaric, the application tool for fuel cell power system on unmanned plane is of great significance.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of gaseous tension that enters fuel cell of can controlling lower than the method for normal pressure, reaches the hydrogen-air fuel cell infrabar serviceability test macro of simulated battery under hypobaric work.
For solving the problems of the technologies described above, a kind of hydrogen-air fuel cell infrabar of the present invention serviceability test macro, comprises the hydrogen-air fuel cell that is positioned at hypobaric cabin; Also comprise the hydrogen cylinder and the hydrogen VRV that connect successively, hydrogen VRV is connected with hydrogen-air fuel cell; Also comprise the air in, air flowmeter, the air vacuum reduction valve that connect successively, air vacuum reduction valve is connected with hydrogen-air fuel cell; Also comprise the hydrogen flowing quantity variable valve, hydrogen vacuum buffer tank, hydrogen road vacuum pump, the hydrogen evacuation port that connect successively, hydrogen flowing quantity variable valve is connected with hydrogen-air fuel cell; Also comprise the air flow rate adjustment valve, air road vacuum pump, the air evacuation port that connect successively, air flow rate adjustment valve is connected with hypobaric cabin is inner; Also comprise the load, cooling fan and the electronic monitoring and control system that are connected with hydrogen-air fuel cell respectively.
The present invention can realize the infrabar control that enters fuel battery inside, completes the serviceability test of battery under infrabar, draws polarization curve, for the application of fuel cell power system on unmanned plane provides data supporting.
Brief description of the drawings
Fig. 1 is normal pressure hydrogen-air fuel cell pilot system schematic diagram.
Fig. 2 is the polarization curve schematic diagram under hydrogen-air fuel cell normal pressure and infrabar duty.
Fig. 3 is the schematic diagram of a kind of hydrogen-air fuel cell infrabar serviceability test macro provided by the invention.
In figure: 1 is hydrogen cylinder, 2 is hydrogen VRV, 3 is load, 4 is fuel battery air outlet, 5 is hydrogen-air fuel cell, 6 is cooling fan, 7 is hypobaric cabin, 8 is hydrogen flowing quantity variable valve, 9 is electronic measurement and control system, 10 is hydrogen vacuum buffer tank, 11Wei Qing road vacuum pump, 12 is hydrogen evacuation port, 13 is air evacuation port, 14 is air road vacuum pump, 15 is air flow rate adjustment valve, 16 is air vacuum reduction valve, 17 is air flowmeter, 18 is air in, 19 is air inlet pump, 20 is hydrogen gas exhaust valve, 21 is hydrogen reduction valve, P1 is Hydrogen Vapor Pressure measuring point, P2 is air pressure measuring point.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further detailed explanation.
The present invention includes hydrogen-air fuel cell 5; Also comprise the hydrogen cylinder 1 and hydrogen VRV 2 that connect successively, hydrogen VRV 2 is connected with hydrogen-air fuel cell 5; Also comprise the air in 18, air flowmeter 17, the air vacuum reduction valve 16 that connect successively, air vacuum reduction valve 16 is connected with hydrogen-air fuel cell 5; Also comprise the hydrogen flowing quantity variable valve 8, hydrogen vacuum buffer tank 10, hydrogen road vacuum pump 11, the hydrogen evacuation port 12 that connect successively, hydrogen flowing quantity variable valve 8 is connected with hydrogen-air fuel cell 5; Also comprise the air flow rate adjustment valve 15, air road vacuum pump 14, the air evacuation port 13 that connect successively, air flow rate adjustment valve 15 is connected with hypobaric cabin 7 is inner; Also comprise the load 3, cooling fan 6 and the electronic monitoring and control system 9 that are connected with hydrogen-air fuel cell 5 respectively.
Hydrogen-air fuel cell 5 is placed in hypobaric cabin 7.Hypobaric cabin 7 internal pressures are lower than an atmospheric pressure.
Hydrogen Vapor Pressure measuring point is between hydrogen VRV 2 and hypobaric cabin 7, and air pressure measuring point is between air vacuum reduction valve 16 and hypobaric cabin 7.
Hydrogen-air fuel cell 5 is placed in environment under low pressure cabin 7, and environment under low pressure cabin 7 is closed container, for the hypobaric of simulated altitude.Because the top hole pressure of common reduction valve is generally all higher than normal pressure, therefore VRV 2 is used on hydrogen road instead, by the high pressure air reducing in gas cylinder 1 to required vacuum pressure.Hydrogen-air fuel cell hydrogen outlet arranges flow control valve 8 hydrogen flowing quantity is controlled, and after variable valve, connect vacuum buffer tank 10 and vacuum pump 11, take the hydrogen being discharged in surge tank with vacuum pump away, ensure that the low pressure hydrogen of discharging fuel cell can be discharged in air smoothly.
Because hydrogen-air fuel cell 5 is participated in the air pressure of reacting lower than normal pressure, therefore air intake pump is cancelled on air road, by the pressure reduction inside and outside environment under low pressure cabin directly by air intake inside battery, utilize air vacuum reduction valve 16 to control the air pressure that enters battery, match with hydrogen, reacting remaining air is directly discharged in environment under low pressure cabin 7, if the air that hydrogen-air fuel cell 5 is discharged is not discharged in time, the rising of environment under low pressure cabin 7 pressure will be caused, the imbalance of build-up of pressure, therefore, need to utilize air vacuum pump 14 to extract out out of my cabin this part air, simultaneously, air flow rate adjustment valve 15 is set, and to control the air mass flow of discharging outside environment under low pressure cabins 7 identical with the air mass flow of battery discharge, to keep the stable of cabin internal pressure.
Adopt the present invention can realize the infrabar control that enters hydrogen-air fuel cell 5 inside, completing hydrogen-air fuel cell 5 serviceability of (lower than an atmospheric pressure) under infrabar tests, draw polarization curve, for the application of hydrogen-air fuel cell 5 power systems on unmanned plane provides data supporting, its test effect is as Fig. 2.
Claims (1)
1. a hydrogen-air fuel cell infrabar serviceability test macro, is characterized in that: comprise the hydrogen-air fuel cell that is positioned at hypobaric cabin; Also comprise the hydrogen cylinder and the hydrogen VRV that connect successively, described hydrogen VRV is connected with described hydrogen-air fuel cell; Also comprise the air in, air flowmeter, the air vacuum reduction valve that connect successively, described air vacuum reduction valve is connected with described hydrogen-air fuel cell; Also comprise the hydrogen flowing quantity variable valve, hydrogen vacuum buffer tank, hydrogen road vacuum pump, the hydrogen evacuation port that connect successively, described hydrogen flowing quantity variable valve is connected with described hydrogen-air fuel cell; Also comprise the air flow rate adjustment valve, air road vacuum pump, the air evacuation port that connect successively, described air flow rate adjustment valve is connected with described hypobaric cabin is inner; Also comprise the load, cooling fan and the electronic monitoring and control system that are connected with described hydrogen-air fuel cell respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310083679.0A CN104049212A (en) | 2013-03-15 | 2013-03-15 | Low-pressure work performance test system for hydrogen-air fuel cell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310083679.0A CN104049212A (en) | 2013-03-15 | 2013-03-15 | Low-pressure work performance test system for hydrogen-air fuel cell |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104049212A true CN104049212A (en) | 2014-09-17 |
Family
ID=51502302
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310083679.0A Pending CN104049212A (en) | 2013-03-15 | 2013-03-15 | Low-pressure work performance test system for hydrogen-air fuel cell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104049212A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106876751A (en) * | 2017-02-14 | 2017-06-20 | 北京东方华氢科技有限公司 | A kind of hydrogen-oxygen fuel cell |
| CN112249361A (en) * | 2020-09-22 | 2021-01-22 | 北京卫星环境工程研究所 | Cooling and ventilation simulation device for testing high-altitude airborne equipment and control method |
| CN113571737A (en) * | 2021-07-12 | 2021-10-29 | 大连锐格新能源科技有限公司 | Air-cooled galvanic pile environment simulation test system and control method thereof |
| CN113571739A (en) * | 2021-09-24 | 2021-10-29 | 天津航天瑞莱科技有限公司 | Low-temperature low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
| CN114509681A (en) * | 2021-12-28 | 2022-05-17 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN114673680A (en) * | 2022-04-26 | 2022-06-28 | 中国电子科技集团公司第十四研究所 | Fan capability test device suitable for low atmospheric pressure environment |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020192523A1 (en) * | 1996-06-06 | 2002-12-19 | Lynntech, Inc. | Fuel cell system for low pressure operation |
| TW558852B (en) * | 2002-07-12 | 2003-10-21 | Asia Pacific Fuel Cell Tech | Control apparatus and method of fuel cell set |
| TW572462U (en) * | 2002-12-04 | 2004-01-11 | Asia Pacific Fuel Cell Tech | Function test and exhibition device set of fuel cell power supply device |
| CN1567635A (en) * | 2003-07-09 | 2005-01-19 | 上海神力科技有限公司 | A fuel battery hydrogen gas cyclic utilization device adapting for low-pressure operation |
| CN1649197A (en) * | 2004-01-28 | 2005-08-03 | 三星Sdi株式会社 | Fuel cell system |
| US20080210812A1 (en) * | 2005-03-07 | 2008-09-04 | Airbus Deutschland Gmbh | Fuel Cell Emergency System |
| EP2195870A2 (en) * | 2007-09-27 | 2010-06-16 | Airbus Operations GmbH | Fuel cell system with suction operation for an aircraft |
| CN102060107A (en) * | 2010-11-26 | 2011-05-18 | 北京航空航天大学 | Energy supply system for stratosphere electricity-electricity hybrid solar airship |
-
2013
- 2013-03-15 CN CN201310083679.0A patent/CN104049212A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020192523A1 (en) * | 1996-06-06 | 2002-12-19 | Lynntech, Inc. | Fuel cell system for low pressure operation |
| TW558852B (en) * | 2002-07-12 | 2003-10-21 | Asia Pacific Fuel Cell Tech | Control apparatus and method of fuel cell set |
| TW572462U (en) * | 2002-12-04 | 2004-01-11 | Asia Pacific Fuel Cell Tech | Function test and exhibition device set of fuel cell power supply device |
| CN1567635A (en) * | 2003-07-09 | 2005-01-19 | 上海神力科技有限公司 | A fuel battery hydrogen gas cyclic utilization device adapting for low-pressure operation |
| CN1649197A (en) * | 2004-01-28 | 2005-08-03 | 三星Sdi株式会社 | Fuel cell system |
| US20080210812A1 (en) * | 2005-03-07 | 2008-09-04 | Airbus Deutschland Gmbh | Fuel Cell Emergency System |
| EP2195870A2 (en) * | 2007-09-27 | 2010-06-16 | Airbus Operations GmbH | Fuel cell system with suction operation for an aircraft |
| CN102060107A (en) * | 2010-11-26 | 2011-05-18 | 北京航空航天大学 | Energy supply system for stratosphere electricity-electricity hybrid solar airship |
Non-Patent Citations (3)
| Title |
|---|
| F.BARBIR ET AL.: "Efficiency and weight trade-off analysis of regenerative fuel cells as energy storage for aerospace applications", 《INTERNATIONAL JOURNAL OF HYDROGEN ENERGY》 * |
| SYLVAIN GELFI ET AL.: "Dynamics of Low-Pressure and High-Pressure Fuel Cell Air Supply System", 《PROCEEDINGS OF THE AMERICAN CONTROL CONFERENCE》 * |
| 吴峰 等: "燃料电池在航天中的应用", 《电池》 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106876751A (en) * | 2017-02-14 | 2017-06-20 | 北京东方华氢科技有限公司 | A kind of hydrogen-oxygen fuel cell |
| CN106876751B (en) * | 2017-02-14 | 2020-11-10 | 北京东方华氢科技有限公司 | Hydrogen-oxygen fuel cell |
| CN112249361A (en) * | 2020-09-22 | 2021-01-22 | 北京卫星环境工程研究所 | Cooling and ventilation simulation device for testing high-altitude airborne equipment and control method |
| CN112249361B (en) * | 2020-09-22 | 2022-08-02 | 北京卫星环境工程研究所 | Cooling and ventilation simulation device for testing high-altitude airborne equipment and control method |
| CN113571737A (en) * | 2021-07-12 | 2021-10-29 | 大连锐格新能源科技有限公司 | Air-cooled galvanic pile environment simulation test system and control method thereof |
| CN113571737B (en) * | 2021-07-12 | 2024-04-02 | 大连锐格新能源科技有限公司 | Air cooling pile environment simulation test system and control method thereof |
| CN113571739A (en) * | 2021-09-24 | 2021-10-29 | 天津航天瑞莱科技有限公司 | Low-temperature low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
| CN113571739B (en) * | 2021-09-24 | 2021-12-17 | 天津航天瑞莱科技有限公司 | Low-temperature low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
| WO2023045023A1 (en) * | 2021-09-24 | 2023-03-30 | 天津航天瑞莱科技有限公司 | Low-temperature, low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
| CN114509681A (en) * | 2021-12-28 | 2022-05-17 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN114509681B (en) * | 2021-12-28 | 2022-10-28 | 重庆阿泰可科技股份有限公司 | Vacuum environment test system for hydrogen-air fuel battery |
| CN114673680A (en) * | 2022-04-26 | 2022-06-28 | 中国电子科技集团公司第十四研究所 | Fan capability test device suitable for low atmospheric pressure environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104049212A (en) | Low-pressure work performance test system for hydrogen-air fuel cell | |
| CN102023654B (en) | Large environment simulation laboratory pressure control system and control method thereof | |
| WO2023045023A1 (en) | Low-temperature, low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle | |
| US20130133334A1 (en) | Cooling system for engine and aircraft air | |
| CN101832861B (en) | Submarine environment condition simulating device for diesel engine | |
| CN110411698A (en) | The anti-deicing test method of icing wind tunnel | |
| CN209803307U (en) | fuel cell system modularization test platform | |
| CN112751061B (en) | Fuel cell air circuit testing system and method | |
| CN113571737B (en) | Air cooling pile environment simulation test system and control method thereof | |
| CN102866017A (en) | Altitude environment simulation test cabin for internal combustion power equipment | |
| CN205327441U (en) | Aircraft fuel oil system's testing arrangement under simulated high -altitude environment | |
| CN212621408U (en) | Fuel cell hydrogen test system | |
| CN105480433A (en) | Testing device and method for aircraft fuel system in simulated high altitude environment | |
| CN202582786U (en) | Test device of aircraft engine bleed air system temperature sensor | |
| CN103575540A (en) | High-altitude simulation test device of engine-driven pressure system | |
| CN111090049A (en) | Low-temperature low-pressure cold start test system and test method for fuel cell | |
| CN102287362B (en) | System for testing performance and energy efficiency of air compressor by simulating all-weather working conditions | |
| CN203587313U (en) | Vacuum-pumping device system of wind tunnel pumping experiment | |
| CN203688224U (en) | Engine driven air pressure system high altitude simulation tester | |
| CN108344575A (en) | A kind of test device for fuel battery engines | |
| CN203587314U (en) | Vacuum device with heat exchange function | |
| CN211425782U (en) | Fuel cell system part leakage detection device | |
| CN211478576U (en) | Low-temperature low-pressure cold start test system for fuel cell | |
| US8709670B2 (en) | Fuel cell system with mechanical check valve | |
| CN203587315U (en) | Vacuum buffer device with pressure stable control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140917 |