CN117109862B - Electric aircraft power lithium battery thermal management forced air cooling test platform - Google Patents
Electric aircraft power lithium battery thermal management forced air cooling test platform Download PDFInfo
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- CN117109862B CN117109862B CN202311382368.4A CN202311382368A CN117109862B CN 117109862 B CN117109862 B CN 117109862B CN 202311382368 A CN202311382368 A CN 202311382368A CN 117109862 B CN117109862 B CN 117109862B
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- 238000012360 testing method Methods 0.000 title claims abstract description 56
- 238000001816 cooling Methods 0.000 title claims abstract description 46
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title claims abstract description 40
- 229910052744 lithium Inorganic materials 0.000 title claims abstract description 40
- 238000002474 experimental method Methods 0.000 claims abstract description 13
- 238000001931 thermography Methods 0.000 claims abstract description 13
- 238000004140 cleaning Methods 0.000 claims description 39
- 238000007789 sealing Methods 0.000 claims description 18
- 230000007246 mechanism Effects 0.000 claims description 11
- 239000000428 dust Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 5
- 239000005304 optical glass Substances 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000033228 biological regulation Effects 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 2
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 12
- 230000004907 flux Effects 0.000 abstract description 3
- 230000010405 clearance mechanism Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 238000011160 research Methods 0.000 description 6
- 230000001105 regulatory effect Effects 0.000 description 4
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 229910001416 lithium ion Inorganic materials 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 241000883990 Flabellum Species 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012372 quality testing Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/003—Environmental or reliability tests
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/378—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC] specially adapted for the type of battery or accumulator
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/385—Arrangements for measuring battery or accumulator variables
-
- 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
- Y02E60/10—Energy storage using batteries
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- Environmental & Geological Engineering (AREA)
- Hybrid Cells (AREA)
Abstract
The invention discloses a thermal management air cooling test platform for a power lithium battery of an electric aircraft, and belongs to the field of lithium battery experimental test platforms. The utility model provides an electric aircraft power lithium cell thermal management forced air cooling test platform, includes the wind-tunnel, and the wind-tunnel comprises entry check valve, entry linkage segment, battery placement middle section, export check valve, export linkage segment, fan control system, infrared thermal imaging observation system and clearance mechanism. The invention keeps the same with the environment of the electric aircraft power lithium battery to the greatest extent, thereby simulating the working environment of the electric aircraft power lithium battery to the greatest extent, improving the scientific accuracy of the battery air cooling experiment, avoiding the condition that the wind speed of the air speed blown by the direct measurement test fan in the previous battery air cooling experiment is different along with different wind speeds of the measurement position, greatly improving the accuracy of wind speed measurement, and improving the accuracy of parameters such as heat flux obtained by wind speed calculation.
Description
Technical Field
The invention relates to the technical field of lithium battery experimental test platforms, in particular to a heat management air cooling test platform for a power lithium battery of an electric aircraft.
Background
Lithium Ion Batteries (LIB) become more and more pets in new energy vehicles due to the advantages of low self-discharge rate, long service life, high power, high energy density and the like, but the problems of battery degradation, thermal safety and the like caused by the material characteristics of the lithium ion batteries are also greatly restricted from further popularization and application of the lithium ion batteries. One of the main measures proposed by the current commercial market and universities of scientific research institutes for solving the problem is to perform heat management on the lithium battery, and the main purpose of the heat management is to enable the lithium battery to be always in a proper working temperature range, reduce the possibility of occurrence of disasters such as thermal runaway and improve the application safety of the lithium battery. The main current lithium battery heat management modes mainly comprise air cooling, liquid cooling, heat pipe cooling, semiconductor cooling and the like.
The electric aircraft is also one of the most-hot lithium battery application directions at present, and because of special requirements of the operation of the aircraft, particularly light-weight requirements, the heat management mode that the cooling effect such as liquid cooling is remarkable but the weight of the aircraft is additionally increased is not applicable to the field of the electric aircraft, and the air cooling with simple structure and easy realization becomes the optimal mode of the heat management of the power battery of the electric aircraft. For the application scenario of thermal management of electric aircraft power batteries using air cooling, many scientific research institutes and universities have been currently performing follow-up research on this topic, but no research on test platforms in this scenario has been performed. Based on the above, we propose a thermal management air cooling test platform for an electric aircraft power lithium battery.
Disclosure of Invention
The invention aims to solve the problem that in the prior art, aiming at the application scene of performing heat management on an electric aircraft power battery by using air cooling, more scientific research institutes and universities currently perform follow-up research on the problem, but the problem of researching a test platform in the scene is not solved, and provides a heat management air cooling test platform for an electric aircraft power lithium battery.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the electric aircraft power lithium battery thermal management air cooling test platform comprises an air tunnel, wherein the air tunnel consists of an inlet check valve, an inlet connecting section, a battery placement middle section, an outlet check valve, an outlet connecting section, a fan control system, an infrared thermal imaging observation system and a cleaning mechanism;
the inlet check valve is arranged at the inlet of the inlet connecting section, and the outlet check valve is arranged between the battery placing middle section and the outlet connecting section and is connected with the battery placing middle section through a flange;
the inlet connecting section is connected with the battery placing middle section through a flange, sealing strips are used for sealing the connecting parts, and the battery placing middle section is positioned in the middle of the wind tunnel and is used for placing a battery and performing related tests;
the outlet check valve is connected with the other side of the middle section of the battery placement by a flange, sealing strips are used for sealing the connecting parts, the fan control system is arranged at the tail end of the wind tunnel, is connected with the connecting section of the wind tunnel outlet by a flange and is sealed by the sealing strips; the infrared thermal imaging observation system is connected with the middle section of the battery.
In order to enable the cleaning plate in the cleaning mechanism to circularly slide inside and outside, preferably, one end, close to the inlet connecting section, of the inlet check valve is fixedly connected with a check valve flange, a check valve connecting hole is formed in the check valve flange, a butterfly blade is mounted at one end, far away from the inlet connecting section, of the inlet check valve, an ash discharge port is formed in the bottom of the inlet check valve, and a magnetic ring is fixedly connected to the inner side wall of the inlet check valve.
In order to enable the cleaning mechanism to rotate and filter air, preferably, the inlet connecting section is close to the filter screen fixedly connected with one end inner side wall of the inlet check valve, the inlet connecting section is close to the one end fixedly connected with flange of the inlet check valve, the fixed hole is formed in the flange, the middle part of the filter screen is rotationally connected with a rotating shaft, the outer side wall of the rotating shaft is fixedly connected with fan blades, and one end of the rotating shaft is rotationally connected with the inner side wall of the inlet connecting section.
Further, the battery is placed the middle section both sides wall and is equipped with the installation department and is used for fixed test battery, and the lower lateral wall is equipped with inserts the installation department and is used for fixed wind velocity measurement meter, has seted up experimental circuit preformed hole on the battery is placed the middle section for arrange battery charging and discharging line and temperature measurement line, has seted up battery fixed preformed hole on the battery is placed the middle section, is used for fixed battery.
Further, the inlet connection section, the battery placement middle section and the outlet connection section exist as a constriction section, a throat section and a divergent section respectively, and the design accords with the Venturi effect.
Further, the fan control system is arranged outside the outlet connecting section and consists of a power supply line, a PWM speed regulating module, a direct current power supply and a test fan.
Further, the infrared thermal imaging observation system consists of an observation hole, optical glass, an infrared thermal imager, a transmission line and a control computer.
In order to clear up the filter screen, prevent that the filter screen from being blocked by the dust in the air, influence the air inlet efficiency of air, further, clearance mechanism includes the piston cylinder with pivot tip fixed connection, the inside wall sliding connection of piston cylinder has the piston board, one side fixedly connected with reset spring of piston board, one side fixedly connected with connecting pipe that the piston board is close to reset spring, one end fixedly connected with clearance board of piston board is kept away from to the connecting pipe, clearance board's lateral wall sliding connection has the balladeur train, the inlet port has been seted up on the piston cylinder.
Further, one side of the check valve flange far away from the inlet check valve is attached to the fixing flange, and the check valve connecting hole corresponds to the fixing hole.
Still further, the one end that reset spring kept away from the piston board is fixed connection with the inside wall of piston cylinder, the tip of balladeur train and the tip fixed connection of piston cylinder, the connecting pipe runs through piston cylinder and with piston cylinder sliding connection, the clearance board is laminated mutually with the filter screen, the clearance board sets up to four, and two clearance boards of same side are one with the magnetic ring actuation mutually, another is repulsed mutually with the magnetic ring.
Compared with the prior art, the invention provides the electric aircraft power lithium battery thermal management air cooling test platform, which has the following beneficial effects:
1. the lithium battery air cooling test platform can measure the air speed in the channel, under the requirement of fully considering battery air cooling experiments, the surface temperature change condition in the battery experiment process is conveniently observed, the test wires such as the charging and discharging equipment are conveniently arranged, the connection among all the components of the whole platform is tight, the cooling air entering the platform is uniform and controllable, the check valve aims to ensure that the battery is in a closed space under the condition that a test fan is not involved, so that the environment where the battery is located is kept consistent to the greatest extent, the working environment of the lithium battery of the electric aircraft is simulated to the greatest extent, the problems of low data reliability and deviation are avoided, and the accuracy of the scientificity of the battery air cooling experiments is improved.
2. The whole photosensitive resin material is adopted by the test platform, the heat conductivity is relatively low and is generally between 0.1 and 0.3W/mK, the heat dissipation caused by the material in the test process is reduced, the accuracy of experimental data is ensured, meanwhile, the whole wind tunnel is formed by assembling and splicing after modularized 3D printing, the degree of freedom is high, the later assembly of components, the adjustment of parts and the maintenance are convenient, and the practicability of the test platform is improved.
3. The platform is designed mainly by adopting a Venturi effect, and air is sucked out from the tail part by utilizing the test fan so as to control the air entering the wind tunnel to be automatically sucked due to pressure difference change, so that the measured wind speed is uniform, the condition that the wind speed of the air blown out by the test fan is different along with different wind speeds at different measuring positions in the previous battery air cooling experiment is avoided, the accuracy of wind speed measurement is greatly improved, the accuracy of parameters such as heat flux obtained by wind speed calculation is also improved compared with the prior art, and the method is beneficial to the whole scientificity of the experiment.
4. This electric aircraft power lithium cell thermal management forced air cooling test platform, at test fan during operation, can make the flabellum rotate, drive the pivot and rotate for cleaning mechanism rotates along the surface of filter screen, at cleaning mechanism pivoted in-process, cleaning mechanism can reciprocate inside and outside slip under the effect of magnetic ring, make the cleaning plate pivoted in-process provide inside and outside slip, improve the cleaning efficiency to the filter screen, and can make the cleaning plate circulation blow to the filter screen simultaneously, further improve the cleaning efficiency to the filter screen, prevent that the dust from blocking up the filter screen, influence the quality and the efficiency of forced air cooling test.
The device has the advantages that the device is identical to or can be realized by adopting the prior art, the device is consistent with the environment of the power lithium battery of the electric aircraft to the greatest extent, the working environment of the power lithium battery of the electric aircraft is simulated to the greatest extent, the problems of low data reliability and deviation are avoided, the scientifically accurate performance of a battery air cooling experiment is improved, the device has higher practicability, the situation that the wind speed of the air speed blown by a direct measurement test fan in the prior battery air cooling experiment is different along with different wind speeds at the measurement position is avoided, the accuracy of wind speed measurement is greatly improved, and the accuracy of parameters such as heat flux obtained by wind speed calculation is also improved compared with the prior art, so that the device is beneficial to the scientificity of the whole experiment.
Drawings
Fig. 1 is a schematic diagram of a three-dimensional structure of a front side of an electric aircraft power lithium battery thermal management air cooling test platform according to the present invention;
fig. 2 is a schematic diagram of a side three-dimensional structure of a thermal management air cooling test platform for an electric aircraft power lithium battery according to the present invention;
fig. 3 is a schematic diagram of a front middle cutaway structure of an electric aircraft power lithium battery thermal management air cooling test platform according to the present invention;
fig. 4 is a schematic three-dimensional structure diagram of an inlet check valve of an electric aircraft power lithium battery thermal management air cooling test platform according to the present invention;
fig. 5 is a schematic diagram of a middle cut-away structure of an inlet check valve and an inlet connecting section of an electric aircraft power lithium battery thermal management air cooling test platform according to the present invention;
fig. 6 is a schematic three-dimensional structure diagram of an inlet connection section of an electric aircraft power lithium battery thermal management air cooling test platform according to the present invention;
fig. 7 is a schematic diagram of a three-dimensional partially cut-away structure of a cleaning mechanism of a thermal management air cooling test platform for an electric aircraft power lithium battery.
In the figure: 1. an inlet check valve; 11. butterfly blades; 12. a check valve flange; 13. a check valve connection hole; 14. an ash discharge port; 15. a magnetic ring; 2. an inlet connection section; 21. a fixed flange; 22. a fixing hole; 23. a filter screen; 24. a fan blade; 25. a rotating shaft; 3. a battery is placed in the middle section; 31. a battery fixing preformed hole; 32. an experiment line preformed hole; 4. an outlet check valve; 5. an outlet connection section; 6. a fan control system; 61. a power supply line; 62. a PWM speed regulation module; 63. a direct current power supply; 64. testing a fan; 7. an infrared thermal imaging viewing system; 71. an optical glass; 72. an infrared thermal imager; 73. a transmission line; 8. a piston cylinder; 81. a piston plate; 82. a return spring; 83. a connecting pipe; 84. a cleaning plate; 85. a carriage; 86. an air inlet hole.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-7, a thermal management air cooling test platform for an electric aircraft power lithium battery comprises a wind tunnel, wherein the wind tunnel consists of an inlet check valve 1, an inlet connecting section 2, a battery placement middle section 3, an outlet check valve 4, an outlet connecting section 5, a fan control system 6, an infrared thermal imaging observation system 7 and a cleaning mechanism; the inlet check valve 1 is arranged at the inlet of the inlet connecting section 2, and the outlet check valve 4 is arranged between the battery placing middle section 3 and the outlet connecting section 5 and is connected through a flange; the inlet connecting section 2 is connected with the battery placing middle section 3 by a flange, sealing strips are used for sealing the connecting parts, and the battery placing middle section 3 is positioned in the middle of the wind tunnel and is used for placing a battery and carrying out related tests; the outlet check valve 4 is connected with the other side of the battery placing middle section 3 by a flange, sealing strips are used for sealing the connecting parts, the fan control system 6 is arranged at the tail end of the wind tunnel, is connected with the wind tunnel outlet connecting section 5 by a flange and is sealed by the sealing strips; the infrared thermal imaging observation system 7 is connected with the battery placing middle section 3;
the parts are fixed through the flanges by using bolts, and sealing rubber rings are filled between the flanges so as to ensure the tightness of the whole wind tunnel except the position of the wind tunnel, reduce experimental errors, and the outlet check valve 4 is mainly used for controlling the outlet air quantity and ensuring that no movable air flow flows between the parts when the wind tunnel is not subjected to experiments, thereby reducing the measurement errors of parameters such as air flow rate, flow quantity and the like and ensuring the reliability and accuracy of experimental data.
Referring to fig. 1-6, a check valve flange 12 is fixedly connected to one end of an inlet check valve 1 close to an inlet connection section 2, a check valve connection hole 13 is formed in the check valve flange 12, a butterfly blade 11 is mounted at one end of the inlet check valve 1 far away from the inlet connection section 2, an ash discharge port 14 is formed in the bottom of the inlet check valve 1, a magnetic ring 15 is fixedly connected to the inner side wall of the inlet check valve 1, a filter screen 23 is fixedly connected to the inner side wall of one end of the inlet connection section 2 close to the inlet check valve 1, a fixing flange 21 is fixedly connected to one end of the inlet connection section 2 close to the inlet check valve 1, a fixing hole 22 is formed in the fixing flange 21, one side of the check valve flange 12 far away from the inlet check valve 1 is attached to the fixing flange 21, the check valve connection hole 13 corresponds to the fixing hole 22, a rotating shaft 25 is rotatably connected to the middle of the filter screen 23, fan blades 24 are fixedly connected to the outer side walls of the rotating shaft 25, mounting parts are arranged at two side walls of a battery placement middle section 3 for fixing test batteries, insertion mounting parts are arranged at the lower side walls for fixing wind gauges, a battery placement middle section 3 is provided with a reserved battery placement middle section 32, a reserved battery placement line is used for arranging a measurement line, a reserved battery placement line is used as a charging line is used for a measurement line, and a measurement line is reserved for a charging line is used for being used as a venturi section 5, and is connected to an outlet section is placed, and is a charging section is 3 is in a is placed, and is in a 3, and is in a line is designed, and is in a 3 and is in a and a 3 and is placed;
it should be noted that, the inlet check valve 1 is connected with the whole flow port, ensure that the uniformity of the air entering from the inlet check valve 1 is stronger, the diameter of the middle section 3 is reduced when the air flow enters the battery from the inlet connecting section 2, the fluid resistance is small, the pressure loss is also small, the measuring range is wider, the accuracy can be ensured, the installation part required by the fixed anemometer is inserted into the reserved position reserved at the bottom of the middle section 3 of the battery, the anemometer is fixed, and the air flow rate entering the middle section 3 of the battery is conveniently, stably and accurately measured.
Referring to fig. 1-3, a fan control system 6 is disposed outside the outlet connection section 5, the fan control system 6 being composed of a power supply line 61, a PWM speed regulation module 62, a dc power supply 63, and a test fan 64.
Referring to fig. 1 to 3, the infrared thermal imaging observation system 7 is composed of an observation hole, an optical glass 71, an infrared thermal imager 72, a transmission line 73 and a control computer.
Referring to fig. 5-7, the cleaning mechanism comprises a piston cylinder 8 fixedly connected with the end of a rotating shaft 25, a piston plate 81 is slidably connected to the inner side wall of the piston cylinder 8, a return spring 82 is fixedly connected to one side of the piston plate 81, one end of the return spring 82, which is far away from the piston plate 81, is fixedly connected with the inner side wall of the piston cylinder 8, a connecting pipe 83 is fixedly connected to one side of the piston plate 81, which is close to the return spring 82, the connecting pipe 83 penetrates through the piston cylinder 8 and is slidably connected with the piston cylinder 8, one end of the connecting pipe 83, which is far away from the piston plate 81, is fixedly connected with cleaning plates 84, the cleaning plates 84 are four, one cleaning plate 84 on the same side is attracted with a magnetic ring 15, the other cleaning plate 84 is repelled with the magnetic ring 15, the cleaning plates 84 are attached to a filter screen 23, the outer side wall of the cleaning plate 84 is slidably connected with a sliding frame 85, the end of the sliding frame 85 is fixedly connected with the end of the piston cylinder 8, and an air inlet hole 86 is formed in the piston cylinder 8;
it should be noted that, the air inlet 86 is provided with a one-way valve, so that external air can only enter the piston cylinder 8 through the air inlet 86, the connecting pipe 83 and the cleaning plate 84 are hollow, hollow bristles are arranged on the cleaning plate 84, and the connecting pipe 83 is provided with a one-way valve, so that air in the piston cylinder 8 can only be discharged through the connecting pipe 83.
In the invention, an inlet check valve 1 is firstly placed at an inlet, a sealing ring is used for being placed between the inlet check valve 1 and an inlet connecting section 2, a bolt is connected with the inlet check valve 1 and the inlet connecting section 2 through a check valve connecting hole 13 and a fixing hole 22, and a honeycomb inlet is arranged between the inlet check valve 1 and the inlet connecting section 2, so that the air entering is uniform; the battery placing middle section 3, the outlet check valve 4, the outlet connecting section 5 and the fan control system 6 are all connected through bolts and sealing rings, in the connecting process, the battery is installed in the battery placing middle section 3 through a clamp, the clamp passes through a battery fixing reserved hole 31, and the whole wind tunnel connecting sequence is sequentially an inlet check valve 1, an inlet connecting section 2, the battery placing middle section 3, the outlet check valve 4, the outlet connecting section 5 and the fan control system 6;
the wind tunnel is controlled by sucking out air in the wind tunnel through a last part of test fan 64 so that the air flows, the wind speed is controlled by PWM speed regulating module 62 and DC power supply 63 connected with test fan 64, the air flow speed in the whole wind tunnel is regulated by regulating the power of test fan 64, the inlet check valve 1 and the outlet check valve 4 installed at the inlet and outlet are used for ensuring that the battery is in a closed space under the condition that test fan 64 is not interposed, so that the battery is kept consistent with the environment of the electric aircraft power lithium battery to the greatest extent, the working environment of the electric aircraft power lithium battery is simulated to the greatest extent, and the butterfly blades 11 and discs arranged at the inlet check valve 1 and the outlet check valve 4 act according to the wind speed, so that the butterfly blades 11 and discs have corresponding opening amplitude so as to enable the air inflow to be controllable and stable; an observation hole is reserved above the battery placement middle section 3 and matched with the optical glass 71 to observe the surface temperature change condition of the battery under the working condition, an infrared thermal imaging picture is obtained through the infrared thermal imaging instrument 72, and two inserted mounting parts are reserved at the bottom of the battery placement middle section 3 and can be matched with related components to play a role in fixing an anemometer;
when the air cooling test is carried out, as air circulates in the wind tunnel, the fan blades 24 rotate under the action of the air, the rotating shaft 25 is driven to rotate, the piston cylinder 8 is driven to rotate, the cleaning plate 84 rotates to clean the filter screen 23, when the cleaning plate 84 rotates to the position of the magnetic ring 15, the cleaning plate 84 on the same side slides inwards under the action of the magnetic ring 15, and one outwards slides, when the cleaning plate 84 slides inwards, the piston plate 81 is pushed to slide inwards through the connecting pipe 83, the air in the piston cylinder 8 is extruded into the cleaning plate 84, the cleaning plate 84 blows to the outer surface of the filter screen 23, the sufficient cleaning of the outer surface of the filter screen 23 is realized, the blocking of the filter screen 23 is prevented, the air inlet efficiency is influenced, when the cleaning plate 84 slides outwards, the piston plate 81 slides outwards through the connecting pipe 83, the outside air is sucked into the piston cylinder 8 through the air inlet hole 86, and the cleaned dust is discharged through the dust outlet 14, so that the cleanliness of the filter screen 23 is ensured, and the air inlet efficiency and the battery quality testing and the air cooling efficiency are ensured.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (7)
1. The electric aircraft power lithium battery thermal management air cooling test platform comprises a wind tunnel and is characterized by comprising an inlet check valve (1), an inlet connecting section (2), a battery placing middle section (3), an outlet check valve (4), an outlet connecting section (5), a fan control system (6), an infrared thermal imaging observation system (7) and a cleaning mechanism;
the inlet check valve (1) is arranged at the inlet of the inlet connecting section (2), the outlet check valve (4) is arranged between the battery placing middle section (3) and the outlet connecting section (5) and is connected through a flange, one end, close to the inlet connecting section (2), of the inlet check valve (1) is fixedly connected with a check valve flange (12), check valve connecting holes (13) are formed in the check valve flange (12), butterfly blades (11) are arranged at one end, far away from the inlet connecting section (2), of the inlet check valve (1), a dust outlet (14) is formed in the bottom of the inlet check valve (1), and a magnetic ring (15) is fixedly connected to the inner side wall of the inlet check valve (1);
the inlet connecting section (2) is connected with the battery placing middle section (3) through a flange, sealing strips are used for sealing the connecting parts, the battery placing middle section (3) is positioned in the middle of a wind tunnel and is used for placing a battery and carrying out relevant tests, a filter screen (23) is fixedly connected to the inner side wall of one end, close to the inlet check valve (1), of the inlet connecting section (2), a fixing flange (21) is fixedly connected to one end, close to the inlet check valve (1), of the inlet connecting section (2), a fixing hole (22) is formed in the fixing flange (21), a rotating shaft (25) is rotatably connected to the middle part of the filter screen (23), a fan blade (24) is fixedly connected to the outer side wall of the rotating shaft (25), and one end of the rotating shaft (25) is rotatably connected with the inner side wall of the inlet connecting section (2);
the cleaning mechanism comprises a piston cylinder (8) fixedly connected with the end part of the rotating shaft (25), a piston plate (81) is slidably connected to the inner side wall of the piston cylinder (8), a return spring (82) is fixedly connected to one side of the piston plate (81), a connecting pipe (83) is fixedly connected to one side, close to the return spring (82), of the piston plate (81), a cleaning plate (84) is fixedly connected to one end, far away from the piston plate (81), of the connecting pipe (83), a sliding frame (85) is slidably connected to the outer side wall of the cleaning plate (84), and an air inlet hole (86) is formed in the piston cylinder (8);
the outlet check valve (4) is connected with the other side of the battery placing middle section (3) by a flange, sealing strips are used for sealing the connecting parts, the fan control system (6) is arranged at the tail end of the wind tunnel, is connected with the wind tunnel outlet connecting section (5) by a flange and is sealed by the sealing strips; the infrared thermal imaging observation system (7) is connected with the battery placement middle section (3).
2. The electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein two side walls of the battery placement middle section (3) are provided with mounting parts for fixing test batteries, the lower side wall is provided with insertion mounting parts for fixing an air velocity meter, the battery placement middle section (3) is provided with experiment line reserved holes (32) for arranging battery charging and discharging wires and temperature measuring wires, and the battery placement middle section (3) is provided with battery fixing reserved holes (31) for fixing batteries.
3. The electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein the inlet connection section (2), the battery placement middle section (3) and the outlet connection section (5) exist as a constriction section, a throat section and a divergent section respectively, and the design conforms to a venturi effect.
4. The electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein the fan control system (6) is placed outside the outlet connection section (5), and the fan control system (6) is composed of a power supply line (61), a PWM speed regulation module (62), a direct current power supply (63) and a test fan (64).
5. The electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein the infrared thermal imaging observation system (7) consists of an observation hole, an optical glass (71), an infrared thermal imager (72), a transmission line (73) and a control computer.
6. An electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein one side of the check valve flange (12) away from the inlet check valve (1) is attached to the fixing flange (21), and the check valve connecting hole (13) corresponds to the fixing hole (22).
7. An electric aircraft power lithium battery thermal management air cooling test platform according to claim 1, wherein one end of the return spring (82) far away from the piston plate (81) is fixedly connected with the inner side wall of the piston cylinder (8), the end of the sliding frame (85) is fixedly connected with the end of the piston cylinder (8), the connecting pipe (83) penetrates through the piston cylinder (8) and is in sliding connection with the piston cylinder (8), the cleaning plates (84) are attached to the filter screen (23), the cleaning plates (84) are four, one cleaning plate (84) on the same side is attracted with the magnetic ring (15), and the other cleaning plate (84) on the same side is repelled with the magnetic ring (15).
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