CN212412132U - Lithium battery cooling system for aviation - Google Patents
Lithium battery cooling system for aviation Download PDFInfo
- Publication number
- CN212412132U CN212412132U CN202022198460.3U CN202022198460U CN212412132U CN 212412132 U CN212412132 U CN 212412132U CN 202022198460 U CN202022198460 U CN 202022198460U CN 212412132 U CN212412132 U CN 212412132U
- Authority
- CN
- China
- Prior art keywords
- cooling
- pipeline
- aviation
- plate
- lithium battery
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 77
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title claims abstract description 45
- 229910052744 lithium Inorganic materials 0.000 title claims abstract description 45
- 230000017525 heat dissipation Effects 0.000 claims abstract description 27
- 239000000110 cooling liquid Substances 0.000 claims abstract description 24
- 239000007788 liquid Substances 0.000 claims description 23
- 238000003466 welding Methods 0.000 claims description 7
- 230000004089 microcirculation Effects 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 3
- 239000010439 graphite Substances 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 239000002480 mineral oil Substances 0.000 claims description 3
- 235000010446 mineral oil Nutrition 0.000 claims description 3
- 239000003921 oil Substances 0.000 claims description 3
- 229910052710 silicon Inorganic materials 0.000 claims description 3
- 239000010703 silicon Substances 0.000 claims description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 230000004087 circulation Effects 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 14
- 239000002826 coolant Substances 0.000 description 6
- 238000007789 sealing Methods 0.000 description 3
- 239000012809 cooling fluid Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 150000001298 alcohols Chemical class 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003063 flame retardant Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000002861 polymer material Substances 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
Classifications
-
- 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
Abstract
The utility model discloses an aviation lithium battery heat dissipation system, which comprises a heat conducting plate group, a radiator and a cooling pipeline; the cooling pipeline is communicated with the cooling liquid source and then communicated between the heat conducting plate group and the radiator to form a circulating pipeline; the heat conducting plate group consists of a plurality of heat conducting plates which are arranged at intervals, the cooling pipeline is branched into a plurality of cooling branch pipes which are in one-to-one correspondence with the heat conducting plates, and the cooling branch pipes are communicated with the cooling pipeline after being connected with the corresponding heat conducting plates. The utility model forms a heat dissipation circulation pipeline of the lithium battery through the heat conducting plate group, the radiator and the cooling pipeline; the utility model adopts a plurality of guide plates to be matched with the cooling branch pipes of the cooling pipeline branches, thereby greatly improving the heat exchange area of the cooling liquid and effectively improving the heat dissipation effect; the utility model provides a problem that lithium cell group heat distributes, the operating temperature who makes the aviation use lithium cell obtains effective control, has prolonged life, the performance decay rate of lithium cell and has obtained effective control, guaranteed the security of lithium cell work.
Description
Technical Field
The utility model belongs to the technical field of the lithium cell technique and specifically relates to a lithium cell cooling system for aviation.
Background
The lithium battery pack for aviation is a novel high-energy battery, is successfully applied to an airborne direct-current chemical power supply at present, plays roles of providing emergency power supply and starting an engine for key equipment in the using process of an airplane, and is a reliable guarantee for safe flight of the airplane. The lithium battery pack has the advantages of high output power and long working time in use, but also has the defect of large heat productivity of the battery, if the service temperature of the lithium battery pack exceeds 55 ℃, the performance attenuation of the lithium battery pack is aggravated, the service life is greatly shortened, and the safety risk of the lithium battery pack is also increased.
At present, three main measures for battery heat dissipation in the aviation field are available, one is to adopt filled polymer materials for heat conduction and heat dissipation, such as polyurethane, heat-conducting silica gel and the like; one type adopts natural heat dissipation, and the interior of the battery pack is directly used without considering the heat dissipation problem; and the last method is to fill the metal aluminum plate in the battery pack to increase heat conduction. Although the above heat dissipation scheme has the characteristics of simple design and low cost, and can be used under the condition that the working current of the lithium battery pack is very small, a new heat dissipation measure must be adopted under the working environment of high multiplying power and large current of the airplane, and the traditional heat dissipation method cannot meet the use requirement.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve is: the lithium battery heat dissipation system for the aviation is good in heat dissipation effect.
For solving the technical problem the utility model discloses the technical scheme who adopts is: the lithium battery heat dissipation system for aviation comprises a heat conduction plate group, a radiator and a cooling pipeline; the cooling pipeline is communicated with the cooling liquid source and then communicated between the heat conducting plate group and the radiator to form a circulating pipeline; the heat conducting plate group consists of a plurality of heat conducting plates which are arranged at intervals, the cooling pipeline is branched into a plurality of cooling branch pipes which are in one-to-one correspondence with the heat conducting plates, and the cooling branch pipes are communicated with the cooling pipeline after being connected with the corresponding heat conducting plates.
Further, the method comprises the following steps: the heat conducting plate consists of a cover plate and a liquid flow plate, and the liquid flow plate is fixed on the cover plate; the liquid flow plate is provided with liquid flow pipelines distributed throughout the liquid flow plate, and the liquid flow pipelines are communicated with the cooling branch pipes.
Further, the method comprises the following steps: the heat conducting plate is an aluminum plate or a graphite plate.
Further, the method comprises the following steps: the radiator comprises radiating fins, a flow guide pipe and a protective plate, wherein the radiating fins are arranged at intervals and fixed on the protective plate, and the flow guide pipe penetrates through the radiating fins and then is communicated with the cooling pipeline.
Further, the method comprises the following steps: the thickness of the radiating fins is 0.2-0.3 mm, and the spacing distance between every two adjacent radiating fins is 1-2 mm; the radiating fins are made of metal materials.
Further, the method comprises the following steps: the honeycomb duct is composed of a plurality of branch pipe sections and bent pipe sections, the branch pipe sections penetrate through the radiating fins and are arranged in parallel, and the bent pipe sections are communicated with the end heads of the adjacent branch pipe sections.
Further, the method comprises the following steps: the radiating fins and the guide pipe are of an integrated structure fixed by welding.
Further, the method comprises the following steps: the cooling system further comprises a discharge valve, and the discharge valve is arranged on a connecting pipeline of the cooling pipeline and the cooling liquid source.
Further, the method comprises the following steps: the device also comprises a micro circulating pump arranged on the cooling pipeline; the micro circulating pump is arranged on the pipeline before the branch of the cooling pipeline.
Further, the method comprises the following steps: the cooling liquid in the cooling liquid source is pure water, silicon oil, mineral oil or alcohol water solution.
The utility model has the advantages that: the cooling liquid in the cooling pipeline flows through the heat conducting plate group to carry out heat exchange to take away heat, and then enters the cooling pipeline again after the heat is dissipated at the radiator, so that the circulating heat dissipation of the cooling liquid to the heat conducting plate group is realized; the utility model adopts a plurality of guide plates to be matched with the cooling branch pipes of the cooling pipeline branches, thereby greatly improving the heat exchange area of the cooling liquid and effectively improving the heat dissipation effect; the utility model provides a problem that lithium cell group heat distributes, the operating temperature who makes the aviation use lithium cell obtains effective control, has prolonged life, the performance decay rate of lithium cell and has obtained effective control, guaranteed the security of lithium cell work.
Drawings
Fig. 1 is a schematic structural view of the present invention;
labeled as: 100-heat conducting plate group, 110-heat conducting plate, 111-cover plate, 112-liquid flow plate, 200-radiator, 210-radiating fin, 220-flow guide pipe, 230-guard plate, 300-cooling pipeline, 310-cooling branch pipe, 400-cooling liquid source, 500-bleeder valve and 600-micro circulating pump.
Detailed Description
In order to facilitate understanding of the present invention, the following description is further provided with reference to the accompanying drawings.
As shown in fig. 1, the heat dissipation system for an aviation lithium battery of the present invention includes a heat conduction plate set 100, a heat sink 200, and a cooling pipeline 300. The cooling pipeline 300 is communicated with a cooling liquid source 400, cooling liquid in the cooling liquid source 400 flows into the cooling pipeline 300 and flows through the cooling pipeline 300, the cooling pipeline 300 is in contact with the heat conduction plate group 100, and the heat conduction plate group 100 is in contact with the lithium battery to transfer heat; the cooling liquid in the cooling pipeline 300 exchanges heat with the heat conduction plate group 100, the lithium battery absorbs heat transferred by the heat conduction plate group 100, then the cooling liquid heated by the absorbed heat flows into the radiator 200 through the cooling pipeline 300, the radiator 200 cools the heated cooling liquid, and the cooled cooling liquid flows to the heat conduction plate group 100 again for heat exchange to form a circulation pipeline so as to realize circulation heat dissipation. The utility model discloses the coolant liquid in well coolant liquid source 400 can adopt the aqueous solution of pure water, silicon oil, mineral oil or alcohols, and the coolant liquid has low, the fire-retardant performance of viscosity.
The heat conducting plate group 100 in the utility model is composed of a plurality of heat conducting plates 110, the heat conducting plates 110 are arranged at intervals and are in contact with the lithium battery for heat exchange, the thickness of the heat conducting plate 110 is 1-3 mm, the occupied space is small, and an aluminum plate or a graphite plate is adopted as the heat conducting plate 110, so that a good heat conducting effect can be achieved; and the cooling line 300 is branched such that the cooling line 300 is branched into a plurality of cooling branch pipes 310 corresponding one-to-one to the heat transfer plates 110. The heat conducting plate 110 is composed of a cover plate 111 and a liquid flow plate 112, the liquid flow plate 112 is fixed on the cover plate 111, and the liquid flow plate 112 and the cover plate 111 can be bonded and fixed by an adhesive or welded and fixed by welding. The flow plate 112 is provided with a flow pipe extending over the flow plate 112, the flow pipe is communicated with the cooling branch pipes 310, the cooling fluid in the cooling pipeline 300 enters different cooling branch pipes 310 and flows into the corresponding flow pipe, and the flow pipe extends over the flow plate 112, so that the cooling fluid also flows through the entire flow plate 112 for heat exchange. The utility model discloses in adopt heat conduction plate group 100 that a plurality of heat conduction plates 110 constitute to carry out the heat exchange with the lithium cell, and set up heat conduction plate 110 through the interval and set up the mode that increases the liquid flow pipeline of heat exchange area on heat conduction plate 110 and improve the radiating effect, the heat transfer that heat conduction plate 110 that a plurality of intervals set up can reply with the lithium cell, absorb the heat of lithium cell in a large number, and the liquid flow pipeline that spreads over heat conduction plate 110 can make the heat exchange area between coolant liquid and the heat conduction plate 110 increase, with heat exchange efficiency and the heat absorption volume between improvement coolant liquid and heat conduction plate 110.
As shown in fig. 1, the heat sink 200 of the present invention comprises heat dissipating fins 210, a flow guiding pipe 220 and a protecting plate 230, wherein the heat dissipating fins 210 are arranged at intervals and fixed on the protecting plate 230, and the flow guiding pipe 220 is communicated with the cooling pipeline 300 after penetrating through the heat dissipating fins 210. The thickness of the heat dissipation fins 210 is 0.2-0.3 mm, and the spacing distance between adjacent heat dissipation fins 210 is 1-2 mm; the heat dissipation fins 210 are made of a metal material with good heat conductivity, and the surfaces of the heat dissipation fins 210 are subjected to blackening treatment. The heat dissipation fins 210 and the flow guide pipe 220 are welded into an integral structure through laser welding, plasma welding or resistance welding; the guard plate 230 is supported by an aluminum plate, the guard plate 230 is welded and fixed to the outer edge of the heat dissipation fin 210 by a laser welding process, and the guard plate 230 protects the heat dissipation fin 210 and improves the stability of the overall structure.
The utility model discloses in order to improve radiator 200's radiating effect, honeycomb duct 220 comprises a plurality of spinal branch sections and bend section, a plurality of spinal branch sections run through radiating fin 210 and mutual parallel arrangement, the bend section sets up and communicates adjacent spinal branch section in the end department of spinal branch section, make honeycomb duct 220 be multistage revolution structure, increase the circulation route of coolant liquid through honeycomb duct 220 extension length in radiator 200, reach the purpose that improves the radiating effect.
As shown in fig. 1, the present invention further provides a relief valve 500 on the cooling pipeline 300, and the relief valve 500 is disposed on the connection pipeline between the cooling pipeline 300 and the cooling liquid source 400. The 500 bleeder valve has the characteristics of high response speed, low-temperature sealing, high-temperature sealing and low-pressure environment sealing, and can discharge gas generated by a heat dissipation system when necessary. In addition, a micro circulation pump 600 is further disposed on the cooling pipeline 300, and the micro circulation pump 600 is disposed on the pipeline before the cooling pipeline 300 branches; the micro-circulation pump 600 has the characteristics of small volume, fast response speed and proper flow rate, and the micro-circulation pump 600 provides power for the flow of the cooling liquid in the cooling pipeline 300, so that the cooling liquid can circularly flow in the cooling pipeline 300.
In order to accurately control the work of the aviation lithium battery cooling system, a monitoring circuit and a temperature sensing device can be added on the aviation lithium battery cooling system to control the starting and the closing of the aviation lithium battery cooling system, and the starting and the closing temperature points of the aviation lithium battery cooling system can be set to be 40 ℃ and 35 ℃. The temperature of the lithium battery for aviation is monitored by the monitoring circuit and the temperature sensing device, and the start and stop of the micro-circulation pump 600 are controlled according to the temperature of the lithium battery for aviation.
Claims (10)
1. Lithium cell cooling system for aviation, its characterized in that: the heat dissipation device comprises a heat conduction plate group (100), a radiator (200) and a cooling pipeline (300); after the cooling pipeline (300) is communicated with the cooling liquid source (400), a circulating pipeline is formed between the heat conduction plate group (100) and the radiator (200); the heat conducting plate group (100) is composed of a plurality of heat conducting plates (110) which are arranged at intervals, the cooling pipeline (300) is branched into a plurality of cooling branch pipes (310) which are in one-to-one correspondence with the heat conducting plates (110), and the cooling branch pipes (310) are communicated with the cooling pipeline (300) after being connected with the corresponding heat conducting plates (110).
2. The lithium battery cooling system for aviation of claim 1, wherein: the heat conducting plate (110) consists of a cover plate (111) and a liquid flow plate (112), and the liquid flow plate (112) is fixed on the cover plate (111); the liquid flow plate (112) is provided with liquid flow pipelines which are distributed on the liquid flow plate (112) and communicated with the cooling branch pipes (310).
3. The lithium battery cooling system for aviation of claim 2, wherein: the heat conducting plate (110) is an aluminum plate or a graphite plate.
4. The lithium battery cooling system for aviation of claim 1, wherein: the radiator (200) is composed of radiating fins (210), a guide pipe (220) and a guard plate (230), the radiating fins (210) are arranged at intervals and fixed on the guard plate (230), and the guide pipe (220) penetrates through the radiating fins (210) and then is communicated with the cooling pipeline (300).
5. The lithium battery cooling system for aviation of claim 4, wherein: the thickness of the radiating fins (210) is 0.2-0.3 mm, and the spacing distance between every two adjacent radiating fins (210) is 1-2 mm; the heat dissipation fins (210) are made of metal materials.
6. The lithium battery cooling system for aviation of claim 4, wherein: the flow guide pipe (220) is composed of a plurality of branch pipe sections and bent pipe sections, the branch pipe sections penetrate through the radiating fins (210) and are arranged in parallel, and the bent pipe sections are communicated with the end heads of the adjacent branch pipe sections.
7. The lithium battery cooling system for aviation of claim 4, wherein: the radiating fins (210) and the guide pipe (220) are of an integrated structure fixed by welding.
8. The lithium battery cooling system for aviation of claim 1, wherein: the cooling system further comprises a relief valve (500), wherein the relief valve (500) is arranged on a connecting pipeline of the cooling pipeline (300) and the cooling liquid source (400).
9. The lithium battery cooling system for aviation of claim 1, wherein: the cooling device also comprises a micro circulating pump (600) arranged on the cooling pipeline (300); the micro circulation pump (600) is arranged on a pipeline before the branch of the cooling pipeline (300).
10. The lithium battery cooling system for aviation of claim 1, wherein: the cooling liquid in the cooling liquid source (400) is pure water, silicon oil, mineral oil or alcohol water solution.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022198460.3U CN212412132U (en) | 2020-09-30 | 2020-09-30 | Lithium battery cooling system for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022198460.3U CN212412132U (en) | 2020-09-30 | 2020-09-30 | Lithium battery cooling system for aviation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212412132U true CN212412132U (en) | 2021-01-26 |
Family
ID=74375261
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022198460.3U Active CN212412132U (en) | 2020-09-30 | 2020-09-30 | Lithium battery cooling system for aviation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212412132U (en) |
-
2020
- 2020-09-30 CN CN202022198460.3U patent/CN212412132U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2019154083A1 (en) | Liquid cooling pipeline and power supply apparatus | |
| CN106960988B (en) | Power lithium battery thermal management system | |
| CN108511850B (en) | Power battery composite thermal management system and method based on natural circulation | |
| US11404735B2 (en) | Immersed heat dissipation device for power battery | |
| CN107275710A (en) | Battery bag heat conducting and heat radiating device | |
| CN207818842U (en) | A kind of power battery heat-radiating device | |
| CN212412132U (en) | Lithium battery cooling system for aviation | |
| CN112510285A (en) | Heat dissipation method and device for vehicle battery module | |
| CN112072212A (en) | Lithium battery cooling system for aviation | |
| CN106602170A (en) | Variable contact-type battery heat management system | |
| CN213335744U (en) | Cold winding type finned tube with high heat exchange efficiency | |
| CN211700499U (en) | High-efficient heat abstractor of car battery | |
| CN209929438U (en) | High-efficient power battery water cooling plant | |
| CN109066007B (en) | Large-scale battery module integration box cooling system based on heat pipe | |
| CN109037833B (en) | Energy-saving battery radiator for electric automobile | |
| CN108807730B (en) | Layered electric automobile battery pack | |
| CN219999868U (en) | Be fit for quality of water automatic monitoring equipment closed cabin heat dissipation heat sink | |
| CN216563306U (en) | Liquid metal battery thermal management device | |
| CN215418309U (en) | New energy automobile power battery radiator assembly based on ultra-thin soaking plate | |
| CN214336785U (en) | Battery thermal management system | |
| CN210778894U (en) | Refrigerant direct cooling device and battery power supply system | |
| CN219873710U (en) | Rear elevation sealing plate convenient for heat dissipation for metal product battery | |
| CN210136990U (en) | Battery pack heat dissipation device | |
| CN210489784U (en) | Binary channels group battery cooling structure | |
| CN219611723U (en) | Photovoltaic module and heat dissipation system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 519 Sanjiang Avenue, Mianyang Economic Development Zone, Sichuan 621000 Patentee after: Sichuan Changhong Power Supply Co.,Ltd. Country or region after: China Address before: No. 519 Sanjiang Avenue, Mianyang Economic Development Zone, Sichuan 621000 Patentee before: SICHUAN CHANGHONG BATTERY Co.,Ltd. Country or region before: China |