CN110718663A - Lithium fluorocarbon battery electrostatic protection device and method for space aircraft - Google Patents
Lithium fluorocarbon battery electrostatic protection device and method for space aircraft Download PDFInfo
- Publication number
- CN110718663A CN110718663A CN201910966841.0A CN201910966841A CN110718663A CN 110718663 A CN110718663 A CN 110718663A CN 201910966841 A CN201910966841 A CN 201910966841A CN 110718663 A CN110718663 A CN 110718663A
- Authority
- CN
- China
- Prior art keywords
- battery
- protection device
- cell
- unit
- lithium fluorocarbon
- 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.)
- Granted
Links
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title claims abstract description 23
- 229910052744 lithium Inorganic materials 0.000 title claims abstract description 23
- NBVXSUQYWXRMNV-UHFFFAOYSA-N fluoromethane Chemical compound FC NBVXSUQYWXRMNV-UHFFFAOYSA-N 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000003068 static effect Effects 0.000 claims abstract description 18
- 238000003860 storage Methods 0.000 claims abstract description 4
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 238000003466 welding Methods 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000005476 soldering Methods 0.000 claims description 3
- YBDACTXVEXNYOU-UHFFFAOYSA-N C(F)(F)(F)F.[Li] Chemical compound C(F)(F)(F)F.[Li] YBDACTXVEXNYOU-UHFFFAOYSA-N 0.000 claims 1
- 239000000126 substance Substances 0.000 abstract description 2
- 230000002265 prevention Effects 0.000 abstract 1
- 229910052751 metal Inorganic materials 0.000 description 5
- 239000002184 metal Substances 0.000 description 5
- 238000009459 flexible packaging Methods 0.000 description 4
- 239000004020 conductor Substances 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/50—Current conducting connections for cells or batteries
- H01M50/502—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/05—Accumulators with non-aqueous electrolyte
- H01M10/052—Li-accumulators
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/425—Structural combination with electronic components, e.g. electronic circuits integrated to the outside of the casing
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Secondary Cells (AREA)
Abstract
The invention relates to a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft, belonging to the technical field of chemical power sources, wherein the lithium fluorocarbon battery comprises a plurality of unit covers, a battery pack is arranged in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the negative electrode of the battery pack through the electrostatic discharge resistors. According to the invention, the static discharge resistor (RJ24/0.25W) is welded on the cell cover and connected with the negative pole column, so that static on the cell shell is discharged into a battery loop, and the function of static prevention is further realized.
Description
Technical Field
The invention belongs to the technical field of chemical power supplies, and particularly relates to a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft.
Background
The lithium fluorocarbon battery is a system with the highest specific energy in the lithium primary battery, and the 0.01C discharge specific energy of the flexible package lithium fluorocarbon battery is up to 720 Wh/kg. The small-capacity lithium fluorocarbon battery has 18650 type and D type structures, and the large-capacity lithium fluorocarbon battery adopts a flexible packaging structure. When the flexible packaging structure is applied to a space aircraft, the sealing performance of the flexible packaging structure does not meet the requirement on the leakage rate of the battery in a vacuum environment, so the flexible packaging structure and the metal shell sealing structure are required to be adopted.
In the use of the spacecraft, an isolated metal conductor is not allowed to exist in the battery pack according to the reliability design requirement, so that the damage of static accumulation to the battery is avoided.
In the unit cell, a unit shell and a cover are welded into a whole, a positive pole column and a negative pole column are installed on the unit cover, a T-shaped gasket is used for insulation, and an O-shaped ring is used for realizing a compression sealing structure of the pole column. The unit shell and the unit cover are made of aluminum alloy materials so as to reduce the weight of the structure and realize high specific energy of the battery pack. Because the single batteries are in a flexible package structure, the single batteries in the unit batteries can be connected in series and in parallel, and the single batteries are insulated from the shell. Therefore, the metal case is an isolated conductor in the unit cell structure of the flexible package + metal case.
In order to realize the electrostatic discharge of the unit shell, an electrostatic discharge loop needs to be provided, and the spacecraft requires equipotential grounding, which is in contradiction with the fact that batteries in the series-connected loop must be isolated.
Disclosure of Invention
The invention provides a lithium fluorocarbon battery electrostatic protection device and method for a space aircraft, aiming at solving the technical problems in the prior art, wherein an electrostatic discharge resistor (RJ24/0.25W) is welded on a cell cover and is connected with a negative pole column, so that the static on a cell shell is discharged into a battery loop, and the function of preventing static is further realized.
The invention provides a lithium fluorocarbon battery electrostatic protection device for a space aircraft, wherein the lithium fluorocarbon battery comprises a plurality of unit covers, a battery pack is arranged in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the cathode of the battery pack through the electrostatic discharge resistors.
Further, the electrostatic discharge is resistance welded in the cell cover.
Further, the static leakage resistor is formed by connecting two resistors in parallel.
The second purpose of the invention is to provide a method for manufacturing the lithium fluorocarbon cell electrostatic protection device for the space aircraft, which comprises the following steps:
s1, before the pole is installed on the unit cover, welding an aluminum-nickel composite belt;
s2, welding a static leakage resistance assembly with a connecting terminal, and soldering a resistance on the aluminum-nickel composite strip;
s3, fixing, gluing and sealing the static leakage resistor;
and S4, mounting the connecting terminal of the static leakage resistor on the negative pole of the unit cell in a threaded manner.
The invention has the advantages and positive effects that:
1) the electrostatic protection design is realized, and no isolated conductor exists in the battery pack;
2) the electrostatic discharge of the cell shell is solved in the battery, so that the complex wiring process is reduced;
3) the isolation of structure is realized through the insulation board between the cell of establishing ties, does not have the electric leakage latent route, and the insulation between the cell is destroyed under the trouble condition, and the static bleeder resistor is fused by heavy current, and the cell shell is insulated with the negative pole post, forms short-circuit protection.
Drawings
Fig. 1 is a circuit diagram of a preferred embodiment of the present invention.
Detailed Description
In order to further understand the contents, features and effects of the present invention, the following embodiments are illustrated and described in detail with reference to the accompanying drawings:
referring to fig. 1, a lithium fluorocarbon battery electrostatic protection device for a space vehicle includes a plurality of unit covers, a battery pack is disposed in each unit cover, and the battery pack is formed by connecting a plurality of storage batteries in parallel; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the cathode of the battery pack through the electrostatic discharge resistors. The two battery packs (unit cells) connected in series are structurally isolated from each other by an insulating plate.
Preferably, the electrostatic discharge is resistance welded into the cell cover.
The static leakage resistor is formed by connecting two resistors in parallel.
The working principle of the preferred embodiment is as follows:
and a metal film resistor is connected between the cell shell and the negative electrode in series, so that the cell shell and the negative electrode are at the same potential, and a discharge passage is provided for the static electricity accumulated on the cell shell.
A method for manufacturing the lithium fluorocarbon cell electrostatic protection device for the space aircraft comprises the following steps:
1) before the unit cover is provided with the pole, an aluminum-nickel composite belt is welded at a position specified by the process by using an ultrasonic welding machine;
2) welding a static leakage resistor assembly with a wiring terminal, and soldering a resistor on the aluminum-nickel composite belt;
3) fixing, gluing and sealing the resistor;
4) and mounting the wiring terminal of the static leakage resistor on the negative pole column of the unit cell in a threaded manner.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications, equivalent changes and modifications made to the above embodiment according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.
Claims (4)
1. A lithium fluorocarbon cell electrostatic protection device for a space aircraft comprises a plurality of unit covers, wherein a battery pack is arranged in each unit cover and consists of a plurality of storage batteries in parallel connection; the battery packs in the two adjacent unit covers are sequentially connected in series; the lithium fluorocarbon battery electrostatic protection device for the space aircraft comprises electrostatic discharge resistors arranged in each unit cover, and the unit covers are connected with the negative electrode of the battery pack through the electrostatic discharge resistors.
2. The lithium fluorocarbon cell electrostatic protection device for space vehicles of claim 1, wherein the electrostatic discharge is solder-welded into the cell cover.
3. The electrostatic protection device for the lithium-carbon fluoride battery for the space aircraft according to claim 1 or 2, wherein the electrostatic discharge resistor consists of two resistors connected in parallel.
4. A method of manufacturing a lithium fluorocarbon cell electrostatic discharge protection device for a space vehicle according to any of claims 1 to 3, characterized by: the method comprises the following steps:
s1, before the pole is installed on the unit cover, welding an aluminum-nickel composite belt;
s2, welding a static leakage resistance assembly with a connecting terminal, and soldering a resistance on the aluminum-nickel composite strip;
s3, fixing, gluing and sealing the static leakage resistor;
and S4, mounting the connecting terminal of the static leakage resistor on the negative pole of the unit cell in a threaded manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910966841.0A CN110718663B (en) | 2019-10-12 | 2019-10-12 | Lithium fluorocarbon battery electrostatic protection device and method for space aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910966841.0A CN110718663B (en) | 2019-10-12 | 2019-10-12 | Lithium fluorocarbon battery electrostatic protection device and method for space aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110718663A true CN110718663A (en) | 2020-01-21 |
| CN110718663B CN110718663B (en) | 2022-03-22 |
Family
ID=69212540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910966841.0A Active CN110718663B (en) | 2019-10-12 | 2019-10-12 | Lithium fluorocarbon battery electrostatic protection device and method for space aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110718663B (en) |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5992669A (en) * | 1997-03-31 | 1999-11-30 | Toyoda Gosei Co., Ltd. | Fuel tank cap and method of manufacturing the same |
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| US20130193927A1 (en) * | 2012-01-18 | 2013-08-01 | Li-Tec Battery Gmbh | Electrochemical energy storage device, battery having at least two such electrochemical energy storage devices, and method for operating such an electrochemical energy strorage device |
| JP2013244928A (en) * | 2012-05-29 | 2013-12-09 | Hitachi Automotive Systems Ltd | On-vehicle electronic device, and vehicle mounted therewith |
| CN203482479U (en) * | 2013-04-22 | 2014-03-12 | 无锡艾柯威科技有限公司 | Electrostatic leakage circuit of static electricity generation body |
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-
2019
- 2019-10-12 CN CN201910966841.0A patent/CN110718663B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5992669A (en) * | 1997-03-31 | 1999-11-30 | Toyoda Gosei Co., Ltd. | Fuel tank cap and method of manufacturing the same |
| JP2000340392A (en) * | 1999-05-26 | 2000-12-08 | Pentel Corp | Static electricity removing tool |
| JP2004208350A (en) * | 2002-12-24 | 2004-07-22 | Brother Ind Ltd | Charger |
| JP2008146896A (en) * | 2006-12-07 | 2008-06-26 | Matsushita Electric Ind Co Ltd | Lead storage battery |
| US20080226980A1 (en) * | 2007-03-15 | 2008-09-18 | Woochoul Kim | Protection circuit board for secondary battery and secondary battery using the protection circuit board |
| JP2009043476A (en) * | 2007-08-07 | 2009-02-26 | Panasonic Corp | Lead storage battery |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN110718663B (en) | 2022-03-22 |
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