CN116487806A - Aircraft battery pack supporting high-rate discharge - Google Patents
Aircraft battery pack supporting high-rate discharge Download PDFInfo
- Publication number
- CN116487806A CN116487806A CN202310509472.9A CN202310509472A CN116487806A CN 116487806 A CN116487806 A CN 116487806A CN 202310509472 A CN202310509472 A CN 202310509472A CN 116487806 A CN116487806 A CN 116487806A
- Authority
- CN
- China
- Prior art keywords
- battery
- aircraft
- rate discharge
- voltage
- supporting high
- 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
- 239000004593 Epoxy Substances 0.000 claims abstract description 8
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000000741 silica gel Substances 0.000 claims abstract description 7
- 229910002027 silica gel Inorganic materials 0.000 claims abstract description 7
- 210000004027 cell Anatomy 0.000 claims description 14
- 239000010410 layer Substances 0.000 claims description 10
- 239000012790 adhesive layer Substances 0.000 claims description 5
- 239000006260 foam Substances 0.000 claims description 5
- 238000009413 insulation Methods 0.000 claims description 5
- 239000004020 conductor Substances 0.000 claims description 4
- 230000017525 heat dissipation Effects 0.000 claims description 3
- 239000000178 monomer Substances 0.000 claims description 3
- 210000005056 cell body Anatomy 0.000 claims description 2
- 229920006300 shrink film Polymers 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 3
- 239000002184 metal Substances 0.000 abstract description 3
- 239000000853 adhesive Substances 0.000 abstract description 2
- 230000001070 adhesive effect Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
- H01M50/244—Secondary casings; Racks; Suspension devices; Carrying devices; Holders characterised by their mounting method
-
- 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
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
- H01M50/249—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
-
- 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
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
- H01M50/262—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders with fastening means, e.g. locks
- H01M50/264—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders with fastening means, e.g. locks for cells or batteries, e.g. straps, tie rods or peripheral frames
-
- 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
- H01M50/503—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing characterised by the shape of the interconnectors
-
- 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
- H01M50/509—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing characterised by the type of connection, e.g. mixed connections
- H01M50/51—Connection only in series
-
- 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 invention discloses an aircraft battery module supporting high-rate discharge, which mainly comprises a heat shrinkage film, a plastic cover plate, a plastic bracket, electric cores, an epoxy plate, a heat conduction silica gel pad, a high-voltage wire harness assembly, a low-voltage wire harness assembly and a current collecting row, wherein each single electric core is adhered and fixed through double-sided adhesive, and the outermost side is wrapped into a whole through the heat shrinkage film; the invention adopts the ternary soft-package battery core, and has extremely high grouping efficiency; on the premise of ensuring the strength of the whole structure, the number and the variety of the metal structural members are reduced to the greatest extent, the energy density of the module is improved, and the cruising ability of the aircraft is greatly improved; the high-voltage connectors are respectively arranged at the output positions of the total positive electrode and the total negative electrode of the battery pack, so that the battery packs are connected in series at random, and different electric quantity requirements are met; the weight of the structural member is small, the grouping efficiency is high, the energy density is high, the modular design is realized, the total electric quantity can be flexibly adjusted, and the high-low voltage connection realizes the quick-plug function.
Description
Technical Field
The invention relates to the technical field of living body detection of wearable equipment, in particular to an aircraft battery module supporting high-rate discharge.
Background
A battery is an energy storage device, and is widely used in various fields. In recent years, with the rapid development of the industries of unmanned aerial vehicles, electric vehicles and the like, the battery technology has also made considerable progress. In order to better meet the demands of use, battery technology is evolving toward high energy density, fast charge speed, and high safety performance. The safety performance of the battery is closely related to the battery temperature. The battery can produce heat at the in-process of charging and discharging, and present power battery for aircraft does not have ripe PACK scheme in groups, and the space that mainly is limited to the inside reservation of aircraft and places the battery is very irregular and scattered, and similar large-scale, highly integrated car power battery package's structural style is not fit for the aircraft and uses.
If the heat dissipation is not effective in time, the temperature of the battery is increased, the battery is extremely sensitive to the temperature, and the battery burns due to the excessively high temperature, so that safety accidents are caused.
Disclosure of Invention
In order to solve the problems of the aircraft battery, the invention provides an aircraft battery module supporting high-rate discharge.
An aircraft battery module supporting high-rate discharge comprises a battery pack box body part, a current collecting row serving as a serial and parallel transfer conductor between battery monomers, a low-voltage wiring harness assembly for collecting module voltage and temperature data, and a positive and negative high-voltage wiring harness assembly for realizing battery pack charge and discharge and serial connection between battery packs; the current collector is arranged on the plastic bracket, and the top end of the plastic bracket is also connected with the low-voltage wire harness assembly and the positive and negative high-voltage wire harness assembly.
Further, a plastic cover plate is arranged on the right side of the plastic support for high-voltage insulation protection.
Further, the bottom surface, the top surface and the side surface opposite to one surface of the plastic cover plate of the battery pack box body are provided with heat-conducting silica gel pads for radiating and homogenizing the temperature of the battery pack.
Further, the front face of the battery pack box body part is provided with a plurality of layers of electric cores.
Further, a foam double-sided adhesive layer for absorbing battery expansion and fixing the battery cell is arranged between each two layers of the battery cell.
Furthermore, the front surface, the bottom surface and the back surface of the battery pack box body part and the side surface opposite to one surface of the plastic cover plate are also provided with epoxy plates which are clung to the battery cell body for structural protection.
Further, the outer layer of the battery pack is also provided with a heat shrinkage film which is fixed integrally and is insulated and protected.
The invention has the beneficial effects that: the invention provides an aircraft battery module supporting high-rate discharge, which adopts a ternary soft-package battery core and has extremely high grouping efficiency; on the premise of ensuring the strength of the whole structure, the number and the variety of the metal structural members are reduced to the greatest extent, the energy density of the module is improved, and the cruising ability of the aircraft is greatly improved; the high-voltage connectors are respectively arranged at the output positions of the total positive electrode and the total negative electrode of the battery pack, so that the battery packs are connected in series at random, and different electric quantity requirements are met; the weight of the structural member is small, the grouping efficiency is high, the energy density is high, the modular design is realized, the total electric quantity can be flexibly adjusted, and the high-low voltage connection realizes the quick-plug function.
Drawings
FIG. 1 is an exploded view of an aircraft battery module of the present invention supporting high rate discharge;
FIG. 2 is an isometric view of an aircraft battery module supporting high-rate discharge in accordance with the present invention;
fig. 3 is a front view of an aircraft battery module supporting high-rate discharge according to the present invention;
FIG. 4 is a top view of an aircraft battery module supporting high-rate discharge in accordance with the present invention;
FIG. 5 is a right side view of an aircraft battery module supporting high-rate discharge in accordance with the present invention;
in the figure, the solar cell module comprises a 1-current collector, a 2-low voltage wire harness assembly, a 3-positive and negative high voltage wire harness assembly, a 4-plastic cover plate, a 5-plastic bracket, a 6-heat conduction silica gel pad, a 7-battery cell, an 8-foam double-sided adhesive layer, a 9-epoxy plate and a 10-heat shrinkage film.
Detailed Description
For a clearer understanding of technical features, objects, and effects of the present invention, a specific embodiment of the present invention will be described with reference to the accompanying drawings.
The invention provides an aircraft battery module supporting high-rate discharge, which is shown in figures 1-5 and comprises a battery pack box body part, a current collector 1 serving as a series and parallel connection transfer conductor between battery monomers, a low-voltage wiring harness assembly 2 for collecting module voltage and temperature data, and a positive-negative high-voltage wiring harness assembly 3 for realizing battery pack charge and discharge and series connection between battery packs; the current collector 1 is arranged on a plastic bracket 5, and the top end of the plastic bracket 5 is also connected with a low-voltage wiring harness assembly 2 and a positive-negative high-voltage wiring harness assembly 2.
The right side of the plastic bracket 5 is provided with a plastic cover plate 4 for high-voltage insulation protection.
The bottom surface, the top surface and the side surface opposite to one surface of the plastic cover plate 4 of the battery pack box body are provided with a heat-conducting silica gel pad 6 for radiating and homogenizing the temperature of the battery pack.
The front face of the battery pack box body part is provided with a plurality of layers of battery cells 7.
And a foam double-sided adhesive layer 8 for absorbing battery expansion and fixing the battery cells is also arranged between each two layers of the battery cells 7.
The front face, the bottom face and the back face of the battery pack box body part and the side face opposite to one face of the plastic cover plate 4 are also provided with an epoxy plate 9 which clings to the battery core body for structural protection.
The outer layer of the battery pack is also provided with a heat shrinkage film 10 which is fixed integrally and performs insulation protection.
In this embodiment, the constituent components of the aircraft battery module mainly include the following:
(1) Heat shrinkage film 10: as important components for insulating protection and integral fixation of the outer layer of the battery pack, the number of the components is as follows: 1.
(2) Epoxy board 9: the battery cell 7 body is closely attached to the battery for structural protection; quantity: 3.
(3) Heat conductive silica gel pad 6: the heat dissipation and the temperature equalization functions of the battery pack are realized; quantity: 3.
(4) Positive and negative high voltage wire harness assembly 3: realizing the series connection among the battery packs in charge and discharge; quantity: 1.
(5) Low voltage harness assembly 2: collecting module voltage and temperature data; quantity: 1.
(6) Collector bar 1: as switching conductors connected in series and in parallel between the battery cells; quantity: a plurality of.
(7) Plastic cover plate 4: high-voltage insulation protection; quantity: 1.
(8) Plastic support 5: as the support member of the collector 1, serial and parallel connection between the individual cells is realized.
(9) Foam double-sided adhesive layer 8: absorbing the expansion of the battery and fixing the battery core; quantity: a plurality of.
The whole structure of the aircraft battery module supporting high-rate discharge adopts a scheme of heat shrinkage films and epoxy plates, so that the structural strength of the assembled batteries can be ensured, the weight of a battery pack structural member can be effectively reduced, and the energy density can be improved; the positive output pole and the negative output pole of the battery pack are provided with wire harnesses and connectors, so that the quick serial connection between the battery packs can be realized; the number of the series battery packs is increased or decreased, so that different electric quantity requirements can be met, the technology is facilitated to be platform, and the development cost is saved; and the ternary soft-package multiplying power type battery cell is adopted, so that various working conditions of high-multiplying power discharge of the aircraft are met.
The invention provides an aircraft battery module supporting high-rate discharge, which mainly comprises a heat shrinkage film, a plastic cover plate, a plastic bracket, electric cores, an epoxy plate, a heat conduction silica gel pad, a high-voltage wire harness assembly, a low-voltage wire harness assembly and a current collecting row, wherein each single electric core is adhered and fixed through double-sided adhesive, and the outermost side is wrapped into a whole through the heat shrinkage film; the invention adopts the ternary soft-package battery core, and has extremely high grouping efficiency; on the premise of ensuring the strength of the whole structure, the number and the variety of the metal structural members are reduced to the greatest extent, the energy density of the module is improved, and the cruising ability of the aircraft is greatly improved; the high-voltage connectors are respectively arranged at the output positions of the total positive electrode and the total negative electrode of the battery pack, so that the battery packs are connected in series at random, and different electric quantity requirements are met; the weight of the structural member is small, the grouping efficiency is high, the energy density is high, the modular design is realized, the total electric quantity can be flexibly adjusted, and the high-low voltage connection realizes the quick-plug function.
The foregoing has shown and described the basic principles and features of the invention and the advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The aircraft battery module supporting high-rate discharge is characterized by comprising a battery pack box body part, a current collecting row (1) serving as a serial and parallel switching conductor between battery monomers, a low-voltage wire harness assembly (2) for collecting module voltage and temperature data, and a positive-negative high-voltage wire harness assembly (3) for realizing battery pack charge and discharge and serial connection between battery packs; the current collecting row (1) is arranged on the plastic bracket (5), and the top end of the plastic bracket (5) is also connected with the low-voltage wiring harness assembly (2) and the positive and negative high-voltage wiring harness assembly (2).
2. The aircraft battery module supporting high-rate discharge according to claim 1, wherein a plastic cover plate (4) is arranged on the right side of the plastic bracket (5) for high-voltage insulation protection.
3. The aircraft battery module supporting high-rate discharge according to claim 1, wherein the battery box portion bottom surface, the top surface and the side surface opposite to one surface of the plastic cover plate (4) are provided with a heat-conducting silica gel pad (6) for heat dissipation and temperature equalization of the battery.
4. An aircraft battery module supporting high-rate discharge according to claim 3, wherein the battery box portion is provided with a plurality of layers of cells (7) on the front face.
5. The aircraft battery module supporting high-rate discharge according to claim 4, wherein a foam double-sided adhesive layer (8) for absorbing battery expansion and fixing the battery cells is further arranged between each two layers of the battery cells (7).
6. An aircraft battery module supporting high-rate discharge according to claim 3, wherein the front face, the back face and the side face opposite to the side of the plastic cover plate (4) of the battery box are further provided with an epoxy plate (9) which is tightly attached to the battery cell body for structural protection.
7. An aircraft battery module supporting high-rate discharge according to claim 1, wherein the battery pack outer layer is further provided with a heat shrink film (10) which is fixed integrally and insulated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310509472.9A CN116487806A (en) | 2023-05-08 | 2023-05-08 | Aircraft battery pack supporting high-rate discharge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310509472.9A CN116487806A (en) | 2023-05-08 | 2023-05-08 | Aircraft battery pack supporting high-rate discharge |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116487806A true CN116487806A (en) | 2023-07-25 |
Family
ID=87225023
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310509472.9A Pending CN116487806A (en) | 2023-05-08 | 2023-05-08 | Aircraft battery pack supporting high-rate discharge |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116487806A (en) |
-
2023
- 2023-05-08 CN CN202310509472.9A patent/CN116487806A/en active Pending
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |