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18650 lithium ion battery pack structure

A battery pack and lithium-ion technology, applied to battery pack parts, secondary batteries, structural parts, etc., can solve the problems of poor heat dissipation and low energy, achieve good thermal conductivity, good thermal conductivity, and enhance the effect of strength connection

Inactive Publication Date: 2019-12-13
SHANGHAI INST OF SPACE POWER SOURCES
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a 18650 lithium-ion battery pack structure, which can solve the problems of low specific energy and poor heat dissipation of the traditional circular lithium-ion battery pack structure

Method used

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  • 18650 lithium ion battery pack structure
  • 18650 lithium ion battery pack structure
  • 18650 lithium ion battery pack structure

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Embodiment Construction

[0033] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0034] In this embodiment, the structure of 18650 lithium-ion battery packs provided by the embodiment of the present invention is described by taking 140 lithium-ion battery cells to form a structure of 20 parallel 7 strings as an example. In other embodiments of the present invention, lithium The number and arrangement of ion battery cells are adjusted adaptively.

[0035] Such as Figure 1 to Figure 4 As shown, the present invention provides a 18650 lithium-ion battery pack structure, including: a lithium-ion battery cell 1, a bottom plate 2, a side plate 3, a pressure plate 4, a cover plate 5, an electrical connector fixing plate 6, an elastic plate 7, an electrical connector Connector 8 , guide bar 9 , grounding device 10 . ...

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Abstract

The invention provides a 18650 lithium ion battery pack structure, which includes: lithium ion battery individuals, a bottom plate, a side plate, a pressure plate, a cover plate, an electrical connector fixing plate, an elastic plate, an electrical connector, a guide bar, and a grounding device, and is characterized in that the positive electrodes of all the lithium ion battery individuals have the same orientation so as to contribute to modular expansion; the lithium ion battery individuals are directly bonded in the sleeve-type bottom plate so as to achieve rapid heat transfer; sufficient gaps are arranged between the lithium ion battery individuals to release the stress generated during the cyclic process of the lithium ion battery individuals; the elastic plate is arranged between thelithium ion battery individuals and the pressure plate; by adjusting the amount of deformation of the elastic plate, the lithium ion battery individuals and the bottom plate can be tightly connected;the high-resistance grounding device can release the charges accumulated in the battery pack structure. The structure provided by the invention has high specific energy, good thermal conductivity, high structural strength, and good safety and reliability, and is suitable for the field of small satellites.

Description

technical field [0001] The invention relates to a structure suitable for 18650 lithium-ion battery packs used in spacecraft. Background technique [0002] With the maturity of new small satellite technology, the emerging industry of small satellites has gradually grown, making small satellites present an unprecedented prosperity. Due to the extensive adoption of new technologies and the widening of the range of product selection, modern small satellites have the characteristics of high functional integration, short development cycle, and low cost, showing a very broad development and application market prospect for the international aerospace industry. [0003] Lithium-ion battery, as the energy storage power supply, is the key stand-alone unit of the small satellite. It undertakes the task of supplying power to the aircraft during the active flight of the satellite and the earth shadow period. core factor. Compared with traditional zinc-silver batteries, cadmium-nickel ba...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01M2/10H01M10/0525H01M10/613H01M10/653H01M50/20
CPCH01M10/0525H01M10/613H01M10/653H01M50/20Y02E60/10
Inventor 陈海锋伍玉琴舒晨吴惠民刘文娟李娟娟杨波闻海王臻陆林汇于希秦继业闻凯
Owner SHANGHAI INST OF SPACE POWER SOURCES
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