Modular structure for rectangular battery pack applied to spacecraft

A technology for space vehicles and battery packs, which is applied to battery pack components, batteries, structural components, etc., can solve the problems of poor maintainability, difficulty in controlling the flatness of the installation surface of the tie-rod structure and installation dimensional accuracy, and high production costs. Improved accuracy, strong scalability, and cost-saving effects

Active Publication Date: 2019-08-09
SHANGHAI INST OF SPACE POWER SOURCES
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problems such as difficulty in controlling the flatness of the installation surface of the tie-rod structure and the accuracy of i

Method used

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  • Modular structure for rectangular battery pack applied to spacecraft
  • Modular structure for rectangular battery pack applied to spacecraft
  • Modular structure for rectangular battery pack applied to spacecraft

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Embodiment Construction

[0024] 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.

[0025] figure 1 It is a structural schematic diagram of a modular rectangular lithium-ion battery pack, marked in the figure as: single cell 1; regulating piece 2; pressure plate 3; end plate 4; bottom plate 5. figure 2 Schematic diagram of the one-piece bottom plate. image 3 It is a schematic diagram of a small module.

[0026] The large bottom plate of the battery pack has 6 grooves of the same shape and size, which are used to install 6 small modules. Each small module is composed of a single battery 1, an adjusting piece 2, a pressure plate 3 and an end plate 4 (the thickness specification and quantity of the adjusting piece 2 are determined by the difference between the total length of the small module and the size of th...

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Abstract

The invention provides a modular structure for a rectangular battery pack applied to a spacecraft. The modular structure comprises battery monomers, regulating pieces, pressure plates, end plates anda bottom plate. The battery monomers and the regulating pieces form a relatively independent small module through left and right pressure plates and front and rear end plates. The left and right pressure plates can realize limit in width and height directions. The size and number of the regulating pieces between monomers in the small module can be changed to adjust the length of the small module.After the three-dimensional size of the small module is adjusted, the small module can be directly inserted into an integrated large bottom plate and fixed by screws. Heat-conducting glue is pre-coated between monomer pores in the small module and between the small module and the bottom plate to enhance the mechanical properties and thermal conductivity of the entire battery pack. The structure has the characteristics of modular structure design, less component specifications and simple assembly. The modular structure provided by the invention has the advantages of controllable installation flatness and installation size, high maintainability and low production cost, and the mechanical resistance and thermal properties are in line with the requirements of space applications.

Description

technical field [0001] The invention relates to a space vehicle power supply, in particular to a modular structure of a rectangular storage battery pack for a space vehicle. Background technique [0002] As an energy storage power source, the battery is an important part of the power supply subsystem of the spacecraft. It undertakes the task of supplying power to the aircraft during the active flight and the shadow period of the aircraft after the internal power is switched. It is the only energy for the spacecraft during the shadow period. source. The reliability of the battery pack is the core factor that determines the safety of the power supply for the launch stage and orbital operation of the spacecraft. [0003] The structure of the common battery pack is a tie-rod structure. The single battery is spliced ​​and fixed by structural parts such as L-shaped heat sinks, layering bars, and intermediate brackets. The two ends of the tie rods are respectively fixed on the lef...

Claims

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Application Information

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IPC IPC(8): H01M2/10
CPCH01M2220/20H01M50/20Y02E60/10
Inventor 杨进杨淼王琳任杰伟淳莉李国瑞陈海锋李旭评雷虎李琳琳
Owner SHANGHAI INST OF SPACE POWER SOURCES
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