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Energy integration system for software-defined satellite

A software-oriented, integrated system technology, applied in the field of artificial satellites, which can solve the problems of large installation space, inconvenient removal of single batteries, and occupation of aircraft.

Active Publication Date: 2021-05-18
INST OF SOFTWARE - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the structure of the frame body and the sleeve, the battery pack will inevitably occupy a large installation space inside the aircraft after installation, and the frame and the sleeve are usually c

Method used

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  • Energy integration system for software-defined satellite
  • Energy integration system for software-defined satellite
  • Energy integration system for software-defined satellite

Examples

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no. 1 example

[0035] figure 1 A schematic structural diagram of an energy integration system oriented to software-defined satellites provided in the first embodiment of the present invention; figure 2 A schematic structural diagram of the substrate 100 in the energy integration system for software-defined satellites provided by the first embodiment of the present invention; image 3 A schematic structural diagram of the battery slot 110 in the software-defined satellite-oriented energy integration system provided by the first embodiment of the present invention. Please refer to figure 1 , figure 2 , image 3 , this embodiment provides a software-defined satellite-oriented energy integration system, which includes a substrate 100 and a casing 200; the casing 200 is provided with an opening, and the substrate 100 is used to block the opening; the substrate 100 is provided with a plurality of battery slots 110 on a plane; the depth direction of the battery slots 110 is the same as the th...

no. 2 example

[0044] Figure 4 A schematic structural diagram of the battery slot 110 in the software-defined satellite-oriented energy integration system provided by the second embodiment of the present invention. Please refer to Figure 4 , this embodiment provides an energy integration system for software-defined satellites, which is roughly the same as the energy integration system for software-defined satellites in the first embodiment, the difference between the two is that the energy integration system for software-defined satellites in this embodiment The positive electrode 120 in the system includes a rotating shaft 121 and a cam 122 disposed on the rotating shaft 121 ; rotating the rotating shaft 121 can change the distance between the positive electrode 120 and the negative electrode 130 in the battery slot 110 .

[0045] It should be emphasized that, in order to improve disassembly efficiency, multiple cams 122 in the same row of battery slots 110 should be connected by a rotat...

no. 3 example

[0047] Figure 5 A schematic structural diagram of the substrate 100 in the software-defined satellite-oriented energy integration system provided by the third embodiment of the present invention; Figure 6 A schematic structural diagram of the base plate 100 and the base plate 140 in the energy integration system for software-defined satellites provided by the third embodiment of the present invention. Please refer to Figure 5 , Figure 6 , this embodiment provides a software-defined satellite-oriented energy integration system, which is roughly the same as the software-defined satellite-oriented energy integration system in the first embodiment or the second embodiment. The energy integration system defining the satellite is also provided with a bottom plate 140 ; ​​the bottom plate 140 is detachably set on the base plate 100 , and the battery slot 110 is set on the side of the base plate 140 away from the base plate 100 .

[0048] Further, as Figure 6 As shown, one of...

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Abstract

The invention provides an energy integration system for a software-defined satellite. The energy integration system comprises a substrate and a shell, the shell is provided with an opening, and the substrate is used for blocking the opening; a plurality of battery slots are formed in one plane of the substrate; the depth direction of the battery slot is the same as the thickness direction of the substrate; positive electrodes and negative electrodes are arranged in the battery slots, and the plurality of battery slots are electrically connected; and the battery slots face the interior of the shell. According to the energy integration system for the software-defined satellite, the battery slot is formed in the substrate in the thickness direction of the substrate, so that the occupation of a battery on the internal space of the software-defined satellite is greatly reduced, and the installation space and the loading capacity of the software-defined satellite are released; and the structural design of electrical connection among all the battery slots, including series connection or parallel connection among the battery slots, enables the software-defined satellite to be able to load or unload a reasonable number of batteries according to actual needs, and greatly enhances the expansion flexibility of the power supply.

Description

technical field [0001] The invention relates to the technical field of artificial satellites. Specifically, it relates to an energy integration system for software-defined satellites. Background technique [0002] At present, space vehicles such as satellites, space stations, and spacecraft mainly use battery packs as energy storage power sources to ensure the energy supply of space vehicles. [0003] In the prior art, the battery pack is generally installed in the aircraft using a frame structure or a sleeve structure. Specifically, a plurality of single cells that have been insulated are fixedly placed in a frame, a vertical sleeve or a horizontal sleeve, and then the frame or the sleeve is installed on the inner wall of the aircraft. [0004] The structural form and installation method of the above-mentioned aircraft battery pack have the advantages of high stability and good heat dissipation. However, due to the structure of the frame body and the sleeve, the battery ...

Claims

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Application Information

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IPC IPC(8): H01M50/244H01M50/258H01M50/253B64G1/42
CPCB64G1/42Y02E60/10
Inventor 乔鹏赵军锁范永庆夏玉立耿世松
Owner INST OF SOFTWARE - CHINESE ACAD OF SCI
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