Satellite structure and satellite assembly method

A satellite structure and satellite technology, applied in the field of aerospace satellites, can solve the problems of low satellite disassembly efficiency, difficult disassembly, and narrow operation space, and achieve the effect of improving the efficiency of satellite assembly and disassembly, and widely used value.

Active Publication Date: 2021-08-10
北京最终前沿深空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Most of the existing satellite structures are box-plate structures. The operating space of the box-plate satellite structure is narrow, and parts are prone to shield each other in the narrow space. Many parts of the connection between the decks are located inside the deck, making it difficult to use mechanical arms, etc. Automatic equipment enters the interior of the cabin for assembly, and usually requires manual installation of various equipment in the satellite cabin, so it can only be produced in a single piece, and batch production of satellites cannot be realized, and the efficiency of satellite assembly is low
In addition, when some equipment in the satellite needs to be tested or repaired, the satellite structure needs to be disassembled, and the satellite deck of the existing satellite structure is mostly in a fixed and fixed state, so disassembly is difficult and the efficiency of satellite disassembly is low. Low
Moreover, different devices of the existing satellite structure are installed on different decks, and the cables connected between the devices will be fixed on each deck. When the deck of a device is disassembled, the interconnected cables need to be disconnected first. The deck can only be removed, and when reassembling, the assembly process is complicated

Method used

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  • Satellite structure and satellite assembly method
  • Satellite structure and satellite assembly method
  • Satellite structure and satellite assembly method

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Experimental program
Comparison scheme
Effect test

Embodiment approach

[0036] For the installation of the intermediate board 16, it can be realized through the following two specific implementation methods:

Embodiment approach 1

[0038] The installation method of each intermediate board 16 is the same as that of the front side board 12, rear side board 13, left side board 14, and right side board 15. Specifically, the lower cover board 11 is inserted in each middle board. The installation position corresponding to the board 16 is provided with at least two second positioning pins (not shown in the figure), and each of the intermediate boards 16 is provided with a second positioning hole corresponding to the second positioning pins (in the figure not shown), the intermediate board 16 and the lower cover 11 are installed and positioned based on the second positioning pin and the second positioning hole. Preferably, the first locating pin 4 and the second locating pin are the same model locating pins, such as Figure 4 Locating pins shown.

Embodiment approach 2

[0040] Such as figure 1 The satellite structure shown, the satellite structure also includes a plurality of docking bosses 5, and the enlarged view of the docking bosses 5 is as follows Figure 5 As shown, both ends of the intermediate board 16 are provided with docking grooves 160 corresponding to the docking boss 5, as Figure 6 As shown, when the satellite deck 1 is a single plate structure, the docking boss 5 is installed on the corresponding position of the satellite deck 1 according to the preset satellite structure layout, when the front side plate 12, After the rear side plate 13, the left side plate 14, and the right side plate 15 are installed on the lower cover plate 11, install the first intermediate insert plate 161 on the Corresponding positions in the box structure, after all the first intermediate boards 161 are installed, the second intermediate boards are installed in the box structure based on the docking groove 160 and the docking boss 5 plug-in structure ...

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PUM

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Abstract

The invention relates to a satellite structure and a satellite assembly method. The satellite structure includes: a plurality of satellite decks, electronic equipment, cables and plug-in components, wherein, when the satellite decks are of a single-board structure, according to preset The satellite structure layout installs the electronic equipment, cables and plug-in components on the corresponding satellite cabin board; on the same satellite cabin board, one end of the cable is connected to the electronic equipment, and the other end is connected to the plug-in Components; between different satellite decks, electrical connections are established through the plug-in components. The invention improves the efficiency of satellite assembly and disassembly, thereby realizing automatic mass production of satellites.

Description

technical field [0001] The invention relates to the technical field of aerospace satellites, in particular to a satellite structure and a satellite assembly method. Background technique [0002] Most of the existing satellite structures are box-plate structures. The operating space of the box-plate satellite structure is narrow, and parts are prone to shield each other in the narrow space. Many parts of the connection between the decks are located inside the deck, making it difficult to use mechanical arms, etc. Automatic equipment enters the interior of the cabin for assembly, and usually requires manual installation of various equipment in the satellite cabin, so it can only be produced in a single piece, and batch production of satellites cannot be achieved, and the efficiency of satellite assembly is low. In addition, when some equipment in the satellite needs to be tested or repaired, the satellite structure needs to be disassembled, and the satellite deck of the existi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/22
CPCB64G1/10B64G1/22
Inventor 陈津林贾利敏焦石
Owner 北京最终前沿深空科技有限公司
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