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A high-orbit satellite assembly method based on bipropellant unified propulsion system

A technology for propulsion systems and high-orbit satellites, which is applied in the field of satellite assembly process, can solve the problems of mutual influence of the assembly process and the inability to achieve complete independence of assembly, and ensure the accuracy of assembly and product quality, product installation accuracy and excess control guarantee. , good coordination effect

Active Publication Date: 2018-12-21
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

[0002] The satellite dual-component unified propulsion system has a large number of supporting products, the layout of the propulsion components is compact, and the connecting pipelines between the components are densely interspersed in the star structure, which makes the final assembly process of the three systems of structure, thermal control and propulsion affect each other , it is impossible to realize the complete independence of the final assembly of each process

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  • A high-orbit satellite assembly method based on bipropellant unified propulsion system
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  • A high-orbit satellite assembly method based on bipropellant unified propulsion system

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Embodiment Construction

[0025] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0026] attached figure 1 It is a schematic diagram of the star structure and propulsion composition, and the propulsion products are all installed on the main star structure.

[0027] The main star structure 5 adopts the structural form of the central load-bearing tube 20+upper bulkhead 11 / lower bulkhead 18+bottom plate 19. The planar section is hexagonal. Mounting plate 14, top plate 1 divide vertical space into 3 spaces, vertical space is divided into 2 spaces by base plate 19, tank mounting plate 16...

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Abstract

The invention provides a high-orbit satellite assembly method based on bipropellant unified propulsion system, the method is divided into star structure assembly, propulsion product welding and thermal control product assembly, in which star structure assembly and propulsion product welding are divided into two stages I and II. According to star structure assembly stage I, propulsion product welding stage I, star structure assembly stage II and propulsion product welding stage II are implemented sequentially. Thermal control products include propulsion thermal control products and star structure thermal control products, according to the principle of irreversible process in the entire assembly process interspersed implementation. The process of the invention is conducive to improving theassembly efficiency and ensuring the assembly accuracy and product quality. Through engineering practice, the invention has the advantages of good coordination of the general assembly flow, high general assembly efficiency, strong guarantee of product installation accuracy and redundant control.

Description

technical field [0001] The invention relates to a satellite general assembly process, which is based on the general assembly of a high-orbit satellite platform and is suitable for the process of a satellite based on a dual-component unified propulsion system. Background technique [0002] The satellite dual-component unified propulsion system has a large number of supporting products, the layout of the propulsion components is compact, and the connecting pipelines between the components are densely interspersed in the star structure, which makes the final assembly process of the three systems of structure, thermal control and propulsion affect each other , It is impossible to realize the complete independence of the final assembly of each process. Contents of the invention [0003] In view of the defects in the prior art, the purpose of the present invention is to provide a high-orbit satellite assembly method based on a dual-component unified propulsion system, which can ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/40
CPCB64G1/22B64G1/40
Inventor 俞洁张凌燕蒋国伟王华
Owner SHANGHAI SATELLITE ENG INST
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