Expansion type satellite configuration based on metal main bearing force and batch production design and assembly method

The deployable satellite configuration, designed with a metal main load-bearing structure, employs mounting plate hinge components and two-dimensional planar installation, which solves the problems of high processing difficulty and long cycle of carbon fiber main load-bearing structures. This improves satellite assembly efficiency and liberates personnel, making it suitable for mass production of satellites.

CN120902997APending Publication Date: 2025-11-07CHANGGUANG SATELLITE TECH CO LTD
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Patent Information

Application Number
CN202511257847.2
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-09-04
Publication Date
2025-11-07

AI Technical Summary

Technical Problem

In existing technologies, the satellite configuration with carbon fiber main load-bearing structure is difficult to process, has a long cycle, and is expensive. Moreover, it does not involve metal main load-bearing structure, resulting in low satellite assembly efficiency and high personnel occupation.

Method used

The deployable satellite configuration, designed with metal as the main load-bearing component, is connected by -Y mounting plates, +Z mounting plates, +X mounting plates, -Z mounting plates, and standard component assemblies. Combined with the mounting plate hinge assembly, it enables two-dimensional planar installation and serial assembly of the satellite, reducing processing difficulty and cycle time.

Benefits of technology

It effectively reduces the difficulty and cycle of satellite processing, improves satellite assembly efficiency, frees up personnel, and enhances personnel utilization efficiency, making it suitable for mass production of satellites.

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Abstract

The invention discloses an expanded satellite configuration based on metal main bearing force and batch production design and an assembly method. The satellite configuration comprises a-Y mounting plate and-Y sailboard assembly, a + Z mounting plate assembly, a-Z mounting plate assembly, a + Y mounting plate and + Y sailboard assembly, a + X mounting plate assembly, a-X mounting plate, a standard component assembly and the like. The single machine mounting plates in all directions form a satellite main bearing structure to provide mounting space for single machines; in the satellite assembling process, the adjacent mounting plates are connected through the mounting plate hinging assemblies. Three-dimensional space installation of a single machine in a satellite cabin is converted into two-dimensional plane installation, so that the installation difficulty is reduced; the single mounting plate single-machine assembly, thermal control product implementation and cable laying work are carried out in series and independently, the assembly work among the mounting plates is carried out in parallel, occupation of various assembly process personnel is relieved in advance, other satellite assembly work can be carried out, and the system is suitable for satellite batch assembly.
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