A flexible interconnection system and method based on a whole satellite structure

CN122315416APending Publication Date: 2026-06-30GUIZHOU SPACE APPLIANCE CO LTD
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Patent Information

Application Number
CN202610678356.3
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2026-05-18
Publication Date
2026-06-30

AI Technical Summary

Technical Problem

Traditional satellite electrical interconnection technologies suffer from problems such as heavy weight, long manufacturing cycle, poor wiring flexibility, easy loosening of connections, and unstable signal transmission, which cannot meet the requirements of modern satellite systems for lightweight, high reliability, and flexible wiring.

Method used

A flexible interconnect system based on the whole satellite structure is adopted, using multi-layer rigid-flex board cables, including longitudinal trunks and lateral branches, setting up relay motherboards and lateral relay interfaces, fixing the cables to the satellite structure at intervals, and designing high core count connectors and port connectors. The cabling is optimized by combining 3D modeling and testing procedures.

Benefits of technology

It improves the utilization of internal space in satellites, reduces weight, enhances the stability and reliability of signal transmission, adapts to complex structural layouts, reduces manufacturing cycles and the risk of loose connections, and improves overall interconnection performance.

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Abstract

This invention relates to the field of satellite technology, and more particularly to a flexible interconnection system and method based on a whole-satellite structure, used to interconnect multiple individual payloads on different modules or locations on a satellite, comprising: multiple rigid-flex cable plates; each rigid-flex cable plate includes a longitudinal backbone and transverse branches, the longitudinal backbone is used to integrate and transmit all signals, and the transverse branches are used to connect each satellite individual payload; a relay main board is provided at the intersection of the longitudinal backbone, and the relay main board is equipped with a high-pin-count, easy-to-plug connector as a relay interface; a transverse relay interface is provided at the intersection of the longitudinal backbone and the transverse branch; plate fixing structures are provided at predetermined intervals on the rigid-flex cable plate for fixing the rigid-flex cable plate to the satellite structure; the ports of the transverse branches are provided with port connectors that match the interfaces of the satellite individual payloads for signal and energy transmission.
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