Active regulation heat resistance insulation structure for switching gravity condition and manufacturing method thereof

By actively adjusting the thermal resistance insulation structure, and utilizing shape memory alloys and isolation screw mechanisms to achieve active adjustment of thermal resistance, the problems of large heat leakage in traditional support structures and incomplete separation of passive supports are solved, thereby improving the safety and reliability of spacecraft and meeting the requirements of long-life missions.

CN122354809APending Publication Date: 2026-07-10CENT SOUTH UNIV +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CENT SOUTH UNIV
Filing Date
2026-04-10
Publication Date
2026-07-10

AI Technical Summary

Technical Problem

Traditional composite material support structures have unadjustable thermal resistance, resulting in large heat leakage and failing to meet the requirements of long-life space missions. Furthermore, passive on-orbit non-connected thermal supports do not completely separate under microgravity conditions, affecting the reliability and lifespan of spacecraft.

Method used

An active thermal resistance adjustment insulation structure is adopted, including components such as hot end interface, hot end support assembly, isolation screw mechanism, locking module, and heater. The active adjustment of thermal resistance is achieved through shape memory alloy and isolation screw mechanism, ensuring reliable separation of the support structure and low heat leakage under different gravity conditions.

Benefits of technology

It enables active adjustment of thermal resistance under different gravity conditions, improves the safety and reliability of spacecraft, meets the thermal management requirements of long-life space missions, and reduces the risk of heat leakage.

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Abstract

This application relates to the field of satellite cryogenic thermal insulation support technology, specifically to an active adjustable thermal resistance thermal insulation structure for gravity condition switching and its manufacturing method. The structure includes a hot-end interface, a hot-end support assembly, an isolation screw mechanism, a locking module, a heater, a fixing structure, a ground-side support pipe, an on-orbit support pipe, a cold-end support assembly, and a cold-end interface. The active on-orbit non-connected thermal insulation support technology employed in this application solves the problems of small separation gaps and poor repeatability associated with passive on-orbit non-connected thermal insulation support technologies. It achieves effective active separation and large displacement isolation between the locking module and the fixing structure, ensuring separation and isolation are unaffected by residual microgravity disturbances, improving safety margins, allowing for multiple ground tests and verifications, and enhancing mission confidence.
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