一种用于卫星大功率搭载载荷高效散热的装置
By employing a thermal drive structure consisting of dual-drive shape memory alloy pillars and thin-film heating elements on the satellite, combined with a flexible thermal conductive structure and thermal control coating, the problem of heat dissipation and heat preservation coexisting for high-power payloads on satellites has been solved, achieving efficient and reliable thermal management and enhancing heat dissipation capacity and temperature control accuracy.
CN121084648BActive Publication Date: 2026-07-17CHANGGUANG SATELLITE TECH CO LTD
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHANGGUANG SATELLITE TECH CO LTD
- Filing Date
- 2025-09-10
- Publication Date
- 2026-07-17
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Figure CN121084648B_ABST
Abstract
本发明公开了一种用于卫星大功率搭载载荷高效散热的装置，涉及航天卫星热控制技术领域，解决了间歇性工作的大功率单机在搭载飞行过程中额外带来的长期高功耗、散热效率低以及自身温度不稳定的问题。本发明均温活动金属板通过热驱结构设置于均温散热结构上；搭载载荷通过隔热柱设置于均温散热结构上；均温活动金属板和搭载载荷下表面之间设置有间隙；热驱结构驱动均温活动金属板上下移动和搭载载荷下表面接触；均温活动金属板和均温散热结构之间通过柔性导热结构导热。本发明在不占用卫星长期能源的情况下，便捷迅速的解决间歇性工作的大功率单机的散热难题，并维持其在不工作时的低温阈值，保证其在复杂空间热流情况或不工作状态时的温度稳定性。
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