The invention relates to the technical field of spaceflight, in particular to a radiation radiator and a spacecraft, and the radiation radiator comprises a heat conduction support, a pressing and unlocking unit and an expandable heat dissipation unit, one end of the unfoldable heat dissipation unit in the length direction of the unfoldable heat dissipation unit is a fixed end fixed to the heat conduction support, the other end of the unfoldable heat dissipation unit is a connecting end, and the unfoldable heat dissipation unit is used for being arranged to be in a spiral roll shape so that the connecting end can be one end of the inner side of the spiral roll shape; the pressing and unlocking unit is fixed to the heat conduction support, and the pressing and unlocking unit is detachably connected with the connecting end. The invention aims to provide a radiation radiator aiming at at least one technical problem related in the background technology.
本申请涉及航天技术领域,具体而言,涉及一种辐射散热器及航天器,包括导热支座、压固解锁单元和可展开散热单元,所述导热支座用于固定于航天器本体,在所述可展开散热单元的长度方向上所述可展开散热单元的一端为固定于所述导热支座的固定端,所述可展开散热单元的另一端为连接端,所述可展开散热单元用于设置成螺旋卷状以使所述连接端为所述螺旋卷状内侧的一端,所述压固解锁单元固定于所述导热支座,所述压固解锁单元与所述连接端可分离连接。本申请的目的在于针对背景技术中所涉及的至少一个技术问题,提供一种辐射散热器。
Radiation radiator and spacecraft
辐射散热器及航天器
2025-01-10
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Engineering Index Backfile | 1968
|NTRS | 2012
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