航天器可展开式热辐射器的设计方法与应用研究

Design Method and Application Research of Deployable Heat Radiator for Spacecraft

受限于运载火箭的包络尺寸,航天器体装式辐射器的散热面积有限,为进一步提高大功率航天器的系统级散热能力,提出了基于单相流体回路的可展开式热辐射器的热控方案。建立热辐射器的热分析模型,通过肋参数选取、红外辐射影响分析、工质选用对比等方法,完成可展开式热辐射器的设计优化,提高辐射器的散热效率及散热能力,为可展开式热辐射器的在轨首飞应用奠定基础。结果表明,在地球同步轨道航天器的恶劣外热流条件下,单幅辐射器的散热能力可达254 W/m^(2)以上,采用多幅可展开式热辐射器的方法,可有效解决航天器散热能力不足的问题。

Constrained by the envelope size of the launch vehicle,the heat dissipation area of the radiator installed on the spacecraft body is limited.To further enhance the system-level heat dissipation capacity of high-power spacecraft,a thermal control solution based on a single-phase fluid loop expandable radiator is proposed.A thermal analysis model of the radiator is established.Through fin parameter selection,analysis of the influence of infrared radiation,comparison of working fluids,etc.,the design optimization of the expandable radiator is accomplished,improving the heat dissipation efficiency and capacity of the radiator and laying the foundation for the first in-orbit flight application of the expandable radiator.The results indicate that under the harsh external heat flux conditions of the geostationary orbit spacecraft,the heat dissipation capacity of a single radiator can reach more than 254 W/m^(2).Employing multiple expandable radiators can effectively address the issue of insufficient heat dissipation capacity of spacecraft.