针对某大型星载合成孔径雷达可展开天线尺寸大、结构柔度大、天线单元面积小、有源通道排布紧凑、热流密度大、热稳定性较差等问题,进行了泵驱动流体回路配合可展开式辐射器的系统散热方式可行性研究。建立了星载相控阵天线在轨辐射换热计算数值模型,通过模拟计算对极端外热流工况的天线阵面在轨温度场进行了分析;同时,针对天线T/ R 模块内部进行了散热设计和仿真分析,对该热控方案的合理性进行了分析验证。数值计算结果显示,天线阵面具有良好的在轨温度性能,芯片结温满足I 级降额需求,泵驱动流体回路的可展开式辐射器能够解决某星载相控阵天线的散热难题。

Considering that the large space-borne synthetic aperture radar deployable antenna has large size, big structural flexibility, small antenna unit area and compact arrangement, high heat flux and poor thermal stability, feasibility study on the thermal design based on the liquid cooling loop and deployable radiators is adopted for the antenna system. The in-orbit numerical model for radioactive heat transfer is built and numerical simulations are conducted for in-orbit temperature analysis. The heat transfer paths of the T/ R modules are optimized, and simulations are conducted to verify the effectiveness of the thermal control methods. The simulation results show that the phased array antenna has good thermal performance and the chip junction temperature can satisfy the requirements of the primary derating. The deployable radiators based on the fluid loop are helpful for the thermal managements of the phased array antenna.

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