大口径空间光学遥感器辐射散热器的设计及应用

Design and on-orbit application of radiator for space optical remote sensor with large aperture

为满足大口径空间光学遥感器高效率、低密度散热的需求,提出一种基于高导热石墨膜的空间辐射散热器。对高导热石墨膜的基础物理性能、结构成分、力学性能、热性能、空间环境适应性等进行较全面的测试分析。将高导热石墨膜与热管、蜂窝板等结合起来解决高导热石墨膜应用中常见的厚度方向导热系数低、力学强度低、硬度低、厚度薄、单块尺寸小的难题。对散热器和2种传统空间辐射散热器进行对比仿真分析,仿真分析结果表明:同等散热能力下,高导热石墨辐射散热器的质量仅为传统铝合金板散热器的约1/3,仅为传统铝蜂窝板辐射散热器的约1/2。通过热平衡实验和在轨飞行应用对散热器的散热性能进行验证,验证结果表明:仿真值与在轨值具有良好的一致性,散热器具有优异的力、热性能及显著的减重优势,可广泛应用于各种航天器的散热及均温。

To meet the light-weight and high-efficiency heat dissipation requirements of space optical remote sensors with large aperture,a space radiator based on high thermal conductivity graphite film is proposed for the first time.The basic physical properties,structural composition,mechanical properties,thermal properties and space environment adaptability of the high thermal conductivity graphite film were tested and analyzed.The common disadvantages in the application of high thermal conductivity graphite film,such as low thermal conductivity in the thickness direction,low mechanical strength,low hardness,thin thickness and small single block size,are solved by combining the high thermal conductivity graphite film with heat pipe and honeycomb plate.The high thermal conductivity graphite radiator is simulated and compared with two traditional radiators.The simulation results indicated that under the same heat dissipation capacity,the weight of high thermal conductivity graphite radiator is only about 1/3 of that of traditional aluminum alloy plate radiator,and about 1/2 of that of traditional aluminum honeycomb radiator.The heat dissipation performance of the radiator is verified by heat balance experiment and on-orbit flight application.The verification results show that the simulation values are in good agreement with the on-orbit values.The radiator not only has excellent mechanical and thermal performance,but also has significant weight reduction advantages,and can be widely used in the heat radiation of spacecraft.