| Citation: | YANG M，WANG L，YU F，et al. Design and on-orbit application of radiator for space optical remote sensor with large aperture[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（12）：3293-3302 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0116
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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.
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