In response to the heat dissipation requirements of space optical remote sensor electronics and other heat sources, the characteristics of the orbital heat flux of the high inclination orbit where the remote sensor is located are analyzed. Combined with the position characteristics of the remote sensor platform and the two-dimensional manoeuvring characteristics, the spatial layout position and required area of the heat dissipation radiator are determined. Utilizing heat pipe network to achieve the realization of the heat dissipation radiator groups, achieving effective heat dissipation of the heat source while the high orbital heat flux on the single position of the radiator. Adopting a non-metallic and graphite film composite heat dissipation radiator form, further improving the temperature uniformity of the heat dissipation radiator and effectively enhancing the heat dissipation of the remote sensor. Through this technology, the heat dissipation problem of complex orbit heat flux remote sensors can be solved.
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