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ISSN 2070-7401 (Print), ISSN 2411-0280 (Online)
Sovremennye problemy distantsionnogo zondirovaniya Zemli iz kosmosa
CURRENT PROBLEMS IN REMOTE SENSING OF THE EARTH FROM SPACE

  

Sovremennye problemy distantsionnogo zondirovaniya Zemli iz kosmosa, 2024, Vol. 21, No. 1, pp. 172-184

Stabilization of the thermal regime of the imaging system under space flight conditions

G.A. Avanesov 1 , B.S. Zhukov 1 , N.N. Brysin 1 , M.A. Zaitsev 1 
1 Space Research Institute RAS, Moscow, Russia
Accepted: 15.01.2024
DOI: 10.21046/2070-7401-2024-21-1-172-184
The telescope of the imaging system at a low Earth orbit is constantly affected by the radiation flux coming from the Earth. It consists of the Earth’s own thermal radiation and reflected solar radiation, which depend on the altitude of the orbit, the altitude of the Sun and the type of underlying surface. Inside the telescope, about 20 % of the thermal energy coming from the Earth falls on the main mirror. The remaining 80 % of the thermal energy falls on the hood, which is in radiative interaction with the telescope structure. The paper examines the possibility of stabilizing the thermal regime of the imaging system, in which the hood of the telescope observing the Earth’s surface is used as a radiator. It also houses heat accumulators containing a substance whose heat of melting and solidification is used to recuperate radiation energy fluxes coming from the Earth. To estimate real variations in the Earth’s radiation flux at low Earth orbits, we used data from daily measurements of short-wave and long-wave radiation fluxes obtained by the CERES (Clouds and the Earth’s Radiant Energy System) scanning radiometer on the Terra spacecraft 2 times a month during 2021. Based on them, the radiation fluxes at the telescope aperture in the day and night parts of the spacecraft orbit were calculated, which were used to estimate the surplus and deficit of thermal energy at the instrument aperture. The operation cycle of the thermal stabilization system of the blend is considered, including the recuperation of thermal energy coming from the Earth using a heat accumulator and the use of electric heaters to compensate for the deficit of heat flux. Estimates of the required amount of thermal accumulator were obtained. A conclusion is made about the feasibility of using thermal accumulators in thermal stabilizing systems of space-borne instruments.
Keywords: telescope, hood, thermal energy, recovery, battery, heat, melting-solidification, satellite changes, emission spectrum, reflection spectrum
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